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1. 发明公开

EP3417152A1 INDUSTRIAL GAS TURBINE ENGINE WITH FIRST AND SECOND STAGE ROTOR COOLING 审中-公开
公开(公告)号：EP3417152A1
公开(公告)日：2018-12-26
申请号：EP17708041.3
申请日：2017-02-14
申请人： Florida Turbine Technologies, Inc.
发明人： JONES, Russell B. , BROWN, Wesley D.
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/085 , F01D25/12 , F05D2260/205
摘要： An industrial gas turbine engine with first and stage turbine rotor blade cooling circuit in which the blade cooling air flows through a central passage within the rotor of the engine, flows through a space between first and second stage rotors, separates into two flows with one flow going to the first stage blades and the second flow going to the second stage blades, the two flows then collecting in a common manifold, where the spent blade cooling air flows forward through the first stage rotor and along a rotor cooling passage and into a stator cavity, where the cooling air then is discharged into a combustor.

2. 发明公开

EP3390780A1 COMPRESSOR BLEED COOLING SYSTEM FOR MID-FRAME TORQUE DISCS DOWNSTREAM FROM A COMPRESSOR ASSEMBLY IN A GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3390780A1
公开(公告)日：2018-10-24
申请号：EP16709243.6
申请日：2016-03-01
申请人： Siemens Aktiengesellschaft
发明人： YIN, Yan , SUNSHINE, Robert W. , THAM, Kok-Mun , EBERT, Todd A. , LIGHT, Kevin M. , CAMPBELL, Ernie B.
IPC分类号： F01D5/08
CPC分类号： F01D5/084 , F01D5/082 , F01D5/085 , F01D17/105 , F02C7/12 , F05D2260/22141
摘要： A cooling system (10) configured to cool aspects of the turbine engine (12) between a compressor (14) and a turbine assembly (16) is disclosed. In at least one embodiment, the cooling system (10) may include one or more mid-frame cooling channels (18) extending from an inlet (20) through one or more mid-frame torque discs (22) positioned downstream of the compressor (14) and upstream of the turbine assembly (16). The inlet (20) may be positioned to receive compressor bleed air. The mid-frame cooling channel (18) may be positioned in a radially outer portion of the mid-frame torque disc (22) to provide cooling to outer aspects of the mid-frame torque disc (22) such that conventional, low cost materials may be used to form the mid-frame torque disc (22) rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel (18) in the mid-frame torque disc (22) may be exhausted into a cooling system (10) for the downstream turbine assembly (16).

3. 发明授权

EP2784267B1 A gas turbine engine cooling arrangement 失效转让
公开(公告)号：EP2784267B1
公开(公告)日：2018-07-25
申请号：EP14158097.7
申请日：2014-03-06
申请人： Rolls-Royce plc
发明人： Mulcaire, Thomas
IPC分类号： F01D9/06 , F02C7/18 , F01D5/08 , F01D25/24 , F02C6/08 , F04D29/54
CPC分类号： F01D25/12 , F01D5/082 , F01D5/085 , F01D9/065 , F01D25/246 , F02C6/08 , F02C7/185 , F04D29/321 , F04D29/542 , F05D2240/90 , F05D2260/213 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine (10) comprises a compressor (14), a combustion chamber (15), an outer casing (20), an inner casing (22) and a cooling arrangement (24). The outer casing (20) surrounds the compressor (14) and the combustion chamber (15) and the combustion chamber (15) has turbine nozzle guide vanes (26). The compressor (14) has load carrying outlet guide vanes (28) connected to the outer casing (20) and the inner casing (22). The turbine nozzle guide vanes (26) connect the outer casing (20) and the inner casing (22). The cooling arrangement (24) comprises a cooling air duct (38) located between the compressor (14) and the combustion chamber (15). The compressor outlet guide vanes (28) carry at least one aerodynamic fairing (40). A support structure (42) supports the cooling air duct (38) from the inner casing (22) at two spaced positions and the support structure (42) forms a chamber (50) with the inner casing (22). The support structure (42) comprises at least one hollow duct (48) and each hollow duct (48) locates behind a respective one of the aerodynamic fairings (40).

4. 发明授权

EP2060741B1 Turbine arrangement 有权转让
公开(公告)号：EP2060741B1
公开(公告)日：2018-05-23
申请号：EP08253344.9
申请日：2008-10-15
申请人： Rolls-Royce plc
发明人： Young, Colin , Snowsill, Guy David , Ferra, Paul William , Gravett, Clive Peter
IPC分类号： F01D11/00 , F01D5/08
CPC分类号： F01D11/001 , F01D5/085 , F05D2240/126
摘要： A gas turbine engine (10) comprising a rotor (30) and a stator (32) which define first, second and third cavities (52, 54, 56); the rotor (30) and stator (32) define a seal (60) therebetween and which is located for sealing between the second and third cavities (54, 56), the rotor (30) comprises an aperture (70) through which a gas flow (72) passes from the first cavity (52) to the second cavity (54) characterised in that the seal (60) comprises a deflector (74) that extends axially over at least a portion of the aperture (74) to deflect at least a part of the gas towards the rotor (30).

5. 发明公开

EP2584142A3 Gas turbine engine cooling systems having hub-bleed impellers and methods for the production thereof 失效转让
标题翻译：具有轮毂排气叶轮的燃气轮机发动机冷却系统及其生产方法
公开(公告)号：EP2584142A3
公开(公告)日：2017-12-27
申请号：EP12180423.1
申请日：2012-08-14
申请人： Honeywell International Inc.
发明人： Matwey, Mark , Jan, David K. , Chunduru, Srinivas Jaya
IPC分类号： F01D5/04 , F01D5/08 , F04D29/28
CPC分类号： F01D5/046 , F01D5/085 , F04D29/284 , F04D29/285 , Y10T29/4932
摘要： Embodiments of a gas turbine engine cooling system (100) for deployment within a gas turbine engine (18) are provided, as are embodiment of a method for producing the same. In one embodiment, the gas turbine engine cooling system (100) includes an impeller (36) having a hub (52), a plurality of hub bleed air passages (102), and a central bleed air conduit (104). Each hub bleed air passage (102) has an inlet (106) and an outlet (108) formed in outer and inner circumferential surfaces of the hub (52), respectively. The central bleed air conduit (104) is fluidly coupled to the outlets (108) of the plurality of hub bleed air passages (102) and is configured to conduct bleed air discharged by the plurality of hub bleed air passages (102) to a section of the gas turbine engine (18) downstream of the impeller (36) to provide cooling air thereto.
摘要翻译：提供用于在燃气涡轮发动机（18）内部署的燃气涡轮发动机冷却系统（100）的实施例，以及用于生产燃气涡轮发动机（18）的方法的实施例。在一个实施例中，燃气涡轮发动机冷却系统（100）包括具有轮毂（52），多个毂式放气管道（102）和中央放气管道（104）的叶轮（36）。每个衬套放气通道（102）分别具有形成在衬套（52）的外圆周表面和内圆周表面中的入口（106）和出口（108）。中央放气管道（104）流体连接到多个管道放气管道（102）的出口（108），并且被配置成将由多个管道放气管道（102）排放的放出的空气引导到区段在叶轮（36）下游的燃气涡轮发动机（18）向其提供冷却空气。

6. 发明公开

EP2208859A3 Steam turbine and cooling method thereof 审中-公开
标题翻译：汽轮机及其冷却方法
公开(公告)号：EP2208859A3
公开(公告)日：2017-11-08
申请号：EP10000260.9
申请日：2010-01-13
申请人： Kabushiki Kaisha Toshiba
发明人： Inomata, Asako , Yamashita, Katsuya , Saito, Kazuhiro , Inukai, Takao , Ikeda, Kazutaka
IPC分类号： F01D5/30 , F01D5/04 , F01D5/08
CPC分类号： F01D5/3007 , F01D5/08 , F01D5/085
摘要： A steam turbine includes a casing, a rotor arranged inside the casing so as to extend in an axial direction of the casing, a rotor disk integrally formed with the rotor, a rotor-side implanting portion formed in the rotor disk, a plurality of moving blades arranged on the rotor disk in a circumferential direction of the rotor, and a moving blade-side implanting portion formed in the moving blade, in which the moving blade-side implanting portions of the moving blades are engaged with the rotor-side implanting portions, respectively. A cooling medium flows through a gap formed at least on a blade portion side of the moving blade among gaps formed between the moving blade-side implanting portions and the rotor-side implanting portions (18,19,20,42,43,44,45).
摘要翻译：本发明提供一种蒸汽涡轮机，该蒸汽涡轮机具有壳体，配置在壳体内并沿壳体的轴向延伸的转子，与该转子一体形成的转子盘，形成于该转子盘的转子侧植入部，在转子圆周方向上配置在转子圆盘上的叶片;以及形成在动叶片上的动叶片侧植入部，其中动叶片的动叶片侧植入部与转子侧植入部，分别。冷却介质流过形成在动叶片侧植入部与转子侧植入部之间的间隙中的至少形成在动叶片的叶片部侧的间隙， 45）。

7. 发明公开

EP3058176A4 GAS TURBINE ENGINE WITH COMPRESSOR DISK DEFLECTORS 有权转让
标题翻译： GASTURBINENMOTOR MIT VERDICHTERPLATTENDEFLEKTOREN
公开(公告)号：EP3058176A4
公开(公告)日：2017-06-28
申请号：EP14850225
申请日：2014-09-10
申请人： UNITED TECHNOLOGIES CORP
发明人： HIESTER PAUL J
IPC分类号： F01D5/08 , F01D25/12 , F02C7/18 , F04D29/26 , F04D29/58
CPC分类号： F04D29/582 , F01D5/085 , F01D25/12 , F02C7/18 , F04D25/045 , F04D29/321 , F04D29/584 , F05D2260/20 , Y02T50/676
摘要： A compressor section for use in a gas turbine engine is comprised of a plurality of compressor stages, with each stage including a disk having an inner periphery defining a bore that faces a shaft. A flow path flows in a generally axial direction between the shaft and the bores of each disk. At least one deflector is positioned between a pair of adjacent bores to direct the air flow radially outwardly into a cavity formed between an associated pair of adjacent disks.
摘要翻译：用于燃气涡轮发动机的压缩机部分包括多个压缩机级，每个级包括具有限定面向轴的孔的内周边的盘。流动路径在轴和每个盘的孔之间的大致轴向方向上流动。至少一个偏转器位于一对相邻孔之间，以将气流径向向外引导到形成在相关的一对相邻圆盘之间的空腔中。

8. 发明公开

EP3037674A1 Engine and method for operating said engine 审中-公开
标题翻译：汽车和Verfahren zum Betrieb des besagten汽车
公开(公告)号：EP3037674A1
公开(公告)日：2016-06-29
申请号：EP14199808.8
申请日：2014-12-22
申请人： ALSTOM Technology Ltd
发明人： Simon-Delgado, Carlos , Taheny, Oliver Joseph , Olmes, Sven , Busekros, Armin , Alberti, Luca , Jemora, Daniel , Rossi, Eugenio , Simonet, Christophe
IPC分类号： F04D27/02 , F04D29/54 , F02C6/08 , F01D5/08 , F01D11/00 , F01D25/12
CPC分类号： F02C7/185 , F01D5/084 , F01D5/085 , F01D9/02 , F01D11/001 , F01D25/12 , F02C3/06 , F02C6/08 , F04D29/321 , F04D29/544 , F05D2260/14 , F05D2260/201 , F05D2260/232 , Y02T50/676
摘要： Disclosed is an engine, said engine comprising a compressor, an expansion machine, and a shaft (21), the shaft having a direction of rotation. The engine comprises a compressed fluid main flow path, a flow divider means (4) arranged at and fluidly connected to the compressed fluid main flow path, and a duct (12) fluidly connecting the flow divider and components of the expansion machine. The duct is arranged such that, when the engine is operated, a fluid (7) is guided through the duct from the flow divider towards said expansion machine components. A flow deflector device (8) is arranged within a flow path provided by any of the flow divider means and/or said duct, said flow deflector device being arranged and adapted to deflect and thereby accelerate a flow therethrough directed form the flow divider towards the expansion machine components in a tangential direction, wherein said deflection is in particular effected into the shaft direction of rotation.
Corresponding method of cooling components of an engine (1).
摘要翻译：公开了一种发动机，所述发动机包括压缩机，膨胀机和轴（21），所述轴具有旋转方向。发动机包括压缩流体主流路，布置在流体连接到压缩流体主流路的流量分配装置（4）和流体连接分流器和膨胀机组件的管道（12）。管道被布置成使得当发动机被操作时，流体（7）被引导通过管道从分流器朝向所述膨胀机部件。导流装置（8）布置在由任何分流装置和/或所述管道提供的流动路径内，所述导流装置被布置并适于偏转并从而加速从流量分配器朝向膨胀机部件处于切向方向，其中所述偏转特别地影响轴的旋转方向。发动机冷却组件的相应方法（1）。

9. 发明公开

EP2915955A1 A blade tip seal for a gas turbine engine 审中-公开
标题翻译： Eine Schaufel-Spitzendichtungfüreine Gasturbine
公开(公告)号：EP2915955A1
公开(公告)日：2015-09-09
申请号：EP15157435.7
申请日：2015-03-03
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Dierksmeier, Douglas, D
IPC分类号： F01D5/20 , F01D11/08 , F01D11/14 , F01D11/16 , F01D11/20 , F01D11/22 , F01D5/14 , F01D5/30 , F01D5/08 , F01D11/12
CPC分类号： F02C7/28 , F01D5/085 , F01D5/147 , F01D5/20 , F01D5/225 , F01D5/3007 , F01D11/001 , F01D11/006 , F01D11/08 , F01D11/12 , F01D11/14 , F01D11/16 , F01D11/20 , F01D11/22 , F05D2220/32 , Y02T50/672 , Y02T50/676
摘要： A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.
摘要翻译：用于燃气涡轮发动机的叶片包括固定长度构件和浮动叶片密封件，其可相对于浮动叶片密封件移动以改变叶片的长度并改变叶片和发动机壳体部件之间的间隙。

10. 发明公开

EP2826958A1 Rotor für eine thermische Strömungsmaschine 审中-公开
标题翻译：转子用于热涡轮机
公开(公告)号：EP2826958A1
公开(公告)日：2015-01-21
申请号：EP13176862.4
申请日：2013-07-17
申请人： Siemens Aktiengesellschaft
发明人： Kolk, Karsten , Schröder, Peter , Springborn, Dirk , Veitsman, Vyacheslav
IPC分类号： F01D5/06 , F01D5/08 , F04D29/32 , F04D29/58
CPC分类号： F04D29/667 , F01D5/06 , F01D5/085 , F01D5/087 , F04D17/02 , F04D29/266 , F04D29/321 , F04D29/5846 , F05D2220/32 , F05D2240/61 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Die Erfindung betrifft somit insgesamt einen Rotor (10) für eine thermische Strömungsmaschine, insbesondere eine Gasturbine, der ausgestaltet ist, in seinem Inneren ein Medium, beispielsweise Verdichterluft, zu führen. Um dieses Medium strömungsverlustarm im Inneren zu führen und um gleichzeitig einen vergleichsweisen einfach sowie kostengünstig herstellbaren Rotor (10) anzugeben, ist vorgesehen, dass zwischen den einander benachbarten Nabenbereichen der beiden Rotorscheiben (34, 42) ein separat gefertigtes Flügelrad (50) angeordnet ist, dass zur Befestigung des Flügelrads (50) an der einer der beiden Rotorscheiben (34, 42) eine Hülse (62) vorgesehen ist, welche sich durch die zentrale Öffnung (30) der betreffenden Rotorscheibe erstreckt (34, 42) und die an ihrem ersten Ende (63) einen als Anschlag dienenden Kragen (64) und ein dem ersten Ende (63) gegenliegendes zweites Ende (65) umfasst, auf welchem zweiten Ende (65) das Flügelrad (50) befestigt ist.
摘要翻译：因此，本发明涉及一种总的转子（10），用于热涡轮机，特别是燃气涡轮机，其被设计在其一个介质内，诸如空气压缩机领先。到该培养基中，以内部执行strömungsverlustarm，并在同一时间，以提供一个相对简单且廉价地制造转子（10），它提供了在两个转子盘（34，42）的相邻轮毂部分之间的是一个单独制造的叶轮（50）被布置，通过相应的转子盘的延伸的中心开口（30）（34，42）和所述第一在延伸的套筒（62）被提供用于在两个转子盘的一个（34，42）的叶轮（50）的紧固其端（63）作为一个止动环（64）和第一端（63）位于其上的第二端部（65），叶轮（50）被附接相对的第二端（65）。

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