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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...
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...
5899058 Bypass air valve for a gas turbine engine  
A bypass air valve for a gas turbine engine is provided which includes a liner, a strap, and means for selectively actuating the valve. The liner includes an inner radial surface, an outer radial...
5867980 Turbofan engine with a low pressure turbine driven supercharger in a bypass duct operated by a fuel rich combustor and an afterburner  
A multiple bypass turbofan engine includes a core Brayton Cycle gas generator with a fuel rich burning combustor and is provided with a variable supercharged bypass duct around the gas generator...
5845482 Combined bleed valve and annular diffuser for gas turbine inter compressor duct  
A multi-spool gas turbine engine of the type having an annular inter compressor duct connecting a low pressure compressor to a further compressor stage, and having improved bleed means for bleeding...
5809772 Turbofan engine with a core driven supercharged bypass duct  
A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and...
5806303 Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle  
A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and...
5775098 Bypass air valve for a gas turbine  
A bypass air valve is provided comprising a liner, a strap, and apparatus for selectively actuating the valve. The liner includes an inner surface, an outer surface, a plurality of first regions,...
5727755 Aircraft engines with a controllable outer casing  
An aircraft comprises at least one jet engine having a surrounding, open-ended duct coaxial with the engine and spaced therefrom radially to define a passage of annular cross-section. The casing or...
5694768 Variable cycle turbofan-ramjet engine  
An improved variable cycle turbofan-ramjet engine is disclosed. The engine includes a split fan assembly, a bypass channel surrounding a core engine and a mode selector valve for selectively...
5694767 Variable slot bypass injector system  
An afterburning, gas turbine aircraft engine with an annular duct for carrying bypass airflow is provided with a sliding valve type of rear Variable Area Bypass Injector (VABI) system. This rear...
5687562 Bypass air valve for turbofan engine  
A bypass air valve is provided which includes a liner, a strap, apparatus for biasing the strap into contact with the liner, a selective actuator, and apparatus for passage of bypass air. To open...
5687563 Multi-spool turbofan engine with turbine bleed  
A multi-spool turbofan engine has a plurality of circumferentially spaced poppet valves with diverters secured thereto for precisely controlling bleed of combustion gas aft of the high pressure...
5623823 Variable cycle engine with enhanced stability  
A variable cycle gas turbine engine (10) includes a core unit (30) having a guide vane array (36), and a hybrid stage (38) with a rotor blade array (40) and a stator vane array (42). The engine is...
5515673 Device for controlling the opening and closing of discharge valves of a turbojet engine  
A control device makes it possible to rapidly shift the bleed valves of an aircraft turbojet engine to a large opening position when the engine is under low power operation in order to prevent...
5417055 Valve for diverting fluid flows in turbomachines  
This invention provides a valve for diverting fluid flow in a tandem fan type engine. The valve comprises an axially displaceable sleeve 38 which is provided with two circumferentially extending...
5406787 After-burning turbo-jet engine with a fixed geometry exhaust nozzle  
A method and apparatus are provided for generating thrust in a turbo-fan engine (10), including generating additional thrust with after-burning. Sensors are used for monitoring a temperature in...
5404713 Spillage drag and infrared reducing flade engine  
A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine and having a FLADE fan disposed in the FLADE duct and radially outward of...
5402638 Spillage drag reducing flade engine  
A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine. A FLADE fan is disposed in the FLADE duct radially outward of and...
5381655 Admission mixing duct assembly  
A variable cycle jet engine is provided with a mixing duct assembly which mixes core engine exhaust gas with bypass air when the engine is operating in a turbofan mode and which blocks flow from...
5343697 Variable area bypass injector  
A variable area bypass injector (VABI) for a variable cycle gas turbine engine includes a circumferentially continuous valve with a conical surface sloping into a screech suppressor surface, a...
5317867 Changeover valve  
A changeover valve for a tandem fan type of engine is located in a duct between fan stages at either end. The valve arrangement has a butterfly flap valve to selectively obstruct flow along the...
5315821 Aircraft bypass turbofan engine thrust reverser  
An aircraft bypass turbofan engine subassembly for ground deceleration (e.g., thrust reversal). A fan nacelle has a through passageway connecting its inner exterior surface and outer exterior...
5311736 Variable cycle propulsion engine for supersonic aircraft  
A turbojet propulsion engine for supersonic aircraft has a primary unit including a compressor, a combustion chamber, a turbine which drives the compressor, and an exhaust assembly, and a secondary...
5307624 Variable area bypass valve assembly  
A bypass valve assembly includes an outer casing and a spaced outer liner defining an annular bypass channel for channeling bypass air. The outer liner includes a plurality of circumferentially...
5305599 Pressure-ratio control of gas turbine engine  
Control of a gas turbine engine, suitable for powering an aircraft, is accomplished by varying outlet nozzle cross section and/or a mixing of bypass air with exhaust gas at an inlet to the nozzle....
5305600 Propulsion engine  
The rotor of a fan disposed in the annular noncombusted air flow duct of a urbojet propulsion engine of the bypass type is carried by a rotary body which includes the rotor assembly of a...
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