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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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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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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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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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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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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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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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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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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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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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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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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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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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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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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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