Matches 1 - 50 out of 134 1 2 3 >


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US20150252732 GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION AND INTERCOOLING TURBINE SECTION BYPASS  
A gas turbine engine includes an intercooling turbine section to selectively cool the core flow. An intercooling turbine section bypass is also included to selectively bypass at least a portion of...
US20110167790 TRANSLATABLE CASCADE THRUST REVERSER  
A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable...
US20120124965 VARIABLE AREA FAN NOZZLE FAN FLUTTER MANAGEMENT SYSTEM  
A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.
US20130145745 GAS TURBINE ENGINE WITH FAN VARIABLE AREA NOZZLE FOR LOW FAN PRESSURE RATIO  
A gas turbine engine includes a fan section with twenty (20) or less fan blades and a fan pressure ratio less than about 1.45.
US20140260180 Gas Turbine Engine with Stream Diverter  
In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and...
US20110120083 GAS TURBINE ENGINE WITH OUTER FANS  
A gas turbine engine comprising an outer fan system is disclosed, having an outer fan first stage having a circumferential row of outer fan first blades, an outer fan second stage having a...
US20120222398 GAS TURBINE ENGINE WITH GEARED ARCHITECTURE  
A turbofan engine includes a geared architecture and a fan variable area nozzle axially movable relative to a fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan...
US20140041360 FLOW CONDUCTING ASSEMBLY FOR COOLING THE LOW-PRESSURE TURBINE HOUSING OF A GAS TURBINE JET ENGINE  
A gas turbine jet engine having a main flow channel (20) and a housing structure (22) which radially surrounds this main flow channel, in which a housing gas flow flows in the same direction as...
US20130104522 GAS TURBINE ENGINE WITH VARIABLE PITCH FIRST STAGE FAN SECTION  
A gas turbine engine with a two-spool fan and a method of operating the gas turbine engine includes modulating a pitch of a variable pitch first stage fan section of a low pressure spool, the...
US20150158597 EMERGENCY POWER GENERATION VIA LIMITED VARIABLE PITCH FAN BLADE  
A method of generating emergency power includes identifying a power-loss condition. In the power-loss condition, a desired quantity of power is determined Emergency power is generated from a...
US20120067025 BLOOM MIXER FOR A TURBOFAN ENGINE  
An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow...
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...
US20140060005 MAGNETIC ADVANCED GENERATION JET ELECTRIC TURBINE  
Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and...
US20120011827 BLEED AIR OUTLET IN THE BYPASS DUCT OF A TURBOFAN ENGINE  
A bleed air outlet provided in the bypass duct of a turbofan engine includes a bleed air tube protruding into the bypass duct and a cover having a plurality of air outlet openings provided in the...
US20130174534 SYSTEM AND DEVICE FOR CONTROLLING FLUID FLOW THROUGH A GAS TURBINE EXHAUST  
A system and device for controlling fluid flow through a gas turbine exhaust. One gas turbine exhaust may include a strut of the gas turbine exhaust having a first opening configured to permit a...
US20120159925 TURBINE BASED COMBINED CYCLE ENGINE  
An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression...
US20130008147 Aircraft gas turbine with variable bypass nozzle  
The present invention relates to an aircraft gas turbine with a core engine 10 which is surrounded by a bypass duct 29 enclosed radially outwards by a bypass wall 30, with a radially inner wall 31...
US20120279198 GAS TURBINE ENGINE WITH BYPASS MIXER  
One embodiment of the present invention is a gas turbine engine with a bypass mixer. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine...
US20120233981 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO  
A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine...
US20120222397 GAS TURBINE ENGINE WITH LOW FAN PRESSURE RATIO  
A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine...
US20140130479 Gas Turbine Engine With Mount for 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...
US20090139202 Convertible gas turbine propulsion system  
A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary...
US20120011825 GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE  
A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.
US20130199153 METHOD AND APPARATUS TO CONTROL PART-LOAD PERFORMANCE OF A TURBINE  
A method of controlling the part-load performance of a turbine includes generating a bypass flow in the turbine by removing a portion of a compressed fluid from a compressor of the turbine,...
US20120109593 GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE  
A bypass gas turbine engine includes a variable area fan nozzle with a second fan nacelle section axially movable relative to a first fan nacelle section to define an auxiliary port to vary a fan...
US20080141655 DUCT BURNING MIXED FLOW TURBOFAN AND METHOD OF OPERATION  
A gas turbine engine includes a turbomachinery core operable to generating a first flow of pressurized combustion gases, the core having an exit plane; a fan disposed upstream of the core adapted...
US20120023901 Variable area fan nozzle for gas turbine engine  
A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
US20130008146 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES  
A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the...
US20110120082 MULTISTAGE TIP FAN  
A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.
US20090288387 GAS TURBINE ENGINE BIFURCATION LOCATED IN A FAN VARIABLE AREA NOZZLE  
A turbofan engine pylon structure having a fan variable area nozzle defined by a variable area flow system between a pylon intake and a pylon exhaust to selectively adjust a bypass flow. The...
US20110167791 CONVERTIBLE FAN ENGINE  
A gas turbine engine is disclosed having a fan system with a front stage fan rotor and an aft fan rotor coupled to a low-pressure turbine, a core having a compressor coupled to a high-pressure...
US20110120080 VARIABLE AREA FAN NOZZLE COWL AIRFOIL  
A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section...
US20110302907 VARIABLE AREA FAN NOZZLE  
A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle in communication with a fan bypass flow path. An actuator assembly is operable to move a second fan...
US20130014490 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
US20120198815 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.
US20120073263 GAS TURBINE ENGINE WITH AXIAL MOVABLE FAN VARIABLE AREA NOZZLE  
A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and...
US20130014489 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
US20120198817 GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.
US20080163606 Variable area nozzle with woven sleeve extension  
A variable area fan nozzle for use with a gas turbine engine system includes a nozzle section that is attachable to a gas turbine engine for influencing flow through the fan bypass passage of the...
US20090090096 Epicyclic gear train for variable cycle engine  
A two-stage turbofan system for use in a gas turbine engine comprises a first-stage fan shaft, a second-stage fan shaft, a stationary torque tube and a gear system. The second-stage fan shaft...
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...
US20150107223 HIGH DURABILITY TURBINE EXHAUST CASE  
A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least...
US20100043394 GAS TURBINE ENGINE FAN VARIABLE AREA NOZZLE WITH SWIVALABLE INSERT SYSTEM  
A turbofan engine (10) includes a fan variable area nozzle (FVAN) (50) which effectively changes the physical area and geometry within a fan bypass flow path (40) to manipulate the pressure ratio...
US20070130913 Coaxial propulsion systems with flow modification element  
A coaxial propulsion system has a primary propeller, a flow control element to reduce swirl, and a secondary propeller, mounted in series configuration. A connecting shroud directs the combined...
US20120124964 GAS TURBINE ENGINE WITH IMPROVED FUEL EFFICIENCY  
A turbofan engine includes a fan driven by a low pressure turbine through a gear reduction. The gear reduction has a gear ratio of greater than or equal to about 2.4. The low pressure turbine has...
US20120073262 AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE  
An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising...
US20130160425 VARIABLE AREA FAN NOZZLE WITH DRIVE SYSTEM HEALTH MONITORING  
A nacelle for a turbofan engine includes a variable area fan nozzle (VAFN) and a proximity sensor that is attached to a nacelle forward portion to sense the presence of the VAFN when stowed. The...
US20090056307 ACTUATING DEVICE, BYPASS AIR BLEED SYSTEM EQUIPPED THEREWITH, AND TURBOJET ENGINE COMPRISING THESE  
The actuating device for opening and closing at least one shutter in a gas turbine engine such as a turbojet engine, comprises at least one actuator made of a two-way shape memory alloy having a...
US20100064659 TRANSLATING VARIABLE AREA FAN NOZZLE WITH SPLIT BEAVERTAIL FAIRINGS  
A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each...
US20140366554 CROSS REFERENCE TO RELATED APPLICATIONS  
A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at...

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