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71. 发明授权

US09890704B2 Compressor system 有权
公开(公告)号：US09890704B2
公开(公告)日：2018-02-13
申请号：US14785628
申请日：2014-04-01
申请人： DERWENT AVIATION CONSULTING LTD. , Trevor H. Speak , Robert J. Sellick
发明人： Trevor H. Speak , Robert J. Sellick
IPC分类号： F01D15/12 , F02C3/107 , F02K3/06 , F02C3/067 , F02C7/36 , F02C3/34
CPC分类号： F02C3/107 , F01D15/12 , F02C3/067 , F02C3/34 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2220/62 , F05D2260/40311 , Y02T50/671
摘要： In a gas turbine engine, the booster compressor is driven by both the low pressure or fan shaft and high pressure shaft through a differential gear arrangement. The rotational speed of the booster compressor is intermediate between the speed of the fan and the speed of the high pressure compressor.

72. 发明授权

US09835093B2 Contra-rotating open fan propulsion system 有权
公开(公告)号：US09835093B2
公开(公告)日：2017-12-05
申请号：US14032163
申请日：2013-09-19
申请人： The Boeing Company
发明人： Sina S. Golshany , David Miles Huntly , Adriana W. Blom , Todd W. Erickson , Paul R. Tretow
IPC分类号： F02C7/36 , F02C6/20 , B64C27/12 , B64D35/04 , F02C3/36 , B64D35/06 , B64C27/10 , B64C11/46 , F02C3/067
CPC分类号： F02C7/36 , B64C11/46 , B64C27/10 , B64C27/12 , B64D35/04 , B64D35/06 , F02C3/067 , F02C3/36 , F02C6/206 , F05D2220/325
摘要： In one aspect a propulsion system comprises an engine and a drive assembly coupled to the engine, comprising a first driveshaft rotatable in a first direction about a first axis, a first fan coupled to the first driveshaft to rotate in the first direction, and a clutch assembly to selectively disengage the first fan from the first driveshaft. Other aspects may be described.

73. 发明授权

US09650962B2 Rotor noise suppression 有权
公开(公告)号：US09650962B2
公开(公告)日：2017-05-16
申请号：US14143343
申请日：2013-12-30
申请人： Rolls-Royce Corporation
发明人： Michael Abraham Karam
IPC分类号： F02B27/04 , F02C7/24 , B64C11/48 , F01D5/14 , F02K3/02 , F02C3/067 , F02C6/20 , B64D27/00
CPC分类号： F02C7/24 , B64C11/48 , B64C2230/04 , B64C2230/14 , B64C2230/16 , B64C2230/28 , B64D2027/005 , F01D5/142 , F02C3/067 , F02C6/206 , F02K3/025 , F05D2220/324 , F05D2220/325 , F05D2260/60 , F05D2260/96 , Y02T50/166 , Y02T50/66 , Y02T50/673
摘要： An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture.

74. 发明申请

US20160160867A1 ELECTRICALLY COUPLED COUNTER-ROTATION FOR GAS TURBINE COMPRESSORS 审中-公开
标题翻译：用于气体涡轮压缩机的电气联接计数器
公开(公告)号：US20160160867A1
公开(公告)日：2016-06-09
申请号：US14849941
申请日：2015-09-10
申请人： Embry-Riddle Aeronautical University, Inc.
发明人： Vinod Gehlot
IPC分类号： F04D27/00 , F04D25/06 , F04D29/32 , F02C3/067 , F01D15/10
CPC分类号： F04D27/004 , F01D15/10 , F02C3/067 , F02C7/36 , F04D25/06 , F04D27/02 , F04D29/325 , F05D2220/32 , F05D2220/76 , F05D2240/24 , F05D2240/35 , F05D2240/60 , Y02T50/671
摘要： A system and method for implementing stage-by-stage counter rotation in a multi-stage axial compressor of a gas turbine engine. The system includes an electrical power generator and an electric motor. A turbine-driven shaft connected to an armature of the electrical generator drives a first plurality of compressor blades. The electrical generator armature induces changing magnetic flux in the stator coils of the electrical generator which generates electrical power that is sent to a power control module. The power control module controls the electrical motor and excites the coils in the electric motor stator which drives the electric motor armature. The electric motor armature drives a second shaft which drives a second plurality of compressor blades in an opposite direction to the first plurality of compressor blades.
摘要翻译：一种用于在燃气涡轮发动机的多级轴向压缩机中实现逐级反向旋转的系统和方法。该系统包括发电机和电动机。连接到发电机的电枢的涡轮机驱动的轴驱动第一多个压缩机叶片。发电机电枢引起发电机定子线圈中的变化的磁通量，其产生发送到功率控制模块的电力。功率控制模块控制电动机并激励驱动电动机电枢的电动机定子中的线圈。电动机电枢驱动第二轴，该第二轴沿着与第一多个压缩机叶片相反的方向驱动第二多个压缩机叶片。

75. 发明授权

US09353754B2 Multi-stage axial compressor with counter-rotation using accessory drive 有权
标题翻译：多级轴流式压缩机采用配套驱动方式进行反向旋转
公开(公告)号：US09353754B2
公开(公告)日：2016-05-31
申请号：US13800836
申请日：2013-03-13
申请人： Embry-Riddle Aeronautical University, Inc.
发明人： Vinod Gehlot , Magdy S. Attia
IPC分类号： F04D19/02 , F02C3/067 , F01D1/24 , F04D29/059
CPC分类号： F04D19/02 , F01D1/24 , F02C3/067 , F04D19/024 , F04D29/059 , F05D2250/44
摘要： A multi-stage axial compressor for counter rotation. A first series of rotor blade assemblies are mounted on and rotate with the driveshaft, each rotor blade assembly of the first series comprising a rotating stage of the multi-stage axial compressor. A second series of rotor blade assemblies provide a counter-rotating stage of the multi-stage axial compressor. An accessory drive links the second series of rotor blade assemblies to the driveshaft and causes counter-rotation of the second series of rotor blade assemblies.
摘要翻译：一种用于反向旋转的多级轴流式压缩机。第一系列转子叶片组件安装在驱动轴上并与驱动轴一起旋转，第一系列的每个转子叶片组件包括多级轴向压缩机的旋转级。第二系列转子叶片组件提供多级轴流式压缩机的反向旋转级。附件驱动器将第二系列转子叶片组件连接到驱动轴并引起第二系列转子叶片组件的反向旋转。

76. 发明申请

US20150219014A1 DEVICE FOR THE TRANSFER OF HEAT BETWEEN A LUBRICATION PIPE AND A TURBOMACHINE BLADE PITCH ACTUATOR CONTROL HYDRAULIC PIPE 审中-公开
标题翻译：润滑管和涡轮叶片转子之间的转移装置叶片调节器控制液压管
公开(公告)号：US20150219014A1
公开(公告)日：2015-08-06
申请号：US14414343
申请日：2013-07-18
申请人： SNECMA
发明人： Olivier Belmonte , Augustin Curlier
IPC分类号： F02C7/24 , F02C9/16 , F02C7/06 , F02C3/10 , F02C3/067
CPC分类号： F02C7/24 , B64C11/306 , B64C11/308 , B64D2027/005 , F01D17/26 , F01D25/18 , F02C3/067 , F02C3/10 , F02C7/06 , F02C7/14 , F02C7/36 , F02C9/16 , F02K3/072 , F05D2210/12 , F05D2220/323 , F05D2260/213 , F05D2260/2214 , F05D2260/22141 , F05D2260/74 , F05D2270/20 , F05D2270/64 , F05D2300/172 , Y02T50/66 , Y02T50/676
摘要： An aircraft turbomachine including a lubricant circulation pipe and a hydraulic pipe for controlling an actuator for changing a pitch of blades of a propeller of the turbomachine. The assembly, integrated to a receiver of the turbomachine, further includes a mechanism forming a thermal bridge between the lubricant circulation pipe and the hydraulic pipe.
摘要翻译：一种飞机涡轮机，包括润滑剂循环管和用于控制用于改变涡轮机的螺旋桨的桨叶的桨距的致动器的液压管。集成到涡轮机的接收器的组件还包括在润滑剂循环管和液压管之间形成热桥的机构。

77. 发明申请

US20090145102A1 Gas Turbine Engine Systems Involving Tip Fans 有权
标题翻译：燃气轮机发动机系统涉及风机
公开(公告)号：US20090145102A1
公开(公告)日：2009-06-11
申请号：US11950614
申请日：2007-12-05
申请人： Gary D. Roberge , Gabriel L. Suciu
发明人： Gary D. Roberge , Gabriel L. Suciu
IPC分类号： F02C3/067 , F02C9/18
CPC分类号： F02C3/067 , F01D1/023 , F05D2220/36
摘要： Gas turbine engine systems involving tip fans are provided. In this regard, a representative gas turbine engine system includes: a multi-stage fan having a first rotatable set of blades and a second counter-rotatable set of blades, the first rotatable set of blades defining an inner fan and a tip fan; and an epicyclic differential gear assembly operative to receive a torque input and differentially apply the torque input to the first set of blades and the second set of blades.
摘要翻译：提供了涉及尖端风扇的燃气涡轮发动机系统。在这方面，代表性的燃气涡轮发动机系统包括：多级风扇，具有第一可旋转组的叶片和第二可反向旋转的叶片组，第一可旋转组的叶片限定内部风扇和顶端风扇; 以及行星差速齿轮组件，其操作以接收扭矩输入并且差分地施加到第一组叶片和第二组叶片的扭矩输入。

78. 发明授权

US5119626A Combined turborocket and ramjet propulsion unit 失效
标题翻译：组合式涡轮机和凸轮推进装置
公开(公告)号：US5119626A
公开(公告)日：1992-06-09
申请号：US537773
申请日：1990-06-14
申请人： Alain M. J. Lardellier , Raymond P. M. Thetiot
发明人： Alain M. J. Lardellier , Raymond P. M. Thetiot
IPC分类号： F02C3/04 , F02C3/067 , F02C3/14 , F02K3/08 , F02K7/16 , F02K7/18 , F02K9/78
CPC分类号： F02C3/067 , F02C3/145 , F02K7/16 , F02K9/78
摘要： A combined turborocket and ramjet propulsion unit comprises an air intake duct, and an air compressor with two counter-rotating rotor stages disposed downstream of the duct in an annular path formed between an outer casing and a central body which is maintained in position relative to the casing by structural arms. The rotor stages of the compressor are driven by a power turbine driven by combustion gases from a gas generator which burns liquid propellants. The power turbine includes two interleaved counter-rotating modules arraanged within the central body in a position longitudinally between the two compressor stages which they drive, and the gas generator is disposed axially within the central body to the rear of the turbine modules, the generator supplying the combustion gases to the turbine in an upstream direction through a central ejection chamber and an annular reversing chamber which redirects the gases rearwards through the turbine. The gases from the turbine are discharged into the compressed air stream at the rear of the central body and are subjected to afterburning before discharge through an exhaust nozzle. On changeover to ramjet operation the fuel supply to the gas generator is shut off and is directed instead to fuel injectors disposed in a combustion chamber located in the air flow path downstream of the compressor. The compressor blades are feathered and the fuel is burned in the combustion chamber with the air compressed in the air intake duct.
摘要翻译：组合的涡轮套筒和冲压喷气推进单元包括进气管道和空气压缩机，该空气压缩机具有设置在管道下游的环形路径中的两个反向旋转的转子级，该环形路径形成在外壳和中心体之间，该环形路径相对于套管由结构臂。压缩机的转子级由燃烧液体推进剂的气体发生器的燃烧气体驱动的动力涡轮机驱动。动力涡轮机包括两个交错的反向旋转模块，其在中心体内纵向位于它们驱动的两个压缩机级之间的位置处，并且气体发生器轴向设置在中心体内至涡轮模块的后部，发电机供应通过中心喷射室的上游方向的涡轮机的燃烧气体和将气体向后通过涡轮重定向的环形反转室。来自涡轮机的气体被排放到中心体的后部的压缩空气流中，并在通过排气喷嘴排出之前进行再燃烧。在切换到冲压喷气操作时，切断对气体发生器的燃料供给，并且被引导到位于设置在位于压缩机下游的空气流动通道内的燃烧室中的燃料喷射器上。压缩机叶片是羽毛的，并且燃料在燃烧室中燃烧，空气在进气管中被压缩。

79. 发明授权

US4947642A Propfan turbo-engine 失效
标题翻译： Propfan涡轮发动机
公开(公告)号：US4947642A
公开(公告)日：1990-08-14
申请号：US334533
申请日：1989-04-07
申请人： Hubert Grieb , Helmut-Arnd Geidel
发明人： Hubert Grieb , Helmut-Arnd Geidel
IPC分类号： F02C3/067 , F02C3/113 , F02K3/00 , F02K3/06 , F02K3/072
CPC分类号： F02C3/113 , F02C3/067 , F02K3/06 , F02K3/072 , Y10S74/05
摘要： A propfan turbo-engine has two shrouded propfan rotors arranged upstream of a gas turbine which are driven by a contra-rotating working turbine. In addition to a favorable flow onto the blades, a low weight of the engine can be achieved.
摘要翻译： propfan涡轮发动机具有两个安装在燃气轮机上游的带有旋转式的旋翼式转子，它们由反向旋转的工作涡轮驱动。除了在叶片上有利的流动之外，还可以实现发动机的重量轻。

80. 发明授权

US4860537A High bypass ratio counterrotating gearless front fan engine 失效
标题翻译：高旁路比逆转无齿轮前风扇发动机
公开(公告)号：US4860537A
公开(公告)日：1989-08-29
申请号：US169135
申请日：1988-03-10
申请人： John B. Taylor
发明人： John B. Taylor
IPC分类号： F02C3/067 , F02K3/072
CPC分类号： F02C3/067 , F02K3/072 , Y02T50/672
摘要： A gas turbine engine having a core gas generator engine for generating combustion gases, with an additional power turbine, an additional fan section, and a booster compressor. The power turbine includes two counter rotatable turbine blade rows which are alternately interdigitized and serve to rotate counter rotating first and second drive shafts, respectively. The fan section also includes counter rotating spaced apart fan blade sections which are respectively connected to the first and second drive shafts. A booster compressor is axially positioned between the spaced apart fan sections. The booster compressor likewise includes first and second blade rows which are counter rotating alternately interdigitized and are likewise driven by the first and second drive shafts. The engine is supported from the two frames to permit the nacelle to be non-structural. The core engine is a modular unit so that it can be separable from the counter rotating turbine, fans and booster.
摘要翻译：具有用于产生燃烧气体的核心气体发生器发动机的燃气涡轮发动机，附加的动力涡轮机，附加的风扇部分和增压压缩机。动力涡轮机包括两个可反向旋转的涡轮机叶片排，它们交替地交叉排列并用于分别旋转相对旋转的第一和第二驱动轴。风扇部分还包括分别连接到第一和第二驱动轴的反向旋转间隔开的风扇叶片部分。增压压缩机轴向地定位在间隔开的风扇部分之间。增压压缩机同样包括第一和第二叶片排，它们是反向旋转的，交替地叉指，并且同样由第一和第二驱动轴驱动。发动机从两个框架支撑，以允许机舱是非结构的。核心发动机是一个模块化单元，使其能够与反向旋转的涡轮机，风扇和增压器分离。

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