Patent application number | Description | Published |
20090214349 | Airfoil Structure Shim - An airfoil structure, shim and retention member combination is provided. The combination comprises an airfoil structure, a retention member and a shim. The airfoil structure may comprise a first recess. The retention member may comprising a second recess. The first and second recesses may define a cavity. The shim may comprise a main body and a plurality of first fins extending outwardly from a first side of the main body. The first fins may further extend transverse to a longitudinal axis of the main body. The shim may be positioned in the cavity such that the first fins extend in a direction substantially transverse to a longitudinal axis of the cavity. | 08-27-2009 |
20100018210 | COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE - A combustion apparatus in a gas turbine engine comprises a combustor shell for receiving air, a fuel injection system associated with the combustor shell, a first fuel supply structure, and a shield structure. The fuel supply structure is in fluid communication with a source of fuel for delivering fuel from the source of fuel to the fuel injection system and comprises a first fuel supply elements including a first section extending along a first path having a component in an axial direction and a second section extending from the first section along a second path having a component in a circumferential direction. The shield structure is associated with at least a portion of the second section of the first fuel supply element. | 01-28-2010 |
20100071376 | Combustor Assembly in a Gas Turbine Engine - A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct. | 03-25-2010 |
20100071377 | Combustor Apparatus for Use in a Gas Turbine Engine - A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume. | 03-25-2010 |
20100074731 | Gas Turbine Sealing Apparatus - A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine. | 03-25-2010 |
20110056206 | Fuel Injector for Use in a Gas Turbine Engine - A fuel injector in a combustor apparatus of a gas turbine engine. An outer wall of the injector defines an interior volume in which an intermediate wall is disposed. A first gap is formed between the outer wall and the intermediate wall. The intermediate wall defines an internal volume in which an inner wall is disposed. A second gap is formed between the intermediate wall and the inner wall. The second gap receives cooling fluid that cools the injector. The cooling fluid provides convective cooling to the intermediate wall as it flows within the second gap. The cooling fluid also flows through apertures in the intermediate wall into the first gap where it provides impingement cooling to the outer wall and provides convective cooling to the outer wall. The inner wall defines a passageway that delivers fuel into a liner downstream from a main combustion zone. | 03-10-2011 |
20110067402 | Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine - A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure. | 03-24-2011 |
20110217179 | TURBINE AIRFOIL FILLET COOLING SYSTEM - A cooling system for the fillet of a turbine blade is provided. The blade includes an airfoil transitioning to a platform having a flow path surface. The transition region is defined by a fillet. A cooling passage is formed in the platform and extends about at least a portion of the periphery of the airfoil. The cooling passage is located proximate to the flow path surface and is substantially aligned with at least a portion of the fillet. Coolant is delivered to the passage by a supply hole, which can reduce the temperature in the fillet region. As a result, thermal gradients in the fillet region can be minimized, which can reduce thermal stresses. An exhaust hole extends between the passage and the flow path surface of the platform. Thus, coolant discharged from the exhaust holes enters the flow path of the turbine. | 09-08-2011 |
20110236182 | Control of Blade Tip-To-Shroud Leakage in a Turbine Engine By Directed Plasma Flow - An electrode ( | 09-29-2011 |
20120275918 | LOCKING SPACER ASSEMBLY FOR A TURBINE ENGINE - A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from radially inward and outward supports coupled together with a locking device. The inward and outward supports establish the desired spacing between adjacent blade supports. The locking device may include components that prevent the locking device from accidentally loosening during use. | 11-01-2012 |
20130011242 | GAS TURBINE ENGINE WITH ANGLED AND RADIAL SUPPORTS - A support structure in a gas turbine engine including an inner annular wall and an outer annular wall defining an annular flow path, a casing housing the structure defining the flow path, and a bearing compartment housing a rotor shaft bearing located radially inwardly from the inner annular wall. The support structure includes a plurality of circumferentially spaced radial support members extending radially inwardly from an outer mount connection at the casing to an inner mount connection at the bearing compartment housing. The radial support members provide structural support for radial bearing loads on the rotor shaft bearing. A plurality of circumferentially spaced axial support members extend radially and axially inwardly from an outer mount connection at the casing to an inner mount connection located on an annular structure extending radially between connection locations at the bearing compartment housing and the inner annular wall. | 01-10-2013 |
20130081399 | CASING FOR A GAS TURBINE ENGINE - A casing for a can annular gas turbine engine, including: a compressed air section ( | 04-04-2013 |
20130081407 | AERO-DERIVATIVE GAS TURBINE ENGINE WITH AN ADVANCED TRANSITION DUCT COMBUSTION ASSEMBLY - An aero-derivative can annular gas turbine engine having: an aero gas turbine engine core including an aero high pressure compressor ( | 04-04-2013 |
20130084163 | WEAR INDICATION SYSTEM FOR COMPRESSOR DIAPHRAGMS OF GAS TURBINE ENGINES - A wear indication system for use in turbine engines to measure gap closure that indicates the amount of wear found on a compressor diaphragm outer hook to prevent contact between a compressor vane attached to the compressor diaphragm outer hook and an upstream compressor blade. The wear indication system enables the wear to be serviced before failure occurs. The wear indication system may be formed from a base mounting plate having one or more wearable material layers attached thereto. In one embodiment, the wear indication system may have multiple wearable material layers. The outermost wearable layer may have a cross-sectional area less than a wearable layer to which it is attached to enable visual determination of the amount of wear that has occurred. The wearable layers may be formed from a honeycomb shaped material enabling wear to occur without threatening downstream components with damage. | 04-04-2013 |
20130089417 | WEAR PREVENTION SYSTEM FOR SECURING COMPRESSOR AIRFOILS WITHIN A TURBINE ENGINE - A wear prevention system for securing compressor airfoils within a turbine engine while reducing wear of related components is disclosed. The wear prevention system may include a compressor diaphragm spring positioned in an airfoil receiving channel between a radially outer surface of a diaphragm base and a radially inner surface of the airfoil receiving channel. The spring may bias the diaphragm base and airfoil attached thereto radially inward against upstream and downstream arms formed from upstream and downstream recesses extending axially from the airfoil receiving channel in the compressor case. The compressor diaphragm spring may dampen vibration and increase service life of the diaphragm base. | 04-11-2013 |
20130133330 | DEVICE TO LOWER NOx IN A GAS TURBINE ENGINE COMBUSTION SYSTEM - An emissions control system for a gas turbine engine including a flow-directing structure ( | 05-30-2013 |
20130152543 | RADIAL INFLOW GAS TURBINE ENGINE WITH ADVANCED TRANSITION DUCT - A gas turbine engine ( | 06-20-2013 |
20130174560 | COMBUSTOR ASSEMBLY IN A GAS TURBINE ENGINE - A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct. | 07-11-2013 |
20130219921 | MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH A COOLING SYSTEM FOR THE TRANSITION - A cooling system is provided for a transition ( | 08-29-2013 |
20140023483 | AIRFOIL ASSEMBLY INCLUDING VORTEX REDUCING AT AN AIRFOIL LEADING EDGE - An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge. | 01-23-2014 |
20140205447 | PURGE AND COOLING AIR FOR AN EXHAUST SECTION OF A GAS TURBINE ASSEMBLY - A turbine exhaust casing having an outer casing, an inner casing, an annular exhaust gas path defined between outer and inner flow path walls, and a turbine exhaust casing cavity located radially outward and radially inward from the gas path. A plurality of structural struts support the inner casing to the outer casing, and a fairing surrounds each of the struts in an area extending between the outer and inner flow path walls. A first purge air path extends through at least one of the struts for conducting purge cooling air radially inward to the inner casing, and a second purge air path extends through the strut for further conducting the purge cooling air radially outward to provide a flow of purge air to a location of the exhaust casing cavity radially outward from the outer flow path wall. | 07-24-2014 |
20140245740 | COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE - A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall. | 09-04-2014 |
20150056068 | BELLY BAND SEAL WITH CIRCUMFERENTIAL SPACER - A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other. | 02-26-2015 |
20150107264 | STRUCTURAL MOUNTING ARRANGEMENT FOR GAS TURBINE ENGINE COMBUSTION GAS DUCT - A gas turbine engine ducting arrangement ( | 04-23-2015 |
Patent application number | Description | Published |
20090198884 | REDUCED HARD-DRIVE-CAPACITY DETECTION DEVICE - The present disclosure relates to a device for detecting accessible capacity in an external hard drive. The disclosed device may detect reduced accessible capacity in an external hard drive due to an modification or deletion of either the Host-Protected Area or the Device Configuration Overlay table. | 08-06-2009 |
20100141036 | UNINTERRUPTIBLE A/C POWER SUPPLY TRANSFER UNIT - A power transfer device ( | 06-10-2010 |
20150143898 | FLUID-LEVEL MEASURING SENSOR - A pressure sensor system for determining fluid level in a tank, includes a pressure sensor constructed to exhibit a force value corresponding to a sensed force, and a computer operatively coupled to the pressure sensor. A tank containing fluid is also includes and there is a communication link between the pressure sensor and the tank, thereby allowing determination of the level of fluid in the tank by calibration and interpretation of the force value exhibited by the pressure sensor. | 05-28-2015 |
20150194835 | POWER CONTROL OF BATTERIES - A system for regulating voltage from a battery pack includes a series of cells that forms a battery pack, and a series of electronic switches interspersed among the cells, and in operative communication with them. A controller is in operative communication with the switches to allow selective actuation of each of them. | 07-09-2015 |
20150300864 | LIQUID LEVEL SENSOR SYSTEM - A liquid level sensor system for use in a fuel tank, includes an arm that is movable, and constructed to be sufficiently buoyant so that the arm will provide an upward force as the fuel tank is filled with fuel. A sensing subsystem is coupled to the arm and is operable to indicate continuously the amount of fuel in the fuel tank. The sensing subsystem may include a Wheatstone strain gauge, and the system may further include a microprocessor that coupled to the strain gauge to receive electrical signals corresponding to the upward force generated by the arm. A computer program provides instructions to the microprocessor to calibrate the arm according to preselected fuel-level conditions. The sensing subsystem may be located external to the fuel tank to limit the possibility of undesired igniting of the fuel. | 10-22-2015 |
20150301013 | REAL TIME FUEL DISCRIMINATOR - A real time fuel discriminator for use with a fuel conveyance system that conveys fuel from a fuel supply to a fuel-powered engine includes a body with an inlet port and an outlet port. Each port is coupled to the fuel conveyance system so that fuel enters the inlet port, passes through the body, and exits the outlet port. A fuel analyzer is associated with the body, and constructed to determine whether the fuel is contaminated with an undesired material. The undesired material may be water or conductive metal fragments. | 10-22-2015 |