| Patent Number |
Title Of Patent |
Date Issued |
| 7445399 |
Low profile gimbal |
November 4, 2008 |
| A gimbal includes a first lug housing. The first lug housing includes a first base plate and a first lug protruding from the second surface of the first base plate. The gimbal also includes a second lug housing. The second lug housing includes a second base plate and a second lug pro |
| 6431832 |
Gas turbine engine airfoils with improved cooling |
August 13, 2002 |
| Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas tur |
| 6360418 |
Method for controlling the concentricity of a member with a centering device |
March 26, 2002 |
| Conventional gas compressors use dry gas sealing arrangements mounted on a shaft of the gas compressor. Functionally, for the dry gas sealing arrangement to properly seal, the concentricity of shaft and the dry gas sealing arrangement must be maintained at a close tolerance. Past assembl |
| 6314716 |
Serial cooling of a combustor for a gas turbine engine |
November 13, 2001 |
| A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of |
| 6308409 |
Recuperator cell assembly system |
October 30, 2001 |
| Recuperators include a core which is commonly constructed of a plurality of relatively thin flat sheets having an angled or corrugated spacer fixedly attached therebetween. The sheets are joined into cells, sealed and form passages between the sheets. These cells are stacked or rolled an |
| 6283479 |
High temperature low leakage seal for a shaft on a gas turbine engine |
September 4, 2001 |
| A sealing arrangement improves sealing of a shaft in a control system on a gas turbine engine. The sealing arrangement includes a first plate and a non-metallic plate. The non-metallic plate has a glass transition temperature above an operating temperature range. The non-metallic plate |
| 6239583 |
Regulation system for a permanent magnet generator |
May 29, 2001 |
| A regulation system for a permanent magnet generator for generating electrical power and for supplying the electrical power to a load comprises a switching circuit connected between the permanent magnet generator and the load, the switching circuit being capable of regulating the ele |
| 6158121 |
Method and apparatus for making a recuperator cell |
December 12, 2000 |
| Circular recuperators are used to increase the efficiency of gas turbine engines. The present circular recuperators is made of a plurality of cells. Each of the plurality of cells includes a plurality of components, such as, a plurality of sheets, a plurality of bars and guide strips. To |
| 6139256 |
Apparatus for controlling the concentricity of a member with a centering device |
October 31, 2000 |
| Conventional gas compressors use dry gas sealing arrangements mounted on a shaft of the gas compressor. Functionally, for the dry gas sealing arrangement to properly seal, the concentricity of shaft and the dry gas sealing arrangement must be maintained at a close tolerance. Past assembl |
| 6112403 |
Method and apparatus for making a recuperator cell |
September 5, 2000 |
| Circular recuperators are used to increase the efficiency of gas turbine engines. The present circular recuperators are made of a plurality of cells. Each of the plurality of cells includes a plurality of components, such as, a plurality of sheets, a plurality of bars and guide strips. T |
| 5836163 |
Liquid pilot fuel injection method and apparatus for a gas turbine engine dual fuel injector |
November 17, 1998 |
| A dual fuel injector includes an apparatus for injecting liquid pilot fuel into a gas turbine engine. The injector includes a liquid pilot fuel feedline having an outlet that sprays fuel on the conically-shaped pintle swirler that causes the fuel to form a cylindrically-shaped film on th |
| 5826423 |
Dual fuel injection method and apparatus with multiple air blast liquid fuel atomizers |
October 27, 1998 |
| A dual fuel injector for injecting liquid and/or gaseous fuel into a gas turbine engine includes a plurality of hollow spoke members for injecting gaseous fuel that are located upstream of a plurality of main air swirling vanes that are in turn upstream of a plurality of air-blast atomiz |
| 5810076 |
High pressure ceramic heat exchanger |
September 22, 1998 |
| Many recuperators have components which react to corrosive gases and are used in applications where the donor fluid includes highly corrosive gases. These recuperators have suffered reduced life, increased service or maintenance, and resulted in increased cost. The present header assembl |
| 5779436 |
Turbine blade clearance control system |
July 14, 1998 |
| Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on |
| 5758504 |
Impingement/effusion cooled combustor liner |
June 2, 1998 |
| Existing combustors have the tendency to emit emissions and require a large quantity of cooling air to retain or extend the life of the components to a reasonable life expectancy. The present combustor reduces the emissions emitted therefrom, requires a reduced quantity of cooling air wh |
| 5752802 |
Sealing apparatus for airfoils of gas turbine engines |
May 19, 1998 |
| An improved airfoil tip sealing apparatus is disclosed wherein brush seals are attached to airfoil tips with the distal ends of the brush seal fibers sealingly contacting opposing wall surfaces. Embodiments for variable vanes, stators and both cooled and uncooled turbine blade applicatio |
| 5726411 |
Method and apparatus for making holes in a workpiece |
March 10, 1998 |
| The present method of making a workpiece having a plurality of holes defined therein includes the plurality of holes defining a specific flow at a specific flow condition. The method of making the plurality of holes includes generally the steps of forming a first portion of holes having |
| 5706647 |
Airfoil structure |
January 13, 1998 |
| Past airfoil configurations have been used to improve aerodynamic performance and engine efficiencies. The present airfoil configuration further increases component life and reduces maintenance by reducing internal stress within the airfoil itself. The airfoil includes a chord and a |
| 5697208 |
Turbine cooling cycle |
December 16, 1997 |
| Air flow delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by directing a portion of a compressed air formed by the compressor section and located |
| 5694803 |
Fin folding machine for corrugating sheet material |
December 9, 1997 |
| A fin folding machine is disclosed for sequentially folding relatively thin sheet metal material into narrowly grooved corrugations. The fin folding machine includes a pair of opposed clamping tools disposed on opposite sides of the sheet material. The clamping tools are movable in a dir |
| 5673552 |
Fuel injection nozzle |
October 7, 1997 |
| A fuel injection nozzle includes a first cavity having a first preestablished cross-sectional area and a second preestablished cross-sectional area being larger than the first preestablished cross-sectional area. And, an actuating device being positioned at an inlet end of the first |
| 5653580 |
Nozzle and shroud assembly mounting structure |
August 5, 1997 |
| The present nozzle and shroud assembly mounting structure configuration increases component life and reduces maintenance by reducing internal stress between the mounting structure having a preestablished rate of thermal expansion and the nozzle and shroud assembly having a preestabli |
| 5653579 |
Ceramic blade with tip seal |
August 5, 1997 |
| The present gas turbine engine (10) includes a disc assembly (64) defining a disc (66) having a plurality of blades (70) attached thereto. The disc (66) has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less t |
| 5649418 |
Integrated power converter cooling system using turbine intake air |
July 22, 1997 |
| Air flow cooling systems are used to increase component life. The present air flow cooling system increases the component life, increases efficiencies and eliminated components. For example, the power source or gas turbine engine is used to cause a flow of air around and about electr |
| 5645402 |
Turbine blade vibration dampening |
July 8, 1997 |
| The present turbine wheel assembly increases component life and turbine engine longevity. The combination of the strap and the opening combined with the preestablished area of the outer surface of the opening and the preestablished area of the outer circumferential surface of the strap a |
| 5636508 |
Wedge edge ceramic combustor tile |
June 10, 1997 |
| A multipiece combustor has a portion thereof being made of a plurality of ceramic segments. Each of the plurality of ceramic segments have an outer surface and an inner surface. Each of the plurality of ceramic segments have a generally cylindrical configuration and including a plurality |
| 5634768 |
Airfoil nozzle and shroud assembly |
June 3, 1997 |
| An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a |
| 5629479 |
Volume displacement monitoring device |
May 13, 1997 |
| The present volume monitoring device (40) includes a cylindrical portion (66) having a piston assembly (100) therein. The cylindrical portion (66) having a measuring device (48) attached thereto at one end (46) and a readout gage (44) attached thereto at an other end (50). The measuring |
| 5616001 |
Ceramic cerami turbine nozzle |
April 1, 1997 |
| A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablish |
| 5603606 |
Turbine cooling system |
February 18, 1997 |
| Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas tur |
| 5601238 |
Fuel injection nozzle |
February 11, 1997 |
| A premix fuel injection nozzle includes a first mixing chamber having a preestablished cross-sectional area and a second mixing chamber having a preestablished cross-sectional areal being larger than the preestablished cross-sectional area of the first mixing chamber. The first mixing ch |
| 5600965 |
Air conditioning system |
February 11, 1997 |
| The present air conditioning system bleeds high pressure, hot, compressed air from the compressor section of a gas turbine engine and passes the high pressure flow of air directly through a single heat exchanger, through a flow control valve, is used to drive a supersonic turbine dev |
| 5593085 |
Method of manufacturing an impeller assembly |
January 14, 1997 |
| A method for determining the generation of a diffusion bond between two articles is disclosed. The two articles are sealed together to define a cavity therebetween. A vacuum is drawn in the cavity by means of an evacuation tube having a passageway. The passageway is then sealed and the |
| 5591003 |
Turbine nozzle/nozzle support structure |
January 7, 1997 |
| An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed rela |
| 5584652 |
Ceramic turbine nozzle |
December 17, 1996 |
| A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preest |
| 5580219 |
Ceramic blade attachment system |
December 3, 1996 |
| A turbine blade having a preestablished rate of thermal expansion is attached to a turbine flange having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine blade. The turbine flange includes a first upstanding fla |
| 5580172 |
Method and apparatus for producing a surface temperature map |
December 3, 1996 |
| A method and apparatus are provided for producing a temperature profile of a part operating within a machine is provided. The machine is operated with the part for a predetermined period of time. The part is placed in a light box in which a camera produces an image of the part. The image |
| 5576984 |
Hydrodynamic bearing rotor orbit simulator |
November 19, 1996 |
| An apparatus and method is provided for simulating a plurality of bearing orbits. The apparatus includes a first simulator for producing signals indicative of a first simulated bearing orbit; a second simulator for producing signals indicative of a second simulated bearing orbit; a c |
| 5555933 |
Primary surface heat exchanger for use with a high pressure ratio gas turbine engine |
September 17, 1996 |
| Prior art recuperators or heat exchangers have been restricted in use to only part speed and power application when adapted for use with high pressure gas turbine engine. The present recuperator or heat exchanger has been adapted for use with a high pressure ratio gas turbine engine. The |
| 5554001 |
Turbine nozzle/nozzle support structure |
September 10, 1996 |
| An axial flow turbine's nozzle/nozzle support structure having a cantilevered nozzle outer structure including an outer shroud and airfoil vanes extending radially inwardly therefrom, an inner shroud radially adjacent the inner end of the airfoil vanes and cooperatively disposed rela |
| 5553525 |
Punch press machine |
September 10, 1996 |
| A punch press machine for punching a series of holes in a cylindrical work piece has a main frame, a clamping fixture for holding the work piece, and a punch press frame having a horizontal moving punch and a die for receiving the punch. The clamping fixture is moveable relative to the m |
| 5545010 |
Method and apparatus for trim balancing a gas turbine engine |
August 13, 1996 |
| Trim balancing of rotating components in the past has increased manufacturing cost. In many past applications, the time and energy required to trim balance rotating components required partial disassembly of an outer case or structure member. The present trim balancing system allows |
| 5538380 |
Metallic nut for use with ceramic threads |
July 23, 1996 |
| A nozzle guide vane assembly has ceramic components therein having a conventional thread thereon including a preestablished pitch and having a preestablished rate of thermal expansion. The nozzle guide vane assembly has a metallic components therein having a preestablished rate of therma |
| 5538380 |
Metallic nut for use with ceramic threads |
July 23, 1996 |
| A nozzle guide vane assembly has ceramic components therein having a conventional thread thereon including a preestablished pitch and having a preestablished rate of thermal expansion. The nozzle guide vane assembly has a metallic components therein having a preestablished rate of therma |
| 5537864 |
Apparatus and method for determining and controlling combustor primary zone temperature |
July 23, 1996 |
| An apparatus and method for determining and maintaining the temperature of a primary zone of a combustor of a gas turbine engine at a predetermined level is provided. A first sensor senses the inlet air temperature of the combustor, a second sensor senses the inlet temperature of the tur |
| 5517310 |
Method and apparatus for obtaining and analyzing an image of a elongate slot |
May 14, 1996 |
| An inspection device and method determines the accuracy of an irregular shaped elongate slot disposed through a piece part supported on an indexable turntable. The inspection device includes a movable illumination device for directing backlighting towards the piece part and illuminating |
| 5511945 |
Turbine motor and blade interface cooling system |
April 30, 1996 |
| Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas tur |
| 5511940 |
Ceramic turbine nozzle |
April 30, 1996 |
| A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablish |
| 5503528 |
Rim seal for turbine wheel |
April 2, 1996 |
| A turbine wheel assembly includes a disk having a plurality of blades therearound. A ceramic ring is mounted to the housing of the turbine wheel assembly. A labyrinth rim seal mounted on the disk cooperates with the ceramic ring to seal the hot gases acting on the blades from the disk. T |
| 5494402 |
Low thermal stress ceramic turbine nozzle |
February 27, 1996 |
| A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablish |
