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31. 发明申请

US20100247304A1 EXHAUST PLENUM FOR A TURBINE ENGINE 有权
标题翻译：用于涡轮发动机的排气孔
公开(公告)号：US20100247304A1
公开(公告)日：2010-09-30
申请号：US12416034
申请日：2009-03-31
申请人： Laxmikant Merchant , Prabhakaran Saraswathi Rajesh
发明人： Laxmikant Merchant , Prabhakaran Saraswathi Rajesh
IPC分类号： F01D25/24 , F01D1/06
CPC分类号： F01D25/30 , B64D33/04 , B64D33/06 , F02K1/002 , F05D2210/42 , F05D2260/97 , Y02T50/671
摘要： An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exhaust plenum may also include one or more flow splitters that further reduce turbulence in the plenum and provide a more uniform gas flow in the plenum and other downstream exhaust components.
摘要翻译：提供了一种用于燃气涡轮发动机的排气系统，其减少了排气系统内的紊流和回流，从而提高了涡轮发动机的效率。在各种实施例中，系统包括排气室，其提供排气的逐渐膨胀。排气增压室还可以包括一个或多个分流器，其进一步减少气室中的湍流并且在集气室和其它下游排气组件中提供更均匀的气流。

32. 发明申请

US20090263241A1 DIFFUSER AND EXHAUST SYSTEM FOR TURBINE 有权
标题翻译：涡轮膨胀机和排气系统
公开(公告)号：US20090263241A1
公开(公告)日：2009-10-22
申请号：US12463203
申请日：2009-05-08
申请人： Lale DEMIRAYDIN , Ralf Greim
发明人： Lale DEMIRAYDIN , Ralf Greim
IPC分类号： F01D9/00
CPC分类号： F01D25/30 , F05D2210/42 , F05D2220/3215 , F05D2240/12
摘要： A diffuser and exhaust system is provided for a turbine having an axial-radial diffuser and an exhaust hood including diffuser inner and outer flow guides that extend from an inlet to an outlet. The exhaust hood includes two throats or flow passages between the diffuser outlet and an exhaust hood side wall. The outer flow guide includes a recess, at one of the said two flow passages. The flow passage is positioned in relation to a point in the exhaust hood in the direction of the tangential flow velocity vector, where the point in the exhaust hood is farthest away from the exhaust hood outlet. The recess prevents a re-acceleration of the flow within the exhaust hood and affects an increase in the performance of the diffuser and exhaust hood system.
摘要翻译：为具有轴向 - 径向扩散器和排气罩的涡轮机提供扩散器和排气系统，该排气罩包括从入口延伸到出口的扩散器内部和外部流动引导件。排气罩包括在扩散器出口和排气罩侧壁之间的两个喉部或流动通道。所述外部流动引导件包括在所述两个流动通道中的一个处的凹部。流道相对于排气罩中的一个点沿着切向流速矢量的方向定位，其中排气罩中的点距排气罩出口最远。该凹槽防止排气罩内的流动的再加速并且影响扩散器和排气罩系统的性能的增加。

33. 发明授权

US4544167A Face seal with resilient packing ring forcing face rings together 失效
标题翻译：带有弹性密封圈的面密封件将面环一起拉紧
公开(公告)号：US4544167A
公开(公告)日：1985-10-01
申请号：US639719
申请日：1984-08-13
申请人： Claude Giroux
发明人： Claude Giroux
IPC分类号： F01D11/02 , F01D25/12 , F01D25/18 , F16J15/00 , F16J15/34 , F16J15/44
CPC分类号： F01D11/02 , F01D25/12 , F01D25/183 , F16J15/004 , F16J15/344 , F16J15/443 , F05D2210/42 , F05D2210/43 , F05D2220/40
摘要： A turboexpander compressor for use in a gas processing system has a seal system that avoids communication of gas with the oil being pumped through the bearings. The device has a shaft carried in a housing on bearings with a compressor wheel on one side and an expander wheel on the other side. Labyrinth seals seal the wheels from the interior of the housing and the bearings. Mechanical seals are located between the bearings and the labyrinth seals for preventing leakage of oil. The mechanical seals are located in a drainage chamber that allows any oil or gas leaked past the seals to be drained from the system, rather than dilute the oil. Gas is injected from the compressor discharge into a groove on the expander side of the shaft to provide a thermal barrier. The mechanical seals each have a rotating ring carried by the shaft and a nonrotating ring carried by the housing. The nonrotating ring is biased into the rotating ring by means of an O-ring. The O-ring is located in a groove in the bore and a recess formed in the nonrotating ring. The recess is offset to deform the ring and cause it to exert a force on the nonrotating ring against the rotating ring.
摘要翻译：用于气体处理系统的涡轮膨胀机压缩机具有密封系统，其避免了气体与被泵送通过轴承的油的通信。该装置具有轴承承载在壳体中的轴承上，一侧具有压缩机叶轮，另一侧具有膨胀轮。迷宫式密封件将密封件从外壳和轴承的内部密封。机械密封位于轴承和迷宫式密封之间，以防止油渗漏。机械密封件位于排水室中，允许从密封件泄漏的任何油或气体从系统中排出，而不是稀释油。将气体从压缩机排出口喷射到轴的膨胀机侧的槽中以提供热障。机械密封件各自具有由轴承载的旋转环和由壳体承载的非旋转环。非旋转环通过O形环被偏压到旋转环中。 O形环位于孔中的凹槽中，并形成在非旋转环中的凹部。凹槽偏移以使环变形，并使其在非旋转环上抵抗旋转环施加力。

34. 发明授权

US4264271A Impeller shroud of a centrifugal compressor 失效
标题翻译：离心压缩机的叶轮护罩
公开(公告)号：US4264271A
公开(公告)日：1981-04-28
申请号：US20566
申请日：1979-03-15
申请人： Zoltan L. Libertini
发明人： Zoltan L. Libertini
IPC分类号： F01D11/08 , F01D25/24 , F04D29/44 , F01D5/08
CPC分类号： F04D29/441 , F01D11/08 , F01D25/24 , F05D2210/42 , F05D2210/43
摘要： The shroud or stationary housing for the impeller of a centrifugal compressor includes inherent means for selectively controlling the displacement thereof during operation of the centrifugal compressor, and in a manner to substantially maintain uniform spacing or clearance between the shroud and the blade tips of the rotating impeller in order to achieve improved performance at both part and full power operating conditions. The shroud is preferably formed of a unitary member including an annular, concave disc portion substantially corresponding to the configuration of the tips of the blades of the impeller, with the annular concave disc portion being rigid and connected to a fixed flange support portion by a flexible, annular diaphragm which extends generally perpendicular to the shaft of the impeller. The annular diaphragm is sufficiently flexible such that during operation of the centrifugal compressor, the differential thermal and pressure forces generated along the length of the blades within the compressor cause deformation of the flexible diaphragm and a substantially linear movement of the rigid, concave disc portion relative to the flange support portion. The movement of the annular concave disc portion substantially corresponds to the change in configuration of the blades, thereby minimizing blade tip losses.
摘要翻译：用于离心压缩机的叶轮的护罩或固定壳体包括用于在离心式压缩机的操作期间选择性地控制其位移的固有装置，并且以使得护罩和旋转叶轮的叶片尖端之间基本上保持均匀间隔或间隙的方式以便在部分和全功率工作条件下实现改进的性能。护罩优选地由整体构件形成，该整体构件包括基本上对应于叶轮的叶片的构造的环形凹槽部分，环形凹形盘部分是刚性的并且通过柔性的连接到固定法兰支撑部分环形隔膜，其大致垂直于叶轮的轴延伸。环形隔膜具有足够的柔性，使得在离心式压缩机的操作期间，沿着压缩机内的叶片长度产生的不同的热和压力导致柔性隔膜的变形，并且刚性的凹盘部分相对到凸缘支撑部分。环形凹盘部分的运动基本上对应于叶片的构造变化，从而最小化叶片尖端损失。

35. 发明申请

WO2014053722A1 COUVERCLE DE COMPRESSEUR CENTRIFUGE, ASSEMBLAGE DE COUVERCLE ET DE COMPRESSEUR CENTRIFUGE, ET TURBOMACHINE COMPORTANT UN TEL ASSEMBLAGE 审中-公开
标题翻译：离心式压缩机盖，离心机和压缩机组件以及包含这种组件的涡轮机
公开(公告)号：WO2014053722A1
公开(公告)日：2014-04-10
申请号：PCT/FR2013/052118
申请日：2013-09-16
申请人： TURBOMECA
发明人： MIRATON, Clément , CHABANNE, Pierre , GIRARDOT, Julien , LEFEBVRE, Hélène
IPC分类号： F01D11/18 , F04D29/42 , F04D29/44
CPC分类号： F01D11/18 , F02C3/08 , F04D29/622 , F05D2210/42 , F05D2250/71
摘要： La présente invention vise, dans un encombrement axial réduit, à permettre une dilatation libre de l'enveloppe d'un couvercle de compresseur centrifuge selon la direction radiale lors des montées en température, afin de maîtriser la tenue des jeux radiaux en bord d'attaque et des jeux axiaux en bord de fuite. Pour ce faire, l'invention prévoit un couvercle (30) dans lequel la jonction (41) entre l'attache (4) et l'enveloppe (3) est formée entre sensiblement le milieu (I) de l'enveloppe (3) et son bord de fuite (B F ) et dans lequel, à froid, l'attache (4) présente essentiellement une forme concave (43) élastiquement déformable en flexion. Cette forme concave (43) est raccordée à l'enveloppe (3) par une paroi (5) se prolongeant au niveau de la jonction (41) par une forme convexe (44), de sorte que l'attache (4) présente, globalement, une configuration en coupe en forme de « S » avec une jonction (41) située plus près du bord de fuite (B F ) de l'enveloppe (3) que de son bord d'attaque (B A ).
摘要翻译：本发明的目的是在减小的轴向空间中允许离心式压缩机盖在温度升高期间在径向上的自由膨胀，以便控制前缘的径向间隙的控制和后缘的轴向间隙。为此，本发明提供了一种盖子，其中紧固件（4）和封套（3）之间的接合部（41）形成在信封（3）的大致中间（I）与后缘（BF），并且其中当冷时，紧固件（4）具有基本上是凹形的并且可通过弯曲而弹性变形的形状（43）。这种凹形（43）通过一个通过凸形（44）在接合处延伸的壁（5）连接到外壳（3），使得紧固件（4）整体上具有具有位于更靠近外壳（3）的后缘（BF）的结（41）的“S”形状的横截面构造比其前缘（BA）更靠近。

36. 发明申请

WO2008041964A8 INFRARED SUPPRESSION SYSTEM 审中-公开
标题翻译：红外抑制系统
公开(公告)号：WO2008041964A8
公开(公告)日：2008-08-14
申请号：PCT/US2006029419
申请日：2006-07-27
申请人： SIKORSKY AIRCRAFT CORP
发明人： CHAPKOVICH JOHN S III , FITTS RICHARD ALAN , ZACK DAVID
IPC分类号： F02C7/00
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , F05D2210/42 , F05D2220/329 , Y02T50/671
摘要： An InfraRed Suppression System (IRSS) includes an exhaust manifold and a high aspect ratio exhaust duct along a longitudinal length thereof. The IRSS minimizes impingement of engine exhaust onto adjacent aircraft structure by discharging the flow upwardly and/or outwardly, away from the fuselage at relatively high velocity to reduce fuselage heating due to plume impingement in both hover and forward flight thus minimizing fuselage IR signature contributions. Furthermore, by directing the exhaust stream upward, a direct line of sight to the exhausted IR energy is masked from ground threats. The high aspect ratio exhaust duct and exhaust manifold are also preferably shrouded by an aerodynamic fairing which provides an aerodynamic contour to minimize aerodynamic impact to the aircraft and defines an air-cooled ejector gap to augment airflow to further insulate and obscure the high temperature exhaust gas exhausted through the exhaust duct.
摘要翻译：红外抑制系统（IRSS）包括沿其纵向长度的排气歧管和高纵横比排气管。 IRSS通过向上和/或向外，以相对较高的速度离开机身排出气流，将发动机排气冲击最小化，从而减少由于在悬停和向前飞行中的羽流撞击而导致的机身加热，从而使机身IR签名贡献最小化。此外，通过将排气流向上引导，红外线能量的直接视线被地面威胁所掩盖。高纵横比排气管和排气歧管最好还被空气动力学整流罩覆盖，该空气动力整流罩提供空气动力学轮廓以最小化对飞机的空气动力学冲击，并限定空气冷却喷射器间隙以增大气流以进一步隔离和遮蔽高温排气通过排气管排出。

37. 发明申请

WO2013150018A2 DEVICE FOR POWER GENERATION ACCORDING TO A RANKINE CYCLE 审中-公开
标题翻译：根据RANKINE CYCLE发电的装置
公开(公告)号：WO2013150018A2
公开(公告)日：2013-10-10
申请号：PCT/EP2013056918
申请日：2013-04-02
申请人： EQUITHERM S A R L
发明人： MAITREJEAN LUC
CPC分类号： F01K25/10 , F01D1/023 , F01D5/043 , F01K3/04 , F01K11/02 , F01K13/00 , F05D2210/42
摘要： A device for power generation according to a Rankine cycle, in particular according to an organic Rankine cycle (ORC), comprises a turbine (16), for expanding a vapour of a working fluid, and at least one heat exchanger (18, 20, 22), through which the expanded vapour has to flow. The turbine (16) and the heat exchanger(s) (18, 20, 22) are contained in a vapour tight container (10). The turbine (16) is a radial-outward-flow type turbine having a shaft that is led in a sealed manner out of said container (10), an axial vapour inlet port arranged opposite the shaft and located inside the container (10), and a stator exhaust ring with stator exhaust blades defining peripheral vapour exhaust openings for discharging the expanded vapour directly into the vapour tight container (10), in which the expanded vapour flows through the heat exchanger(s) (18, 20, 22).
摘要翻译：根据兰金循环的发电装置，特别是根据有机朗肯循环（ORC）的发电装置，包括用于膨胀工作流体蒸汽的涡轮机（16）和至少一个热交换器（18,20） 22），膨胀的蒸气必须通过其流动。涡轮（16）和热交换器（18,20,22）被容纳在气密容器（10）中。涡轮机（16）是径向向外流动的涡轮机，其具有以密封方式从所述容器（10）引出的轴，与所述轴相对设置并位于所述容器（10）内部的轴向蒸气入口，以及定子排气环，其具有限定用于将膨胀的蒸气直接排放到所述蒸汽密封容器（10）中的外围蒸汽排气口的定子排气叶片，其中所述膨胀的蒸气流过所述热交换器（18,20,22）。

38. 发明申请

WO2007001427A2 UNIVERSAL CARNOT PROPULSION SYSTEMS FOR TURBO ROCKETRY 审中-公开
标题翻译：用于涡轮轴承的通用卡车推进系统
公开(公告)号：WO2007001427A2
公开(公告)日：2007-01-04
申请号：PCT/US2005038008
申请日：2005-10-21
申请人： PAUL MARIUS A
发明人： PAUL MARIUS A
IPC分类号： F02K3/02
CPC分类号： F02C3/073 , F02C3/045 , F02C3/14 , F02C7/08 , F02C7/10 , F02K3/02 , F02K3/06 , F02K3/08 , F05D2210/42 , F05D2220/327 , F05D2220/36 , Y02T50/671
摘要： Turbofan jet engines utilizing the Carnot cycle for improved performance with isothermal compression of combustion air and, in part, isothermal expansion of thermally heated air, the engines having a turbofan compressor rotor with hollow fan blades in a core bypass passage through the engine and an annular, peripheral thermal chamber with staged turbine blades in an expansion chamber where heated gases are supplied to multiple stages to maintain peak temperatures.
摘要翻译： Turbofan喷气发动机利用卡诺循环来改善燃烧空气的等温压缩性能，并且部分地是热加热空气的等温膨胀，发动机具有涡轮风扇压缩机转子，其具有穿过发动机的铁芯旁通通道中的中空风扇叶片，，具有分级涡轮机叶片的外围热室，在膨胀室中，其中加热的气体被供应到多个级以保持峰值温度。

39. 发明申请

US20190060809A1 INTEGRATED OXYGEN REMOVAL UNIT AND FUEL FILTER 审中-公开
公开(公告)号：US20190060809A1
公开(公告)日：2019-02-28
申请号：US15686330
申请日：2017-08-25
申请人： Hamilton Sundstrand Corporation
发明人： Gerald P. Dyer
IPC分类号： B01D36/00 , F02C7/22 , B01D29/90 , B01D29/35 , B01D19/00
CPC分类号： B01D36/001 , B01D19/00 , B01D19/0031 , B01D19/0036 , B01D29/117 , B01D29/35 , B01D29/902 , B01D46/0023 , B01D50/002 , B01D2201/02 , F02C7/22 , F02C7/222 , F05D2210/42 , F23K5/18 , F23K2900/05082
摘要： A system for use in a gas turbine engine fuel supply has an internal fuel filter having an internal bore and an external surface. A chamber within the internal bore of the fuel filter for receives a fuel and allows fuel to pass radially outwardly across the fuel filter. An oxygen removal unit is outwardly of the external surface of the fuel filter, such that fuel passes through the fuel filter, encounters the oxygen removal unit such that oxygen can be removed from the fuel, an outlet port for removed oxygen, and a separate outlet port for fuel having passed over the fuel filter and the oxygen removal unit.

40. 发明申请

US20150082793A1 DEVICE FOR POWER GENERATION ACCORDING TO A RANKINE CYCLE 审中-公开
标题翻译：根据RANKINE CYCLE发电的装置
公开(公告)号：US20150082793A1
公开(公告)日：2015-03-26
申请号：US14390284
申请日：2013-04-02
申请人： EQUITHERM S.À R.L.
发明人： Luc Maîtrejean
IPC分类号： F01K25/10 , F01K11/02 , F01K13/00
CPC分类号： F01K25/10 , F01D1/023 , F01D5/043 , F01K3/04 , F01K11/02 , F01K13/00 , F05D2210/42
摘要： A device for power generation according to a Rankine cycle, in particular according to an organic Rankine cycle (ORC), comprises a turbine (16), for expanding a vapour of a working fluid, and at least one heat exchanger (18, 20, 22), through which the expanded vapour has to flow. The turbine (16) and the heat exchanger(s) (18, 20, 22) are contained in a vapour tight container (10). The turbine (16) is a radial-outward-flow type turbine having a shaft that is led in a sealed manner out of said container (10), an axial vapour inlet port arranged opposite the shaft and located inside the container (10), and a stator exhaust ring with stator exhaust blades defining peripheral vapour exhaust openings for discharging the expanded vapour directly into the vapour tight container (10), in which the expanded vapour flows through the heat exchanger(s) (18, 20, 22).
摘要翻译：根据兰金循环的发电装置，特别是根据有机朗肯循环（ORC）的发电装置，包括用于膨胀工作流体的蒸汽的涡轮机（16）和至少一个热交换器（18,20） 22），膨胀的蒸气必须通过其流动。涡轮（16）和热交换器（18,20,22）被容纳在气密容器（10）中。涡轮机（16）是径向向外流动的涡轮机，其具有以密封方式从所述容器（10）引出的轴，与所述轴相对设置并位于所述容器（10）内部的轴向蒸气入口，以及定子排气环，其具有限定用于将膨胀的蒸气直接排放到所述蒸汽密封容器（10）中的外围蒸汽排气口的定子排气叶片，其中所述膨胀的蒸气流过所述热交换器（18,20,22）。

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