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81. 发明申请

US20200025102A1 PLANETARY GEAR, SPLINED SLEEVE, GAS TURBINE ENGINE WITH A PLANETARY GEAR AND METHOD FOR MANUFACTURING A PLANETARY GEAR 审中-公开
公开(公告)号：US20200025102A1
公开(公告)日：2020-01-23
申请号：US16357484
申请日：2019-03-19
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Christos KALLIANTERIS , Jan SCHWARZE
IPC分类号： F02C7/36 , F16H57/02 , F16H57/025 , F16H57/08 , F02K3/02 , F02K3/12 , B64D35/02 , B64D27/10
摘要： A planetary gearbox, a splined sleeve, a gas turbine engine with a planetary gearbox and a method for producing a torque-proof connection between a planetary carrier and a support element. The splined sleeve is formed with an outer substantially cylindrical shell surface area and an inner conical shell surface area, and is inserted between the planetary carrier and the support element for creating the torque-proof connection. The diameter of the inner conical shell surface area decreases in the axial direction, starting from an end of the splined sleeve in the direction of a second end of the splined sleeve. The outer cylindrical shell surface area is formed in a stepped manner. The outer cylindrical shell surface area comprises a first cylindrical section and a second cylindrical section which has a diameter larger than the diameter of the first cylindrical section. Between the sections, a conical area is provided.

82. 发明授权

US10400710B2 Secondary nozzle for jet engine 有权
公开(公告)号：US10400710B2
公开(公告)日：2019-09-03
申请号：US13889003
申请日：2013-05-07
申请人： GENERAL ELECTRIC COMPANY
发明人： David Lynn Dawson , Erin Lee Lariviere , Brian Joseph Petersen , Robert Jerome Ellerhorst
IPC分类号： F02K3/077 , F02K3/12 , F02K3/02 , F02K3/075 , F02K1/12 , F02K1/82
摘要： A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine.

83. 发明申请

US20180209443A1 AIRCRAFT COMPRISING A TURBINE ENGINE INCORPORATED INTO THE REAR FUSELAGE COMPRISING A SYSTEM FOR BLOCKING THE FANS 审中-公开
公开(公告)号：US20180209443A1
公开(公告)日：2018-07-26
申请号：US15745661
申请日：2016-07-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： François Gallet
IPC分类号： F04D29/56 , B64D27/20 , F02K3/072 , F02K3/12 , F04D29/36 , F04D27/00
摘要： An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.

84. 发明申请

US20160363128A1 GAS TURBINE ENGINE AIRFOIL 审中-公开
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20160363128A1
公开(公告)日：2016-12-15
申请号：US15114167
申请日：2015-02-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
IPC分类号： F04D29/38 , F04D29/56 , F02K3/12 , F01D5/14 , F01D9/04 , F02C3/04 , F04D29/32 , F04D29/54
CPC分类号： F04D29/384 , F01D5/141 , F01D9/041 , F02C3/04 , F04D29/324 , F04D29/325 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2240/121 , F05D2240/303 , F05D2240/35 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
摘要翻译：涡轮发动机的翼型包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。翼型件具有前缘角度和跨度位置之间的关系，其限定了具有从80％跨度到100％跨度的递减负斜率或正斜率中的至少一个的曲线。

85. 发明申请

US20150000251A1 System, Method and Apparatus for Lean Combustion with Plasma from an Electrical Arc 有权
标题翻译：用于从电弧等离子体的精细燃烧的系统，方法和装置
公开(公告)号：US20150000251A1
公开(公告)日：2015-01-01
申请号：US14486521
申请日：2014-09-15
申请人： Foret Plasma Labs, LLC
发明人： Todd Foret
IPC分类号： F02K3/12 , F23R3/00 , F23R3/58 , F01D13/00
CPC分类号： F02K3/12 , B64G1/405 , B64G1/406 , F01D13/00 , F02C3/14 , F02C7/266 , F02K9/425 , F23R3/007 , F23R3/58 , F23R2900/00002 , F23R2900/00009 , G21D5/02 , H05H1/24 , H05H1/32 , H05H1/48 , H05H2001/4695 , Y02E50/12 , Y02T50/678
摘要： The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.
摘要翻译：本发明提供了可用于稀薄燃烧的等离子弧焊炬。等离子弧焊炬包括圆柱形容器，连接到圆柱形容器的第一端的电极壳体，使得第一电极（a）与圆柱形容器的纵向轴线对齐，并且（b）延伸到圆柱形容器中，连接到第一电极以调节第一电极的位置的线性致动器，连接到圆柱形容器的第二端的中空电极喷嘴，使得中空电极喷嘴的中心线与圆柱形容器的纵向轴线对准并且其中所述切向入口和所述切向出口在所述圆柱形容器内产生涡流，并且所述第一电极和所述中空电极喷嘴产生通过所述中空电极喷嘴排出的等离子体。

86. 发明授权

US07770381B2 Duct burning mixed flow turbofan and method of operation 有权
标题翻译：管道燃烧混流涡轮风扇和操作方法
公开(公告)号：US07770381B2
公开(公告)日：2010-08-10
申请号：US11612116
申请日：2006-12-18
申请人： James E. Johnson , Ronald B. Steinmetz
发明人： James E. Johnson , Ronald B. Steinmetz
IPC分类号： F02K3/10 , F02K3/12
CPC分类号： F02K1/82 , F02K3/06 , F02K3/077 , F02K3/11 , F02K3/115
摘要： 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 to extract energy from the core and generate a first flow of pressurized air; a bypass duct surrounding the core which receives a portion of the flow of pressurized air from the fan; a duct burner disposed in the bypass duct, upstream of the exit plane, for receiving the first flow of pressurized air and generating a second flow of pressurized combustion gases; and an exhaust duct disposed downstream of the core and operable to receive and the first and second flows of pressurized combustion gases and to discharge the combined flows downstream.
摘要翻译：燃气涡轮发动机包括可操作以产生第一加压燃烧气体流的涡轮机芯，所述芯具有出射平面; 设置在所述芯的上游的风扇，其适于从所述芯提取能量并产生第一压缩空气流; 围绕所述芯的旁路管道，其接收来自所述风扇的一部分加压空气流; 设置在所述旁路管道中的管道燃烧器，在所述出口平面的上游，用于接收所述第一加压空气流并产生第二加压燃烧气体流; 以及设置在所述芯的下游的排气管，并且可操作以接收和加压燃烧气体的第一和第二流，并将下游的组合流排出。

87. 发明申请

US20090056309A1 Gas Turbine Engine Systems and Related Methods Involving Multiple Gas Turbine Cores 有权
标题翻译：燃气轮机发动机系统及相关方法涉及多台燃气轮机内核
公开(公告)号：US20090056309A1
公开(公告)日：2009-03-05
申请号：US11847640
申请日：2007-08-30
申请人： Gary D. Roberge
发明人： Gary D. Roberge
IPC分类号： F02K3/12
CPC分类号： F02C9/00 , F02C3/113 , F02K3/06 , F02K3/12 , F05D2220/76 , F05D2240/40 , F05D2260/74
摘要： Gas turbine engine systems and related methods involving multiple gas turbine cores are provided. In this regard, a representative gas turbine engine includes: an inlet; a blade assembly mounted to receive intake air via the inlet; and multiple gas turbine cores located downstream of the blade assembly, each of the multiple gas turbine cores being independently operative in a first state, in which rotational energy is provided to rotate the blade assembly, and a second state, in which rotational energy is not provided to rotate the blade assembly.
摘要翻译：提供了涉及多个燃气涡轮机磁芯的燃气涡轮发动机系统和相关方法。在这方面，代表性的燃气涡轮发动机包括：入口; 安装成经由所述入口接收进气的叶片组件; 以及位于叶片组件下游的多个燃气涡轮机芯，多个燃气涡轮机芯中的每一个独立地在第一状态下工作，其中提供旋转能量以旋转叶片组件，以及第二状态，其中转动能不是被提供以旋转叶片组件。

88. 发明授权

US06968674B2 Methods and apparatus for operating gas turbine engines 失效
标题翻译：运行燃气轮机的方法和装置
公开(公告)号：US06968674B2
公开(公告)日：2005-11-29
申请号：US10352446
申请日：2003-01-28
申请人： Gary Craig Wollenweber
发明人： Gary Craig Wollenweber
IPC分类号： B64D41/00 , F02C6/06 , F02C6/08 , F02K3/02 , F02K3/06 , F02K3/12 , F02C6/00 , F02K3/04
CPC分类号： F02K3/12 , F02C6/06 , F02K3/06 , F05D2220/50
摘要： A method facilitates operating a gas turbine engine assembly including a propelling engine and an auxiliary power engine. The method comprises channeling a portion of airflow entering an inlet to the propelling gas turbine engine through a fan assembly and a bypass duct such that the air bypasses the core engine, and channeling a portion of airflow from the bypass duct towards the auxiliary power engine.
摘要翻译：一种方法便于操作包括推进发动机和辅助动力发动机的燃气涡轮发动机组件。该方法包括通过风扇组件和旁路管道将进入入口的一部分气流引导到推进燃气涡轮发动机，使得空气绕过核心发动机，并将一部分气流从旁路管道引向辅助动力发动机。

89. 发明授权

US5269134A Variable cycle propulsion unit for aircraft 失效
标题翻译：飞机可变循环推进装置
公开(公告)号：US5269134A
公开(公告)日：1993-12-14
申请号：US51168
申请日：1993-04-22
申请人： Claude C. F. Menioux
发明人： Claude C. F. Menioux
IPC分类号： F02K3/075 , F02K3/12 , F02K3/00
CPC分类号： F02K3/12 , F02K3/075 , Y02T50/671
摘要： A variable cycle propulsion unit comprises at least two turbojet engines of the bypass type in which the low pressure compressor of each engine is in two parts connected by a shaft, and the flow of compressed air issuing from the first part of the low pressure compressor of a first of the engines is supplied to the second part of the low pressure compressor of a second of the engines and the flow of compressed air issuing from the first part of the low pressure compressor of the second engine is supplied to the second part of the low pressure compressor of the first engine. At full throttle operation the combustion chambers of the two engines are both ignited, and at operation at reduced engine speeds the combustion chamber of one of the engines is extinguished and the engine windmills while the other engine continues to run normally.
摘要翻译：可变循环推进单元包括至少两个旁通型涡轮喷气发动机，其中每个发动机的低压压缩机在两个部分中通过轴连接，并且从低压压缩机的第一部分排出的压缩空气流第一发动机被供应到第二发动机的低压压缩机的第二部分，并且从第二发动机的低压压缩机的第一部分排出的压缩空气流被供给到第二发动机的第二部分第一台发动机的低压压缩机。在全油门操作时，两个发动机的燃烧室都被点燃，并且在发动机速度降低的情况下，一个发动机的燃烧室熄灭，并且发动机风车，而另一个发动机继续正常运行。

90. 发明授权

US4679394A Gas turbine engine power plant 失效
标题翻译：燃气轮机发电厂
公开(公告)号：US4679394A
公开(公告)日：1987-07-14
申请号：US33093
申请日：1979-04-24
申请人： Maurice I. Taylor
发明人： Maurice I. Taylor
IPC分类号： B64C29/00 , B64D33/02 , F02K1/00 , F02K1/12 , F02K1/62 , F02K3/12
CPC分类号： B64D33/02 , B64C29/0066 , F02K1/006 , F02K1/1207 , F02K1/62 , B64D2033/026
摘要： A nozzle structure for a gas turbine power plant for a V.T.O.L. or S.T.O.L. type aircraft includes a main engine and at least one auxiliary engine; the efflux from the at least one auxiliary engine may be directed downwardly or alternatively horizontally through a convergent/divergent nozzle which may be closed off when the at least one auxiliary engine is inoperative.
摘要翻译：一种用于V.T.O.L.的燃气轮机发电厂的喷嘴结构或S.T.O.L. 型飞机包括主机和至少一个辅助发动机; 来自至少一个辅助发动机的流出可以通过会聚/发散的喷嘴向下或者水平地指向，当所述至少一个辅助发动机不起作用时可以将其关闭。

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