| HAMILTON SUNDSTRAND CORPORATION Patent applications |
| Patent application number | Title | Published |
|---|
| 20130127161 | REFRIGERATION SYSTEM CONNECTION FITTING - A disclosed connector assembly for a refrigerant system mounted within an aircraft includes a metal seal disposed within a seal bore of a connector and compressed against a seal face of a nipple secured to the connector by a threaded member. The connector includes a seal bore that receives the metal seal with the inner portion of the seal bore open to the bore. In one example, the connector and nut are formed from aluminum and the nipple is formed from stainless steel and includes an aluminum coating applied to surfaces in contact with the metal seal and the connector. | 05-23-2013 |
| 20130118624 | SEALED FLAPPER DIVERTER VALVE - A valve includes a housing having a first opening and a second opening, a single flapper disposed in the housing about a point of rotation between the first opening and the second opening wherein the flapper is rotatable between the first opening and the second opening to seal one of the first opening and the second opening, the flapper having one of a first seal or a first seal land disposed on each of a first side and a second side thereof, and a second seal or a second seal land disposed about the first opening and the second opening, the second seal or the second seal land of the first opening and the second opening cooperating with the one of the first seal or the first seal land disposed on each of a first side and a second side of the flapper to seal the first opening and the second opening wherein the first and second land and/or the first or second seal is tapered towards or away from the point of rotation. | 05-16-2013 |
| 20130118191 | TURBO AIR COMPRESSOR WITH PRESSURE RECOVERY - A method for operating an air-conditioning system for an aircraft includes compressing ambient air with a compressor driven by a shaft in communication with a motor and a turbine. The method includes forwarding the compressed air to an aircraft cabin for circulation and removing circulated compressed air from the aircraft cabin. The method also includes forwarding the circulated compressed air to the turbine, depressurizing the circulated compressed air in the turbine and capturing energy created by depressurizing the circulated compressed air. | 05-16-2013 |
| 20130118190 | TURBO AIR COMPRESSOR - A method for operating an air-conditioning system for an aircraft including receiving an available power level from a control system of the aircraft, forwarding air from a first compressed air source to an aircraft cabin and forwarding air from a second compressed air source to the aircraft cabin if the available power level exceeds a threshold value. | 05-16-2013 |
| 20130113324 | TAPERED ROTOR ASSEMBLY - A rotor assembly for an electric machine includes an outer sleeve and a plurality of permanent magnets disposed in the outer sleeve. An inner sleeve is located inboard of the plurality of permanent magnets and includes a plurality of inner sleeve segments that form a tapered inner sleeve surface. A rotor shaft is located inboard of the inner sleeve and has a tapered outer shaft surface engageable with the tapered inner sleeve surface in an interference fit to force the plurality of inner sleeve segments into engagement with the plurality of permanent magnets. | 05-09-2013 |
| 20130113311 | INTERNAL COOLING OF MAGNETIC CORE FOR ELECTRIC MACHINE - A core for an electric machine includes a core component having a plurality of core teeth defining a plurality of core slots between adjacent core teeth of the plurality of core teeth. The plurality of core slots are receptive of one or more windings. A coolant flowpath through the core component is formed through at least one core tooth. The at least one core tooth has one or more coolant tube banks and one or more mixing chambers arranged in an alternating pattern along the at least one core tooth. | 05-09-2013 |
| 20130113222 | ELECTROMAGNETIC DEVICE - An electromagnetic device is provided and includes a stator defining a bore, a rotor rotatable within the stator bore and having permanent magnetic elements disposed about an outer surface thereof to define a series of magnetic poles, power coils configured to generate a power current as a first portion of the magnetic poles pass each of the power coils due to rotor rotation and sense coils configured to generate a sense current as a second portion of the magnetic poles pass each of the sense coils due to the rotor rotation. | 05-09-2013 |
| 20130112029 | GEARBOX DEOILER WITH PRE-PRESSURING COMPONENT - A gearbox includes an inlet configured to receive a mixture of air and oil from an external source and a deoiler. The deoiler includes a shaft including an inlet passage and an outlet passage, both formed on an inner portion of the shaft and separated from one another, a separator unit coupled to and surrounding a portion of the shaft and including an inlet and an outlet and a pre-pressuring component coupled to the shaft that increases the pressure of the mixture of oil and air to form a pressurized mixture and provides the pressurized mixture to the inlet of the separator unit. | 05-09-2013 |
| 20130101436 | FAN ROTOR WITH COOLING HOLES - A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter. | 04-25-2013 |
| 20130101435 | SHAFT CAP - A shaft cap to connect between a shaft and a tie rod on a rotative assembly includes a circular portion with a central opening for connecting to the tie rod; a conical portion extending out from the circular portion at a slope; and a pilot around the outer edge of the conical portion. The pilot includes an outer lip to connect to an end of the shaft, an inner portion to connect to the inner circumference of the shaft and an undercut portion between the outer lip and the inner portion. | 04-25-2013 |
| 20130101433 | TIE ROD - A tie rod for extending between a fan shroud and a shaft cap in a rotative assembly includes a first end with threads; a second end with threads; and an elongated portion between the first end and the second end. The tie rod has diameter to length ratio of about 1 to 40.810 to about 1 to 40.768. | 04-25-2013 |
| 20130101402 | FAN HOUSING WITH COOLING SLOTS - A fan housing for a ram air fan includes an outer portion to connect the fan housing to ram air fan components; a tubular portion; a plurality of struts connecting the outer portion and the tubular portion; and a central disc portion inside of the tubular portion. The central disc portion comprises six cooling slots around an outer circumference. | 04-25-2013 |
| 20130101400 | RAM AIR FAN INNER HOUSING - A ram air fan inner housing for a ram air fan assembly comprises a center body housing, an end cup attached to the center body housing, and a perforated cone. The perforated cone is attached to the center body housing and the end cup such that the perforated cone extends away from the center body housing and radially inward toward an axis of the inner housing. | 04-25-2013 |
| 20130101399 | RAM AIR FAN BEARING HOUSING - A ram air fan bearing housing for a ram air fan assembly includes a bearing section, a disk section, and radial support ribs. The disk section is at one end of the bearing section for connecting the bearing section to the ram air fan assembly. The disk section includes an outer ring with a circumferential support rib; and a disk wall connecting the outer ring to the bearing section. The disk wall includes arcuate cooling slots defined by edges, including an arcuate edge having an arc center at an axis of the bearing housing and positioned adjacent to and radially inward from the circumferential support rib. The radial support ribs extend axially along most of the length of the bearing section and extend radially along the disk wall to the circumferential support rib. The radial support ribs and the cooling slots alternate about the axis of the bearing housing. | 04-25-2013 |
| 20130101394 | FREE-SURFACE LIQUID TRANSFER DEVICE FOR ROTATING MACHINERY - A free-surface liquid transfer apparatus for rotating machinery includes a rotating member. The rotating member includes a main shaft defining a hollow inner cavity, an outer cylindrical wall defining a hollow annular cavity in fluid communication with the hollow inner cavity through a plurality of orifices formed on the main shaft, and a slinger formation in fluid communication with the hollow annular cavity through a plurality of radial slots formed through the slinger formation. A central axis of the main shaft, a central axis of the hollow annular cavity, and a central axis of the slinger formation are collinear, and the slinger formation is configured to transmit working fluid received through the plurality of radial slots outward as a continuous film having both tangential and radial velocity components. | 04-25-2013 |
| 20130098585 | FREE-SURFACE LIQUID CAPTURE DEVICE FOR ROTATING MACHINERY - A free-surface liquid transfer apparatus for rotating machinery includes a stationary member. The stationary member includes a main surface configured to align to a rotating member, a landing surface arranged around the main surface configured to receive and slow a continuous film of working fluid transferred from the rotating member, an annular gap arranged around the landing surface, and a hollow torus cavity arranged proximate the annular gap configured to receive the slowed continuous film of working fluid transmitted through the annular gap. | 04-25-2013 |
| 20130098045 | RAM AIR FAN OUTER HOUSING - A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder and a plenum connected at a joint region. The outer cylinder and the plenum are made of a laminate stacking sequence of at least four adjacent layers of plain-weave carbon-fiber fabric. Each layer of the stacking sequence has a weave orientation such that a first layer and a fourth layer are oriented forty-five degrees from each of a second layer and a third layer. The joint region is made of at least eight adjacent layers of plain-weave carbon-fiber fabric. The joint region laminate stacking sequence is formed by interleaving the four adjacent outer cylinder layers in the joint region with the four adjacent plenum layers in the joint region. | 04-25-2013 |
| 20130097997 | RAM AIR FAN DIFFUSER - A diffuser for a ram air fan assembly includes a perforated cone, an inlet ring seal, and an outlet ring seal. The perforated cone has a frustoconical shape symmetrical about an axis of the diffuser. The inlet ring seal is attached to, and axially disposed about, a first end of the perforated cone. The inlet ring seal includes a fan housing connection having a cylindrical shape. The outlet ring seal is attached to, and axially disposed about, a second end of the perforated cone. An average external diameter of the second end is greater than an average external diameter of the first end such that the perforated cone extends away from the inlet ring seal and radially outward from the axis of the diffuser. | 04-25-2013 |
| 20130097996 | RAM AIR FAN INLET HOUSING - A ram air fan inlet housing for containing a ram air fan rotor. The inlet housing includes a flanged surface and an interior surface. The flanged surface is perpendicular to an axis of the inlet housing and defines a flange plane at an axial end of the inlet housing. The interior surface is symmetric about the axis of the inlet housing and includes a flange section, a transition section, an outlet section, a rotor section, and an inlet section. | 04-25-2013 |
| 20130094999 | OZONE CONVERTER WITH INTERNAL BYPASS - An ozone converter that includes an outer housing having an inlet and an outlet is disclosed. In this embodiment the ozone converter includes a core disposed within the outer housing and a bypass cylinder disposed between the inlet and the outlet and that passes through the core such that air within the bypass cylinder does not contact the core. The ozone converter of this embodiment also includes a blocking sleeve that surrounds a portion of the bypass cylinder and that is moveable from a first position to a second position. When the bypass sleeve is in the first position air that enters in the inlet is directed by the blocking sleeve into the bypass cylinder and when it is in the second position air that enters the inlet is allowed to enter an outer passage between the bypass cylinder and the outer housing. | 04-18-2013 |
| 20130093285 | STATOR CORE RETENTION CYLINDER FOR ELECTRIC MACHINERY - An electric machine system includes a rotor core, a stator core disposed about the rotor core, an electric machine housing coupled to the stator core, a holding-cylinder disposed between the electric machine housing and the stator core, a first flange coupled to the electric machine housing at a first end of the holding-cylinder and a second flange coupled to the electric machine housing at an opposite end of the holding-cylinder. | 04-18-2013 |
| 20130093270 | HIGH TEMPERATURE ENVIRONMENT CAPABLE MOTOR CONTROLLER - A motor controller for use in an environment at a high maximum environmental temperature comprises an insulated chassis, a high-temperature capable electronic component, a low-temperature capable electronic component, and a heat pump. The high-temperature capable electronic component is rated for temperatures higher than the environmental temperature, whereas the low-temperature capable electronic component is rated for temperatures lower than the maximum environmental temperature. The insulated chassis has a finned surface to which the high-temperature capable electronic component is mounted. The low-temperature capable electronic component is attached to or integrated into a printed wiring board supported inside the insulated chassis by the thermally conductive posts. The heat pump is configured to draw heat from the low-temperature capable electronic component through the thermally conductive posts and a thermal spreader abutting the heat pump, and to expel heat into the finned surface of the insulating chassis. | 04-18-2013 |
| 20130091850 | METHOD AND SYSTEM FOR REDUCING HOT SOAKBACK - A method for cooling a gas turbine engine includes supplying power to a motor to generate mechanical motion and translating the mechanical motion of the motor to a shaft of the gas turbine engine to rotate a compressor stage and a turbine stage after the engine has been shutdown to circulate air within the engine and cool engine components. A system for preventing hot soakback in an auxiliary power unit includes a starter motor, a compressor, a turbine, a shaft connected to at least one stage of the compressor and at least one stage of the turbine, a gearbox for connecting the starter motor to the shaft, a temperature sensor and a controller. The controller receives information from the temperature sensor and instructs the starter motor to rotate and drive the shaft when the temperature sensor senses a temperature above a low limit temperature threshold. | 04-18-2013 |
| 20130088903 | CONTROL ARCHITECTURE FOR A MULTI-LEVEL ACTIVE RECTIFIER - The present invention is a control architecture for an active rectifier. The control architecture monitors the AC input voltage provided to the active rectifier at a sampling rate grater than the frequency of the AC input voltage and calculates, in response, a phase estimate associated with the monitored AC input voltage that is updated with each new sample of the AC input voltage. Based on the phase and frequency estimates, along with monitoring of the AC input current and DC output voltage, the control architecture calculates voltage commands that are used to generate the pulse-width modulation (PWM) controls signals for provision to solid-state switching devices in the active rectifier. | 04-11-2013 |
| 20130087732 | PRESSURE VALVE CONTROLLER INCLUDING A DIAPHRAGM RETENTION DEVICE - A pressure regulating valve controller includes a housing. A piston having a surface portion is arranged in the housing. A spring seat is arranged in the housing adjacent the piston. The spring seat includes a surface section. A diaphragm is arranged in the housing between the surface portion of the piston and the surface section of the spring seat. The diaphragm includes an opening. A diaphragm retention device is arranged in the opening of the diaphragm. The diaphragm retention device is configured and disposed to contact each of the surface portion of the piston and the surface section of the spring seat to reduce forces on the diaphragm. | 04-11-2013 |
| 20130084193 | MOTOR HOUSING THERMAL SENSING - A motor driven compressor apparatus includes a first stage compressor, a second stage compressor, an electric motor disposed between and coupled to the first stage compressor and the second stage compressor, thermal sensors disposed on the electric motor and configured to externally measure internal temperatures of the electric motor or internal bearings or components, and an external controller coupled to the electric motor and to the thermal sensors, and configured to at least one of slow down a speed of the electric motor and shut down the electric motor in response to at least one of an excess of a predetermined internal temperature and a rate of internal temperature change. | 04-04-2013 |
| 20130084179 | VARIABLE VANE ANGULAR POSITION SENSOR - A variable vane control system for use with a gas turbine engine includes an actuator, a mechanical linkage assembly, and a vane position sensor. The gas turbine engine has a plurality of variable vanes each having an airfoil disposed in a gas flow path of the gas turbine engine. The plurality of variable vanes includes a first variable vane. The mechanical linkage assembly operably connects the actuator to at least the first variable vane. The vane position sensor is connected to one of the first variable vane or a portion of the mechanical linkage assembly proximate the first variable vane for sensing angular position of the first variable vane. | 04-04-2013 |
| 20130084176 | FAN INLET DIFFUSER HOUSING RIVETED CENTER BODY RETENTION - A fan inlet diffuser housing system includes an air cycle machine, a housing coupled to the air cycle machine, an inlet fan disposed on the air cycle machine and configured to pass inlet air into the fan inlet diffuser housing, a center tube disposed in the housing, a diffuser cone disposed around the center tube, an inboard strut supporting the inner tube within the diffuser cone, and an outboard strut supporting the inner tube within the diffuser cone, the outboard strut being integral with the diffuser cone, wherein the inboard strut is coupled to the inner tube with a first plurality of mechanical fasteners, and the outboard strut is coupled to the inner tube with a second plurality of mechanical fasteners. | 04-04-2013 |
| 20130083574 | DUAL-INPUT NINE-PHASE AUTOTRANSFORMER FOR ELECTRIC AIRCRAFT AC-DC CONVERTER - A dual-input nine-phase autotransformer converts first and second three-phase AC inputs to a nine-phase AC output. The autotransformer includes input terminals for connection to a first three-phase AC input and a second three-phase AC input smaller than the first three-phase AC input. The autotransformer includes a first plurality of coils, a second plurality, and a third plurality of coils wound on respective phase legs of the autotransformer. The autotransformer includes a plurality of output terminals for providing a plurality of AC output voltages, and a plurality of internal terminals for connecting the first, second, and third plurality of coils in a configuration that provides a 40° phase shift in the AC outputs provided by the dual-input nine-phase autotransformer. | 04-04-2013 |
| 20130082786 | CONFIGURABLE SPREAD SPECTRUM OSCILLATOR - A spread spectrum oscillator includes a high frequency oscillator circuit configured to oscillate at a first frequency, and a low frequency oscillator circuit configured to oscillate at a second frequency and resistively coupled to a current summing node of the high frequency oscillator circuit. The first frequency is higher than the second frequency. | 04-04-2013 |
| 20130081920 | HYDRAULIC CLUTCH - A hydraulic clutch apparatus includes a first hub, wherein the first hub includes a plurality of frictional clutch discs arranged therein, and a second hub arranged within the first hub and proximate the plurality of frictional clutch discs, wherein the second hub includes a first toroidal hydraulic chamber configured to depress the plurality of frictional clutch discs and a second toroidal hydraulic chamber opposing the first toroidal hydraulic chamber. | 04-04-2013 |
| 20130081243 | Fastener Assembly - A fastener assembly comprises: an insertion-extraction tool comprising a lever with a sleeve passing through one end from a front surface to a back surface and protruding from the back surface, a first ramp that circumscribes about one-half of the sleeve and a second ramp that circumscribes about one-half of the sleeve opposite the first ramp, the first ramp with a ramped surface that faces away from the back surface of the lever and the second ramp with a ramped surface that faces toward the back surface of the lever; and a wedge lock assembly comprising multiple wedges and a captive screw passing there through, the captive screw having a shank that passes through the sleeve of the insertion-extraction tool and a head on the distal end of the shank adjacent to the front surface of the lever of the insertion-extraction tool. | 04-04-2013 |
| 20130078541 | JET FUEL BASED HIGH PRESSURE SOLID OXIDE FUEL CELL SYSTEM - A power system for an aircraft includes a solid oxide fuel cell system which generates electric power for the aircraft and an exhaust stream; and a heat exchanger for transferring heat from the exhaust stream of the solid oxide fuel cell to a heat requiring system or component of the aircraft. The heat can be transferred to fuel for the primary engine of the aircraft. Further, the same fuel can be used to power both the primary engine and the SOFC. A heat exchanger is positioned to cool reformate before feeding to the fuel cell. SOFC exhaust is treated and used as inerting gas. Finally, oxidant to the SOFC can be obtained from the aircraft cabin, or exterior, or both. | 03-28-2013 |
| 20130076169 | ELECTRICAL MACHINE WITH REDUCED WINDAGE LOSS - An electrical machine includes a rotor located at a central shaft and a stator located radially outboard of the rotor and secured at a back iron. A first baffle is coupled to the central shaft at one axial end of the rotor, the baffle extending radially outwardly from the shaft toward a baffle cavity at the back iron. A flow of coolant is urged toward the baffle cavity along the baffle via centrifugal force. A method of flowing coolant through an electrical machine includes injecting a flow of coolant substantially radially into an electrical machine cavity. The flow of coolant is urged radially outwardly along a rotating baffle located at one axial end of a rotor of the electrical machine via centrifugal force and into a baffle cavity disposed at the back iron at a radial end of the baffle. | 03-28-2013 |
| 20130076120 | AIRCRAFT EMERGENCY POWER SYSTEM - An emergency power system for use on an aircraft includes an emergency electrical generator coupled to a mechanical power source for generating emergency electrical power. An electrical power distribution network connects the emergency electrical generator to a plurality of electrical loads. A controller controls the electrical power distribution network to selectively couple and decouple the electrical loads to and from the emergency electrical generator based upon a priority rank assigned to each of the electrical loads. | 03-28-2013 |
| 20130068421 | PROTECTIVE LEAKAGE SHIELD FOR LIQUID TO AIR HEAT EXCHANGER - A leakage shield for an air to liquid heat exchanger includes a drain pan, a liquid header panel, and a closure bar. The drain pan has a first side and a second side opposite the first side. The liquid header panel has a lower end attached to the first side of the drain pan, and extends vertically upwards from the first side of the drain pan. The closure bar panel has a lower end attached to the second side of the drain pan, and extends vertically upwards from the second side of the drain pan. | 03-21-2013 |
| 20130064672 | METHOD OF MANUFACTURING A TURBINE ROTOR - A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they are pressed together with a selected force while rotating to weld the ring interior wall and the disk side to form the assembled structure. | 03-14-2013 |
| 20130063235 | ELECTRO-MAGNETIC DEVICE HAVING A POLYMER HOUSING - An electro-magnetic device includes a core having a first end that extends to a second end through an outer core surface and an inner core surface. A plurality of windings extend about the core, and a polymer housing covers the core and the plurality of windings. The polymer housing includes an outer housing member that extends adjacent to the outer core surface and an inner housing member that extends adjacent to the inner core surface. | 03-14-2013 |
| 20130062943 | LOAD SHEDDING CIRCUIT FOR RAM AIR TURBINES - A power generation/distribution system includes a RAM air turbine (RAT) generator and an emergency integrated control center (EICC) that selectively applies either primary power provided by a primary power source or emergency power developed by the RAT generator to an alternating current essential bus (AC ESS bus) for distribution to one or more essential loads. The EICC monitors the primary power and in response to a loss of primary power selectively disables the supply of power from the AC ESS bus to the essential loads and manages subsequent loading of the RAT generator by the essential loads. | 03-14-2013 |
| 20130056190 | COOLING STRUCTURE - A heat exchanger structure includes a monolithic extrusion and a plurality of headers. The extrusion includes a first end; a second end; a first, smooth side; and a second side with a plurality of smooth portions alternating with a plurality of raised portions defining a plurality of parallel flow passages extending from the first end to the second end; and a plurality of headers connecting the plurality of flow passages to form a flow path. | 03-07-2013 |
| 20130055723 | Apparatus and Method for Separating Ice from Fuel in a Gas Turbine Engine - According to one aspect of the invention, an ice separating apparatus for a gas turbine engine includes a can having a first end and a tangential inlet proximate the first end of the can to receive a fluid flow within the can, wherein the fluid flow includes fuel and ice. The apparatus also includes a first conduit within the can to receive a separated fuel flow proximate a second end of the can, wherein the fluid flow separates ice from fuel to form the separated fuel flow. | 03-07-2013 |
| 20130054175 | VIBRATION SIGNAL COMPENSATION - A system comprises a vibration sensor for generating a vibration signal on a turbomachine, a signal conditioner for conditioning the vibration signal, and a test signal generator for calibrating the signal conditioner. The test signal generator calibrates the signal conditioner with a test signal having a base frequency and a modulation frequency. The signal conditioner introduces a phase error into the vibration signal, and the signal conditioner introduces a phase shift into the test signal. A processor compensates for the phase error in the vibration signal by correcting the vibration signal based on the phase shift in the test signal, where the processor determines the phase shift in the test signal based on harmonic analysis of the modulation frequency. | 02-28-2013 |
| 20130052047 | VARIABLE OUTPUT PUMP - A variable output pump includes a fluid input, a control stage pump having an input portion and an output portion, a main stage pump having an input portion and an output portion, and a differential linkage in mechanical communication with the control stage pump and the main stage pump. The input portion of the control stage pump is in fluid communication with the fluid input and the input portion of the main stage pump is in fluid communication with the fluid input and the output portion of the control stage pump. | 02-28-2013 |
| 20130051975 | AIR TURBINE STARTER AND METHOD FOR VENTING WITHOUT LOSS OF OIL - A clutch assembly includes a shaft, vent plug and oil guide sleeve. The shaft includes an internal cavity, first passages for allowing oil to lubricate clutch components, and second passages for allowing excess oil to drain from the internal cavity. The vent plug has a radial passage in communication with the internal cavity for venting the cavity with an external source of air. The oil guide sleeve directs oil into the internal cavity. A method for lubricating and venting an air turbine starter includes delivering lubricating oil to an internal cavity of a clutch via an oil guide sleeve. The oil guide sleeve prevents oil from exiting the cavity through excess oil drainage passages before it lubricates the clutch components. The method also includes draining excess oil from the cavity through excess oil drainage passages so that excess oil does not substantially impede air flow through a vent plug passage. | 02-28-2013 |
| 20130050890 | MULTI-FUNCTIONAL SOLID STATE POWER CONTROLLER - A solid state power controller apparatus can include an on/off-current limit controller, a pre-charge controller coupled to the on/off-current limit controller, an active damper controller coupled to the on/off-current limit controller and a main switch coupled to and responsive to on/off and protective commands from the on/off-current limit controller. | 02-28-2013 |
| 20130050880 | SOLID STATE POWER CONTROLLER FOR HIGH VOLTAGE DIRECT CURRENT SYSTEMS - A solid state power controller system can include a direct current load, a solid state power controller apparatus including an alternating current sensor coupled to the direct current load, a direct current sensor coupled to the direct current load, a voltage sensor coupled to the direct current load, a main switch coupled to the direct current load via the alternating and direct current sensors, an auxiliary switch coupled in parallel to the main switch, a current limiting resistor coupled in series to the auxiliary switch and a solid state power controller coupled to the main switch, the auxiliary switch, the alternating current sensor, the direct current sensor, and the voltage sensor, and a direct current power source coupled to the solid state power controller apparatus. | 02-28-2013 |
| 20130049648 | DIRECT CURRENT BUS MANAGEMENT CONTROLLER - A direct current bus management system can include a power management and distribution unit, having a source management section, a bus management section coupled to the source management section, a load management section coupled to the bus management section, a DC bus coupled to the power management and distribution unit, a plurality of DC sources coupled to the source management section and a plurality of loads coupled to the load management section, wherein the bus management section is configured to reconfigure excess DC power on the DC bus from the DC inputs from the plurality of DC sources based on a plurality of priorities, a plurality of feedback signals and a plurality of system parameters. | 02-28-2013 |
| 20130046486 | SPEED RATE ERROR REDUCTION IN A PULSE DISPLACEMENT CONVERTER SYSTEM - A method for determining a duty cycle in a pulse displacement system, includes generating an analog waveform indicative of an angular displacement of a reference wheel from a wheel; generating a pulse waveform of the analog waveform; generating a duty cycle waveform responsive to the generating of the pulse waveform; accumulating a first count of high states of the duty cycle waveform; accumulating a second count of low states of the duty cycle waveform; determining a first average for the first count and a second average for the second count; and calculating a duty cycle of the pulse waveform as a function of the first average and the second average. Also, the first count includes an additional high state over the low state. | 02-21-2013 |
| 20130042760 | GEARBOX DEOILER WITH SYCHNRONIZER - A gearbox that includes an inlet configured to receive a mixture of air and oil from an external source and a deoiler. The deoiler includes a shaft including an outlet passage formed on an inner portion of the shaft, a separator unit coupled to and surrounding a portion of the shaft and including an inlet port, and a synchronizer including one or more blades and that is coupled to the shaft proximate the inlet port. | 02-21-2013 |
| 20130042713 | FRAME AND SHELL GEARBOX HOUSING - A gearbox housing to enclose a gearbox with a geartrain and a lubrication system includes a frame made of a first material to carry gearbox loads; and a shell made of a second material to connecting to the frame and to keep lubrication sealed within the lubrication system. | 02-21-2013 |
| 20130042622 | FLOW BALANCING VALVE - A flow balancing valve for a multistage combustor includes a first pressure feedback line, a first burn line, and a first metering port fluidly connected to the first fuel injector. The flow balancing valve further includes a second pressure feedback line, a second burn line, and a second metering port fluidly connected to the second fuel injector. A metering land is located between and defines sizes of the first metering port and the second metering port. An increase in pressure differential between the first pressure feedback line and the second pressure feedback line causes a compensatory movement in the metering land to balance fuel flow for the first fuel injector and the second fuel injector. | 02-21-2013 |
| 20130040545 | LOW PRESSURE COMPRESSOR BLEED EXIT FOR AN AIRCRAFT PRESSURIZATION SYSTEM - An aircraft pressurization system, includes an auxiliary compressor for further compressing compressed air received from a low pressure compressor section of a gas turbine engine while the compressed air is below a predetermined pressure level; a bleed passage for fluidically connecting the auxiliary compressor to the low pressure compressor section; and an environmental control system coupled to an output of the auxiliary compressor for conditioning the compressed air to a predetermined level. | 02-14-2013 |
| 20130039765 | AIRCRAFT PROPELLERS - An aircraft propeller taper bore insert apparatus includes an outer surface, the outer surface dimensioned and configured to fit within an aircraft propeller taper bore or an aircraft propeller balancing tube, and an inner surface, the inner surface defining an inner cavity configured to receive a balancing medium, the inner surface comprising a plurality of retention formations arranged thereon, and the plurality of retention formations being configured to support the balancing medium. | 02-14-2013 |
| 20130039105 | FILTER CIRCUIT FOR A MULTI-PHASE AC INPUT - A filter circuit is employed to filter undesirable harmonics in a multi-phase AC input and provide damping for oscillations associated with the filter circuit. The filter circuit includes a damping circuit connected between phases of the multi-phase AC input. The damping circuit including a rectifier for rectifying harmonics in the multi-phase AC input and a single damping resistor connected across the rectifier. | 02-14-2013 |
| 20130036730 | HYBRID POWER SYSTEM ARCHITECTURE FOR AN AIRCRAFT - A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft. | 02-14-2013 |
| 20130036602 | HIGH ALTITUDE, HIGH VOLTAGE TERMINAL BLOCK ASSEMBLY - A method of installing the terminal block assembly onto a generator includes the step of providing a terminal block with multiple terminal studs. Protrusions that are integral with the terminal block are aligned with corresponding bores in a generator housing. The terminal block is mounted on the generator housing with the protrusions received in the bores. A terminal lead assembly is inserted through the protrusion, and a terminal pad of the terminal lead assembly is arranged over the terminal stud. A terminal lug is fastened to the terminal stud. A terminal cover is secured to the terminal block over the terminal with a boss of the terminal block received in a corresponding recess of the terminal cover. | 02-14-2013 |
| 20130033945 | SYSTEM AND METHOD FOR INTERFACING BURST MODE DEVICES AND PAGE MODE DEVICES - A burst read control circuit acts as an interface to allow a burst-read capable device to execute burst reads from a page-mode capable memory device. The burst read control circuit coordinates burst read requests from the burst-read capable device and subsequent responses from the page-mode capable memory device by accessing subsequent and contiguous memory locations of the page-mode capable memory device. | 02-07-2013 |
| 20130033246 | POWER MANAGEMENT FOR LOADS SUPPLIED WITH POWER FROM WILD SOURCES - A solid-state power regulator (SSPR) regulates power delivered to a frequency tolerant load from a wild-source generator. The SSPR includes a solid-state switching device and a controller. The solid-state switching device is turned On to deliver power from the wild-source generator to the frequency-tolerant load and Off to prevent the delivery of power to the frequency-tolerant load. The controller monitors the power delivered to the frequency-tolerant load and selectively modulates the solid-state switching device to regulate the power delivered. | 02-07-2013 |
| 20130033038 | STARTING/GENERATING SYSTEM WITH MULTI-FUNCTIONAL CIRCUIT BREAKER - A starting/generating system includes a rotor portion and a stator portion. The stator portion is connected to a DC power source during starting operations and to a DC load during generating operations, and includes a DC link having a first and second DC link bus, a DC link capacitor connected between the DC link buses, and an inverter/rectifier that converts AC power to DC power and vice versa. A switching device is connected in series on the first DC link bus and is controlled by a controller that turns the switching device On and Off to provide various functionality to the starting/generating system. | 02-07-2013 |
| 20130031912 | GAS TURBINE START ARCHITECTURE - A gas turbine starting architecture is used to start a gas turbine engine having at least a first spool. The architecture includes an electric power distribution bus, a motor, a compressor, a pneumatic distribution circuit, an air turbine starter, and a first tower shaft. The motor converts electric power provided by the electric power distribution bus to mechanical power. In turn, the mechanical power provided by the motor is converted to pneumatic power by the compressor for provision to a pneumatic distribution circuit. The air turbine starter converts pneumatic power from the pneumatic distribution circuit to mechanical power is provided via the first tower shaft to the at least one spool on the gas turbine engine. | 02-07-2013 |
| 20130025828 | MOTOR WITH COOLED ROTOR - A fan includes an air movement implement including a blade and a motor that drives the air movement implement. The motor includes a rotor that includes an internal diameter heat exchanger and a heat pipe having a first end and a second end, the first end in thermal contact with the internal diameter heat exchanger and the second end in thermal contact with the blade. | 01-31-2013 |
| 20130022454 | AIR TURBINE STARTER - A blade profile section for an air turbine starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Z-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip. | 01-24-2013 |
| 20130020047 | Aircraft Precooler Heat Exchanger - A heat exchanger is provided. The heat exchanger includes a first member having an inlet at a first end and a first flange at an opposite end. The first member is made from a nickel-chromium material. A second member is provided having a second flange one end coupled to the first flange. The second member further having an outlet on a second end opposite the second flange. The second member is made from titanium. | 01-24-2013 |
| 20130019917 | THERMOELECTRIC CONVERSION OF WASTE HEAT FROM GENERATOR COOLING SYSTEM - An electrical generator includes a rotor, a stator core disposed axially around the rotor, a stator sleeve assembly disposed axially around the stator core, and a stator housing disposed axially around the stator sleeve assembly. The stator sleeve assembly includes a cylindrical stator sleeve and thermoelectric elements. The cylindrical stator sleeve has a radially inward facing surface and a radially outward facing surface. The thermoelectric elements are affixed to the radially outward facing surface of the cylindrical stator sleeve. The stator housing includes at least one coolant channel. The coolant channel is in thermal contact with the thermoelectric elements. The thermoelectric elements generate power as a function of the temperature difference between the cylindrical stator sleeve and the coolant channel. | 01-24-2013 |
| 20130019420 | WIPER FOR TRANSLATING RAM - A wiper for a translating ram with recessed features includes a first element conforming to the recessed features of the translating ram; and a second element conforming to the external surface of the translating ram. The first element and second element conform to the cross-section of the translating ram when placed axially adjacent. | 01-24-2013 |
| 20130015291 | FIRE RESISTANT STRUCTURAL MOUNT YOKE AND SYSTEMAANM DeDe; Brian C.AACI San DiegoAAST CAAACO USAAGP DeDe; Brian C. San Diego CA USAANM Lau; DavidAACI San DiegoAAST CAAACO USAAGP Lau; David San Diego CA USAANM Jewess; Gordon F.AACI RzeszowAACO PLAAGP Jewess; Gordon F. Rzeszow PL - A mount yoke assembly comprises a first main hanger bracket and a first anchor bracket. The first main hanger bracket includes a first receiving portion for a first auxiliary power unit (APU) mount with first and second hanger arms. The first hanger arm includes a first hanger flange extending proximate a distal end of the first hanger arm. The first anchor bracket includes a first plurality of anchor holes and a first anchor flange. The first plurality of anchor holes are disposed substantially along a length of the first anchor bracket for securing the mount yoke assembly to a component of an APU assembly. The first anchor flange extends from the first anchor bracket for hingeably securing the first anchor bracket to the first main hanger bracket. | 01-17-2013 |
| 20130013145 | DECOUPLING CONTROL ARCHITECTURE FOR PRESSURE AND FLOW CONTROLS IN SERIES - An electronic controller for a sub-system of an air management system including an area conversion module and a sub-system area control module. The area conversion module includes inputs for a bleed output pressure set point, a bleed output pressure measurement, a sub-system parameter set point, a sub-system parameter measurement, and a sub-system output pressure measurement; and sub-modules for calculating an area set point and an area measurement. The sub-modules generate the area set point as a function of the engine bleed output pressure set point, the sub-system parameter set point, and the sub-system output pressure measurement; and the area measurement as a function of the bleed output pressure measurement, the sub-system parameter measurement, and the sub-system output pressure measurement. The sub-system area control module generates a control output for the sub-system as a function of the calculated area set point and the calculated area measurement. | 01-10-2013 |
| 20130009584 | VOLTAGE REGULATED PERMANENT MAGNET MACHINE - A permanent magnet generator comprises a stator core, a plurality of windings situated on the stator core, and a plurality of stress elements. The stress elements apply or relieve mechanical stress in response to control signals from a generator controller, thereby increasing or reducing voltage across the stator windings. | 01-10-2013 |
| 20130008638 | PHASE CHANGE MATERIAL HEAT SINK - A phase change material heat sink includes a sealed enclosure containing a phase change material. A fluid passage element is in contact with the sealed enclosure and includes a thermal exchange layer in thermal contact with the top and that directs fluid in a first flow direction and a shunt passage element in thermal contact with at least one of the sides or the bottom and that directs fluid in a second flow direction. | 01-10-2013 |
| 20120328417 | Engine bearing compartment - An engine bearing compartment is provided and includes an engine casing defining a discharge pathway for a fluid to drain from the engine bearing compartment, a shaft rotatably disposed within the engine casing to define an annulus, a housing disposed within the annulus below an elevation of the discharge pathway, an impeller rotatable with the shaft and including a centrifugal element, the impeller being disposed within the annulus at least partially below the discharge pathway elevation whereby, due to impeller rotation, the centrifugal element expels the fluid through the discharge pathway from the annulus above the discharge pathway elevation and a circuit by which fluid expelled through the discharge pathway is communicated to an interior of the housing. | 12-27-2012 |
| 20120326880 | Low Oil Indication - A method of indicating low oil level of lubrication oil for a gas turbine engine automatically eliminates false low oil readings due to temperature-induced lubrication oil shrinkage and operation-induced changes in lubrication oil level. | 12-27-2012 |
| 20120325348 | SYSTEM AND METHOD FOR FUEL SYSTEM HEALTH MONITORING - A method of monitoring operation of a fuel system includes urging a fuel flow from a fuel source toward a pressure regulating valve via a fuel pump. A pressure of the fuel flow is detected at the pressure regulating valve, and a pump speed required to produce a selected pressure at the pressure regulating valve is detected. The pump speed is compared to a range of acceptable pump speeds, and an operational status of the fuel pump is determined based on a result of the comparison. | 12-27-2012 |
| 20120323531 | ENGINE NOISE MONITORING AS ENGINE HEALTH MANAGEMENT TOOL - A system and method are provided for determining the health of an engine. The method includes a plurality of standard noise spectra collected from engines with known defects. A noise spectrum of the engine being monitored is sensed and compared to the plurality of standard noise spectra from the engines with known defects. From the comparison, a type and a degree of defect is identified based upon the comparison. | 12-20-2012 |
| 20120321451 | Bearing Housing Cooling System - A cooling system for the rear bearing capsule of a turbine in a gas turbine engine supported by an exhaust cone attached to multiple exit guide vanes that extend radially from the exhaust cone to an exhaust housing, comprises: an inlet air flow path through each guide vane between a source of cool ambient air and the rear bearing capsule; and at least one discharge air flow path that receives air from the inlet air flow path through each guide vane and passes the air through the exhaust cone from the rear bearing capsule to a high velocity gas flow path in the exhaust housing. | 12-20-2012 |
| 20120321446 | FAIL-SAFE MANUAL ROTATOR COVER - A gearbox includes an outer housing including manual rotation access passage and a manual rotation shaft coupled to a spool of an engine to rotate the engine spool. The gearbox also includes coupled to the outer housing that includes a flapper valve that, in a closed position, prevents a lubricant from escaping from the outer housing via the manual rotation access passage. | 12-20-2012 |
| 20120320530 | VERTICALLY MOUNTED MULTI-HYBRID MODULE AND HEAT SINK - A multi-hybrid module includes a plurality of hybrid assemblies that are perpendicularly mounted with respect to a plane of a circuit board. The hybrid assemblies are mounted on opposing sides of a heat sink. The heat sink has a first column disposed at a first end, a second column disposed at a second opposing end, and a generally flat center wall extending between the first column and the second column to which the hybrid assemblies are mounted. During operation the hybrid assemblies are mounted on edge perpendicular with respect to the circuit board to minimize an area profile of the multi-hybrid module on the circuit board. | 12-20-2012 |
| 20120319469 | INTELLIGENT ELECTRICAL POWER DISTRIBUTION SYSTEM - An intelligent power distribution system distributes power on a vehicle. The system includes at least a first power source and a second power source for supplying electrical power, and at least a first power block and a second power block, each connected to receive power from the first power source and the second power source. Each power block includes at least one load and a power selector having a first input for receiving power from the first power source and a second power source and an output for supplying power from either the first power source or the second power source to the at least one load. The power selector selects either the first power source or the second power source for provision to the at least one load based on characteristics of the at least one load. | 12-20-2012 |
| 20120319355 | Integrated End Face Seal Removal Apparatus - A mechanical seal includes a seal cartridge and a removal formation. The seal cartridge includes an outer cylindrical surface, an inner cylindrical surface concentric to the outer cylindrical surface, and a ring surface connecting the outer cylindrical surface and the inner cylindrical surface to define an inner cavity interior to the seal cartridge. The removal formation is arranged on the ring surface, and includes a first surface proximate the ring surface, an indentation feature proximate the first surface, and a seal puller feature proximate the indentation feature defining a channel configured to allow application of removal forces to the seal cartridge. | 12-20-2012 |
| 20120318368 | LEAK DETECTION LOGIC FOR CLOSED-VOLUME SYSTEM - A method for detecting a leak in a closed-volume liquid system comprises circulating a fluid through a closed-loop with a pump having a reservoir and that is driven by an electric motor. The method also comprises sensing a pressure in the closed-loop, sensing current draw by the motor and sensing fluid level in the reservoir. The method further comprises determining a presence of a leak of fluid from the closed-loop based upon two of the sensed signals using a first leak detection logic, and determining the presence of a leak of fluid from the closed-loop based upon at least one of the sensed signals using a second leak detection logic. | 12-20-2012 |
| 20120318366 | LEAK ISOLATION LOGIC FOR CLOSED-VOLUME SYSTEM - A method for isolating a leak in a closed-volume liquid system comprises circulating a fluid through a plurality of isolatable zones and a non-isolatable zone in a closed-volume liquid system, detecting a leak in the closed-volume liquid system, isolating all of the isolatable zones from the non-isolatable zone, sequentially detecting if the leak is present in the non-isolatable zone and each of isolatable zones, and taking corrective action after the leak is detected. | 12-20-2012 |
| 20120312037 | VAPOR CYCLE SYSTEM WITH DE-SUPERHEATER - A vapor cycle system comprises a compressor for compressing a coolant to form a superheated vapor, a de-superheater for cooling the superheated vapor to form a reduced temperature vapor by exchanging heat with a cooling fluid flow, a condenser for condensing the reduced temperature vapor to form a condensed liquid by exchanging heat with the cooling fluid flow, and an evaporator for evaporating the condensed liquid. The de-superheater is located downstream of the condenser in the cooling fluid flow, and a temperature of the cooling fluid flow is higher at the de-superheater than at the condenser. | 12-13-2012 |
| 20120306513 | HIGH TEMPERATURE POSITION SENSOR - A position sensor comprises first and second stationary poles with first and second electrodes, and a reference pole positioned therebetween. The reference pole is coupled to a shaft, and includes a semi-metal via that forms a conducting path between the first and second electrodes. The shaft positions the reference pole between the first and second stationary poles, and a resistance of the conducting path varies with a position of the shaft. | 12-06-2012 |
| 20120300519 | MULTI-PHASE ACTIVE RECTIFIER - A multi-phase active rectifier includes a plurality of active switching devices selectively controlled to convert a plurality of alternating current (AC) input voltages to a direct current (DC) output voltage. Control of the active switching devices is provided by a controller that includes an outer control loop for regulating the DC output voltage to a desired value, and an inner current loop for shaping the AC line current. The outer control loop compares the DC output to a threshold value to generate an error value, and multiples the error value with the plurality of monitored AC input voltages to generate modified AC input voltages. An inner control loop compares the modified AC input voltages with monitored AC line current values to generate a plurality of difference signals used to selectively control the plurality of active switching devices. | 11-29-2012 |
| 20120297780 | ACTIVE FUEL TEMPERATURE CONTROL - A system for managing fuel temperature in an engine includes a source of hot pressurized air and a turbine for converting hot pressurized air into cool expanded air. The system further includes a fuel tank for storing fuel, a fuel conduit fluidly connected to the fuel tank, and a first heat exchanger located on the fuel conduit. The first heat exchanger places the cool expanded air from the turbine in a heat exchange relationship with the fuel, thereby cooling the fuel. | 11-29-2012 |
| 20120291450 | AUXILIARY POWER UNIT MOUNTING FEATURE - An auxiliary power unit assembly includes an auxiliary power unit with an auxiliary power unit exhaust duct, a bell mouth, and one or more bell mouth struts. The auxiliary power unit exhaust duct extends from the auxiliary power unit and has an aft end portion that is received within the bell mouth. The bell mouth struts extend from an inner surface of the bell mouth and extend generally radially toward the auxiliary power unit exhaust duct. | 11-22-2012 |
| 20120288373 | ROTOR WITH ASYMMETRIC BLADE SPACING - A turbine apparatus comprises a rotor with a hub section defined about a rotational axis and a plurality of blades attached to the hub section. The plurality of blades comprises a first group having a first angular spacing in a first circumferential sector of the rotor, and a second group having a second angular spacing in a second circumferential sector of the rotor. The first angular spacing is different from the second angular spacing, and the rotor blades are asymmetric about the rotational axis. | 11-15-2012 |
| 20120288372 | TEETER-RESTRAINT DEVICE FOR WIND TURBINES - A wind turbine system includes a shaft, a rotor for driving the shaft, and a first fluidic teeter control assembly. The rotor includes a first blade engaged to the shaft by a hub, and has a degree of freedom to pivot relative to the shaft. A first teeter angle is defined between an instantaneous position of the first blade and a time-averaged plane of rotation of the first blade. The first fluidic teeter control assembly is engaged between the rotor and the shaft for providing a first dynamic teeter restraining force as a function of the first teeter angle and a fluidic resistance. The first dynamic restraining force is relatively low when the first teeter angle is within a first teeter operation range, and the first dynamic restraining force is higher when the first teeter angle is outside that range. | 11-15-2012 |
| 20120282102 | SPLIT BLADE RETENTION RACE WITH INNER AND OUTER CHAMFERS - A blade shank assembly for an aircraft propeller blade includes a blade shank; a split blade retention race encircling the blade shank, the split blade retention race including two splits, wherein the split blade retention race comprises: inner chamfers located between the blade shank and the split blade retention race at each of the two splits; and outer chamfers located adjacent to a race surface of the split blade retention race at each of the two splits; and a plurality of ball bearings located on the race surface of the split blade retention race. | 11-08-2012 |
| 20120280499 | Generator Frequency Controlled Load Shifting - In a power generation system that includes a ram air turbine that drives an electric generator and at least one electric bus that couples alternating current electric power from the electric generator to at least one electric load, a method of maintaining the speed of the ram air turbine within a desired range of speeds that comprises the step of uncoupling the at least one electric bus from the electric generator when the frequency of the alternating current falls under a desired minimum frequency. | 11-08-2012 |
| 20120275935 | Inlet Plenum with Shock Wave Suppression - An inlet plenum for a compressor that suppresses acoustic shock waves generated by the compressor, which inlet plenum has an inlet duct with a wall that surrounds an air flow path between a mouth of the inlet plenum and the compressor, comprises: at least one cavity that penetrates an inner surface of the wall, circumscribes the inner surface generally transversely to the air flow path and has a position along the air flow path that is generally coincident with at least one constructive interference peak of the acoustic shock waves along the inner surface; a width of the cavity along the direction of the air flow that is less than or equal to the wavelength of at least one of the acoustic shock waves; and a depth of the cavity generally perpendicular to the direction of the air flow that approximates a multiple of a quarter wavelength of at least one of the acoustic shock waves. | 11-01-2012 |
| 20120275924 | INTERLOCKING BLADE SHEATH - A blade assembly includes a blade body and at least one sheath assembly located at a leading edge of the blade assembly. The at least one sheath assembly is retained to the blade body in a chordwise direction via an interlocking arrangement between the at least one sheath assembly and the blade body. A tip cap is located at a tip portion of the blade and secured to the blade body thus securing the at least one sheath assembly to the blade body in a spanwise direction. A method of assembling an airfoil includes securing at least one sheath assembly to a leading edge of a blade body via an interlocking arrangement between the at least one sheath assembly and the blade body, and assembling a tip cap to the blade body, thereby retaining the at least one sheath assembly to the blade body in a spanwise direction. | 11-01-2012 |
| 20120273611 | EXHAUST SILENCER WITH BAFFLES - An exhaust silencer assembly includes an exhaust duct and an exhaust silencer. The exhaust silencer is disposed about the exhaust duct and has a plurality of solid baffles and at least one perforated baffle The exhaust silencer assembly is disposed downstream of an auxiliary power unit and at least partially attenuates the downstream noise of the combustion gases that result from operation of the auxiliary power unit. In one embodiment, at least one of the plurality of solid baffles is disposed to extend axially between generally radially extending solid baffles, perforated baffle(s), or partially perforated baffles. The axially extending solid baffle allows for cavity depth variation in the silencer to optimize tuning of particular frequencies from the auxiliary power unit. | 11-01-2012 |
| 20120273079 | OIL TRANSFER TUBE AND ASSEMBLY - A fluid transfer tube comprises a base, a plurality of external threads, and an annular shoulder. The base is disposed at a first axial end of the tube. The plurality of external threads are integrally formed into at least a portion of the base for securing the base into a boss. The annular shoulder is fixed to an outer diameter of the tube at a first distance from the first axial end, causing the shoulder to contact an outer surface of the boss with the base of the tube at a maximum depth in the receiving portion of the boss to prevent further downward travel of the base. | 11-01-2012 |
| 20120272636 | COMBUSTOR DRAIN VALVE AND ASSEMBLY - A valve assembly comprises a housing, a movable member, a fixed member, and a resilient member. The seat element has an upstream side, a downstream side, and an outlet port providing fluid communication therebetween, with the seat element fixed in a flow control segment adjacent a valve outlet. The drain element, operable between a first axial position closest to an inlet structure, and a second axial position abutting an upstream surface of the fixed seat element, is retained upstream from the fixed seat element and includes an upstream side, a downstream side, and a plurality of inlet ports through the drain element providing fluid communication therebetween. The resilient element is disposed axially within a middle fluid chamber defined by a portion of the flow control segment located between the fixed seat element and the movable drain element, the resilient element applying a first biasing force to urge the drain element upstream toward the first position, urging the valve into an open, flow permissive configuration. | 11-01-2012 |
| 20120271527 | DISTRIBUTED AIRCRAFT ENGINE FUEL SYSTEM - A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output. | 10-25-2012 |
| 20120269634 | STRUT DRIVESHAFT FOR RAM AIR TURBINE - A driveshaft for an aircraft ram air turbine includes a substantially cylindrical elongate portion, a first end extending from the elongate portion, and a second end extending from the elongate portion opposite the first end. The first and second ends each include a substantially frusto-conical section having a curved generatrix, such that distal portions of each of the first and second ends have smaller outer diameters than an outer diameter of the elongate portion. The elongate portion provides relatively high lateral stiffness and the first and second ends provide relatively low torsional stiffness, such that the driveshaft has a lateral natural frequency higher than an operating range of the driveshaft and has a torsional natural frequency below the operating range of the driveshaft. | 10-25-2012 |
| 20120269616 | TURBINE DRIVESHAFT FOR RAM AIR TURBINE - A driveshaft for an aircraft ram air turbine includes a tubular body and a flange. The tubular body defines an axis of rotation and includes a forward portion and a frusto-conical portion located rearward of the forward portion. The flange adjoins the forward portion of the tubular body opposite the frusto-conical portion, and has a forward face and an opposite rear face. A ratio of an outer diameter of the forward portion of the tubular body to an inner diameter of the forward portion of the tubular body is in a range of approximately 1.423 to 1.425. | 10-25-2012 |
| 20120268974 | HIGH-RESOLUTION AND LOW-RESOLUTION SENSORS FOR PHASE DETECTION - A phase detection system includes a low-resolution sensor and a high-resolution sensor for monitoring an alternating current (AC) voltage. A phase detector receives voltage samples from both the low-resolution sensor and the high-resolution sensor. The phase detector monitors the low-resolution sensor to detect approaching zero cross events (i.e., monitored voltage values approaching zero). In response to an approaching zero-cross event, the phase detector uses the magnitude of the high-resolution voltage samples measured on either side of the zero cross event to determine the phase of the monitored AC voltage. | 10-25-2012 |
| 20120267557 | Butterfly Valve - A butterfly valve having a valve body is provided. The butterfly valve includes a valve disk assembly rotationally coupled to the valve body. The valve disk assembly has a disk member with a first surface disposed about a periphery having a first diameter and a second surface offset from the first surface. A seal ring is arranged adjacent the first surface, the seal ring having a first outer surface with a second diameter, wherein the second diameter is larger than the first diameter. A retainer is coupled to the second surface adjacent the seal ring opposite the first surface. The retainer has inner surface arranged to radially constraining the seal ring on the disk member. | 10-25-2012 |
| 20120266623 | CONTROL ALGORITHM FOR ELECTRONIC EXPANSION VALVE MODULATION - An electronic expansion valve (EEV) is employed in refrigeration systems to regulate the flow of refrigerant through an evaporator. The position of the EEV is controlled through a first control loop that generates a first position signal based on superheat feedback associated with the refrigeration system, and a second control loop that generates a second position signal based on pressure feedback associated with the refrigeration system. The larger of the first position signal and the second position signal is selected to control the position of the EEV value, and the selected position signal is provided in feedback to both the first control loop and the second control loop. | 10-25-2012 |
| 20120266615 | ADAPTABLE EVAPORATOR DEFROST LOGIC - Adaptable evaporator defrost logic is employed in a refrigeration system to detect a build-up of ice on the evaporator. In response to the detected build-up of ice, a defrost operation is initiated that includes decreasing the speed of the compressor. At the end of the defrost operation, the adaptable evaporator defrost logic determines whether the defrost operation was a success. If the defrost operation was a success, then normal operation is resumed. If the defrost operation was not a success, then the defrost operation is modified by turning the compressor off and extending a duration of the defrost operation. | 10-25-2012 |
| 20120265466 | MONITORING THE LOW CYCLE FATIGUE OF RUGGEDIZED AVIONICS ELECTRONICS - A health monitoring system for monitoring the health of an electronic system. The health monitoring system includes an analog-to-digital converter, and a monitoring circuit within the electronic system. The monitoring circuit includes fatigue life characterized electrical components representative of electrical components comprising the balance of the electronic system. The fatigue life characterized electrical components are employed solely to monitor the health of the electronic system. The monitoring circuit output is electrically connected to the analog-to-digital converter. | 10-18-2012 |
| 20120263618 | Bi-Metal Pump Gear - A pump gear is provided. The pump gear includes a first shaft portion having a first end and a second end with an integral gear portion formed therebetween. The first shaft portion is made from a first tool steel material. A second shaft portion having a third end brazed to the first end. The second shaft portion has at least one integral drive spline formed adjacent one end. The second shaft portion is made from a second tool material. The first tool steel material has a vanadium content by weight of greater than | 10-18-2012 |
| 20120259483 | ACTUATION CONTROL SYSTEM - A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components. The actuation control system includes a component controller. The component controller includes two component control channels. Each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators. | 10-11-2012 |
| 20120257427 | ACTIVE RECTIFICATION OUTPUT CAPACITORS BALANCING ALGORITHM - An active rectification system includes an active rectifier that converts an alternating current (AC) input to a direct current (DC) output. The active rectifier includes a plurality of switching devices and at least a first output capacitor and a second output capacitor connected at the DC output of the active rectifier. A controller includes a DC output regulation portion and an output capacitor balancing portion, wherein the DC output regulation portion monitors the DC output and in response generates control signals for regulating the DC output to a desired value. The output capacitor balancing portion monitors first and second output capacitor voltages associated with the first and second output capacitors, respectively, and generates an accumulated adjustment value that modifies the control signals provided by the DC output regulation portion to balance the first and second output capacitor voltages. | 10-11-2012 |
| 20120255715 | LIQUID-TO-AIR HEAT EXCHANGER - A liquid-to-air heat exchanger includes an air inlet header, an air outlet header and a core. The air inlet header has an air inlet connection and the air outlet header has an air outlet connection. The core is connected to the air inlet header and the air outlet header and is angled relative to the air inlet connection and the air outlet connection. More particularly, the air inlet connection and air outlet connection do not align in a straight flow path and the core is disposed at an acute angle relative to one of the air inlet connection and the air outlet connection and an obtuse angle relative to the other of the air inlet connection and the air outlet connection. | 10-11-2012 |
| 20120255711 | THERMAL ACCUMULATOR AND METHOD OF USE - A thermal management system for a vehicle includes a tank, a heat exchanger, a pump, and a valve located on a conduit. The heat exchanger is located downstream of the tank, the pump is located between the tank and the heat exchanger, and the valve is located downstream of the heat exchanger. The heat exchanger places the coolant in a heat exchange relationship with a heat load from the vehicle such that the coolant vaporizes. The valve regulates pressure within the heat exchanger and controls exhaustion of the vaporized coolant from the vehicle. Water, used as a coolant, can be replenished in flight by condensing a portion of the heat exchanger exhaust or condensing water as part of the environmental control system function or by condensing a portion of the engine exhaust. | 10-11-2012 |
| 20120255631 | Check Valve - A valve is provided. The valve includes a flapper member. A barrel is coupled to the flapper member, the barrel having an interior volume and at least one movable vane within the interior volume. A shaft member is rotationally coupled to the barrel, the barrel having at least one stationary vane disposed within the interior volume. | 10-11-2012 |
| 20120255276 | LOAD LIMITED ACTUATOR - An actuator includes a first piston and a second piston. The first piston has a piston ring that separates a first chamber from a second chamber of the actuator. The first piston has an interior chamber that communicates with the first chamber. The second piston is disposed within the interior chamber of the first piston so as to be movable with respect thereto. The second piston has a surface that interfaces with the second chamber. | 10-11-2012 |
| 20120245746 | Automatic Ram Air Turbine Deployment - A method of deploying a ram air turbine for an aircraft only during flight that deploys the ram air turbine only when a predetermined number of aeronautical power generation contactor signals are in an engaged state, an external power generation contactor is in a disengaged state, wheels for the aircraft are in an airborne state and all of multiple primary electric buses are in a fault state that represents electric potential below a predetermined level. | 09-27-2012 |
| 20120243177 | INDIRECT BLEED AIR COOLING OF A FAN MOTOR CONTROLLER - A cooling system comprises a fan in a fan duct, a housing, electrical components, an air intake, an air outlet, and a cooling passage. The housing is mounted on the exterior of the fan duct. The electrical components are mounted on interior sides of the housing, for cooling. The cooling passage is located inside the sides of the housing on which the electrical components are mounted. The air intake draws air into the cooling passage from a region of the fan duct downstream of the fan. This air passes through the cooling passage, cooling the electrical components while remaining fluidly isolated from the interior of the housing. Air from the cooling passage is released by the air outlet into the environment, or into a region of the fan duct upstream of the fan. | 09-27-2012 |
| 20120243128 | DISCRETE INPUT SIGNAL GENERATION VIA OUTPUT SHORT-CIRCUIT DETECTION - A controller has an output for supplying power to an output device. The controller monitors the supplied power to provide short-circuit protection to the output device. The controller also receives discrete inputs at the output based on the introduction of temporary short-circuit conditions introduced by a momentary switch connected between outputs of the controller in parallel with the output device. The controller detects short-circuit conditions in the output and distinguishes between short-circuit fault conditions and discrete inputs generated by activation of the momentary switch based on measured characteristics of the detected short-circuit conditions. | 09-27-2012 |
| 20120242357 | AUTOMATIC FAULT INSERTION, CALIBRATION AND TEST SYSTEM - An automatic fault insertion and test (FIT) system provides an interface between a unit under test and test equipment that can be configured to allow for automatic fault insertion, testing and calibration of the test equipment. The FIT system includes an input connection terminal for connection to the UUT, an output connection terminal for connection to the test equipment and a plurality of bus circuit binding posts that can be connected to external devices. The FIT system includes a plurality of switch matrices and a plurality of common buses. Each switch matrix is connected to an input contact associated with the input connection terminal and an output contact associated with the output connection terminal, and each of the plurality of common buses. Selective control of the switches within each switch matrix allow the input contacts to be connected to the associated output contact, the input contacts to be connected to each of the four common buses, and the output contacts to be connected to each of the four common buses. | 09-27-2012 |
| 20120241459 | DEMISABLE FUEL SUPPLY SYSTEM - A demisable fuel supply system for a satellite includes a pressurized aluminum alloy tank with an aluminum alloy propellant management device therein. The propellant management device (PMD) can have any capillary action surface tension fluid transport features known in the art. Selected inner surfaces of the tank and the PMD are covered with a titanium based coating to guarantee propellant wettability and corrosion resistance of the fuel supply system. | 09-27-2012 |
| 20120240107 | METHOD FOR DOWNLOADING SOFTWARE TO AN ELECTRONICS PRODUCT - A method for updating software on an electronics system that includes a processor switchable between modes and non-volatile memory includes over-writing original application software stored in an application sector of the memory to store cloned boot software such that original boot software remains in the memory, switching the system to a mode that accesses the cloned boot software, storing a temporary key in a key sector of the non-volatile memory that overrides an original key and is configured to instruct the processor to boot the cloned boot software upon initialization, over-writing the original boot software in the boot sector to store new boot software after storing the temporary key, storing a new key in the memory that is configured to instruct the processor to boot the new boot software upon initialization, erasing the temporary key, and switching the system to a mode that accesses the new boot software. | 09-20-2012 |
| 20120237347 | Ram Air Turbine with Controlled Vibrational Resonances - A ram air turbine with a strut that is pivotable through a pivot plane about a pivot point on the strut from a generally horizontal rearward rest position to a generally vertical central operating position comprises at least one movable brace that extends between a stationary brace mounting point and a brace support point on the strut below the pivot point. | 09-20-2012 |
| 20120236498 | INTEGRATED FAN MOTOR AND CONTROLLER HOUSING - An electronics cooling system comprises a tubular fan duct and an electronics housing. The fan duct includes has a fan duct casing containing a fan with rotor blades and stator vanes. The electronics housing is mounted directly on the tubular fan duct, such that the electronics housing and the fan duct casing together enclose an interior space. A cooling airflow path extends from a high-pressure region of the tubular fan duct, through an inlet hole into the interior space, and out a bleed hole into a surrounding environment. The electronics cooling system further comprises three electronics mounts within the interior space. A first electronics mount is located immediately adjacent to the inlet hole, on the fan duct. A second electronics mount is located immediately radially outward of the stator vanes, on the fan duct. A third electronics mount is located immediately adjacent to the bleed hole, on the housing. | 09-20-2012 |
| 20120236439 | ELECTRICAL ACCUMULATOR UNITS WITH SAFE TURN-OFF - An electrical accumulator unit includes a power storage device, a first switch, a power converter, a controller, and a dissipation circuit for dissipating energy remnant in the power converter when the electrical accumulator unit is turned Off. The first switch connects the power storage device to the power converter, which includes at least a second switch that is selectively turned On and Off to regulate the transfer of power between the power storage device and an output of the electrical accumulator unit. The controller turns Off the electrical accumulator device by turning Off the first switch, thereby disconnecting the power storage device from the power converter, and turning On the second switch to connect the dissipation circuit to the power converter in a recirculation circuit path that dissipates energy stored in the power converter. | 09-20-2012 |
| 20120235496 | POWER DISTRIBUTION UNIT AND METHOD OF DISTRIBUTING HIGH DENSITY POWER - A power distribution unit includes a first solid state power module comprising a first plurality of solid state power controllers, where the first solid state power module comprises a first set of power characteristics. Also included is a second solid state power module comprising a second plurality of solid state power controllers. The second solid state power module comprises a second set of power characteristics. Also, the first solid state power module and the second solid state power module are interchangeably coupled to a first location of a common chassis. | 09-20-2012 |
| 20120234520 | TRANSFORMER ASSEMBLY WITH ENHANCED AIR COOLING - A cooling system for a transformer comprises a fan duct and a housing which together enclose an interior space. A transformer located in the interior space is mounted on the fan duct, and has a plurality of core sections surrounded by windings and separated by gaps. An air channeling structure is located between the transformer and the fan duct. A cooling airflow path extends through the air channeling structure, and between core sections of the transformer. | 09-20-2012 |
| 20120234015 | DUAL PUMP FUEL FLOW SYSTEM FOR A GAS TURBINE ENGINE AND METHOD OF CONTROLLING - A fuel flow system for a gas turbine includes a first pump, a main fuel flow path and a second pump. The first pump is connected to an actuator and a metering valve. The main fuel flow path is formed between the first pump and the metering valve. The second pump is connected to the main fuel flow path and supplements the fuel flow from the first pump under certain conditions. The second pump and first pump are in parallel. | 09-20-2012 |
| 20120234014 | FLOW CONTROL SYSTEM AND METHOD FOR CONTROLLING TWO POSITIVE DISPLACEMENT PUMPS - A fuel flow system for a gas turbine engine includes a first pump, a second pump, a bypass loop, an integrating bypass valve and a pilot valve. The first pump connects to an actuator and a metering valve. The second pump connects to the metering valve and is arranged in parallel with the first pump. The bypass loop recycles fuel flow from the first pump and the second pump to inlets of the first pump and second pump integrating bypass valve includes first and second windows. The first window regulates fuel from the first pump through the bypass loop and the second window that regulates fuel from the second pump through the bypass loop. The pilot valve controls the size of the first and second windows. | 09-20-2012 |
| 20120223702 | SPRING LOADED GEAR DRIVEN RESOLVER - A resolver apparatus can include a resolver driven gear, a resolver stator, a resolver rotor coupled to the resolver stator and a resolver rotor drive shaft coupled to the resolver rotor, wherein the resolver rotor drive shaft is spring loaded to the resolver driven gear. | 09-06-2012 |
| 20120221157 | LOW PRESSURE SPOOL EMERGENCY GENERATOR - An emergency power system is useable on an aircraft having a gas turbine engine with a low pressure spool and a high pressure spool. The emergency power system includes an emergency electrical generator coupled to the low pressure spool during an emergency for generating emergency electrical power and one or more additional electrical power sources. A plurality of electrical loads are electrically connected to the emergency electrical generator and the one or more additional electrical power sources. Aircraft sensors provide data regarding emergency electrical power availability and emergency electrical power demand. A controller for controlling the emergency electrical generator determines emergency electrical power demand and emergency electrical power availability based upon data from the aircraft sensors. The controller controls the emergency electrical generator based upon the emergency electrical power demand and the emergency electrical power availability. | 08-30-2012 |
| 20120219429 | FUEL SYSTEM - An aircraft engine fuel system is provided and includes a pump, including an inlet and an outlet, from which pressurized output is produced, a valve disposed downstream from the pump outlet to receive and to direct the pump output flow toward the engine and to provide a leak tight seal when the pump is not operating, a sensor configured to issue a signal reflective of a state of the valve at first and second conditions and a controller, operably coupled to the pump and the sensor, which is receptive of the signal and which modifies performance models of the pump and engine to control pump speed to modify pump flow accordingly. | 08-30-2012 |
| 20120212083 | COOLING OF PERMANENT MAGNET ELECTRIC MACHINE - A cooling system for a sealed permanent magnet electric machine includes one or more flow driving devices disposed at a rotor of the electric machine configured to urge an airflow across a plurality of permanent magnets of the rotor and across a plurality of stator end turns of the electric machine to remove thermal energy therefrom. A plurality of cooling channels are located in the electric machine in thermal communication with the stator configured to transfer thermal energy from the stator to a flow of fluid coolant through the plurality of cooling channels. A heat exchanger is in thermal communication with the plurality of cooling channels to transfer thermal energy from the airflow to the fluid coolant. | 08-23-2012 |
| 20120212082 | COOLING OF PERMANENT MAGNET ELECTRIC MACHINE - A cooling system for a sealed permanent magnet electric machine includes a fan element configured to urge an airflow across a plurality of permanent magnets of a rotor of the electric machine to remove thermal energy therefrom. A plurality of cooling channels are located in a housing of the electric machine and are configured to transfer thermal energy from a stator of the electric machine to a flow of liquid coolant through the plurality of cooling channels. A heat exchanger is located in thermal communication with the plurality of cooling channels to transfer thermal energy from the airflow to the liquid coolant. One or more coolant supply conduits are configured to divert a portion of the airflow from the heat exchanger to an ancillary component of the electric machine to allow for transfer of thermal energy from the ancillary component to the airflow. | 08-23-2012 |
| 20120206880 | THERMAL SPREADER WITH PHASE CHANGE THERMAL CAPACITOR FOR ELECTRICAL COOLING - A cooling assembly comprises an electronic component, a thermal spreader, a cold plate, and a phase change thermal capacitor. The thermal spreader conducts heat freely between the electronic component, the phase change thermal capacitor, and the cold plate. The cold plate dissipates heat. The phase change thermal capacitor stores undissipated heat in a phase transition of a phase change material. | 08-16-2012 |
| 20120205994 | FLOODED VARIABLE SPEED ELECTRIC MACHINE WITH VARIABLE FLOW - An electric machine includes a rotor, a stator, and an air gap defined by a space between the rotor and a stator. A volume of cooling fluid is located in the air gap and in contact with both the rotor and the stator. A method for cooling the electric machine includes sensing speed of the electric machine and varying the volume of coolant located in the air gap in response to the sensed speed of the electric machine. | 08-16-2012 |
| 20120200183 | BEARINGLESS MACHINE - A rotating machine comprises a stationary subassembly, a rotating subassembly, and a first circumferential track. The stationary subassembly includes a plurality of stator elements disposed proximate an inner circumference of a portion of the stationary subassembly, and a casing having a first portal. The rotating subassembly includes a plurality of rotor elements disposed proximate an outer circumference of a portion of the rotating subassembly. The rotating subassembly is aligned coaxially within the stationary subassembly and is rotatable relative to the stationary subassembly without the aid of support bearings. The first circumferential track is defined by a first rotor track portion on the rotating subassembly and a first stator track portion on the stationary subassembly, and is in communication with a first portal on the casing. | 08-09-2012 |
| 20120199229 | GAS OVER LIQUID ACCUMULATOR - A fluid system comprises a pressure vessel with a baffle oriented at a skew angle. The baffle divides the vessel into first and second volumes. A first port is provided to introduce a pressurizing fluid into the first volume, and a second port is provided to circulate a working fluid within the second volume. A purge aperture is provided to purge the pressurizing fluid from the second volume across the baffle into the first volume, and a flow aperture is provided to transfer the working fluid through the baffle between the first and second volumes. | 08-09-2012 |
| 20120199211 | AIRFLOW CONTROL SYSTEM - An airflow control system for controlling pressure and flow through a flow passage with an upstream portion and a downstream portion includes a valve which can open to different positions for controlling pressure at a downstream portion of the flow passage; a valve actuator which receives electrical signals to control the opening and closing of the valve; and a pneumatic feedback system to stabilize the valve actuator. | 08-09-2012 |
| 20120198697 | ANTI-ROTATION MECHANISM FOR PITOT TUBE - A valve assembly is provided and includes a pitot tube having an angled tip to extract from a duct formed by a housing a sample of a fluid to be communicated to an actuator configured to operate the duct, the pitot tube being disposed within the housing whereby the pitot tube is fixed longitudinally between the actuator and the housing and laterally within the housing and an anti-rotation mechanism coupled with the pitot tube to rotationally secure the pitot tube such that the angled tip is fixed to face rearwardly. | 08-09-2012 |
| 20120195578 | IMAGING SYSTEM FOR HOLLOW CONE SPRAY - An imaging system to collect image data relating to a conical liquid film and its hollow conical spray emanating from an injector with a central spray axis includes a light source for emitting light into the film and spray generated by the injector; and a detector array located downstream from the injector along the central spray axis for panoramically detecting instantaneously for the entire film and spray the emitted light which has interacted with the spray to produce the image data. | 08-02-2012 |
| 20120194948 | INDEPENDENT, REDUNDANT OVERVOLTAGE PROTECTION FOR A GENERATOR - A generator controller provides independent and redundant overvoltage protection to an associated generator. The generator controller monitors the generator output at a first point of a regulation and a second point of regulation. A generator control unit (GCU) provides overvoltage protection based on the generator output monitored at the first point of regulation, including at least one of tripping a first generator control relay (GCR) to remove excitation from an exciter winding and tripping a generator line contactor (GLC) to disconnect the generator output from a bus. A overvoltage protection unit (OPU) provides independent, redundant protection based on the generator output monitored at the second point of regulation, including at least one of tripping a second GCR to remove excitation from the exciter winding and tripping the GLC to disconnect the generator output from the bus. | 08-02-2012 |
| 20120194201 | FREQUENCY BASED FAULT DETECTION - A electrical circuit includes an excitation voltage connected via a first circuit path to an output, a switching device having a control terminal and first and second controlled terminals connected to the first circuit path, and a controller that generates a control signal provided to the control terminal of the switching device to selectively supply the excitation voltage to the output. Faults in the electrical circuit are detected by monitoring the switching device voltage at one of the controlled terminals of the switching device. | 08-02-2012 |
| 20120192578 | GAS TURBINE BLEED ECS COOLING - A method for managing heat in an airplane includes extracting hot bleed air from a gas turbine engine, and cooling the hot bleed air in a first heat exchanger thereby forming warm bleed air. The method further includes expanding the warm bleed air with a turbine thereby forming cool bleed air, and using the cool bleed air as a heat sink in a second heat exchanger associated with an environmental control system and thereby forming used bleed air. | 08-02-2012 |
| 20120192569 | PITOT TUBE WITH INCREASED PARTICLE SEPARATION EFFICIENCY - A pneumatically actuated valve includes a valve body, a pneumatic actuator, and a pitot tube. The valve body includes a valve disc positioned in a valve housing that defines a flow passage with a flow passage diameter. The pneumatic actuator rotates the valve disc in the valve housing. The pitot tube is connected to the pneumatic actuator and has a tip extending into the flow passage. The tip is spaced apart from the valve housing by at least 1/20 of the flow passage diameter. The tip is substantially free of downstream obstructions for a distance equal to at least ½ of the flow passage diameter when the valve is in an open position. | 08-02-2012 |
| 20120187969 | BUILT-IN TEST FOR AN OVERVOLTAGE PROTECTION CIRCUIT - An overvoltage protection circuit connected to protect electrical components from overvoltage conditions includes a blocking diode connected in series with a transient voltage suppression device (TVS) via a first node and includes a reference voltage for biasing the first node at a voltage sufficient to reverse bias the blocking diode during normal operations. A built-in test circuit associated with the overvoltage protection circuit includes a resistor connected to the first node and a switch connected in series with the resistor that is selectively turned On and Off. The built-in test circuit monitors voltage on a control line associated with the electrical components and at the first node while the switch is Off and while the switch is On, and detects fault conditions based on the monitored voltages. | 07-26-2012 |
| 20120186673 | AIRCRAFT ENGINE FUEL SYSTEM - An aircraft fuel system is provided and includes a metering valve having inlet and outlet sides to monitor fuel flow from the inlet to the outlet side, a check valve that, when opened, allows fuel to flow toward the inlet side during start and climb conditions and, when closed, prevents such fuel flow and an ejector pump, which is operably disposed between the check valve and the metering valve, and which, with the check valve closed, pumps fuel toward the inlet side during idle conditions. | 07-26-2012 |
| 20120186283 | COMPRESSOR MOTOR PREHEAT CONTROL - A method of controlling a vapor cycle system having first and second compressors includes operating the first compressor to compress refrigerant while the second compressor is idle, sensing a motor temperature of the second compressor, activating a preheating mode in which the motor of the second compressor is powered to generate heat when the motor temperature of the second compressor is below a lower temperature threshold, turning off the preheating mode when the sensed motor temperature of the second compressor is above an upper temperature threshold, and limiting the maximum duration of the preheating mode to a preheating time period, such that the preheating mode is turned off after being activated for the preheating time period. | 07-26-2012 |
| 20120186282 | RECIRCULATION HEAT EXCHANGER OUTLET HEADER - An air cooling system includes a heat exchanger, an inlet duct, an outlet duct, and an outlet header. The inlet duct is fluidly connected to the heat exchanger and is configured to direct relatively warm air from the cabin into the heat exchanger. The outlet duct is fluidly connected to the heat exchanger and configured to direct relatively cool air out of the heat exchanger and back to the cabin. The outlet header is located between the heat exchanger and the outlet duct. The outlet header has a shape configured to collect water from the cool air. | 07-26-2012 |
| 20120186063 | HYBRID CASCADING LUBRICATION AND COOLING SYSTEM - A hybrid cascading lubrication and cooling system ( | 07-26-2012 |
| 20120185116 | INTEGRATED BLEED AND ENGINE CONTROLLER - An integrated electronic engine control and environmental control system bleed control apparatus for use with an aircraft engine. The apparatus comprises an electronic engine controller, an environmental control system bleed controller for controlling a flow of bleed air from the aircraft engine to an environmental control system located in an aircraft fuselage, and a housing for mounting on or near the aircraft engine. The housing contains both the electronic engine controller and the environmental control system bleed controller. | 07-19-2012 |
| 20120183399 | METHOD AND APPARATUS FOR BALANCING WIND TURBINES - A method for balancing blades of a wind turbine comprises several steps. First, vibration sensor readings are taken while wind turbine blades are in a pre-balancing configuration. These vibration sensor readings are used to determine initial blade imbalance. Next, vibration sensor readings are taken while wind turbine blades are in a first and a second pitch offset configuration. These vibration sensor readings are used to determine system response to the first and second pitch offset configurations. A correction pitch configuration is determined from the initial blade imbalance and the system response. Finally, blades of the wind turbine are pitched according to the correction pitch configuration. | 07-19-2012 |
| 20120181892 | FLUX CANCELLATION IN A PERMANENT MAGNET GENERATOR - A permanent magnet comprises a primary winding, a secondary winding, a permanent magnet, an output terminal for connection to an external load, and a switching mechanism with two modes. In a first mode of the switching mechanism, the primary winding is connected between neutral and the output terminal, and the varying magnetic flux from the permanent magnet induces a nonzero voltage at the output terminal. In the second mode, the secondary winding provides a return path to neutral for the primary winding, thereby providing negligible voltage and current at the output terminal and substantially canceling change in magnetic flux from the permanent magnet. | 07-19-2012 |
| 20120181467 | WEAR INTERFACE FOR BUTTERFLY VALVE - A butterfly valve comprises a housing including a bore, a rotatable shaft passing through the bore, a disc mounted to the shaft for controlling the flow of a fluid through the bore, a thrust load reacting section and a wear interface. The thrust load reacting section includes a thrust plug assembled in a thrust reacting end of the shaft and a thrust plate secured to the housing. The thrust plate has a well for axially retaining the thrust plug and the thrust reacting end of the shaft. The wear interface includes a first contact region on the thrust plug with a first contact surface and a second contact region at the base of the well with a second contact surface. A portion of the first contact surface is spherical and in contact with a portion of the second contact surface. | 07-19-2012 |
| 20120180886 | BLEED VALVE MODULE WITH POSITION FEEDBACK AND COOLING SHROUD - A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements. | 07-19-2012 |
| 20120180509 | LOW PRESSURE BLEED ARCHITECTURE - A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line. | 07-19-2012 |
| 20120180501 | BLEED VALVE MODULE - A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration. | 07-19-2012 |
| 20120176716 | VERTICAL MOUNT TRANSIENT VOLTAGE SUPPRESSOR ARRAY - A system comprises a package with top and bottom surfaces, a plurality of high-power transient voltage suppressors arranged within the package, and a robust lead frame. Each of the transient voltage suppressors has first and second major surfaces substantially perpendicular to the top and bottom surfaces of the package. The lead frame comprises leads connected to the major surfaces of the transient voltage suppressors. Each of the leads has a thickness greater than about 0.015 inches (or 0.381 mm) in a mounting portion, in order to dissipate heat from the transient voltage suppressors and to resist vibration-induced stress on the package. | 07-12-2012 |
| 20120175543 | VALVE RELEASE MECHANISM - A valve release mechanism has an actuator, a ring, a plurality of ball bearings, and a retainer. The retainer is positioned adjacent an inner diameter of the ring and has a plurality of circumferentially spaced holes therein. Each circumferentially spaced hole receives one of the plurality of ball bearings, which are movable therein. The ring has channels and lands along its inner diameter that allow the ball bearings to move varying distances relative to the retainer. The lands contact the ball bearings when the ring is in a first position and the channels receive the ball bearings when the ring is in a second position. The poppet has a groove that is vertically aligned with circumferentially spaced holes in the retainer when the poppet is in a first closed position. The ball bearings are pressed into the groove in the poppet by the lands of the ring. The resulting interference of the ball bearings with poppet locks the poppet in the first closed position. The ring can be moved from the first closed position to a second position by the actuator. | 07-12-2012 |
| 20120173173 | RAM AIR TURBINE WITH FLUX REGULATED PERMANENT MAGNET GENERATOR AND TESTING METHOD - A deployable ram air turbine assembly includes a rotatable turbine, a drivetrain mechanically connected to the rotatable turbine, and a flux regulated permanent magnet generator operably connected to the drivetrain. | 07-05-2012 |
| 20120168112 | LAMINATED HEAT EXCHANGER - A laminated heat exchanger includes at least one heat exchange layer that includes a plurality of side members that define a frame having an interior portion. A plurality of heat exchange members extend between at least two of the plurality of side members across the interior portion. The plurality of heat exchange members are linked by a ligament member to form a heat exchange member chain. | 07-05-2012 |
| 20120167594 | Bypass Monitor for Fuel Supply System - A method for monitoring a fuel supply system for a turbine engine, the fuel supply system comprising a fuel pump and a pressure regulation valve configured to receive fuel from an outlet of the fuel pump includes determining by a bypass monitor an amount of bypass flow in a bypass path located between the pressure regulation valve and an inlet of the fuel pump; determining an amount of leakage flow in the fuel supply system by the bypass monitor based on the bypass flow; and determining whether the leakage flow exceeds a predetermined threshold by the bypass monitor, and in the event the leakage flow exceeds the predetermined threshold, indicating a need for maintenance of the fuel supply system. | 07-05-2012 |
| 20120160466 | SURFACE COOLER HAVING CHANNELED FINS - A surface cooler includes a base plate, and at least one fin element extending from the base plate. The at least one fin element includes an outer surface portion that is configured and disposed to be in direct contact with a first fluid and an inner surface portion that is configured and disposed to be in direct contact with a second fluid. The at least one fin element defines a primary heat exchange member that is configured and disposed to facilitate an exchange of heat between the first and second fluids. | 06-28-2012 |
| 20120160098 | METHOD AND SYSTEM FOR CARBON DIOXIDE REMOVAL - A carbon dioxide (CO | 06-28-2012 |
| 20120156077 | CAM LINER PROFILE - A vane pump is provided and includes a liner having an inlet window and a discharge window, the liner being formed to define a cam surface and a rotor carrying a plurality of radially extending vanes which are forced outwardly such that vane tips thereof contact with the cam surface, the rotor having a direction of rotation such that one end of the inlet window is an upstream end and an opposed end is a downstream end, a radius of each of the vane tips being approximately 0.114 inches (0.3 cm) and a profile of the cam surface being defined in accordance with the radius of the vane tips. | 06-21-2012 |
| 20120155966 | GAS AND LIQUID RECOVERY FROM REGOLITH - A resource recovery system includes a capture container located at a desired surface defining a capture volume between the surface and an interior of the capture container. One or more hole-making devices are configured to excavate soil from at least one hole in the surface. One or more energy emitters direct energy toward the excavated soil to heat the excavated soil thereby releasing one or more compounds. The capture container is configured to capture gas and/or liquid compounds released from the excavated soil. A method of resource extraction from soil includes covering a desired surface with a capture container defining a capture volume between the desired surface and an interior of the capture container. Soil is excavated from a hole in the desired surface into the capture volume. The excavated soil is heated via one or more energy emitters thereby releasing one or more compounds into the capture volume. | 06-21-2012 |
| 20120152537 | AUGER FOR GAS AND LIQUID RECOVERY FROM REGOLITH - A resource recovery system includes a capture container located at a desired surface defining a capture volume between the surface and an interior of the capture container. One or more hole-making devices are located in the capture container to excavate soil from at least one hole in the surface. A heater located in the hole making device heats the excavated soil, releasing one or more compounds from the excavated soil. The capture container is configured to capture gas and/or liquid compounds released from the excavated soil. A method of resource extraction from soil includes covering a desired surface with a capture container defining a capture volume between the desired surface and an interior of the capture container. Soil is excavated from a hole in the desired surface into the capture volume with an auger. The auger heats the excavated soil thereby releasing one or more compounds into the capture volume. | 06-21-2012 |
| 20120152301 | CENTER-TAPPED SOLAR ARRAY AND POWER DISTRIBUTION SYSTEM FOR SAME - A center-tapped solar array includes a plurality of series-connected solar cells connected between a positive terminal and a negative terminal for generating an output voltage. A center-tapped terminal connected to ground is connected to the plurality of series-connected solar cells at a midpoint between the positive and negative terminals. As a result, the positive terminal of the solar array has a positive voltage relative to ground greater than the center-tapped terminal and the negative terminal has a negative voltage relative to ground less than the center-tapped terminal. | 06-21-2012 |
| 20120148369 | SEALING WASHER ASSEMBLY FOR LARGE DIAMETER HOLES ON FLAT SURFACES - A sealing washer assembly includes a main washer with a bottom annular groove for a removable O-ring and a top recess for a sealing washer. A fastener such as a screw or bolt passes through the sealing washer and the main washer, into a hole in a mounting surface. When the fastener is tightened, the main washer is clamped to the mounting surface to create a metal-to-metal seal, the O-ring is deformed to create a seal between the main washer and the mounting surface, and the sealing washer is deformed to create a seal between the fastener and the main washer. | 06-14-2012 |
| 20120144841 | CORE DIFFUSER FOR DEOILER/BREATHER - A breather assembly for use with a gas turbine engine includes a static housing for accepting a fluidic mixture of substances, a rotatable separator having one or more fluid inlets and arranged about an axis of rotation, an exhaust outlet defined in the housing and positioned coaxially with the rotatable separator to accept fluidic exhaust from the rotatable separator, and a static diffuser supported by the housing at or near the exhaust outlet downstream from the rotatable separator. A portion of the static diffuser extends within the rotatable separator. The static diffuser includes a flow-straightening structure configured to reduce vortex flows in fluid flows passing through the exhaust outlet. | 06-14-2012 |
| 20120141258 | AIR TURBINE STARTER - An air turbine starter is provided and includes a rotor including turbine blades, which is rotatable about a rotational axis, a housing including a portion thereof radially surrounding the turbine blades to define a pathway along which fluids flow to interact with the turbine blades and a containment ring affixed to an exterior of the portion of the housing radially surrounding the turbine blades. | 06-07-2012 |
| 20120141248 | ACTIVE FAN FLUTTER CONTROL - A flutter control system for a turbomachine fan includes a plurality of fan case sensors located at a fan case of the turbomachine and configured to sense passing of blade tips of a fan of the turbomachine. A controller is operably connected to the plurality of fan case sensors. A variable fan area nozzle actuator is operably connected to the controller, such that the variable fan area nozzle actuator urges a change in fan nozzle area in response to data from the plurality of fan case sensors indicating flutter or near flutter conditions. A method of flutter control for a turbomachine fan includes sensing a blade tip passing of a plurality of fan blades. Data from a plurality of fan case sensors is compared to a threshold and a fan exit area is changed based on the comparison to dampen flutter of the plurality of fan blades. | 06-07-2012 |
| 20120140537 | ACTIVE RECTIFICATION CONTROL - An active rectification system includes an active rectifier, a pulse width modulation (PWM) control, and a closed loop vector control. The PWM control portion is configured to control switching of the active rectifier and the closed loop vector control is configured to generate the required duty cycles for the PWM signals that regulate the DC voltage output and force a three-phase current input of the active rectifier to align with a three-phase pole voltage input of the active rectifier. | 06-07-2012 |
| 20120139531 | POSITION DETECTING SYSTEM - A position detecting system for a differential movement system which moves a first surface and a second surface from a fixed surface includes an actuation system to move the second surface relative to the first surface and to allow the second surface to move with the first surface; a sensor connected to the actuation system to detect a parameter of the actuation system related to an expected amount of movement of the second surface to determine the expected amount of movement of the second surface; and a sensor system connected to the second surface and the fixed surface to detect the amount of actual movement of the second surface. | 06-07-2012 |
| 20120139354 | No Break Power Transfer for Power Generating System - A method for no break power transfer in a variable frequency power generating system, the power generating system comprising a first bus connected to a first generator and a second bus connected to a second generator includes configuring a power transfer device to output power that is synchronized to match a voltage and a frequency of the second bus to the second bus; reconfiguring the power transfer device to output power that is synchronized to match a voltage and a frequency of the first bus to the second bus; and closing a tie switch located between the first bus and the second bus. | 06-07-2012 |
| 20120137656 | ACTUATION SYSTEM - A system to provide differential movement between a first surface, a second surface and a fixed surface includes a first surface movable between a first position and a second position; a second surface movable with the first surface and further movable beyond the first surface; a shaft connected to the second surface to move the second surface; and a drive unit connected to the fixed surface to drive the shaft to move the second surface relative to the first surface and to allow the shaft to move through the drive unit when the second surface is being moved by the first surface. | 06-07-2012 |
| 20120134800 | PROPELLER PITCHLOCK UN-LOCKING DEVICE - A propeller system includes a plurality of propeller blades and a pitch lock mechanism operably connected to the plurality of propeller blades. The pitch lock mechanism includes a pitch lock chamber and a pitch lock piston located in the pitch lock chamber biased toward a locked position when there is insufficient pressure in the pitch lock chamber thereby locking the pitch of the plurality of propeller blades. The propeller system includes a pitch unlock mechanism including a pitch unlock housing and a pitch unlock piston disposed in the pitch unlock housing. A fitting extends through the propeller system to the pitch unlock housing and introduction of fluid flow into the pitch unlock housing through the fitting urges the pitch unlock piston into contact with the pitch lock piston to overcome the bias of the pitch lock piston thereby unlocking the pitch of the plurality of propeller blades. | 05-31-2012 |
| 20120130587 | METHOD OF MONITORING AN ELECTRONIC ENGINE CONTROL (EEC) TO DETECT A LOSS OF FUEL SCREEN OPEN AREA - A method of sensing a reduction in fuel screen area in a fuel system. The method includes detecting an engine shutdown, initiating an electronic engine control (EEC) built in test, shifting a metering valve from a first position to a second position, determining a travel time of the metering valve, and sensing a reduction in fuel screen area based on the travel time of the metering valve. | 05-24-2012 |
| 20120126758 | HIGH VOLTAGE DC POWER GENERATION - A DC power system includes a permanent magnet generator (PMG), and an active rectifier in electrical communication with the PMG. The active rectifier is adapted to actively rectify power output from the PMG if the PMG is operating at low speed, and the active rectifier is further adapted to passively rectify power output from the PMG if the PMG is operating at high speed. | 05-24-2012 |
| 20120125594 | Heat Exchanger System - A heat exchanger system is provided having a heat exchanger with a first inlet. A first outlet is fluidly coupled to the first inlet by a plurality of first channels. A second outlet is fluidly coupled to the first inlet by a second channel, the second channel having a first portion arranged transverse to the plurality of first channels. A bypass valve having a second inlet fluidly coupled to the first outlet and a third inlet fluidly coupled to the second outlet, and a third outlet selectively fluidly coupled to the second inlet and the third inlet, the third outlet being fluidly coupled to the first inlet. When in a bypass mode of operation, the thermal transfer medium flows through a channel in the heat exchanger to de-congeal the oil within the plurality of first channels. | 05-24-2012 |
| 20120121495 | HIGH TEMPERATURE STABLE NANOCRYSTALLINE SiGe THERMOELECTRIC MATERIAL - A method of forming a nanocomposite thermoelectric material having microstructural stability at temperatures greater than 1,000° C. The method includes creating nanocrystalline powder by cryomilling. The method is particularly useful in forming SiGe alloy powder. | 05-17-2012 |
| 20120121373 | Cranking Pad Interlock - A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing. | 05-17-2012 |
| 20120120689 | FAULT TOLERANT DC POWER SYSTEMS - A fault tolerant DC power system includes a permanent magnet generator (PMG), a first contactor in electrical communication with the PMG, an active rectifier in electrical communication with the first contactor, a second contactor in electrical communication with the first contactor, and a motor drive in electrical communication with the second contactor. The first contactor is configured to sever electrical communication between the PMG and the active rectifier and the second contactor is configured to establish electrical communication between the PMG and the motor drive. | 05-17-2012 |
| 20120119711 | HIGH VOLTAGE DC POWER GENERATION - A DC power generating system includes a permanent magnet generator (PMG), an active rectifier in electrical communication with the PMG, and a controller in electrical communication with the active rectifier, wherein the controller is configured to regulate d-q components of a stator current of the PMG in a synchronous reference frame. | 05-17-2012 |
| 20120119602 | Cooling of Permanent Magnet Electric Machine - A permanent magnet electric machine includes a rotor having a plurality of permanent magnets and a stator in magnetic communication with the rotor and positioned defining a radial air gap between the rotor and the stator. A housing is configured to seal the rotor and the stator from an outside environment. A pumping element is configured to urge a closed loop airflow across the plurality of permanent magnets to remove thermal energy therefrom, and a plurality of cooling channels are located in the housing and are configured to transfer thermal energy from the stator to a flow of fluid coolant through the plurality of cooling channels. A heat exchanger is located in thermal communication with the plurality of cooling channels to transfer thermal energy from the airflow to the fluid coolant. | 05-17-2012 |
| 20120118103 | INTEGRATED ACCESSORY GEARBOX AND ENGINE STARTER - An air turbine starter and accessory gearbox assembly, the accessory gearbox includes a gear shaft and the air turbine starter includes an output shaft and a clutch assembly. The output shaft extends from the accessory gearbox and is coupled to and supported by the gear shaft. The accessory gearbox is adapted to receive the air turbine starter such that the clutch assembly and the output shaft are disposed within a casing of the accessory gearbox when the air turbine starter is mounted to the accessory gearbox. | 05-17-2012 |
| 20120117974 | AIR FLOW DELIVERY AND FUEL CONSUMPTION CONTROL FOR AIRCRAFT AIR MANAGEMENT AND AUXILIARY POWER SYSTEMS - A turbine controller controls the operation of a gas turbine generator used to drive an electric generator of an aircraft. The turbine controller controls the gas turbine generator according to air flow demand signals indicative of air flow required by an air management system that regulates cabin pressure and temperature of the aircraft. | 05-17-2012 |
| 20120114504 | VERTICAL SHAFT PUMPING SYSTEM - A vertical shaft pumping system includes a hollow shaft with an inner bore, an inlet end and an outlet end, the outlet end with at least one liquid distribution hole. It further includes an impeller positioned at the lower inlet end of the shaft, with a cylindrical base portion with a lower end, a central hole for drawing fluid into the shaft, and a plurality of teeth extending upwards from the cylindrical base portion and extending radially from the central hole to the outer cylindrical circumference for increasing tractive force of liquid in the shaft when the impeller and shaft are rotating; and a motor for rotating the shaft with the impeller to centrifugally pump a liquid vertically in the shaft from the lower inlet end to the upper outlet end. | 05-10-2012 |
| 20120114485 | RAM AIR TURBINE STARTUP - A ram air turbine (RAT) in which a cam follower is operably coupled to turbine blades such that a cam follower position determines turbine blade pitch. | 05-10-2012 |
| 20120114475 | AIR TURBINE STARTER ONE-PIECE AIR EXIT PORT BAFFLE - A one-piece air exit port baffle for containment for an air start turbine includes a circular arc section with a circumferentially corrugated circular arc section and a flange section. The circumferentially corrugated circular arc section has a plurality of openings. The flange section is axially adjacent to the circumferentially corrugated circular arc section and configured for attachment adjacent to an air exit port of an air turbine starter. | 05-10-2012 |
| 20120114463 | MOTOR DRIVEN CABIN AIR COMPRESSOR WITH VARIABLE DIFFUSER - An air cycle machine is provided and includes a compressor section having a variable area diffuser, a turbine section having an inlet nozzle with a variable size, a motor to drive the compressor and a common rotating shaft on which the compressor section, the turbine section and the motor are mounted, the turbine section driving rotation of the shaft to drive the compressor section with the motor. | 05-10-2012 |
| 20120112578 | HEAT TRANSFER ASSEMBLY FOR ELECTRIC MOTOR ROTOR - A motor driven assembly comprises a motor shaft, a rotor, a passage, and a corrugated fin heat transfer structure. The motor shaft is mounted for rotation about a rotational axis. The rotor is located radially about the shaft. The passage extends through the rotor alongside the motor shaft. The corrugated fin heat transfer structure is disposed within the passage radially aligned with the rotor. | 05-10-2012 |
| 20120112575 | INTEGRATED PERMANENT MAGNET ALTERNATOR AND COOLING FAN - A permanent magnet alternator includes a permanent magnet alternator stator attached to a housing. A shaft is rotatable with respect to the housing with a permanent magnet alternator rotor attached to the shaft. The permanent magnet alternator rotor is positioned with respect to the permanent magnet alternator stator so as to generate electricity when the shaft rotates. A cooling fan is also attached to the shaft and is positioned in a gas flow path for flowing air through the gas flow path. | 05-10-2012 |
| 20120112103 | SEAL ASSEMBLY FOR METERING VALVE - A seal assembly for an electric component includes a generally cylindrical plug, a first O-ring seal and a second O-ring seal. The plug includes a sidewall extending between first and second end walls. An annular groove circumscribes the sidewall. A first O-ring seal is disposed in the annular groove. A first through-bore extends between the first end wall and the second end wall. A first counter-bore circumscribes the first through-bore in the first end wall. A second O-ring seal is disposed within the first counter-bore. | 05-10-2012 |
| 20120111536 | AQUEOUS BASED COOLING OF COMPONENTS HAVING HIGH SURFACE AREA LEVELS OF ALUMINUM OR NICKEL - An aqueous-based coolant for cooling and reducing corrosion potential in applications having high aluminum or nickel surface area to coolant volume ratios has a pH between 8 and 9 and includes about 35 weight % to about 65 weight % propylene glycol, about 1.0 weight % to about 4.0 weight % 2-ethylhexanoic acid, about 0.25 weight % to about 1.0 weight % sebacic acid, about 0.25 weight % to about 1.0 weight % benzoic acid and about 0.03 weight % to about 0.1 weight % molybdate oxyanion. A cooling system includes an aluminum or nickel surface and the aqueous-based coolant. A method of cooling a component surface containing aluminum or nickel includes delivering the aqueous-based coolant to the component surface and cooling the component surface with the aqueous-based coolant. | 05-10-2012 |
| 20120111046 | THERMAL MANAGEMENT SYSTEM WITH STAGED COOLING - A thermal management system comprises a first heat exchanger having an inlet and an outlet, a second heat exchanger having an inlet and an outlet, a fluid loop, a first heat pump, and a second heat pump. The fluid loop circulates a fluid, and forms a continuous path between the first and second heat exchangers. The first heat pump is connected to the fluid loop and is disposed between the outlet of the second heat exchanger and the inlet of the first heat exchanger. The second heat pump is connected to the fluid loop and is disposed between the outlet of the first heat exchanger and the inlet of the second heat exchanger. | 05-10-2012 |
| 20120111022 | COMBINED AIR TURBINE STARTER, AIR-OIL COOLER, AND FAN - An air turbine starter assembly includes a starter turbine housing having a turbine gas flow path and a fan gas flow path, and a shaft rotatable with respect to the starter turbine housing. A plurality of turbine blades are connected to the shaft. A plurality of fan blades are also connected to the shaft. | 05-10-2012 |
| 20120107131 | CENTRIFUGAL COMPRESSOR IMPELLER - A compressor impeller includes a hub, main blades and splitter blades. The main blades are equally spaced around the circumference of the hub. Each splitter blade is equally spaced between two adjacent main blades. Each main blade and splitter blade has suction and pressure surfaces formed in substantial compliance with normalized Cartesian coordinate values of X, Y, and Z set forth in Tables 1-4. When connected by smooth, continuing arcs, the normalized Cartesian coordinates form complete main blade and splitter blade shapes that are substantially matched by the main blade and splitter blade shapes of the compressor impeller. | 05-03-2012 |
| 20120107119 | PARTIAL COARSE PITCH START RAM AIR TURBINE WITH ENHANCED SPRING SUPPORT - A Ram Air Turbine (RAT) is provided and includes a turbine hub having an end plate and a nose cone attached thereto at trailing and leading ends, respectively, a governor shaft, to which turbine blades are connected, which is coupled to the end plate and supported within the nose cone to be rotatable with the turbine blades about a central axis thereof and axially movable from a first position relative to the turbine hub to a second position relative to the turbine hub and a hub assembly operably coupled to the turbine hub, the governor shaft and the turbine blades whereby the hub assembly biases the governor shaft toward the first position at low rotational speeds such that the turbine blades assume a partial coarse pitch angle, and the second position at high rotational speeds such that the turbine blades assume a fine pitch angle. | 05-03-2012 |
| 20120107094 | SHAFT SPEED AND VIBRATION SENSOR APPARATUS - A rotary apparatus comprises a shaft having a rotational axis, a rotation indicator formed on the shaft, a target feature proximate the rotation indicator, and a sensor proximate the target feature. The target feature extends circumferentially about the shaft, with a radial face transverse to the rotational axis and a circumferential face along the rotational axis. The sensor is oriented toward the rotation indicator to sense a rotational speed of the shaft, and oriented toward the target feature to sense transverse vibrations based on a radial distance to the target feature and longitudinal vibrations based on an axial distance to the target feature. | 05-03-2012 |
| 20120107086 | MOTOR ASSISTED FINE PITCH STARTUP RAM AIR TURBINE - A startup assistance apparatus for a fine pitch Ram Air Turbine (RAT) is provided and includes a generator to provide motive power to the RAT when operating in a first mode and to generate electricity from RAT operation when operating in a second mode and a control unit, including a speed sensing unit configured to sense an operating condition of the generator and a controller operably coupled to the generator and configured to control the generator to operate in the first or the second mode based on the sensed operating condition. | 05-03-2012 |
| 20120106009 | Shunt Regulator at Excitation Output of Generator Control Unit for Overvoltage Protection - An electrical system includes a generator; a generator control unit connected to the generator; and a shunt regulator connected to an excitation output of the generator control unit, wherein the shunt regulator is configured to overload the excitation output of the generator control unit in the event of an overvoltage condition in the electrical system, such that an output voltage of the generator does not exceed a predetermined ceiling voltage during the overvoltage condition. | 05-03-2012 |
| 20120106007 | Shunt Regulator for Overvoltage Protection at Transformer Rectifier Unit of Electrical Generating System - An electrical system includes an alternating current (AC) source; a transformer rectifier unit (TRU) connected to the AC source, the TRU configured to receive AC power from the AC source, convert the AC power to direct current (DC) power, and output DC power; a DC bus configured to receive the DC power output by the TRU; at least one DC load powered by the DC bus; and a shunt regulator connected to the output of the TRU, the shunt regulator configured to overload the output of the TRU in the event of an overvoltage condition at the output of the TRU, such that a voltage available to the DC bus during the overvoltage condition does not exceed a reference voltage. | 05-03-2012 |
| 20120105253 | FAILSAFE LED CONTROL SYSTEM - A display system comprises first and second LED panels for displaying first and second priority aviation data, a power supply, a modulator, a processor and a logic gate. The modulator generates a modulated voltage for the second LED panel, where the second priority data are displayed at a modulated brightness. The processor controls the modulator, and generates a status signal indicating a failure condition of the modulated voltage. The logic gate switches the first LED panel from the modulated voltage to the unmodulated voltage based on the status signal, where the first priority data default from the modulated brightness level to full brightness based on the failure condition. | 05-03-2012 |
| 20120104651 | METHOD OF MAKING A REINFORCED RESIN STRUCTURE - A method of making a reinforced resin structure is disclosed. A volume of uncured resin compound is placed on a first outer surface of a carrier structure comprising a plurality of fibers. The uncured resin compound and the carrier structure are pressed between two cooperating plates to disperse the resin compound into and through a plurality of passages between the plurality of fibers. The dispersed resin compound is cured to fix the resin within the plurality of passages and around the plurality of fibers. | 05-03-2012 |
| 20120103108 | ANTI-ROTATION MECHANISM FOR PITOT TUBE - A valve assembly is provided and includes a pitot tube having an angled tip to extract from a duct formed by a housing a sample of a fluid to be communicated to an actuator configured to operate the duct, the pitot tube being disposed within the housing whereby the pitot tube is fixed longitudinally between the actuator and the housing and laterally within the housing and an anti-rotation mechanism coupled with the pitot tube to rotationally secure the pitot tube such that the angled tip is fixed to face rearwardly. | 05-03-2012 |
| 20120102910 | High Flow Eductor - An exhaust eductor for a gas turbine engine comprises: an engine exhaust chamber with an exhaust chamber inlet that receives engine exhaust from the gas turbine engine and an exhaust chamber outlet that discharges the engine exhaust to establish an exhaust gas flow through the engine exhaust chamber; an air chamber with an air inlet that receives ambient air external to the gas turbine engine; and a mixing baffle that couples the air chamber to the engine exhaust chamber, comprising a first side adjacent the air chamber, a second side adjacent the exhaust chamber, multiple apertures through the mixing baffle that extend from the first side to the second side of the mixing baffle, each aperture having a corresponding canopy that extends from an upstream end of the aperture along the second side of the mixing baffle into the exhaust gas flow for at least a portion of the length of the aperture, to establish an air flow from the air inlet of the air chamber into the exhaust gas flow. | 05-03-2012 |
