| PRATT & WHITNEY CANADA CORP. Patent applications |
| Patent application number | Title | Published |
|---|
| 20120136550 | CONTROL OF GAS TURBINE ENGINE - Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters. | 05-31-2012 |
| 20120134777 | ENGINE CASE WITH WASH SYSTEM - A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct. | 05-31-2012 |
| 20120134069 | LOW INDUCTANCE CAPACITOR ASSEMBLY - A low-inductance capacitor assembly ( | 05-31-2012 |
| 20120133150 | COMBINATION LOW SPOOL GENERATOR AND RAM AIR TURBINE GENERATOR - A power generating apparatus for use with an aircraft gas turbine engine has a low pressure spool assembly which includes an electrical generator. The electrical generator includes a generator stator supported on a stationary structure of the engine and a generator rotor rotatable around the generator stator and mounted to the low pressure spool assembly. | 05-31-2012 |
| 20120126833 | NON-CONTACT STRESS MEASURING DEVICE - Apparatuses and methods for measuring stress or strain in a conductive material without physical contact with the material are provided. The device comprises an inductor circuit configured to induce an alternating current into the material along a first path; and a detector configured to detect a signal representative of the stress in the material along the first path when current is induced in the material. | 05-24-2012 |
| 20120126547 | DC MOTOR ASSEMBLY WITH SOFT STARTING CAPABILITY - A DC motor assembly ( | 05-24-2012 |
| 20120046804 | METHOD AND SYSTEM FOR GENERATING A DATA SET - Systems, methods, and stored coded instruction sets for reducing the amount of data captured, i.e., retained, by a computerized system, such as an aircraft flight control or monitoring system. Such systems can, for example, be used in monitoring and/or controlling the operation of one or more aircraft engines, flight controls, or other aircraft systems, in order to optimize storage required for collected data, and/or to reduce or otherwise control the time required to off-load captured data to another computer system, such as a land-based analysis system. The amount of data collected, e.g., captured or retained in memory, may be reduced by discarding data points that are within a specified tolerance of, for example, a previously observed or expected value in a manner which assists with preserving the accuracy and precision of the original measured data. | 02-23-2012 |
| 20120029786 | AIRCRAFT ENGINE CONTROL DURING ICING OF TEMPERATURE PROBE - Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine. | 02-02-2012 |
| 20110315484 | LUBRICATION SYSTEM FOR AIRCRAFT ENGINE - A lubrication system for an aircraft engine includes a lubrication fluid tank and a fluid passage communicating with the tank to define an entry of the passage inside the tank. The entry is positioned in a location submerged in the lubrication fluid for delivery of the lubrication fluid under a pressure differential, from the tank to the lubrication system regardless of the tank or aircraft attitude. | 12-29-2011 |
| 20110314835 | COOLER IN NACELLE WITH RADIAL COOLANT - A cooling system in an aircraft gas turbine engine includes a heat exchanger positioned within an annular nacelle space surrounding a bypass duct of the engine. The heat exchanger has a radial coolant passage extending between the bypass duct and ambient air surrounding the nacelle, and a flow passage extending substantially normal to the radial passage for direction of a fluid to be cooled therethrough. A configuration of this nature may assist in defining a no-flow length of the heat exchanger in a third direction normal to the other two mentioned directions, which may allow for improved performance within a given radial envelope. | 12-29-2011 |
| 20110213507 | HYBRID CONTROL SYSTEM - A hybrid control system for controlling an electric machine coupled to a gas turbine engine is provided. The control system comprises: a primary analog control loop including an analog controller for controlling the electric machine based on a set point and a measured output of the electric machine; and a digital controller of the turbine engine operationally connected to the primary analog control loop to adjust at least one control parameter associated with the analog controller. | 09-01-2011 |
| 20110212677 | HOUSING ASSEMBLY FOR AN ELECTRICAL DEVICE - A housing assembly for an electrical device for use on an aircraft is provided. The assembly comprises a housing configured for containing at least one electrical component in a portion of the aircraft vented to atmosphere; and a pressure communication line for communicating between an interior of the housing and a source of pressurized gas available on the aircraft for other primary purpose. | 09-01-2011 |
| 20110210688 | CONTROL OF BRUSHLESS MOTOR - Systems and methods for generating a signal useful in the commutation of current through windings of brushless direct current electric motors are provided. Such methods comprises detecting a kickback pulse in a non-driven winding of a motor; detecting a rotor-induced zero crossing in the non-driven winding following the detection of the kickback pulse; and using the detection of the rotor-induced zero crossing to generate a signal useful in commutation of the motor. | 09-01-2011 |
| 20110193534 | MAGNETIC CONTROL CIRCUIT SEPARATION SLIT - An electric alternator/motor having a stator with at least two non-overlapping sectors is provided. Each sector includes a first winding, first and second magnetic circuits and a saturation control assembly. A cross-talk reduction feature, such as a peripheral slit is provided between each sector of the stator for impeding magnetic flux crossing between the sectors. | 08-11-2011 |
| 20110192646 | METHODS AND MATRICES FOR PRODUCTION OF ELECTRICAL CONDUCTORS - Matrices of multiple cast conductors, and methods for making such matrices. Methods according to the disclosure comprise: casting a conductor matrix including a plurality of conductors joined by at least one link; applying a surface treatment to at least a portion of the matrix; finishing a contact face on at least one of the conductors; and separating the conductors from each other at the at least one link. | 08-11-2011 |
| 20110180109 | PRESSURE FLUSH PROCESS FOR COOLED TURBINE BLADES - A pressure flush process for removing debris from internal passageways of a cooled turbine blade includes a step of creating an agitated liquid/gas mixture and a step of injecting the agitated liquid/gas mixture under a positive pressure, into at least some of cooling holes in the blade to pass through the internal passageways and discharging the agitated liquid/gas mixture together with removed debris, through a larger root opening of the blade. | 07-28-2011 |
| 20110085895 | OIL TUBE WITH INTEGRATED HEAT SHIELD - A gas turbine engine has an oil tube for delivering oil through a high temperature zone of the engine to an engine component for cooling and lubrication. An insulation tube surrounds the oil tube and extends in a substantial length of the oil tube. The opposed ends of the insulation tube are integrally and sealingly connected to respective end portions of the oil tube to form a dead air annulus between the oil tube and the insulation tube. | 04-14-2011 |
| 20110081253 | GAS TURBINE ENGINE BALANCING - An apparatus and method for balancing a gas turbine engine rotor includes a plurality of balancing weights adapted to be selectively attached to at least one of inlets or outlets of a cooling passage of the rotor. The weights include cooling access which permits coolant to communicate with the cooling passage. | 04-07-2011 |
| 20110081240 | FABRICATED GAS TURBINE VANE RING - A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes. | 04-07-2011 |
| 20110081239 | FABRICATED STATIC VANE RING - A strut configuration of a static vane ring used in a gas turbine engine having an enlarged end section at least at one of the opposed ends thereof to be welded or brazed to either an outer or inner duct wall of the vane ring. The enlarged end section provides a inner corner curve with a predetermined fillet radius between the strut and the duct wall. | 04-07-2011 |
| 20110081237 | SEALING FOR VANE SEGMENTS - A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array. | 04-07-2011 |
| 20110081234 | GAS TURBINE ENGINE THERMAL EXPANSION JOINT - A thermal expansion joint apparatus includes an insert extending passages passing through respective first and second components to loosely restrain the first component between the second component and an enlarged head of the insert thereby allowing thermal expansion of the respective first and second components relative to each other. The insert is secured to the second component by a fastener which can be removed, for example, when the insert is to be removed from the engine. | 04-07-2011 |
| 20110081228 | INTERTURBINE VANE WITH MULTIPLE AIR CHAMBERS - A gas turbine engine has a mid turbine frame disposed between turbine rotor assemblies. The mid turbine frame includes hollow airfoils radially extending through an annular gas path duct. The airfoils each include a double-walled leading edge structure to define a front chamber separated from a rear chamber defined in the remaining space within the airfoil. | 04-07-2011 |
| 20110079020 | AIR METERING DEVICE FOR GAS TURBINE ENGINE - An air metering apparatus for a secondary air system of gas turbine engine includes a metering gap defined between surfaces comprised of one or more metals having one of similar coefficients of thermal expansion or similar thermal expansions at an operating temperature. Provided is an air metering gap which undergoes thermal growth in a way which provides a suitable air metering gap during engine running conditions. | 04-07-2011 |
| 20110079019 | COOLING AIR SYSTEM FOR MID TURBINE FRAME - A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for containing pressurized cooling air to cool the inter-turbine duct and the hollow struts, and discharges the used cooling air to further cool respective high and low pressure turbine assemblies. | 04-07-2011 |
| 20110078902 | METHOD FOR CENTERING ENGINE STRUCTURES - A method for centering an engine structure such as a bearing housing is provided which may be used, for example, during assembly of a mid turbine frame or other engine case structure. In one aspect, the method includes using spacers with respective radial spokes which connect inner and outer portions of the case. In another aspect, centring may be provided by machining selected contacting surfaces of selected components. | 04-07-2011 |
| 20110067413 | EJECTOR CONTROLLED TWIN AIR SOURCE GAS TURBINE PRESSURIZING AIR SYSTEM - A passive pressurizing air system for a gas turbine engine includes a flow path for directing an air flow having a low temperature and low pressure, extending through a cavity to a pressurized area of the engine. The cavity contains pressurized air having a high temperature and high pressure. An air flow mixing apparatus is provided for adding the pressurized air from the cavity into the flow path to provide a mixed air flow having an intermediate temperature and intermediate pressure. | 03-24-2011 |
| 20110048023 | FUEL NOZZLE SWIRLER ASSEMBLY - A fuel nozzle air swirler assembly has a slotted cap to provide stress-relief. The stress-relief slits in the cap have an axial and a tangential component to impart a swirl to the air leaking therethrough in the same direction as that of the air exiting the swirler body. | 03-03-2011 |
| 20110044804 | BLADE OUTER AIR SEAL SUPPORT - A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case. | 02-24-2011 |
| 20110044803 | BLADE OUTER AIR SEAL ANTI-ROTATION - A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other. | 02-24-2011 |
| 20110044802 | BLADE OUTER AIR SEAL SUPPORT COOLING AIR DISTRIBUTION SYSTEM - A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments. | 02-24-2011 |
| 20110044801 | BLADE OUTER AIR SEAL COOLING - A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform. | 02-24-2011 |
| 20100328866 | AIRBORNE ELECTRONICS HOUSING ASSEMBLY - An aircraft electronics housing assembly maintains the electronics unit at given ambient conditions despite changes in conditions outside the housing during the aircraft flight cycle. | 12-30-2010 |
| 20100327109 | METHOD AND SYSTEM FOR TAXIING AN AIRCRAFT - The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine, the engine having an electrical motor in a torque-driving engagement with a low pressure spool of the engine. The low pressure spool has a propulsor connected thereon to generate thrust when rotated. A controller is connected to the electrical motor and an electrical power source to control an amount of electrical power provided from the power source to the electrical motor so as to drive the propulsor and cause at least a major portion of the thrust to be generated by the propulsor for moving the aircraft during taxiing. | 12-30-2010 |
| 20100326090 | AIR FILTRATION SYSTEM FOR GAS TURBINE ENGINE PNEUMATIC SYSTEM - A gas turbine engine pneumatic system for controlling an air bleed valve includes a variable orifice device for controllably discharging air from the pneumatic system in order to reduce a maximum air pressure applied to the air bleed valve, to a predetermined level. A filter device is provided to filter the air discharged from the variable orifice. | 12-30-2010 |
| 20100290903 | TURBOFAN MOUNTING SYSTEM - A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall. | 11-18-2010 |
| 20100287950 | SUPPORT LINKS WITH LOCKABLE ADJUSTMENT FEATURE - A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus. | 11-18-2010 |
| 20100278642 | BYPASS LIP SEAL - A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided. | 11-04-2010 |
| 20100278469 | BEARING SUPPORT - A bearing support provides a circumferentially-extending structure to substantially transmit a radial bearing load to a housing when a radial deflection/deformation of the circumferentially-extending structure caused by the radial bearing load, is within a predetermined limit. The bearing support provides a direct support link bypassing the circumferentially-extending structure to transmit an over-limit portion of the radial bearing load to the housing when the radial deflection/deformation of the circumferentially-extending structure reaches the predetermined limit. | 11-04-2010 |
| 20100275614 | STRUCTURAL REINFORCEMENT STRUT FOR GAS TURBINE CASE - A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions. | 11-04-2010 |
| 20100275572 | OIL LINE INSULATION SYSTEM FOR MID TURBINE FRAME - A gas turbine engine having a mid turbine frame comprising an annular outer case providing a portion of an engine casing; an interturbine duct (ITD) disposed within the outer case, the ITD including outer and inner rings radially spaced apart one from another and being interconnected by a plurality of radially extending and circumferentially spaced hollow strut fairings, the inner and outer rings co-operating to provide a portion of a hot gas path through the engine; a tube for delivering or discharging a lubricant fluid to or from a bearing housing, the tube extending radially through one of the hollow struts; and an insulation structure radially extending through one said hollow strut fairing, the insulation structure surrounding the tube and being spaced apart from the tube and from a hot internal surface of the one hollow strut fairing for shielding the tube from heat radiated from the hot internal surface of the one hollow strut fairing and for preventing the lubricant fluid from contacting the hot internal surface of said one hollow strut fairing when lubricant fluid leakage occurs. | 11-04-2010 |
| 20100272566 | DEFLECTOR FOR A GAS TURBINE STRUT AND VANE ASSEMBLY - A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut. | 10-28-2010 |
| 20100257864 | REVERSE FLOW CERAMIC MATRIX COMPOSITE COMBUSTOR - A gas turbine engine has an annular reverse-flow combustor with a combustor inner liner enclosing a combustion chamber. The inner liner having a dome portion at an upstream end of the combustor and a downstream combustor exit defined between a small exit duct portion and a large exit duct portion. At least one of the dome portion, the small exit duct portion and the large exit duct portion is made of a separately formed hemi-toroidal shell composed of a ceramic matrix composite. | 10-14-2010 |
| 20100247297 | ACTIVE TIP CLEARANCE CONTROL ARRANGEMENT FOR GAS TURBINE ENGINE - An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance. | 09-30-2010 |
| 20100241331 | CONTROL OF GAS TURBINE ENGINE - Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters. | 09-23-2010 |
| 20100237571 | SPLIT RING SEAL WITH SPRING ELEMENT - A split ring seal assembly includes a metal seal ring having two ends defining a circumferential gap therebetween. At least a first spring element is mounted to the two ends to bias the two ends circumferentially towards each other to reduce the diameter of a circumferential inner sealing surface of the metal seal ring. | 09-23-2010 |
| 20100229387 | MULTI-MATERIAL TURBINE ENGINE SHAFT - A turbine engine shaft comprising an end section thereof made of high temperature resistant super-alloy adapted for working in a hot section of the engine, and a remaining section of the shaft made of steel. The end section and the remaining section are directly joined together to form a single-piece shaft. | 09-16-2010 |
| 20100199681 | FUEL SYSTEM OF GAS TURBINE ENGINES - A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source. | 08-12-2010 |
| 20100186943 | DUAL CHANNEL REGULATED FUEL-OIL HEAT EXCHANGER - A gas turbine engine includes a fuel-oil heat exchange system in which the fuel is continuously heated by a primary hot oil flow in a primary fuel-oil heat exchanger and the fuel is selectively heated in a secondary fuel-oil heat exchanger by a secondary hot oil flow selectively passing through or bypassing a secondary fuel-oil heat exchanger, controlled by a thermal valve. | 07-29-2010 |
| 20100156221 | MULTI-ROTOR ELECTRIC MACHINE - Electric machines comprising a plurality of magnetized rotors, preferably including bi-pole magnets. The rotors are configured to drive and/or be driven by a common shaft, as for example by suitable configurations of gears. The rotors are magnetically indexed, in pairs, with respect to each other and to corresponding electrical windings, such that, when a current is passed through the one or more windings, the rotors provide phased rotary power to the common shaft; or, when torque is applied to the common shaft, a phased electrical output is provided to the windings. | 06-24-2010 |
| 20100150700 | BYPASS AIR SCOOP FOR GAS TURBINE ENGINE - A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine. | 06-17-2010 |
| 20100148622 | ARCHITECTURE FOR ELECTRIC MACHINE - The invention includes an electric machine having a rotor, stator and at least one winding in the stator adapted to conduct a current, and a secondary winding, electrically isolated from the first winding and inductively coupled to the first winding, which may be used to control at least one of the output voltage and current of the first winding. | 06-17-2010 |
| 20100139288 | HEAT EXCHANGER TO COOL TURBINE AIR COOLING FLOW - A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall | 06-10-2010 |
| 20100135770 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame having an inner case supporting at least one bearing and at least three spokes extending radially outwardly to an outer case, the mid turbine frame having an interturbine duct extending through the mid turbine frame, the interturbine duct spaced axially closer to an upstream turbine disc than a bearing supporting structure of the mid turbine frame and mounted axially slidingly relative to the bearing supporting structure to substantially isolate the bearing supporting structure from axial loads, for example such as disc loads incurred in the unlikely event a turbine disc shaft shears within the engine. | 06-03-2010 |
| 20100132377 | FABRICATED ITD-STRUT AND VANE RING FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame having an annular interturbine duct and vane ring assembly includes a duct having outer and inner duct walls of sheet metal interconnected by radial hollow struts of sheet metal and a vane ring is connected to the duct to provide the assembly. The interturbine duct and vane ring assembly may be provided within a mid turbine frame in a manner which is independent of a bearing load path through the mid turbine frame. | 06-03-2010 |
| 20100132376 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A mid turbine frame of a gas turbine engine includes an outer case which supports a spoke casing co-axially positioned therein. The spoke casing has load transfer spokes extending radially from an inner case and secured to the outer case. A load transfer device is provided to transfer load from the spokes to the outer case in addition to load transfer through a first group of fasteners securing the spokes to the outer case, thereby forming a secondary load transfer path from the spokes. The load transfer device includes an opening of the outer case into which at least some of the spokes are inserted. | 06-03-2010 |
| 20100132373 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A mid turbine frame with an annular interturbine duct may be assembled by placing an mid turbine frame inner case of into the interturbine duct, inserting a plurality of mid turbine frame spokes radially through respective hollow radial struts of the interturbine duct to be connected to the mid turbine frame inner case to form a mid turbine frame spoke casing. A mid turbine frame outer case is also connected to the spokes, to provide an assembled mid turbine frame. | 06-03-2010 |
| 20100132372 | MID TURBINE FRAME FOR GAS TURBINE ENGINE - A gas turbine engine has a casing component, such as a mid turbine frame system, which includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing are detachably connected to the outer case and radially extend between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. An arrangement for radially centring the bearing within the outer case is provided, the arrangement including at least three radial locators mounted to the outer case. | 06-03-2010 |
| 20100132371 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine has a mid turbine frame system which includes an outer case surrounding a spoke casing. Spokes of the spoke casing are detachably connected to the outer case and radially extend through hollow struts of a segmented interturbine duct which is disposed between the outer case and an inner case of the spoke casing. A bearing housing is supported by the inner case of the spoke casing. The mid turbine frame is assembly by inserting the interturbine duct segments over the spokes and then inserting the spoke casing into the outer case. | 06-03-2010 |
| 20100132370 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine mid turbine frame apparatus includes a an inner case supporting a bearing, an outer case to which the inner case is mounted, and an apparatus for radially positioning one relative to the other, the apparatus including a plurality of radial locators extending outwardly of the outer case and an associated locking apparatus. The locking apparatus is mounted adjacent to but independent of the locators and provides for anti-rotation of the radial locators once installed. | 06-03-2010 |
| 20100132369 | MID TURBINE FRAME SYSTEM FOR GAS TURBINE ENGINE - A gas turbine engine has an engine casing component, such as a mid turbine frame system, which may includes an outer case surrounding a spoke or strut casing. Load transfer spokes of the spoke casing extend between the outer case and an inner case of the spoke casing. A bearing housing supported by the engine casing may include a fuse arrangement for isolating bearing seizure loads from the engine casing. A seal arrangement may be provided to centralize the rotors after the fuse fails. The mid turbine frame may be provided to have a desired flexibility through the configuration of the casing and bearings in design. | 06-03-2010 |
| 20100107882 | WOVEN ELECTROSTATIC OIL PRECIPITATOR ELEMENT - An electrostatic precipitator element comprises preferably a mesh made of at least two individually insulated conductors with defined openings therebetween. An electrical field in the openings electrostatically attracts suspended particulate to a respective conductors for collection. | 05-06-2010 |
| 20100101310 | Method and Apparatus for Troubleshooting Noise/Vibration Issues of Rotating Components - There is provided a method for troubleshooting noise/vibration issues of rotating components, the method comprising: receiving an audio signal of the rotating components in operation; generating a frequency spectrum corresponding to the audio signal; selecting a frequency ν | 04-29-2010 |
| 20100080699 | TURBINE SHROUD GAS PATH DUCT INTERFACE - An arrangement for sealing a turbine shroud gas path duct interface of a turbine engine comprises a static shroud surrounding a rotatable airfoil array and an annular duct downstream of the shroud with respect to a gas flow passing through the gas path. The shroud and the duct define a portion of the gas path for directing the gas flow, having an axially extending interface gap between the shroud and duct. An annular seal in use engages both the shroud and the duct, thereby sealing the annular gap. | 04-01-2010 |
| 20100072959 | Modulation Control of Power Generation System - Methods and apparatuses are disclosed for producing current with a desired output frequency from one or more fixed or variable speed alternators by varying a saturation level of a portion of the alternator(s) based on a output frequency desired, and preferably then rectifying the output to produce a desired electrical output which may be provided as direct current or alternating current to a suitable load. | 03-25-2010 |
| 20100071663 | EXTERNAL RIGID FUEL MANIFOLD - A fuel manifold of a gas turbine engine includes a tube assembly having substantially rigid inner tubes disposed inside of substantially rigid outer tubes in pairs, concentrically spaced apart by a spacer apparatus. The inner tubes form a primary fuel passage for directing a primary fuel flow and the outer tubes form a secondary fuel passage for directing a secondary fuel flow, the secondary flow being greater than the primary flow. | 03-25-2010 |
| 20100051317 | CRACK CONTROLLED RESIN INSULATED ELECTRICAL COIL - An electrically insulated coil assembly for use in a high vibration environment, such as with an aircraft engine, includes a coil of metal wires encompassed by a resin base matrix. A fabric is embedded in the resin matrix near an outer surface of the resin base matrix to divide a thin layer of the resin base matrix into a plurality of segments. In an embodiment, a notch blunting additive is provided in the resin to impede crack propagation. | 03-04-2010 |
| 20100040453 | APPARATUS AND METHOD FOR CONTROLLING A COMPRESSOR - A compressor comprises a casing having an inner surface surrounding a rotor assembly, the rotor assembly having a plurality of circumferentially spaced radially outwardly extending rotor blades, each blade having leading and trailing edges and a tip, the compressor further comprising at least one plasma actuator for suppressing rotating stall inception of the compressor, the at least one plasma actuator being mounted adjacent to the blade tips. | 02-18-2010 |
| 20100014985 | SHROUD SEGMENT COOLING CONFIGURATION - An cooling arrangement for a turbine shroud provides an air stream directed from a passage extending through a radial wall to impinge on a surface in an area of a back side of the turbine shroud, the surface defining a plane which improves the attack angle of the air stream to the surface. | 01-21-2010 |
| 20090326745 | AIRCRAFT CRUISE SPEED CONTROL - The present invention provides an alternative to the auto-throttle integrated in an aircraft autopilot by restricting the conditions in which the system operates. The proposed system removes the auto-throttle function from the autopilot system and gives it directly to the Full Authority Digital Engine Control (FADEC). A cruise control mode is available to the pilot only under stable flight conditions. | 12-31-2009 |
| 20090322373 | PERMANENT MAGNET ROTOR CRACK DETECTION - A method and apparatus for permanent magnetic (PM) rotor crack detection includes a sensor which monitors magnetic flux distribution of the PM rotor and identifies the presence of a crack in the PM rotor when a magnetic flux distribution change or anomaly is detected. | 12-31-2009 |
| 20090313969 | Thrust Reverser for a Turbofan Gas Turbine Engine - The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm. | 12-24-2009 |
| 20090278413 | ARCHITECTURE FOR ELECTRIC MACHINE - The invention includes an electric machine having a rotor, stator and at least one winding in the stator adapted to conduct a current, and a secondary winding, electrically isolated from the first winding and inductively coupled to the first winding, which may be used to control at least one of the output voltage and current of the first winding. | 11-12-2009 |
| 20090237968 | POWER INVERTER AND METHOD - An apparatus and method for converting an input signal to an output AC signal in which the input voltage signal is inverted and modulated to provide an intermediate AC signal having twice the desired output frequency. The intermediate signal is then full-wave rectified and then the polarity of the rectified signal is switched every second cycle to produce the output AC signal of a desired frequency and voltage. | 09-24-2009 |
| 20090195225 | SATURATION CONTROL OF ELECTRIC MACHINE - The invention includes an electric alternator/motor having a rotor, stator and at least one winding in the stator adapted to conduct a current, the machine also having and first and second magnetic circuits, one of which includes a saturable portion in which saturation may be controlled to permit control of the machine. | 08-06-2009 |
| 20090110548 | ABRADABLE RIM SEAL FOR LOW PRESSURE TURBINE STAGE - An abradable rim seal arrangement for a turbine stage of a gas turbine engine, which includes an abradable rim seat attached to a leading edge of an annular inner duct of a turbine exhaust case, causing a trailing edge platform of each rotor blade to overlap the abradable rim seal, and allowing rubbing with the trailing edge platform during engine operation. | 04-30-2009 |
| 20090110538 | GAS TURBINE ENGINE BLADE CONTAINMENT USING WIRE WRAPPING - A blade containment of a gas turbine engine comprises a casing defining an annular wall radially spaced from and immediately surrounding a plurality of blades radially extending from a rotor, and at least one layer of metal wires wrapped around and directly attached to the annular wall. | 04-30-2009 |
| 20090107223 | METHOD AND APPARATUS FOR TURBINE ENGINE DYANMIC CHARACTERIZATION - A method and apparatus for conducting dynamic characterization of a gas turbine engine which involves generating exciting pressure pulses and measuring responses in the engine, and, in one aspect then analyzing the measured response for engine dynamic characteristics. | 04-30-2009 |
| 20090101444 | GAS TURBINE OIL SCAVENGING SYSTEM - A method for scavenging oil in a gas turbine engine comprises using a driving fluid flow to drive a flow of a fluid collected in an oil system of the engine to pass through an ejector and then the driven flow of the fluid is directed to be discharged into an oil tank. | 04-23-2009 |
| 20090010752 | PUMP AND METHOD - A pump for moving a liquid including a rotor rotatable within a housing and slidable relative to the housing between a first axial rotor position during normal pump operation and a second axial rotor position during a pump inoperative condition. | 01-08-2009 |
| 20080286459 | METHOD FOR APPLYING ABRADABLE COATING - In accordance with one aspect of the invention a process for applying an abradable coating to a component includes cold spraying an abradable coating material in particles towards a target surface of the component. | 11-20-2008 |
| 20080272915 | EQUIPMENT MONITORING SYSTEM AND METHOD - There is provided a system for monitoring a replaceable unit. The system comprises a passive memory device attached to the replaceable unit forming part of an assembly such as an engine. The passive memory is for storing and for providing access to replaceable unit information comprising unit identification and usage information. The system may further comprise an event detector which may be embodied as an electronic engine controller (EEC) operatively connected to the engine, for accumulating the usage information related to the replaceable unit, and for communicating with the passive memory device to update the unit information stored in the passive memory device with the usage information. | 11-06-2008 |
| 20080271433 | LOW PROFILE BLEED AIR COOLER - A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage. | 11-06-2008 |
| 20080260519 | SURGE DETECTION IN A GAS TURBINE ENGINE - A method for detecting a surge condition during operation of a gas turbine engine includes detecting a change of pressure differential between fuel flows in a fuel system of the engine during engine operation. | 10-23-2008 |
| 20080256954 | START FLOW MEASUREMENT - A method and apparatus for measuring a start fuel flow to a pilot nozzle of a fuel system of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles. | 10-23-2008 |
| 20080241370 | COATING REMOVAL FROM VANE RINGS VIA TUMBLE STRIP - A method of removing a coating layer from a gas turbine component, including a step of applying both mechanical and chemical actions in a tumble stripping process to the coating layer of the gas turbine component, wherein the gas turbine component is bathed in an acid solution while being rubbed by a plurality of hard media elements in a tumbling motion. | 10-02-2008 |
| 20080240917 | TURBOFAN CASE AND METHOD OF MAKING - A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed. | 10-02-2008 |
| 20080236951 | OIL SCAVENGE SYSTEM HAVING CHURNING DAMPER FOR GAS TURBINE ENGINES - An oil scavenge system of a gas turbine engine in accordance with one embodiment of the present invention, comprises a housing defined about an axis of rotation, the housing confining an air/oil mixture in motion within the housing and defining an oil scavenge area below the axis of rotation. The housing further includes an outlet at a low location of the housing. A churning damper is supported within the housing and is located in the oil scavenge area. The churning damper includes at least one plate, allowing the air/oil mixture in motion to pass over or through the plate only in a peripheral area of the at least one plate to cause flow energy dissipation. | 10-02-2008 |
| 20080232963 | TURBINE SHROUD SEGMENT TRANSPIRATION COOLING WITH INDIVIDUAL CAST INLET AND OUTLET CAVITIES - A shroud segment of a turbine shroud of a gas turbine engine comprises a platform with front and rear legs. The platform defines a plurality of axially extending holes with individual inlets on an outer surface of the platform for transpiration cooling of the platform of the turbine shroud segment. | 09-25-2008 |
| 20080206000 | MULTI-FLUTE BALL ENDMILL FOR AIRFOIL MACHINING - A milling cutter comprises a shank section joined to a cutting section. The cutting section includes a plurality of peripheral teeth separated by a plurality of flutes to form cutting edges extending around the cutting section in a helix direction. The number of respective teeth and flutes is more than 12. | 08-28-2008 |
