Matches 1 - 50 out of 137 1 2 3 >


Match Document Document Title
8181443 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,...
8181441 Controlled fan stream flow bypass  
A turbine engine component of a turbofan engine fitted with a bypass air valve includes at least one turbine engine component having a surface with at least one aperture, said turbine engine...
8151551 Variable area fan nozzle thrust reverser  
A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow...
8127531 Radially translating fan nozzle nacelle  
A variable area nozzle system for a turbofan gas turbine engine comprises a fan duct inner wall, a fan duct outer wall and a fan nozzle. The fan duct outer wall is disposed in radially-spaced...
8127532 Pivoting fan nozzle nacelle  
A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The...
8127528 Auxiliary propulsor for a variable cycle gas turbine engine  
A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the...
8104262 Dual function cascade integrated variable area fan nozzle and thrust reverser  
A gas turbine engine system includes a nozzle having a plurality of positions for altering a discharge flow received through the nozzle from a gas turbine engine fan bypass passage. The nozzle is...
8096105 Turbojet engine with attenuated jet noise  
A plurality of hatches are distributed on the rear periphery of an engine cowl. The hatches are opened only when turbojet engine power is greater than cruising power. In an open position, the...
8091334 Method of operating a turbofan engine cowl assembly  
An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a...
8082727 Rear propulsor for a variable cycle gas turbine engine  
A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air...
8074440 Gas turbine engine with axial movable fan variable area nozzle  
A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second...
8028513 Variable bypass turbine fan  
An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a...
8020365 Multidirectional turbine engine  
A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating...
8015996 Gas turbine engine air valve assembly  
A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air...
8001763 Managing spool bearing load using variable area flow nozzle  
A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the...
7926290 Turbine engine with modulated flow fan and method of operation  
A gas turbine engine includes a turbomachinery core operable to generating a flow of pressurized combustion gases; a rotating fan adapted to extract energy from the core and generate a first flow...
7886518 Turbofan engine cowl assembly and method of operating the same  
An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a...
7866228 Device for moving at least one moveable element in a gas turbine  
The invention relates to a device (20) for moving at least one moveable element (19) in a gas turbine engine (1) between a first and a second position. The device includes a linkage (21) that...
7837436 Method and apparatus for regulating fluid flow through a turbine engine  
A method for regulating fluid flow through a gas turbine engine is provided. The method includes coupling an outer fairing to a radially outer duct wall and coupling an inner fairing to a radially...
7805924 Thermally decoupled mixer  
The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed...
7770381 Duct burning mixed flow turbofan and method of operation  
A gas turbine engine includes a turbomachinery core operable to generating a first flow of pressurized combustion gases, the core having an exit plane; a fan disposed upstream of the core adapted...
7762057 Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines  
An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through...
7739865 Gas turbine engine inlet with noise reduction features  
A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct...
7730714 Turbofan gas turbine engine with variable fan outlet guide vanes  
A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the...
7726116 Turbofan engine nozzle assembly and method of operating same  
A nozzle assembly for a gas turbine aircraft engine is provided. The nozzle assembly includes a nacelle and a core cowl positioned at least partially within the nacelle such that the core cowl and...
7614210 Double bypass turbofan  
A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the...
7510140 Method and apparatus for generating lift  
A method of generating lift for a vehicle including a gas turbine engine having a combustor, a core flow heated by the combustor, and a bypass flow which bypasses the combustor. The method includes...
7475532 Valve assembly for a gas turbine engine  
A method for channeling compressed air to a gas turbine engine augmentor is provided. The method includes coupling an annular slide valve to a gas turbine engine separation liner, coupling a valve...
7464536 Methods and apparatus for assembling gas turbine engines  
A method is provided for operating a gas turbine engine including a core engine having a core stream duct, an inner bypass duct, an outer bypass duct, and a nozzle assembly downstream of the core...
7416051 Assembly and method for fan noise reduction from turbofan engines using dynamically adaptive Herschel-Quincke tubes  
An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (1) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube por...
7395657 Flade gas turbine engine with fixed geometry inlet  
An aircraft propulsion system includes a gas turbine engine having a fan section, at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to the fan section, the...
7353647 Methods and apparatus for assembling gas turbine engines  
A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a...
7246484 FLADE gas turbine engine with counter-rotatable fans  
An exemplary embodiment of a FLADE counter-rotating fan aircraft gas turbine engine includes at least one row of FLADE fan blades disposed radially outwardly of and drivingly connected to one of...
7093793 Variable cam exhaust nozzle  
An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged...
7010905 Ventilated confluent exhaust nozzle  
An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes...
6901739 Gas turbine engine with variable pressure ratio fan system  
A multiple bypass turbofan engine includes axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to a low pressure shaft. A fan bypass duct...
6837038 Variable cycle boost propulsor  
The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the...
6751944 Confluent variable exhaust nozzle  
A gas turbine engine exhaust nozzle includes coaxial inner and outer conduits. The inner conduit has a main outlet at an aft end thereof, and a row of radial apertures spaced upstream from the...
6742324 Methods and apparatus for supporting variable bypass valve systems  
A method enables a gas turbine engine variable bypass valve system to be assembled. The method comprises positioning a unison ring circumferentially within the gas turbine engine such that the...
6681559 Thrust reverser position determination system and method  
An improved jet engine thrust reverser that includes a sensor to determined the rotational position of a motor. The system includes an actuator, a motor, motor position sensor, and an electronic...
6622475 Bleed system driven in simplified manner for a turbojet or turboprop engine  
A bypass gas turbine engine having an intermediate structural casing positioned between a primary flow path and a bypass flow path, and configured between a low pressure compressor and a high...
6523339 Variable mode jet engine—compact  
This jet engine comprises of a complete low bypass turbofan unit 1 including secondary fan unit 2 and engine core, some five to eight feet ahead of which sits a larger diameter main fan unit 3...
6415597 Switchably coupled turbofan engines for high speed aircraft  
A jet engine for supersonic aircraft which enables supersonic flight and high fuel efficiency to be achieved while suppressing noise at take-off. The engine comprises a front engine consisting of a...
6282881 Cooling system for a turbomachine speed reducer  
A system for cooling the lubricant of the speed reducer of an aircraft turboshaft-engine during high-speed flight and during low-speed taxying. The cooling system includes a radiator through which...
6260800 Aircraft power plant with two air intake fans  
An aircraft power plant for vertical take-off and landing comprises a jet propulsion unit having an air inlet and an exhaust outlet and incorporating a combustion chamber, a high pressure...
6209311 Turbofan engine including fans with reduced speed  
An impeller is directly driven by an output shaft of a core engine. The airflow produced by the impeller rotates an air turbine and a fan disposed integrally with the air turbine. The impeller and...
6102329 Flow diverter system for multiple streams for gas turbine engine  
A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both...
6070407 Ducted fan gas turbine engine with variable area fan duct nozzle  
The fan duct of a ducted fan gas turbine engine is provided with a secondary duct at least partly within the downstream end of the primary duct. The secondary duct is provided with means such as...
6048171 Bleed valve system  
The invention is a valve system particularly useful as a bleed valve system in a gas turbine engine. The valve system includes a valve ring or partition (44) that bounds a plenum (52). The valve...
6041589 Asymmetric turboprop booster  
A booster-compressor assembly for supercharging air into a core engine that powers propellers of a turboprop aircraft engine includes an asymmetric annular booster duct aft of the propellers and...
Matches 1 - 50 out of 137 1 2 3 >