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7434303 |
Nacelle assembly for a gas turbine engine
A nacelle assembly 40 adapted for mounting on a ducted fan gas turbine engine 20 comprising a generally annular body 46 having an air inlet 42 and an air outlet 44 , the generally annular...
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7430852 |
Turbojet having a large bypass ratio
A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its...
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7424360 |
Overspeed control system for gas turbine electric powerplant
A turbine overspeed control system for use with a gas turbine engine of a gas turbine electrical powerplant. The overspeed control system preferably comprises a first and second overspeed control...
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7412819 |
Turbojet architecture with two fans at the front
A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a...
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7413399 |
Method and apparatus for distributing fluid into a turbomachine
An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within...
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7412831 |
Integral cooling system for rotary engine
A rotary combustion engine ( 12 ) with a self-cooling system comprises a heat exchanging interface for discharging excess heat from the rotary combustion engine ( 12 ), and a direct drive fan ( 44...
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7409819 |
Gas turbine engine and method of assembling same
A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to...
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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...
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7377109 |
Apparatus and method for reduction of jet noise from turbofan engines having separate bypass and core flows
An exhaust flow system for use with a turbofan jet engine that provides separate fan flow and core flow streams that are not mixed. The system includes a fan nozzle and a primary flow nozzle. The...
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7363757 |
Turbine engine with semi-fixed turbine driving a receiver controlled so as to preserve a roughly constant rotation speed
The invention relates to a turbine engine ( 1 ) with a semi-fixed turbine, particularly for aircraft driving a receiver ( 2 ) controlled so as to preserve a roughly constant rotation speed. The...
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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...
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7340883 |
Morphing structure
An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between...
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7334393 |
Aircraft engine in which there is a small clearance separating the fan cowls and the thrust inverter cowls
Aircraft engine comprising a pod comprising, in sequence from front to back, an air inlet structure ( 6 ), fan cowls ( 7 ), thrust inverter cowls ( 8 ), and a nozzle ( 9 ), additional stiffening...
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7334394 |
Localized arc filament plasma actuators for noise mitigation and mixing enhancement
A device for controlling fluid flow. The device includes an arc generator coupled to electrodes. The electrodes are placed adjacent a fluid flowpath such that upon being energized by the arc...
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7328623 |
Temperature and/or pressure sensor assembly
A sensor assembly includes a housing and a tube. The housing has a first leading edge portion which is capable of being located in a compressor/fan inlet flow path and which includes an interior...
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7322180 |
Turbo-jet engine with fan integral with a drive shaft supported by first and second bearings
A turbo-jet engine including a fixed structure and a fan rotor mounted on a drive shaft supported by a first bearing and a second bearing. The engine further comprises an axial retaining device...
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7322181 |
Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing
The turbojet includes a fixed structure, a fan rotor fixed to a drive shaft supported by a first bearing and a second bearing. The second bearing is mounted on the fixed structure through a bearing...
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7314035 |
Rotary vane engine and thermodynamic cycle
A heat engine having a rotary vane compressor and a rotary vane turbine operates in a highly efficient thermodynamic cycle which includes a power expansion phase up to ambient pressure and a...
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7305817 |
Sinuous chevron exhaust nozzle
A gas turbine engine exhaust nozzle includes a row of laterally sinuous chevrons extending from an aft end of an exhaust duct. The chevrons have radially outer and inner surfaces bound by a...
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7299621 |
Three-spool by-pass turbojet with a high by-pass ratio
The invention relates to aerodynamically matching the rear fan of a turbojet having two fans and a low-pressure compressor at the front of the intermediate casing, said fans being driven by two...
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7296414 |
Aircraft engine mounting assembly
A mounting assembly ( 10 ) for mounting a gas turbine engine on an aircraft. The assembly ( 10 ) comprising four equispaced hydraulic piston and cylinder thrust links ( 16 ) connecting between the...
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7296398 |
Counter-rotating turbine engine and method of assembling same
A method for assembling a gas turbine engine that includes providing a first fan assembly configured to rotate in a first rotational direction, rotatably coupling a second fan assembly to the first...
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RE39796 |
Method of eliminating mach waves from supersonic jets
A method and device for reducing the amount of noise generated by a supersonic jet engine is provided. The method creates an envelope of air around the supersonic jet exhaust. The temperature and...
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7246482 |
Gas turbine engine bleed air power assist system and method
A bleed air power assist system is coupled to a gas turbine engine that includes a high pressure turbine, a low pressure turbine, and an electrical generator driven by the high pressure turbine....
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7237378 |
Turbomachine with low noise emissions for aircraft
The invention relates to a turbomachine ( 1 ) for an aircraft comprising a gas generator ( 4 ) designed such that hot gases are ejected from a combustion chamber ( 28 ) towards the upstream side of...
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7228683 |
Methods and apparatus for generating gas turbine engine thrust using a pulse detonator
Methods and apparatus for generating thrust from a gas turbine engine using a pulse detonation system is provided. The gas turbine engine includes a fan assembly, and a bypass duct channeling air...
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7219490 |
Nested core gas turbine engine
A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds...
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7216475 |
Aft FLADE engine
An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a...
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7213391 |
Cooling systems
Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point...
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7200999 |
Arrangement for bleeding the boundary layer from an aircraft engine
An aircraft engine comprising a nacelle, a first wall and fan outlet guide vanes. The fan outlet guide vanes comprises a plurality of stator vanes extending between a second wall and a third wall....
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7188467 |
Methods and apparatus for assembling a gas turbine engine
A method for assembling a gas turbine engine includes providing a core engine, and providing a flade system including a flade stream augmentor positioned within a flade duct. The method also...
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7185484 |
Methods and apparatus for assembling a gas turbine engine
Methods and apparatus for assembling a gas turbine engine are provided. The method includes coupling a first turbine shaft that includes m rows of turbine blades within the gas turbine such that...
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7174704 |
Split shroud exhaust nozzle
A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased...
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7159383 |
Apparatus, method and system for gas turbine engine noise reduction
An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas...
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7140174 |
Methods and apparatus for assembling a gas turbine engine
A method for assembling a gas turbine engine includes providing a core engine, an inner fan assembly, and a fladed fan assembly, coupling a plurality of airflow ducts to the engine including an...
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7134271 |
Thrust vectoring aft FLADE engine
An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades...
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7121758 |
Joint arrangement
A joint assembly 80 is provided for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising. In its simplest form, the joint 80 comprises a...
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7107756 |
Turbofan arrangement
A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and...
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7100360 |
Pulsed combustion engine
A pulsed combustion device includes a support structure and a combustor carousel supported by the support structure and rotating relative thereto about an axis. The carousel has a number of...
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7096674 |
High thrust gas turbine engine with improved core system
A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a...
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7094033 |
Methods and apparatus for assembling gas turbine engines
A method for assembling a fan platform for a gas turbine engine is provided. The method includes determining an area of vulnerability to impact and erosion damage across the platform, forming a...
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7086219 |
Cowl structure for a gas turbine engine
A cowl structure ( 18 ) for a gas turbine engine ( 10 ) comprises an outer skin ( 26 ) defining a first path for a load applied to the engine ( 10 ). The cowl structure ( 18 ) includes an inner...
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7065957 |
Segmented mixing device for jet engines and aircraft
Disclosed is a means for reducing jet engine exhaust noise wherein mixing is enhanced between adjacent exhaust flows and between exhaust flow and free-stream flow. Also disclosed is a means for...
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7059136 |
Air turbine powered accessory
An aircraft accessory system includes an aircraft engine powered direct air turbine driven accessory and an air turbine drivingly directly connected by an air turbine shaft to the accessory. The...
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7055306 |
Combined stage single shaft turbofan engine
A turbofan engine includes a combined stage rotor mounted for common rotation with a shaft, a compressor stage, and a turbine stage. Each of the plurality of fan blades of the combined stage rotor...
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7055329 |
Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air
A method enables a gas turbine engine to be operated. The method comprises channeling exhaust gases from a core engine through an exhaust assembly and past at least one flow boundary surface, and...
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7047724 |
Combustion ignition
Distributed initiation (e.g., multipoint or continuous) is utilized to obtain constant volume-like combustion performance in a pulse combustion device in the absence of detonation. A number of such...
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7032387 |
Axisymmetric flap on gas turbine exhaust centerbody
The present invention includes a gas turbine engine exhaust centerbody comprising a forward portion having at least one flap at a downstream end thereof to induce a local low pressure zone in the...
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7021042 |
Geartrain coupling for a turbofan engine
Molybdenum disulfide (MoS 2 ) is used as a journal coating for a gearing system. A particular application is the planetary gear system of a geared turbofan engine. Particularly advantageous...
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7021043 |
Jet engine using exhaust gas
A jet engine using exhaust gas to get the propulsive force by rotating a fan within the exhaust gas burned in and emitted from the engine includes a body, a burner installed to the body to inject...
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