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11. 发明公开

EP2971723A1 GAS TURBINE ENGINE WITH THREE STREAM, VARIABLE AREA, VECTORABLE NOZZLE 有权
标题翻译：具有可变面积的燃气涡轮发动机DREISTROMSCHWENKDÜSE
公开(公告)号：EP2971723A1
公开(公告)日：2016-01-20
申请号：EP14718853.6
申请日：2014-03-13
申请人： Rolls-Royce North American Technologies, Inc.
发明人： PESYNA, Kenneth, M. , PIERLUISSI, Anthony, F. , LERG, Bryan, H. , MOORE, Justin, N.
IPC分类号： F02K1/12 , F02K1/82 , F02K3/075 , F02K3/077
CPC分类号： F02K1/1223 , F02K1/1207 , F02K1/1238 , F02K1/15 , F02K1/80 , F02K3/075 , F02K3/077 , F02K3/115 , F05D2250/411 , F05D2260/50 , F05D2260/56 , F05D2270/051 , F05D2270/66 , Y02T50/671
摘要： An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.

12. 发明公开

EP2924247A1 HYBRID DRIVE FOR GAS TURBINE ENGINE 有权转让
标题翻译： HYBRIDANTRIEBFÜRGASTURBINENMOTOR
公开(公告)号：EP2924247A1
公开(公告)日：2015-09-30
申请号：EP15160776.9
申请日：2015-03-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SHERIDAN, William G.
IPC分类号： F01D25/36 , F02C7/32 , F02C7/36
CPC分类号： F02C7/36 , B64D35/04 , B64D35/08 , B64D2027/026 , F02C3/113 , F02K3/04 , F02K3/077 , F05D2260/532
摘要： A gas turbine engine (20) has a fan drive turbine (28) for selectively driving a fan rotor (45). A drive shaft (30) between the fan drive turbine (28) and the fan rotor (45) includes a clutch (36), and an electric motor (38). The electric motor (38) is positioned such that it is not downstream of a flow path relative to the fan drive turbine (28).
摘要翻译：燃气涡轮发动机（20）具有用于选择性地驱动风扇转子（45）的风扇驱动涡轮机（28）。风扇驱动涡轮（28）和风扇转子（45）之间的驱动轴（30）包括离合器（36）和电动马达（38）。电动机38被定位为使得其不相对于风扇驱动涡轮机28的流动路径的下游。

13. 发明公开

EP2553251A4 ADAPTIVE FAN SYSTEM FOR A VARIABLE CYCLE TURBOFAN ENGINE 有权
标题翻译：自适应系统使用风扇TURBOFANLÜFTER可变冲程
公开(公告)号：EP2553251A4
公开(公告)日：2014-10-01
申请号：EP11798531
申请日：2011-03-27
申请人： ROLLS ROYCE NAM TECH INC
发明人： RESS ROBERT A JR , STRATTON STEVE , STARR MATTHEW J
IPC分类号： F02K3/077 , B64C11/48 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/075 , F16D47/04
CPC分类号： F02K3/075 , F02C3/113 , F02C7/32 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2260/40 , F05D2260/4023 , F05D2260/40311 , F16D21/06 , F16D47/04 , Y02T50/671
摘要： An adaptive fan system for a variable cycle turbofan engine having at least one turbine, includes a shaft structured to receive mechanical power from a turbine in the variable cycle turbofan engine and a first fan stage that is coupled directly to the shaft and is driven directly by the shaft. A transmission system is coupled to the shaft and a second fan stage is coupled to the shaft via the transmission system and is driven by the shaft via the transmission system. The transmission system is structured to selectively vary a speed between high and low speeds at which power is supplied from the shaft to the second fan stage relative to at least one of the shaft and the first fan stage, wherein the first fan stage and the second fan stage are configured to rotate in the same direction and at the same high speed to increase the mechanical power of the turbine.

14. 发明公开

EP2519723A2 GAS TURBINE ENGINE AND HEAT EXCHANGE SYSTEM 有权
标题翻译：燃气涡轮发动机
公开(公告)号：EP2519723A2
公开(公告)日：2012-11-07
申请号：EP10851168.4
申请日：2010-12-30
申请人： Rolls-Royce North American Technologies, Inc.
发明人： SNYDER, Douglas J.
IPC分类号： F02C6/08
CPC分类号： F02C7/14 , F01D25/12 , F02C7/12 , F02C7/18 , F02K3/06 , F02K3/077 , F02K3/115 , F05D2260/20 , Y02T50/676
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique gas turbine engine heat exchange system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and heat exchange systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

15. 发明公开

EP2157305A3 Gas turbine engine with variable area fan nozzle 有权转让
标题翻译：具有可变风扇喷嘴的燃气涡轮发动机
公开(公告)号：EP2157305A3
公开(公告)日：2012-10-24
申请号：EP09251654.1
申请日：2009-06-26
申请人： United Technologies Corporation
发明人： Zamora, Sean P. , Murphy, Michael Joseph
IPC分类号： F02K1/42 , F02K1/46 , F02K1/82 , F02K3/075 , F02K3/077
CPC分类号： F02K3/077 , F02K1/42 , F02K1/46 , F02K1/825 , F02K3/075
摘要： A nozzle section of a gas turbine engine includes a regulator system (50) in fluid communication with a secondary flow duct (40) and a tertiary flow duct (60) to selectively regulate communication of secondary airflow (B) into the tertiary flow duct (60).

16. 发明公开

EP1992807A3 Variable geometry nacelle for an aircraft engine and corresponding operating method 有权转让
标题翻译：缆车与用于飞机发动机的可变几何形状和操作方法对应
公开(公告)号：EP1992807A3
公开(公告)日：2011-12-14
申请号：EP08251734.3
申请日：2008-05-16
申请人： United Technologies Corporation
发明人： Jain, Ashok K.
IPC分类号： F02C7/042 , F02K3/06 , F02K1/42 , F02K3/077
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F02K1/42 , F02K3/06 , F02K3/077 , Y10T137/0536
摘要： A nacelle assembly (26) includes an inlet lip section (38) and a cowl section (50) positioned downstream of the inlet lip section (38). At least a portion (52) of the cowl section (50) is moveable to influence an effective boundary layer thickness of the nacelle assembly (26).

17. 发明公开

EP2344739A1 HYBRID PROPULSIVE ENGINE INCLUDING AT LEAST ONE INDEPENDENTLY ROTATABLE COMPRESSOR ROTOR 失效转让
标题翻译：与至少一个可独立旋转的压气机转子混合动力驱动电机
公开(公告)号：EP2344739A1
公开(公告)日：2011-07-20
申请号：EP09819581.1
申请日：2009-10-08
申请人： Searete LLC
发明人： FOSTER, Glenn, B. , HYDE, Roderick, A. , ISHIKAWA, Muriel, Y. , JUNG, Edward, K.Y. , KARE, Jordin, T. , MYHRVOLD, Nathan, P. , TEGREENE, Clarence, T. , WEAVER, Thomas, Allan , WOOD, Lowell, L., Jr. , WOOD, Victoria, Y.H.
IPC分类号： F02D29/06
CPC分类号： F02C6/206 , B64D27/16 , B64D27/24 , B64D31/04 , B64D31/06 , B64D33/00 , B64D2027/026 , F01D5/03 , F01D15/10 , F01K23/10 , F02C6/00 , F02C6/08 , F02C6/14 , F02C6/18 , F02C7/36 , F02K3/00 , F02K3/025 , F02K3/077 , F05D2220/324 , F05D2220/325 , F05D2220/326 , F05D2220/327 , F05D2220/76 , F05D2260/408 , F05D2260/85 , Y02T50/44 , Y02T50/64 , Y02T50/672 , Y02T50/673
摘要： A hybrid propulsive technique includes providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust.

18. 发明公开

EP2204567A2 Gas turbine engine with ejector and corresponding operating method 有权转让
标题翻译： Vorrichtung und Verfahren zur Steuerung der Grenzschicht in einem Gasturbinentriebwerk
公开(公告)号：EP2204567A2
公开(公告)日：2010-07-07
申请号：EP09015894.0
申请日：2009-12-22
申请人： Rolls-Royce Corporation
发明人： Syed Jalaluddin, Khalid
IPC分类号： F02K1/36 , F02K3/077 , B64C21/06 , F04D29/64
CPC分类号： B64C7/02 , B64D2033/0226 , F01D9/065 , F02K1/36 , F02K3/025 , F02K3/075 , F02K3/077 , F04D29/684 , F05D2260/601 , F05D2270/17
摘要： 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 noise and decrease thrust specific fuel consumption. In one embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with an exhaust flow of a gas turbine engine. In another embodiment a boundary layer withdrawn through the boundary layer bleed slots is entrained with a flow stream internal to the gas turbine engine, such as a fan stream of a turbofan. Members can be provided near an outlet of a passageway conveying the withdrawn boundary layer air to locally reduce the pressure of the fluid in which the withdrawn boundary layer air is to be entrained. A lobed mixer can be used in some embodiments to effect mixing between the boundary layer and a primary fluid of the ejector.
摘要翻译：本发明包括边界层喷射器从飞行器的外表面流体连接边界层排放槽以减少飞机/机舱/塔架阻力，减少喷气噪声并减小推力特定燃料消耗。在一个实施例中，通过边界层排出槽排出的边界层与燃气涡轮发动机的排气流一起被夹带。在另一个实施例中，通过边界层排放槽排出的边界层与气体涡轮发动机内部的流动流（例如涡轮风扇的风扇流）一起被夹带。构件可以设置在通道的出口附近，该通道输送被排出的边界层空气，以局部地减小被抽出的边界层空气被夹带的流体的压力。在一些实施例中，可以使用裂片混合器来实现边界层和喷射器的初级流体之间的混合。

19. 发明公开

EP2157305A2 Gas turbine engine with variable area fan nozzle 有权转让
标题翻译： Gasturbinentriebwerk mit variablerBläser-Düse
公开(公告)号：EP2157305A2
公开(公告)日：2010-02-24
申请号：EP09251654.1
申请日：2009-06-26
申请人： United Technologies Corporation
发明人： Zamora, Sean P. , Murphy, Michael Joseph
IPC分类号： F02K3/06 , F02K1/30
CPC分类号： F02K3/077 , F02K1/42 , F02K1/46 , F02K1/825 , F02K3/075
摘要： A nozzle section of a gas turbine engine includes a regulator system (50) in fluid communication with a secondary flow duct (40) and a tertiary flow duct (60) to selectively regulate communication of secondary airflow (B) into the tertiary flow duct (60).
摘要翻译：燃气涡轮发动机的喷嘴部分包括与二次流动管道（40）和三级流动管道（60）流体连通的调节器系统（50），用于选择性地调节二次气流（B）到三级流动管道（ 60）。

20. 发明公开

EP1995443A2 Method and apparatus for regulating fluid flow through a turbine engine 有权
标题翻译： Verfahren und Ventilvorrichtung zur Regelung einerFluidströmungdurch ein Turbinentriebwerk
公开(公告)号：EP1995443A2
公开(公告)日：2008-11-26
申请号：EP08153213.7
申请日：2008-03-25
申请人： GENERAL ELECTRIC COMPANY
发明人： Corsmeier, Donald Michael , Perveiler, David Andrew , Johnson, George Joseph
IPC分类号： F02K3/075
CPC分类号： F02K3/075 , F02K3/077
摘要： A method for regulating fluid flow through a gas turbine engine (10) is provided. The method includes coupling an outer fairing to a radially outer duct wall and coupling an inner fairing to a radially inner duct wall. An annular valve (102) is coupled between the radially outer and the radially inner duct walls such that an outer bypass flow area is at least partially defined between the annular valve and the outer fairing, and such that an inner bypass flow area is at least partially defined between the annular valve and the inner fairing. The annular valve is selectively positioned between a first operational position and a second operational position, such that at least one of the outer bypass and the inner bypass flow areas is varied during a transition from a first turbine operation to a second turbine operation.
摘要翻译：提供了一种用于调节通过燃气涡轮发动机（10）的流体流量的方法。该方法包括将外部整流罩连接到径向外部管道壁并将内部整流罩联接到径向内部管道壁。环形阀（102）联接在径向外部和径向内部管道壁之间，使得外部旁路流动区域至少部分地限定在环形阀和外部整流罩之间，并且使得内部旁路流动区域至少为部分地限定在环形阀和内部整流罩之间。环形阀被选择性地定位在第一操作位置和第二操作位置之间，使得在从第一涡轮机操作到第二涡轮机操作的转变期间，外部旁路和内部旁路流动区域中的至少一个是变化的。

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