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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...
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7010906 |
Gas turbine engine haveing a disconnect panel for routing pipes and harnesses between a first and a second zone
A gas turbine engine ( 10 ) includes a first fire zone (Zone 3 ) in the region of a core of the engine and a second fire zone (Zone 1 ) in the region of a fan case of the engine, the first and...
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7007890 |
Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position
The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan,...
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7000378 |
Gas turbine engine exhaust nozzle having a noise attenuation device driven by shape memory material actuators
A gas turbine engine exhaust nozzle arrangement for the flow of exhaust gases therethrough between an upstream end and a downstream end thereof comprising a nozzle and a plurality of tabs which...
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6990797 |
Methods and apparatus for operating gas turbine engines
A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the...
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6983588 |
Turbofan variable fan nozzle
A turbofan exhaust nozzle includes a fan duct defined between a fan nacelle and core engine cowling. The duct includes an arcuate outlet at the trailing edge of the nacelle. A movable flap is...
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6983586 |
Two-stage pulse detonation system
A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high...
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6971229 |
Confluent exhaust nozzle
A gas turbine engine exhaust nozzle includes a nacelle having an inlet and main outlet at opposite ends, and a main duct extending therebetween. A secondary bypass duct extends radially through the...
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6968701 |
Engine integrated auxiliary power unit
The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine...
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6968675 |
Cascadeless fan thrust reverser with plume control
A thrust reverser for a turbofan engine having an air duct defined radially inwardly by a wall around the turbofan engine and radially outwardly in part by a fan cowl of the engine. A bulkhead is...
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6966175 |
Rotary adjustable 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...
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6966174 |
Integrated bypass turbojet engines for air craft and other vehicles
Turbojet engines and aircraft configurations for advantageous use of the turbojet engines; the turbojet engines utilizing ram air turbine units that centrifugally compress air isothermally for use...
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6964155 |
Turbofan engine comprising an spicyclic transmission having bearing journals
A planet gear journal for an epicyclic gear system is asymmetrically formed to compensate for carrier twist. The asymmetry may be between a pair of opposed outwardly open annular channels inboard...
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6945031 |
Recessed engine nacelle
A gas turbine engine nacelle includes an inner skin surrounded by a radially outer skin. The inner skin terminates at an exhaust outlet. The outer skin terminates at a recess in the inner skin...
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6938407 |
Bleed-off device in a bypass turbojet
This object is achieved by the bleed-off means comprising means for tapping air from the primary duct which are arranged upstream of the intermediate casing and means for evacuating the air tapped...
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6931858 |
Rotating pulse detonation system for a gas turbine engine
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and...
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6931835 |
Multivariant set point using N1 and N2 for engine control
A method for selecting a setpoint for a turbofan engine having a fan speed and a core idle speed scheduling includes determining a weighting factor based upon a throttle lever position, the...
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6904750 |
Integral pulse detonation system for a gas turbine engine
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and...
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6901738 |
Pulsed combustion turbine engine
A turbine engine has a circumferential array of combustion chamber conduits downstream of the compressor and upstream of the turbine. Means are provided for directing oxygen-containing gas from the...
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6895741 |
Differential geared turbine engine with torque modulation capability
A method and apparatus for controllable distribution of power from a turbine of a gas turbine engine between two rotatable loads of the gas turbine engine, comprises transferring a shaft power of...
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6889505 |
Pulse detonation system for a gas turbine engine
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and...
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6883303 |
Aircraft engine with inter-turbine engine frame
An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline...
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6868664 |
Main propulsion engine system integrated with secondary power unit
A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary...
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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...
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6834495 |
Multi-fan system separated core engine type turbofan engine
This invention provides a multi-fan system separated core engine type turbofan engine in which high pressure air is used as the working fluid for a turbine which drives a fan, thereby reducing the...
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6829883 |
Turbo fan gas turbine engine having a rotor containment assembly
A joint assembly for limiting an extension of the joint in the direction of a load path derived from an impact comprising a first member having a portion and a second member having a portion, the...
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6826901 |
Convergent/divergent segmented exhaust nozzle
A segmented exhaust nozzle for attenuating noise from a turbofan jet engine without adversely impacting the operability or operability limit related performance of the engine. The exhaust nozzle...
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6799416 |
Device for supporting and recentering the shaft of a turbojet fan after uncoupling
The invention provides a device for supporting and recentering a shaft ( 2 ) after decoupling. The device comprises an annular support ( 4 ) surrounding the shaft ( 2 ), a bearing ( 5 ) secured to...
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6792745 |
High bypass multi-fan engine
A turbofan jet engine having a housing and an engine core disposed in the housing. The engine core includes at least a compressor, turbine, and a drive shaft. The drive shaft defines a drive shaft...
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6792746 |
Separated core engine type turbofan engine
A low-noise separated core engine type turbofan engine is provided in which noise generated by a control propulsion device is reduced by using high pressure air as the working fluid of a turbine...
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6786038 |
Duplex mixer exhaust nozzle
A turbofan engine exhaust nozzle includes cooperating outer and inner mixers. The outer mixer includes alternating outer lobes and outer chutes. The inner mixer includes alternating inner lobes and...
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6786036 |
Bimodal fan, heat exchanger and bypass air supercharging for piston or rotary driven turbine
The present invention relates to turbine fan aircraft use. In particular, the present invention is directed toward a turbine fan driven by a piston or rotary (e.g., Wankel) engine. The present...
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6789000 |
Microprocessor-based control system for gas turbine electric powerplant
A microprocessor-based control system for a gas turbine electrical powerplant the microprocessor-based control system controls the startup, operation, and shutdown of the gas turbine electric...
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6766639 |
Acoustic-structural LPC splitter
An acoustic-structural LPC splitter assembly which comprises a structural acoustic splitter through which are arranged a plurality of bleed exhaust ports, the acoustic splitter having a first and...
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6763652 |
Variable torque split aircraft gas turbine engine counter rotating low pressure turbines
An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and low pressure inner and outer shaft turbines with counter rotatable low pressure inner and...
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6763653 |
Counter rotating fan aircraft gas turbine engine with aft booster
A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable...
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6763654 |
Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans
A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable...
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6739120 |
Counterrotatable booster compressor assembly for a gas turbine engine
A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row...
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6732502 |
Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor
An aircraft gas turbine engine includes high and low pressure turbines having respective counter rotatable low pressure inner and outer rotors with low pressure inner and outer shafts in part...
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6725645 |
Turbofan engine internal anti-ice device
A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region, associated with a booster compressor of the...
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6672049 |
Emergency device for relighting a windmilling turbojet
An emergency device for relighting a windmilling turbojet, the jet comprising a fan driven by a low-pressure turbine via a first shaft and a compressor driven by a high-pressure turbine via a...
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6666018 |
Combined cycle pulse detonation turbine engine
A pulse detonation system for a turbofan engine including a fan assembly and a turbine sub-system, which includes at least one turbine, is configured to create a temperature rise and a pressure...
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6666016 |
Mixing enhancement using axial flow
A method and an apparatus for enhancing fluid mixing. The method comprises the following: (a) configuring a duct to have an effective outer wall, an effective inner wall, a cross-sectional shape, a...
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6666017 |
Counterrotatable booster compressor assembly for a gas turbine engine
A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row...
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6662548 |
Jet blade ejector nozzle
A jet engine assembly having a jet engine and an unsteady flow ejector. The unsteady flow ejector segregates the exhaust flow from the jet engine into a plurality of rotating high velocity, low...
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6647708 |
Multi-spool by-pass turbofan engine
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...
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6637186 |
Fan case liner
A fan containment case assembly 30 of a gas turbine engine 10 includes a hardened fan case liner 42 disposed therein. In the event of a fan blade loss condition, the hardened fan case liner...
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6634863 |
Circular arc multi-bore fan disk assembly
A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart...
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6625989 |
Method and apparatus for the cooling of jet-engine turbine casings
This invention relates to a method and an apparatus for the cooling of the casing ( 1 ) of the turbines ( 2, 3 ) of jet engines, in which cooling air is diverted from a bypass flow and supplied to...
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6622473 |
Speed-reducing gear unit to absorb the axial loads generated by a turbojet fan
A turbojet engine having a fan ( 12 ) driven by a speed-reducing gear unit ( 23 ) whose input is driven by a turbine shaft ( 22 ). The speed-reducing gear unit ( 23 ) includes a planet gear ( 24 )...
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