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US20150345426 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE  
A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with...
US20070125066 TURBOFAN ENGINE ASSEMBLY AND METHOD OF ASSEMBLING SAME  
A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a counter-rotating fan assembly...
US20050252195 Noise reduction assembly for aircraft turbojet  
A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic...
US20050274103 Gas turbine engine inlet with noise reduction features  
A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct...
US20160010589 TWO-PART GAS TURBINE ENGINE  
A gas turbine engine propulsion system in which a first propulsive unit has a core engine and a first low pressure turbine arranged to be driven by combustion products from the core engine. The...
US20120096832 FLUTTER SENSING AND CONTROL SYSTEM FOR A GAS TURBINE ENGINE  
An exemplary gas turbine engine assembly includes a nacelle, a core engine casing within the nacelle, a low pressure turbine having a pressure ratio that is greater than five, and a bypass passage...
US20130186058 GEARED TURBOMACHINE FAN AND COMPRESSOR ROTATION  
A high-bypass ratio geared turbomachine comprises a compressor section of a high-bypass ratio geared turbomachine. The compressor section provides at least a low-pressure compressor and a...
US20140174056 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine comprises a gear train defined along an axis. A spool along the axis drives the gear train and includes a low stage count low pressure turbine. A fan i s rotatable at a fan...
US20080072569 GUIDE VANE AND METHOD OF FABRICATING THE SAME  
A method for fabricating a gas turbine engine outlet guide vane includes fabricating an airfoil that includes a leading edge portion and a trailing edge portion each fabricated from a first...
US20130340406 FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE  
A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the...
US20070000232 Gas turbine engine and method of operating same  
A method for operating a gas turbine engine including a core engine, a fan assembly for pressurizing air, a core stream duct, an inner bypass duct, and an outer bypass duct is provided. The method...
US20060288687 Grommeted bypass duct penetration  
A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and an external surface of a projection extending through the opening, where the grommet has...
US20120110980 VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM  
A system and method of controlling a fan blade flutter characteristic of a gas turbine engine includes adjusting a variable area fan nozzle in response to a neural network.
US20090223052 GEARBOX GEAR AND NACELLE ARRANGEMENT  
A gas turbine engine is provided that includes a spool that supports an engine. A gearbox is operatively coupled to the spool through a transmission device configured to transfer rotational drive...
US20050138914 Turbo rocket with real carnot cycle  
Engine embodiments primarily designed for aircraft propulsion and power generation incorporating the Carnot cycle for efficient combustion with typical embodiments including air compressors having...
US20170044978 TURBINE SECTION OF HIGH BYPASS TURBOFAN  
A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating...
US20120117940 GAS TURBINE ENGINE WITH PYLON MOUNTED ACCESSORY DRIVE  
A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well...
US20080053060 Bypass lip seal  
A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed...
US20130192198 COMPRESSOR FLOWPATH  
A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope...
US20130219859 COUNTER ROTATING LOW PRESSURE COMPRESSOR AND TURBINE EACH HAVING A GEAR SYSTEM  
A compressor section includes a counter rotating low pressure compressor that includes outer and inner compressor blades interspersed with one another and are configured to rotate in an opposite...
US20110154805 POWER AUGMENTATION SYSTEM FOR AN ENGINE POWERED AIR VEHICLE  
One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is...
US20160131043 TURBINE ENGINE GEARBOX  
A gas turbine engine comprises a fan, a compressor, a combustor, and a fan drive turbine rotor. The fan drive turbine drives the fan through a gear reduction. The gear reduction includes at least...
US20110108663 PROPULSION DEVICE WITH A PLURALITY OF ENERGY CONVERTERS FOR AN AIRCRAFT  
The present invention relates to a propulsion device for an aircraft. The propulsion device comprises a first energy converter (4), a second energy converter (5) and a propulsion unit (1). The...
US20100162680 GAS TURBINE ENGINE WITH EJECTOR  
The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet...
US20140096508 SYSTEMS AND METHODS INVOLVING MULTIPLE TORQUE PATHS FOR GAS TURBINE ENGINES  
A turbofan engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a shaft...
US20170138781 METHOD AND SYSTEM FOR IMPROVING PARAMETER MEASUREMENT  
Parameter measurement systems including improved sensor calibration are provided herein. The measurement system includes a first sensor with a first output signal including a plurality of output...
US20130333350 AIRFOIL INCLUDING ADHESIVELY BONDED SHROUD  
An airfoil includes an airfoil body that extends between a leading edge and a trailing edge, a suction side and a pressure side, and a first end and a second end. At least one fitting is located...
US20160363055 OFF-SET GEARED TURBOFAN ENGINE  
A turbofan gas turbine engine includes a first shaft for mounting and rotation of a fan, the first shaft including a single stage internal gear mounted on the first shaft aft of the fan. The...
US20060086078 Universal Carnot propulsion systems for turbo rocketry  
Turbofan jet engines utilizing the Carnot cycle for improved performance with isothermal compression of combustion air and, in part, isothermal expansion of thermally heated air, the engines...
US20070022738 Reinforcement rings for a tip turbine engine fan-turbine rotor assembly  
A fan-turbine rotor assembly includes a diffuser mountable to the outer periphery of a multitude of fan blade sections to provide structural support to the outer tips of the fan blade sections and...
US20150027101 GEARED GAS TURBINE ENGINE ARCHITECTURE FOR ENHANCED EFFICIENCY  
An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so...
US20140157754 GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT  
A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second...
US20140117152 Twin Tip Turbine Propulsors Powered by a Single Gas Turbine Generator  
A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles,...
US20160333729 TURBINE ENGINE HAVING VARIABLE PITCH OUTLET GUIDE VANES  
A gas turbine engine including a core engine and a fan configured in mechanical communication with the core engine is provided. The gas turbine engine also includes a plurality of outlet guide...
US20070028595 High pressure gas turbine engine having reduced emissions  
A gas turbine engine having a longitudinal centerline axis therethrough, including a fan section at a forward end of the gas turbine engine for producing a first compressed air flow; a first...
US20150192070 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE  
A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be...
US20050172610 Turbojet having two counter-rotatable fans secured to a counter-rotatable low-pressure compressor  
The invention relates to a turbojet having two counter-rotatable fans (3, 5) at the front of an intermediate casing (2), said fans being secured to a counter-rotatable low-pressure compressor (7)....
US20130192196 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION  
A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine...
US20060196164 Dual mode turbo engine  
A dual mode gas turbine engine includes a dual mode fan and low pressure compressor section upstream of radially inner and outer gas generators which include radially inner and outer combustors...
US20140165534 GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT  
A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second...
US20120167551 ELECTRIC TURBINE BYPASS FAN AND COMPRESSOR FOR HYBRID PROPULSION  
An electric turbine compressor fan for hybrid propulsion wherein the compressor contains one or more rotor stages (compressor and diffuser), each being driven by one or more electric ring motors,...
US20120192543 EXHAUST NOZZLE FOR A BYPASS AIRPLANE TURBOJET HAVING A DEPLOYABLE SECONDARY COVER AND A RETRACTABLE CENTRAL BODY  
The invention relates to an exhaust nozzle for a bypass airplane turbojet comprising an annular central body, an annular primary cover surrounding the central body to define a hot stream flow...
US20070144141 Pulsed combustion fluidic nozzle  
A propulsion system for producing thrust includes a turbine engine. The engine has a compressor, a combustor downstream of the compressor along a flow path, and a turbine downstream of the...
US20170184053 GAS TURBINE ENGINE VANE SPLITTER  
A gas turbine engine duct turns radially inwardly in the downstream direction. The duct includes a plurality of radially extending stator vanes. A generally circumferentially extending splitter...
US20050223693 Engine cooling  
Cavities 4 are defined within an engine nacelle 1 with an inner surface 2 and an outer surface 3. Within these cavities 4, an evaporatable liquid 5 is arranged such that a proportion of the liquid...
US20120060465 DEVICE FOR SPRAYING A FLUID USING THE AIR BLAST EFFECT  
A device making it possible to better spray the fluid that one wishes to spray by using a portion of the air blast which is intended to diffuse it. The device has a low pressure airflow generator,...
US20120167550 THRUST AUGMENTED GAS TURBINE ENGINE  
One embodiment of the present invention is a unique thrust augmented gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for thrust...
US20120198814 USE OF HOT GASES AND DEVICES  
A method of increasing internal combustion engine efficiency is based on using engine cooling air and exhaust gas by flowing this mixture into a convergent nozzle thus accelerating the gas mixture...
US20110192134 AIR INTAKE STRUCTURE FOR A TURBINE ENGINE NACELLE  
The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer...
US20140083079 GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY  
A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core...
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