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US20130098055 GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION AND INTERCOOLING TURBINE SECTION BYPASS  
A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least...
US20140338352 ELECTRICAL GENERATION ARRANGEMENT FOR AN AIRCRAFT  
This invention relates to a multi-spool gas turbine engine, including: a first generator for providing electrical power to an electrical system, the generator being driveably connected to a first...
US20140090388 OFF-TAKE POWER RATIO  
An example method of allocating power within a gas turbine engine includes driving an off-take power delivery assembly using a first amount of power from a spool, the first amount of power...
US20110056213 SPOOL SUPPORT STRUCTURE FOR A MULTI-SPOOL GAS TURBINE ENGINE  
A gas turbine engine is provided that includes a low pressure spool, a high pressure spool, a stationary support frame, and at least one support arch. The low pressure spool extends between a low...
US20100301617 GAS TURBINE ENGINE  
A gas turbine engine includes in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a...
US20150176497 GEARED TURBOFAN WITH A GEARBOX UPSTREAM OF A FAN DRIVE TURBINE  
A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive...
US20150143794 Geared Turbofan Engine Gearbox Arrangement  
A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of...
US20130318999 GAS TURBINE ENGINE WITH A COUNTER ROTATING FAN  
An exemplary gas turbine engine includes a fan, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the...
US20120167591 TURBOSHAFT ENGINE WITH PARALLEL SHAFTS  
A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor,...
US20120017601 GAS TURBINE WITH IMPROVED PART LOAD EMISSIONS BEHAVIOR  
In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (λ) of the operative burners (9) of the second combustor (15) is kept below a...
US20150096303 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...
US20130047623 ACCESSORY GEARBOX BUFFER COOLING AIR PUMP SYSTEM  
A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in...
US20090015011 DEVICE FOR PRODUCING ELECTRICAL POWER IN A TWO-SPOOL GAS TURBINE ENGINE  
The invention relates to a device for producing electrical power in a multi-spool gas turbine engine comprising at least one first rotary spool (69), for example a low-pressure spool, and a second...
US20090211260 Multi-Spool Intercooled Recuperated Gas Turbine  
A method and apparatus are disclosed for a gas turbine power plant with a variable area turbine nozzle and an integrated motor/alternator device for starting the gas turbine and power extraction...
US20130305738 SYSTEM AND METHOD FOR PRODUCING HYDROGEN RICH FUEL  
A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a fuel from a fuel supply and portion of compressed working fluid from the...
US20120000204 MULTI-SPOOL INTERCOOLED RECUPERATED GAS TURBINE  
A method and apparatus are disclosed for a multi-spool gas turbine power plant which utilizes motor/generator devices on two or more spools for starting the gas turbine and for power extraction...
US20150121893 ADAPTIVE FAN REVERSE CORE GEARED TURBOFAN ENGINE WITH SEPARATE COLD TURBINE  
A turbine engine includes a first fan including a plurality of fan blades rotatable about an axis and a reverse flow core engine section including a core turbine axially forward of a combustor and...
US20090007569 HIGH TO LOW PRESSURE SPOOL SUMMING GEARBOX FOR ACCESSORY POWER EXTRACTION AND ELECTRIC START  
A turbine engine includes low and high pressure spools. A high power take-off shaft is coupled to the high spool. An auxiliary component, such as a generator, is configured to be driven by the...
US20150000304 REMOVABLE NOSECONE FOR A GAS TURBINE ENGINE  
A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The...
US20090211222 Rear propulsor for a variable cycle gas turbine engine  
A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air...
US20130000314 VARIABLE CYCLE TURBINE ENGINE  
A gas turbine engine comprises a high spool, a low spool and an intermediate spool. The high spool comprises a high pressure turbine coupled to a high pressure compressor. The intermediate spool...
US20110056208 REVERSED-FLOW CORE FOR A TURBOFAN WITH A FAN DRIVE GEAR SYSTEM  
A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow...
US20150192298 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...
US20070277532 Two-shaft engine for aircraft with high electric power demand  
With an engine for aircraft with high electric power demand, the power of the low-pressure shaft (7) operating in a lower speed range is transmitted to the high-pressure shaft (6) by an...
US20090288421 TURBINE DRIVE SYSTEM WITH LOCK-UP CLUTCH AND METHOD  
A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one...
US20140182299 SYSTEM AND METHOD FOR REHEAT IN GAS TURBINE WITH EXHAUST GAS RECIRCULATION  
A system includes a turbine having an exhaust flow path through a plurality of turbine stages, wherein the plurality of turbine stages is driven by combustion products flowing through the exhaust...
US20130239584 CONSTANT-SPEED PUMP SYSTEM FOR ENGINE THERMAL MANAGEMENT SYSTEM AOC REDUCTION AND ENVIRONMENTAL CONTROL SYSTEM LOSS ELIMINATION  
A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump...
US20110167831 ADAPTIVE CORE ENGINE  
A gas turbine engine having an adaptive core capable of maintaining a substantially constant core pressure ratio while having a variable flow rate is disclosed. In one aspect, the adaptive core...
US20060201160 Multi-shaft arrangement for a turbine engine  
Elimination of a previous intermediate inter-shaft locating bearing allows smaller core sizes to be achieved and avoids relatively sophisticated design complications in order to provide that...
US20080022691 Method for Designing a Low-Pressure Turbine of an Aircraft Engine, and Low-Pressure Turbine  
A low-pressure turbine of a gas turbine is disclosed. The turbine comprises a number of stages arranged one behind the other in an axial manner in the flow-through direction of the turbine. Each...
US20140102076 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...
US20130025286 GAS TURBINE ENGINE WITH AFT CORE DRIVEN FAN SECTION  
A gas turbine engine includes a low spool along an engine axis with a forward fan section and a low pressure turbine section. A high spool along the engine axis with a high pressure turbine...
US20090064683 POWER TAKE-OFF SYSTEM AND GAS TURBINE ENGINE ASSEMBLY INCLUDING SAME  
A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured...
US20100005810 POWER TRANSMISSION AMONG SHAFTS IN A TURBINE ENGINE  
A method of transmitting power among a plurality of shafts in a turbine engine is disclosed herein as well as a turbine engine for practicing the method. The turbine engine includes a compressor...
US20130255275 GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE  
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure...
US20150114002 GEARED TURBOFAN ENGINE WITH A HIGH RATIO OF THRUST TO TURBINE VOLUME  
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure...
US20130255274 GEARED ARCHITECTURE WITH SPEED CHANGE DEVICE FOR GAS TURBINE ENGINE  
A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and...
US20150113943 GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE  
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure...
US20090211221 Auxiliary propulsor for a variable cycle gas turbine engine  
A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the...
US20090145136 TIP TURBINE ENGINE WITH MULTIPLE FAN AND TURBINE STAGES  
A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery...
US20120192570 PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM  
A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine...
US20130318998 GEARED TURBOFAN WITH THREE TURBINES WITH HIGH SPEED FAN DRIVE TURBINE  
A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine...
US20150218965 VARIABLE POSITIONER  
A variable positioner includes a body portion with a cylindrical component, and an axially aligned through hole in the body position. A threading protrudes radially inward from an inner surface of...
US20090205341 GAS TURBINE ENGINE WITH TWIN TOWERSHAFT ACCESSORY GEARBOX  
A gas turbine engine includes a high towershaft driven by a high pressure spool and a low towershaft driven by a low pressure spool.
US20100154435 TURBINE ENGINE HAVING TWO OFF-AXIS SPOOLS WITH VALVING-ENABLED MODULATION BETWEEN HIGH AND LOW POWER MODES  
A turbine engine particularly suited for VTOL aircraft is disclosed. According to various embodiments, the core of the turbine engine includes two spools—a low pressure (LP) spool and a high...
US20120233982 GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.
US20120198816 GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT  
A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.
US20120279231 REGENERATIVE BRAKING FOR GAS TURBINE SYSTEMS  
The present invention is directed to an energy storage system comprised of a heat block having a relatively high specific energy capacity. The heat block can be used, for example, with a...
US20130219908 GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY  
A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor...
US20130219907 GEARED TURBOFAN ARCHITECTURE FOR IMPROVED THRUST DENSITY  
A turbine engine includes a fan, a compressor section having a low pressure compressor section and a high pressure compressor section, a combustor in fluid communication with the compressor...

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