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7637095 |
Thrust vectorable fan variable area nozzle for a gas turbine engine fan nacelle
A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates...
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7631485 |
Tip turbine engine with a heat exchanger
A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a...
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7631483 |
Method and system for reduction of jet engine noise
In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall, is increased to a greater rate than typical velocity of an operational...
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7631484 |
High pressure ratio aft fan
A fan assembly for a gas turbine engine includes a turbine rotor adapted to be disposed aft of a core of the gas turbine engine; a row of turbine blades carried by the rotor, each turbine blade...
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7624581 |
Compact booster bleed turbofan
A Turbofan engine includes a fan mounted to a fan frame inside a fan nacelle. A booster compressor is joined to the fan inboard a flow splitter. A booster bleed system is disposed inside the...
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7621117 |
Apparatus and method for controlling engine windmilling
An apparatus and method are provided for controlling the ground windmilling of at least one of the spools in a gas turbine engine. Electrical power is supplied to a braking apparatus in one aspect....
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7621371 |
Method for attenuating the noise of a turbofan
A jet engine includes a hollow nacelle including a front air intake section and a rear air outlet section having outer and inner annular surfaces which converge to form a trailing edge. A fan...
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7618232 |
Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine
This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F 1 ) and a...
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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...
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7610763 |
Tailorable design configuration topologies for aircraft engine mid-turbine frames
A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The...
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7607286 |
Regenerative turbine blade and vane cooling for a tip turbine engine
A fan-turbine rotor assembly ( 24 ) includes a multitude of turbine blades ( 34 ) which each define a turbine blade passage which bleed air from a diffuser section ( 74 ) to provide for...
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7607308 |
Shrouded turbofan bleed duct
A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The...
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7607287 |
Airfoil acoustic impedance control
A noise control cassette for a gas turbine engine includes a perforated face sheet configured for exposure to an airflow, a non-perforated backing sheet, a core arranged between the face sheet and...
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7604201 |
Nacelle drag reduction device for a turbofan gas turbine engine
The nacelle drag reduction device comprises a substantially circular and axis symmetrical external airfoil concentric with a aft section of the nacelle and located outside a propulsive jet zone...
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7600384 |
Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be varied by moving the secondary cowl
The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary...
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7594404 |
Embedded mount for mid-turbine frame
An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior...
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7594405 |
Catenary mid-turbine frame design
An engine casing assembly having dual load transfer points includes a U-shaped mid-turbine frame, an engine casing, a plurality of dimples, a strut and a mounting apparatus. The engine casing has...
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7594388 |
Counterrotating turbofan engine
A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor...
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7581692 |
Fluidic chevrons and configurable thermal shield for jet noise reduction
A system for jet engine noise control of a jet engine having a main jet stream exiting an exhaust nozzle and flowing along a jet axis includes a thermal acoustic shield directed at a non-zero angle...
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7581382 |
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...
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7578132 |
Gas turbine engine exhaust nozzle
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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7568336 |
Aeroengine fitted with heat exchanger means
An aeroengine includes a primary air circuit; a high-pressure compressor fed by the primary air; and a secondary air circuit. The engine further includes at least one heat exchanger mounted in the...
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7565796 |
Turbofan case and method of making
A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
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7559191 |
Ducted spinner for engine cooling
A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system...
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7555893 |
Aircraft propulsion system
To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly...
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7555904 |
Thermally compliant rivet connection for connecting turbine engine liner to convergent flap and seal for turbine nozzle
A bracket for attaching a liner to the divergent flaps and seals in a gas turbine engine convergent/divergent nozzle includes a rivet connection. There is clearance between a rivet and an opening...
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7549291 |
Methods and apparatus for operating gas turbine engines
A gas turbine engine assembly includes at least one propelling gas turbine engine and an auxiliary engine used for generating power. The propelling gas turbine engine includes a fan assembly and a...
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7546727 |
Reduced noise jet engine
A system for controlling a position of jet engine exhaust mixing tabs includes a plurality of exhaust mixing tabs spaced apart from one another and extending from a lip of an exhaust nozzle of a...
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7543442 |
Turbojet engine comprising a connector arm for ancillary systems, and the connector arm for ancillary systems
A turbofan jet engine includes an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct....
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7543452 |
Serrated nozzle trailing edge for exhaust noise suppression
A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining...
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7540144 |
Bleed valve for a gas turbine engine
A bleed valve for a gas turbine engine having a chamber inward of the bypass flow path and in fluid flow communication with the bypass and primary flow paths, a valve member for alternatively...
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7530217 |
Axial flow positive displacement gas generator with combustion extending into an expansion section
An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet...
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7520124 |
Asymmetric serrated nozzle for exhaust noise reduction
An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects...
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7513103 |
Gas turbine engine assembly and methods of assembling same
A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an...
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7513102 |
Integrated counterrotating turbofan
A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low...
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7506499 |
Turbofan jet engine with ancillaries distribution support
A turbofan jet engine includes an outer casing supported by arms, an inner casing facing the outer casing, ancillaries, and an ancillaries distribution support. The ancillaries distribution support...
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7503164 |
Ducted fan with containment structure
The ducted fan ( 12 ) of a ducted fan gas turbine engine ( 10 ) is surrounded by a compartment ( 26 ), which is packed with bristles ( 38 ). Should a blade of the fan stage ( 12 ) disintegrate...
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7500351 |
Gas turbine powerplant
A gas turbine powerplant for a V/STOL aircraft in which a vectorable exhaust nozzle at a forward part (eg. nose) of the aircraft selectably receives a supply of cold fan air through a duct leading...
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7500352 |
Gas turbine engine
A gas turbine engine ( 2 ) comprises a fan unit ( 4,18,36,42,44,46 ) in flow relationship with an engine core and a bypass duct, of which said engine core and bypass duct ( 16 ) are in parallel...
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7493754 |
Gas turbine engine assembly and methods of assembling same
A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the...
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7487630 |
Jet engine with compact arrangement of fan
A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure...
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7484354 |
Aircraft engine arrangement
In order to avoid external bulging ( 5 ) to accommodate accessory mechanisms ( 27 ) and gearboxes ( 30 ) to drive these mechanisms ( 27 ) in accordance with the present invention splitter fairings...
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7469529 |
Chevron-type primary exhaust nozzle for aircraft turbofan engine, and aircraft comprising such a nozzle
A primary exhaust nozzle for a turbofan engine of the double, separated air-flow type for aircraft comprises: an inner coat, within which there circulates a primary air flow (FP), comprising...
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7458773 |
Turbomachine with contrarotating fans
A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine...
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7458202 |
Lubrication system for a counter-rotating turbine engine and method of assembling same
A method for assembling a gas turbine engine includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first fan...
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7454894 |
Supplemental oil cooler airflow for gas turbine engine
A gas turbine engine is provided with an oil cooler which receives cooling air from a turbo fan. At times when the turbo fan is operating at lower speeds, the volume of cooling air is also lowered....
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7448198 |
Gas turbine braking apparatus and method
A device is provided which can serve one or more of the multiple functions of impeding rotation of a shaft de-coupled turbine rotor, selectively impeding rotation of a first spool of the engine,...
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7448199 |
Self powdered missile turbojet
A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. An integral starter-generator is disposed inside the core engine...
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7444802 |
Gas turbine engine including stator vanes having variable camber and stagger configurations at different circumferential positions
Within an intake for a gas turbine engine provision is provided through stator vanes 25, 45 in the stator whereby back pressure from a necessary obstruction 34, 46 can be utilised to balance...
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7437877 |
Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same
A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage...
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