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1. 发明授权

US12116928B2 Aircraft engine having two radially offset turbines 有权
公开(公告)号：US12116928B2
公开(公告)日：2024-10-15
申请号：US18185007
申请日：2023-03-16
申请人： PRATT & WHITNEY CANADA CORP.
发明人： David Menheere
IPC分类号： F02C3/08 , F02C3/045 , F02C3/09 , F02C3/10 , F02C3/107 , F02C3/13 , F02C6/20 , F02C7/36
CPC分类号： F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
摘要： An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.

2. 发明授权

US11208949B2 System, method and computer program for operating a land- or marine-based multi-spool gas turbine 有权
公开(公告)号：US11208949B2
公开(公告)日：2021-12-28
申请号：US15753807
申请日：2016-08-19
申请人： Aurelia Turbines Oy
发明人： Matti Malkamäki , Ahti Jaatinen-Värri , Jari Backman , Juha Honkatukia
IPC分类号： F02C7/10 , F02C1/06 , F02C9/42 , F02C3/045 , F02C6/00 , H02K7/18
摘要： The present invention is a system, method and computer program for operating a land-or marine-based multi-spool gas turbine system for generating electrical power to supply a load, wherein the system comprises a multi-spool gas turbine engine, and the method comprises controlling the rotational speeds of the at least two generators independently of each other so as to directly control the rotational speeds of the shafts of the spools, the at last two generators being operable to generate electrical current to supply the load, and regulating the amount of heat generated the first heat generating equipment. A computer program to perform the method is also disclosed.

3. 发明授权

US10774788B2 Particle extraction system for a gas turbine engine 有权
公开(公告)号：US10774788B2
公开(公告)日：2020-09-15
申请号：US15194944
申请日：2016-06-28
申请人： United Technologies Corporation
发明人： Matthew R. Feulner
IPC分类号： F02C7/052 , F02K3/06 , F02C3/045 , F02C6/08
摘要： A gas turbine engine includes an engine core includes at least one compressor, a combustor downstream of the compressor, and at least one turbine downstream of the combustor. A primary flowpath fluidly connects each of the compressor, the combustor, and the turbine. At least one particle extraction duct has an extraction duct inlet connected to the primary flowpath fore of the compressor and an extraction duct outlet connected to a bypass flowpath.

4. 发明申请

US20150354403A1 OFF-LINE WASH SYSTEMS AND METHODS FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：气动涡轮发动机的离线清洗系统和方法
公开(公告)号：US20150354403A1
公开(公告)日：2015-12-10
申请号：US14297015
申请日：2014-06-05
申请人： General Electric Company
发明人： Sanji Ekanayake , Alston IIford Scipio
IPC分类号： F01D25/00 , F02C3/045 , B08B3/08
CPC分类号： F01D25/002 , B08B3/02 , C11D3/162 , C11D11/0041
摘要： The present application and the resultant patent provide a wash system for a gas turbine engine. The wash system may include a water source containing a volume of water therein, and a surface filming agent source containing a volume of a surface filming agent therein. The wash system also may include a mixing chamber in fluid communication with the water source and the surface filming agent source, wherein the mixing chamber is configured to mix the water and the surface filming agent therein to produce a film-forming mixture. The film-forming mixture may be a liquid-gas mixture of the surface filming agent in a liquid phase and the water in a gaseous phase. The wash system further may include a number of supply lines in fluid communication with the mixing chamber, wherein the supply lines are configured to direct the film-forming mixture into the gas turbine engine.
摘要翻译：本申请和所得专利提供了一种用于燃气涡轮发动机的洗涤系统。洗涤系统可以包括其中含有一定体积的水的水源和其中含有一定体积的表面成膜剂的表面成膜剂源。洗涤系统还可以包括与水源和表面成膜剂源流体连通的混合室，其中混合室配置成将水和表面成膜剂混合在其中以产生成膜混合物。成膜混合物可以是液相中的表面成膜剂和气相中的水的液 - 气混合物。洗涤系统还可以包括与混合室流体连通的多个供应管线，其中供应管线被配置成将成膜混合物引导到燃气涡轮发动机中。

5. 发明申请

US20130333392A1 TURBINE COMPRESSOR BLADE TIP RESISTANT TO METAL TRANSFER 有权
标题翻译：涡轮压缩机叶片抗金属转移
公开(公告)号：US20130333392A1
公开(公告)日：2013-12-19
申请号：US13525420
申请日：2012-06-18
申请人： Matthew E. Bintz , Christopher W. Strock
发明人： Matthew E. Bintz , Christopher W. Strock
IPC分类号： F01D5/20 , F01D11/12 , F02C3/045
CPC分类号： F01D5/20 , F01D11/12 , F01D11/122 , F05D2230/90 , F05D2300/2112 , F05D2300/2118 , F05D2300/2261 , F05D2300/2283 , F05D2300/611
摘要： A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abrasive.
摘要翻译：一种燃气涡轮发动机，具有围绕发动机中心线轴线周向延伸的发动机壳体; 以及在所述发动机壳体内的压缩机部分，燃烧器部分和涡轮部分。所述压缩机部分和所述涡轮部分中的至少一个包括至少一个翼型件和与所述至少一个翼型件相邻的至少一个密封构件，其中所述至少一个翼型件的尖端是具有薄膜陶瓷涂层的金属，至少一个密封件被涂覆有研磨剂。

6. 发明授权

US08104257B2 Tip turbine engine with multiple fan and turbine stages 有权
标题翻译：具有多个风扇和涡轮级的涡轮发动机
公开(公告)号：US08104257B2
公开(公告)日：2012-01-31
申请号：US11719589
申请日：2004-12-01
申请人： James W. Norris , Craig A. Nordeen , Gary Roberge
发明人： James W. Norris , Craig A. Nordeen , Gary Roberge
IPC分类号： F02C3/045
CPC分类号： F02C3/14 , F01D5/022 , F02C3/067 , F02C3/073 , F02K3/068 , F02K3/072 , F05D2260/40311 , Y02T50/673
摘要： 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 of a first fan (24a), such that the first fan is rotatably driven by the first turbine (32a). The second turbine (32b) is mounted at an outer periphery of a second fan (24b), and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced. Other variations are described in additional embodiments.
摘要翻译：顶端涡轮发动机（10）提供由可产生高能气流的燃烧器（30）可旋转地驱动的第一和第二涡轮机（32）。第一涡轮（32）安装在第一风扇（24a）的外周，使得第一风扇由第一涡轮机（32a）旋转驱动。第二涡轮（32b）安装在第二风扇（24b）的外周，由高能气流旋转驱动。在一个实施例中，第一涡轮机（32a）以第一旋转方向可旋转地驱动轴向压缩机（22）中的多级第一压缩机叶片（54），而第二涡轮（32b）可旋转地驱动多个级第二压缩机叶片（52）在轴向压缩机（22）中沿与第一压缩机相反的第二旋转方向。通过以相反的方向旋转地驱动压缩机叶片的交替级，轴流式压缩机（22）的效率提高和/或压缩机叶片的级数可以减少。在另外的实施例中描述了其它变型。

7. 发明申请

US20080041065A1 Ultra-Micro Gas Turbine 有权
标题翻译：超微型燃气轮机
公开(公告)号：US20080041065A1
公开(公告)日：2008-02-21
申请号：US11631923
申请日：2005-07-07
申请人： Norbert Muller , Florin Iancu , Pezhman Akbari
发明人： Norbert Muller , Florin Iancu , Pezhman Akbari
IPC分类号： F02C3/045
CPC分类号： F01D1/12 , F02C3/05 , F02C5/10 , F05D2230/14 , F05D2250/82 , F05D2250/84 , F05D2260/963
摘要： The present invention provides an ultra micro gas turbine engine which includes a wave rotor. In various embodiments, the ultra micro gas turbine engine of the present invention includes a rotating disk which has a compressor, a wave rotor and a turbine, a first stationary member which includes an inlet and a first wave rotor port end plate, a second stationary member which includes an outlet and a second wave rotor port end plate and a combustion chamber which includes a fuel inlet and an igniter.
摘要翻译：本发明提供一种包括波转子的超微型燃气涡轮发动机。在各种实施例中，本发明的超微型燃气涡轮发动机包括具有压缩机，波转子和涡轮机的旋转盘，包括入口和第一波转子端口端板的第一固定构件，第二静止构件，其包括出口和第二波形转子端口端板以及包括燃料入口和点火器的燃烧室。

8. 发明申请

US20070068135A1 Engine 审中-公开
标题翻译：发动机
公开(公告)号：US20070068135A1
公开(公告)日：2007-03-29
申请号：US11418844
申请日：2006-05-05
申请人： Bernard Gill
发明人： Bernard Gill
IPC分类号： F02C3/045
CPC分类号： F02C3/09 , F02C3/16 , F04D29/442 , F05D2200/11
摘要： Engine 30 has a compression fan 36 coaxially mounted with reaction member 38. Casing 32 extends around reaction member 38 to form volute 52 and extends to turbine wheel 54 which is connected to compression fan 36 via axle 40. Reaction member 38 comprises vanes 60, flame grid 62 and supporting members in the form of side casings 64. A mixture of fuel and air enters engine 30 via inlets 34. The mixture is drawn into compression fan 36 which causes an increase in the pressure of the mixture. From the compression fan 36 the mixture is directed towards the reaction member 38. Because the compression fan 36 is rotating in a first sense and the reaction member 38 is rotating in a second sense, the velocity of the fuel and air mixture entering the reaction member 38, relative to the reaction member 38, is approximately the sum of the external rim velocity of the compression fan 36 and the internal rim velocity of the reaction member 36. The mixture is burnt within the reaction member 38 and the vectored gases cause the rotation of the reaction member 38 in the second sense.
摘要翻译：发动机30具有与反作用件38同轴安装的压缩风扇36。壳体32围绕反作用构件38延伸以形成蜗壳52并延伸到涡轮机轮54，涡轮机叶轮54经由轴40连接到压缩风扇36。反应构件38包括叶片60，火焰栅格62和侧壳体64形式的支撑构件。燃料和空气的混合物通过入口34进入发动机30。混合物被吸入压缩风扇36，这导致混合物的压力增加。从压缩风扇36将混合物引向反应构件38。由于压缩风扇36在第一意义上旋转并且反作用构件38在第二方向旋转，所以进入反作用构件38的燃料和空气混合物相对于反作用构件38的速度大约是压缩风扇36的外部轮辋速度和反作用件36的内部轮辋速度。混合物在反应构件38内燃烧，并且向量气体导致反应构件38在第二方面的旋转。

9. 发明授权

US4706452A Engine 失效
标题翻译：发动机
公开(公告)号：US4706452A
公开(公告)日：1987-11-17
申请号：US911325
申请日：1986-09-25
申请人： Gaston Lavoie
发明人： Gaston Lavoie
IPC分类号： F02C3/05 , F02C3/045 , F02C3/14 , F02C3/16 , F02C7/04 , F23R3/42 , F23R3/52 , F02C3/06
CPC分类号： F23R3/52 , F02C3/045 , F02C3/165
摘要： The present invention provides an internal combustion engine comprising a main body portion defining a combustion chamber in the form of a toroidal cavity with a generally circular axis, an air intake, compressor means for drawing air from said intake and delivering it to said toroidal cavity under pressure in a generally tangential direction to impart a swirl motion to gases in said cavity about said circular axis, means for exhausting combustion gases from said cavity, drive means disposed adjacent said exhaust means so as to be acted on by said combustion gases to perform mechanical work and thereby provide an output of the engine, and means coupling said drive means to said compressor means for providing power thereto.
摘要翻译：本发明提供一种内燃机，其包括主体部分，其限定具有大致圆形轴线的环形腔形式的燃烧室，进气口，用于从所述进气口抽取空气并将其输送到所述环形空腔下面的压缩机装置在大致切线方向上的压力以围绕所述圆形轴线对所述空腔中的气体施加漩涡运动，用于从所述空腔排出燃烧气体的装置，与所述排气装置相邻设置的驱动装置，以便被所述燃烧气体作用以执行机械从而提供发动机的输出，以及将所述驱动装置联接到所述压缩机装置以便向其提供动力的装置。

10. 发明授权

US3685287A Re-entry type integrated gas turbine engine and method of operation 失效
标题翻译：重新输入型集成气体涡轮发动机及其运行方法
公开(公告)号：US3685287A
公开(公告)日：1972-08-22
申请号：US3685287D
申请日：1970-12-08
申请人： MCCULLOCH CORP
发明人： DOOLEY JAMES L
IPC分类号： F02C3/045 , F02C3/04
CPC分类号： F02C3/045
摘要： A gas turbine engine of the integrated type having a single rotor with all working blades subjected to alternate periods of cooling and heating. The rotor is mounted for rotation in a casing and performs the dual functions of compressing primary air and driving a turbine shaft in response to the expansion of combustion gases. The rotor includes two annular channels for receiving the working blades therein in an equally spaced manner. The annular channels and blades define a dual symmetrical series of pockets. The casing includes flush ports which are formed generally adjacent the inlet and exhaust ports. The flush ports cooperate with the inlet ports to purge carry-over gases remaining in the rotor pockets after exhaustion. The flushed pockets cooperate with surrounding annular channels defined by the casing to perform reentry compression on the primary air introduced into the casing annular channels and flushed pockets through inlet ports in the casing. Approximately mid-way between the inlet and exhaust ports, the casing annular channels lead into a combustion chamber into which the compressed primary air is directed. In the combustion chamber, the compressed primary air is mixed with fuel and ignited to form the products of combustion. The products of combustion expand into the casing annular channels and flushed pockets in the direction of the exhaust ports to effect the turbine shaft drive. Sealing blocks are provided in the casing annular channels to properly direct the compressed primary air into the combustion chamber and the expanding exhaust gases out the exhaust ports.
摘要翻译：一种具有单个转子的整体型燃气涡轮发动机，所有工作叶片经历了交替的冷却和加热周期。转子被安装成旋转在壳体中并且执行压缩一次空气并且响应于燃烧气体的膨胀来驱动涡轮机轴的双重功能。转子包括两个环形通道，用于以等间距的方式接收工作叶片。环形通道和叶片限定双重对称系列的口袋。壳体包括大致邻近入口和排气口形成的冲洗口。冲洗口与入口端口配合以排除在排气后残留在转子腔中的残留气体。冲洗的袋与由壳体限定的周围环形通道配合，以在引入到壳体环形通道中的一次空气上进行再入压缩，并且通过壳体中的入口进行冲洗的袋。在入口和排气口之间大致中途，套管环形通道通向压缩一次空气被引导到的燃烧室。在燃烧室中，压缩的一次空气与燃料混合并点燃以形成燃烧产物。燃烧产物沿着排气口的方向扩展到套管的环形通道和冲洗袋中，以实现涡轮轴驱动。密封块设置在壳体环形通道中，以将压缩的一次空气正确地引导到燃烧室中，并且膨胀的废气排出排气口。

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