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| Number | Title | Issue Date |
| 5402963 | Acoustically shielded exhaust system for high thrust jet engines A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight conditions, particularly during takeoff. The flade airflow is conver... | 04/04/1995 |
| 5400952 | Method and apparatus for damping a brush seal There is provided by the present invention method and apparatus for damping vibrations or other unwanted motions of a brush seal, the apparatus including a damper having a plurality of individual plates that are bonded directly to the inlet rows of bristl... | 03/28/1995 |
| 5397217 | Pulse-cooled gas turbine engine assembly A pulse-cooled gas turbine engine assembly includes a hollow airfoil and a fluidic oscillator joined thereto. The fluidic oscillator discharges pressurized cooling air inside the airfoil at a predetermined pulsation frequency for cooling the airfoil.... | 03/14/1995 |
| 5392614 | Gas turbine engine cooling system A gas turbine engine cooling system. Hotter engine compressor air is cooled by a heat exchanger using a colder engine fluid (such as fuel or lower pressure (colder) engine compressor air. The cooled air passes through the compressor section of an auxiliar... | 02/28/1995 |
| 5388964 | Hybrid rotor blade A hybrid gas turbine engine rotor blade includes an airfoil and a dovetail integrally joined thereto. The airfoil includes an inner portion disposed adjacent to the dovetail to provide a structural transition, and an outer portion disposed thereabove for ... | 02/14/1995 |
| 5372476 | Turbine nozzle support assembly A turbine nozzle support assembly includes nozzle segments each having an inner band with an integral retention flange extending radially inwardly therefrom. A plurality of retention tabs extend radially inwardly and are spaced axially aft of the retentio... | 12/13/1994 |
| 5370499 | Film cooling of turbine airfoil wall using mesh cooling hole arrangement A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least at a pressure side and extending from an internal chamber ... | 12/06/1994 |
| 5367871 | Aircraft engine ignition system A plasma jet igniter is used to reliably relight a jet engine at high altitudes under adverse combustion conditions. The air-fuel mixture from the primary combustion zone of the jet engine combustor may be used as the plasma medium or, alternatively, liqu... | 11/29/1994 |
| 5363654 | Recuperative impingement cooling of jet engine components Impingement cooling of a jet engine subassembly, such as a combustor. Adjacent raised corrugation portions and intervening plate portions (having impingement cooling holes) of a corrugated plate define coolant channels in fluid communication with the engi... | 11/15/1994 |
| 5361828 | Scaled heat transfer surface with protruding ramp surface turbulators A heat transfer surface for use along a flowpath along the surface is scaled with rows of turbulators having ramp surfaces protruding into the flowpath operable to generate turbulence promoting vortices. The ramp surfaces may be oriented to present an upw... | 11/08/1994 |
| 5361580 | Gas turbine engine rotor support system A gas turbine engine rotor support system includes outer and inner rotors having respective outer and inner blades interdigitated in respective blade row stages. A stationary rear frame includes a rear support shaft. A rotatable aft frame is disposed forw... | 11/08/1994 |
| 5357744 | Segmented turbine flowpath assembly A turbine flowpath assembly includes a plurality of circumferentially spaced apart airfoils disposed within an annular outer casing. Each of the airfoils includes outer and inner integral bands. A plurality of flowpath outer and inner panels are disposed ... | 10/25/1994 |
| 5357742 | Turbojet cooling system The hot core engine compartment of a turbojet engine is cooled by the metered flow of cooling air exhausted through a laminar flow nacelle system. This arrangement reduces the need for extracting bypass ram air from the engine performance cycle for coolin... | 10/25/1994 |
| 5358374 | Turbine nozzle backflow inhibitor A turbine nozzle includes a vane integrally joined between outer and inner bands, with the inner band having a purge hole for discharging a portion of cooling air channeled through the vane. A checkvalve is provided in the purge hole for preventing backfl... | 10/25/1994 |
| 5351473 | Method for bleeding air A gas turbine engine includes a fan, fan bypass duct, compressor, core duct, and turbine including a clearance control system. The core duct includes a bleed valve, the fan bypass duct includes a bleed vent, and a bleed pipe is disposed in flow communicat... | 10/04/1994 |
| 5351888 | Multi-axis vectorable exhaust nozzle A convergent-divergent exhaust nozzle is mounted to an exhaust duct of a jet aircraft engine by a circumferentially-spaced set of hydraulic cylinders. The cylinders are interconnected in captured flow via hydraulic circuits which allow the cylinders to fu... | 10/04/1994 |
| 5351478 | Compressor casing assembly An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casi... | 10/04/1994 |
| 5349814 | Air-start assembly and method A method and assembly are effective for air-starting an aircraft gas turbine engine having a fan powered by a low pressure turbine through a first shaft, and a compressor powered by a high pressure turbine through a second shaft disposed coaxially therewi... | 09/27/1994 |
| 5348446 | Bimetallic turbine airfoil An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a hi... | 09/20/1994 |
| 5345760 | Turboprop booster A booster-compressor for a high flow coefficient turboprop aircraft engine increases engine thrust by supercharging the air into the inlet of the gas generating core engine. The flow of supercharged air from the booster-compressor is split between the cor... | 09/13/1994 |
| 5344239 | Squeeze film bearing damper with annular end plenums A sealed squeeze film damper having double annular wall sealed plenums at the open ends of the damper which seal the damper and prevent air from being sucked into a sealed film damper thereby preventing degradation of damper performance due to air entrain... | 09/06/1994 |
| 5343691 | Reducing thermal deposits in propulsion systems This invention provides a method to mix a relatively large amount of non-condensable gas with fuel prior to gasification heating thus reducing the residence time of the fuel adjacent to hot surfaces. The non-condensable gas may be air, a cryogenic such as... | 09/06/1994 |
| 5344280 | Impact resistant fan case liner A composite article includes a plurality of laminates each having structural fibers bonded in a matrix, and an adhesive film disposed between and bonding together adjacent ones of the laminates. In an exemplary embodiment, the laminates and the interleave... | 09/06/1994 |
| 5338154 | Turbine disk interstage seal axial retaining ring An axial retention system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk. The interstage seal includes a web portion having an aft arm extending from said web,... | 08/16/1994 |
| 5337568 | Micro-grooved heat transfer wall A gas turbine engine hot section component such as a turbine blade or vane having an airfoil is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the porti... | 08/16/1994 |
| 5338928 | System and method for controlling deformation of a structure having a phase shift detector Vibrations within ceramic matrix and metal matrix composite materials are controlled by applying an excitation voltage to an array of piezoelectric actuators mounted to the surface of such materials. The actuators are driven in response to the phase shift... | 08/16/1994 |
| 5335920 | Brush seal A brush seal is provided having a plurality of bristle layers sandwiched between a pair of circumferential plates with the upstream layers of bristles having a higher first fundamental vibration frequency than downstream seal layers. Such a seal has brist... | 08/09/1994 |
| 5333445 | Scramjet engine having improved fuel/air mixing A scramjet engine for powering an aircraft at supersonic velocities is disclosed. The scramjet engine includes supersonic compressed airflow in a combustor along with a fuel for providing combustion. A monopropellant is also supplied adjacent to the airfl... | 08/02/1994 |
| 5333993 | Stator seal assembly providing improved clearance control A stator seal assembly for a gas turbine engine of a type having a high pressure compressor section and a high pressure turbine section, the stator seal having a seal segment extending between a stator vane support structure and disk seal teeth, the stato... | 08/02/1994 |
| 5332360 | Stator vane having reinforced braze joint A gas turbine engine stator vane includes a groove extending laterally in an outer surface at one end thereof between leading and trailing edges for receiving a brazing material. The vane may be joined to an arcuate band having a complementary groove exte... | 07/26/1994 |
| 5332358 | Uncoupled seal support assembly A seal support assembly for a gas turbine engine includes a stator seal support having an annular seal backing extending axially away therefrom and having an integral retention flange at one end thereof. The retention flange includes a retention groove. A... | 07/26/1994 |
| 5328331 | Turbine airfoil with double shell outer wall A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally form... | 07/12/1994 |
| 5327716 | System and method for tailoring rotor tip bleed air A rotor tip bleed air tailoring system in which a rotor blade is located upstream from an outer stator vane and an inner stator vane. The inner stator vane and outer stator vane are separated by a splitter which extends to the tip region of the rotor blad... | 07/12/1994 |
| 5327727 | Micro-grooved heat transfer combustor wall A gas turbine engine hot section combustor liner is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a di... | 07/12/1994 |
| 5326224 | Cooling hole arrangements in jet engine components exposed to hot gas flow A jet engine component includes a body having a wall portion with an external surface exposed to hot gas flow and an internal surface exposed to a cooling air flow. The engine component incorporates an arrangement of cooling holes defined through the wall... | 07/05/1994 |
| 5320488 | Turbine disk interstage seal anti-rotation system An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk having a rearwardly extending aft shaft and a second stage disk. The interstage seal includes a rearwardly proje... | 06/14/1994 |
| 5320486 | Apparatus for positioning compressor liner segments In a gas turbine engine, a system for maintaining uniform circumferential spacing between adjacent segments of a compressor liner, the liner segments being retained within an outer casing by a flanged connection. The system includes a T-shaped pin retaine... | 06/14/1994 |
| 5320484 | Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring int... | 06/14/1994 |
| 5318405 | Turbine disk interstage seal anti-rotation key through disk dovetail slot An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk and a second stage disk, each having a plurality of dovetail slots. The interstage seal is located between the d... | 06/07/1994 |
| 5316437 | Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub A structural frame assembly for use in a gas turbine engine includes an annular inner hub, an annular outer casing and a plurality of circumferentially-spaced and radially extending hollow struts connected to the inner hub and outer casing. Hot gases are ... | 05/31/1994 |
