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1. 发明授权

US11435078B2 Stand-off device for double-skin combustor liner 有权
公开(公告)号：US11435078B2
公开(公告)日：2022-09-06
申请号：US16448584
申请日：2019-06-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Tin-Cheung John Hu , Oleg Morenko
IPC分类号： F23R3/00 , F23R3/60 , F23R3/48 , F02C3/14 , F02K1/80
摘要： A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.

2. 发明申请

US20180363913A1 ASSEMBLY OF TUBE AND STRUCTURE CROSSING MULTI CHAMBERS 审中-公开
公开(公告)号：US20180363913A1
公开(公告)日：2018-12-20
申请号：US15628257
申请日：2017-06-20
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Guy BOUCHARD , Kenneth PARKMAN
IPC分类号： F23R3/48 , F23R3/50 , F23R3/26
CPC分类号： F23R3/48 , F01D1/023 , F01D11/02 , F01D25/125 , F01D25/183 , F01M2011/021 , F02C7/06 , F02C7/28 , F05D2220/32 , F05D2230/237 , F05D2260/941 , F16C33/1025 , F16C33/106 , F16C33/1085 , F16N39/00 , F16N2210/12 , F23R3/26 , F23R3/50 , F23R2900/00
摘要： A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

3. 发明申请

US20180016922A1 Transition Duct Support Arrangement for a Gas Turbine Engine 审中-公开
公开(公告)号：US20180016922A1
公开(公告)日：2018-01-18
申请号：US15208219
申请日：2016-07-12
申请人： Siemens Energy, Inc.
发明人： Anthony L. Schiavo
IPC分类号： F01D9/02 , F23R3/42 , F23R3/60 , F23R3/48
CPC分类号： F01D9/023 , F23R3/425 , F23R3/48 , F23R3/60 , F23R2900/00005 , F23R2900/00017
摘要： A gas turbine engine has a crown locking device and a seal portion. The crown locking device and seal portion connect a transition duct to an inlet extension piece. The crown locking device and seal portion is located between a metallic integrated exit piece and a transition duct that is made of ceramic matrix composites.

4. 发明申请

US20180016921A1 DUCTING ARRANGEMENT WITH A CERAMIC LINER FOR DELIVERING HOT-TEMPERATURE GASES IN A COMBUSTION TURBINE ENGINE 审中-公开
公开(公告)号：US20180016921A1
公开(公告)日：2018-01-18
申请号：US15207716
申请日：2016-07-12
申请人： Siemens Energy, Inc.
发明人： Anthony L. Schiavo
IPC分类号： F01D9/02 , F23R3/42 , F23R3/60 , F23R3/48
CPC分类号： F01D9/023 , F05D2240/40 , F05D2250/141 , F05D2300/175 , F05D2300/20 , F05D2300/6033 , F23R3/007 , F23R3/425 , F23R3/60 , F23R2900/00005
摘要： A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.

5. 发明申请

US20170227228A1 CROSS IGNITION FLAME DUCT 审中-公开
公开(公告)号：US20170227228A1
公开(公告)日：2017-08-10
申请号：US15502638
申请日：2014-09-05
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Daniel W. Garan , Richard L. Thackway , David P. Holzapfel , Stephen A. Ramier , Charalambos Polyzopoulos , Kevin J. Spence , Joseph Scott Markovitz
IPC分类号： F23R3/48 , F23R3/46
摘要： A cross-flame duct (100) for connecting adjacent combustors (1, 2) together in a gas turbine to guard against flameout conditions within the combustors (1, 2), whereby the cross-flame duct (100) may include first and second ducts (102, 106) forming a slip joint to prevent stress from developing within the cross-flame duct (100) is disclosed. The cross-flame duct (100) remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct (100) and enhancing the useful life of the cross-flame duct (100) and associated components. The first and second ducts (102, 106) may also include cooling chambers (138, 156, 174) positioned between outer sleeves (122, 140) and inner housings (128, 146) and maintained with one or more standoffs (134, 152, 170) to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers (138, 156, 174) may be supplied with cooling fluids via one or more fluid ports (176) extending through the outer sleeves (122, 140) enabling air to flow through the cooling chambers (1138, 156, 174) and into the combustors (1, 2).

6. 发明申请

US20170059165A1 CMC CROSS-OVER TUBE 审中-公开
公开(公告)号：US20170059165A1
公开(公告)日：2017-03-02
申请号：US14839260
申请日：2015-08-28
申请人： Rolls-Royce High Temperature Composites Inc.
发明人： Sujit Nanda
IPC分类号： F23R3/48 , F16L23/12
CPC分类号： F23R3/48 , F16L49/04
摘要： A fluid conduit may be provided comprising a ceramic matrix composite (CMC) cross-over tube and a flange. The CMC cross-over tube may comprise a first end configured to extend into a first combustor liner of a gas turbine engine, and a second end configured to extend into a second combustor liner of a gas turbine engine. The interior of the CMC cross-over tube may define a passageway. The flange may extend outwardly from an outer surface of the CMC cross-over tube. The flange may be configured to engage at least one of the first combustor liner and the second combustor liner.
摘要翻译：可以提供流体导管，其包括陶瓷基复合（CMC）交叉管和凸缘。 CMC交叉管可以包括构造成延伸到燃气涡轮发动机的第一燃烧器衬套中的第一端和构造成延伸到燃气涡轮发动机的第二燃烧器衬套中的第二端。 CMC交叉管的内部可以限定通道。凸缘可以从CMC交叉管的外表面向外延伸。凸缘可以被构造成接合第一燃烧器衬套和第二燃烧器衬套中的至少一个。

7. 发明申请

US20160348911A1 W501 D5/D5A DF42 COMBUSTION SYSTEM 审中-公开
标题翻译： W501 D5 / D5A DF42燃烧系统
公开(公告)号：US20160348911A1
公开(公告)日：2016-12-01
申请号：US14566125
申请日：2014-12-10
申请人： Siemens Energy, Inc.
发明人： Charalambos Polyzopoulos , Richard L. Thackway , Stephen A. Ramier , Vinayak V. Barve , Khalil Farid Abou-Jaoude , Daniel W. Garan , David P. Holzapfel , Kevin J. Spence , Joseph Scott Markovitz , Blake R. Cotten , Urmi B. Dave , Vaidyanathan Krishnan , Michael C. Escandon
IPC分类号： F23R3/00 , F23R3/48 , F02C3/04
CPC分类号： F23R3/002 , F01D9/023 , F02C3/04 , F05B2240/35 , F05B2240/40 , F05D2240/35 , F23R3/06 , F23R3/16 , F23R3/28 , F23R3/36 , F23R3/48 , F23R2900/03041 , F23R2900/03043 , Y02T50/675
摘要： An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.
摘要翻译：公开了一种用于燃气涡轮发动机的改进的燃烧部分。燃料喷嘴包括提供油燃料和冷却水的改进喷射模式的新特征，从而更好地控制燃烧气体温度和NOx排放，并且消除了冷却水在燃烧室壁上的冲击。新的燃烧器包括板翅设计，其提供改进的冷却，同时燃烧器还可以更有效地利用可用的冷却空气并且具有改善的部件寿命。新的过渡部件具有更平滑的形状，其减少燃烧气体流动的停滞和燃烧气体在过渡部件壁上的冲击，改进的材料和局部厚度增加以获得更好的耐久性，以及改进的冷却特征以更有效地利用冷却空气。

8. 发明授权

US09464809B2 Gas turbine combustor and operating method for gas turbine combustor 有权
标题翻译：燃气轮机燃烧器和燃气轮机燃烧器的操作方法
公开(公告)号：US09464809B2
公开(公告)日：2016-10-11
申请号：US13933227
申请日：2013-07-02
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Kazuki Abe , Tomomi Koganezawa , Takeo Saito , Keisuke Miura
IPC分类号： F23R3/28 , F02C7/22 , F02C7/26 , F23R3/12 , F23R3/16 , F23R3/48 , F23R3/34 , F23D14/24
CPC分类号： F23R3/286 , F02C7/22 , F02C7/26 , F23D14/24 , F23N2027/02 , F23R3/12 , F23R3/16 , F23R3/28 , F23R3/346 , F23R3/48
摘要： Disclosed is a gas turbine combustor equipped with a burner constructed to fire a plurality of combustors at the same time at a fuel/air ratio suitable for gas turbine ignition. A plurality of supports mounted for fixing an air injection hole plate to the combustor are provided at substantially the same phase position as that of cross fire tubes, and combustion air allocations are adjusted. Thus, flame propagation during gas turbine ignition is accelerated and all combustor cans are fired. In addition, porous plates are disposed downstream of the supports and the combustion air allocations are readjusted. Furthermore, air injection holes proximate to the cross fire tubes are particularly reduced in diameter to further adjust the combustion air allocations.
摘要翻译：公开了一种装备有燃烧器的燃气轮机燃烧器，该燃烧器构造成以适于燃气轮机点火的燃料/空气比同时燃烧多个燃烧器。多个安装用于将空气喷射孔板固定到燃烧器的支撑件设置在与防火管基本相同的相位位置，并且调节燃烧空气分配。因此，燃气轮机点火期间的火焰传播被加速并且所有燃烧器罐都被点燃。此外，多孔板设置在支撑件的下游，并且重新调节燃烧空气分配。此外，靠近十字火管的空气喷射孔的直径特别减小，以进一步调节燃烧空气分配。

9. 发明申请

US20140137536A1 SUPER TELESCOPING CROSS-FIRE TUBE AND METHOD OF ASSEMBLING A COMBUSTOR STRUCTURE 审中-公开
标题翻译：超级冲击火管和组装燃烧器结构的方法
公开(公告)号：US20140137536A1
公开(公告)日：2014-05-22
申请号：US13682965
申请日：2012-11-21
申请人： GENERAL ELECTRIC COMPANY
发明人： Joel Russell Cloninger , Patrick Benedict Melton , Lucas John Stoia , James Harold Westmoreland
IPC分类号： F23R3/48
CPC分类号： F23R3/48
摘要： A super-telescoping cross-fire tube includes a cross-fire tube including a first portion and a second portion in mating engagement, the cross-fire tube extending from a first end region to a second end region for fluidly connecting a combustor chamber and an adjacent combustor chamber. Also included is an outer shield spaced radially outwardly and surrounding at least a portion of the cross-fire tube. Further included is a spring extending from proximate the first end region to the second end region and disposed between the cross-fire tube and the outer shield, wherein the cross-fire tube is telescopingly moveable between a first position and a second position.
摘要翻译：超伸缩式横火管包括交叉火管，其包括配合接合的第一部分和第二部分，所述交叉火焰管从第一端部区域延伸到第二端部区域，用于流体连接燃烧室和相邻的燃烧室。还包括外部屏蔽件，其径向向外隔开并且围绕交叉火管的至少一部分。还包括从靠近第一端部区域延伸到第二端部区域并且设置在交叉火焰管和外部护罩之间的弹簧，其中交叉火焰管可在第一位置和第二位置之间伸缩移动。

10. 发明申请

US20140123619A1 COMBUSTOR ASSEMBLY 有权
标题翻译：燃烧器总成
公开(公告)号：US20140123619A1
公开(公告)日：2014-05-08
申请号：US13672248
申请日：2012-11-08
申请人： GENERAL ELECTRIC COMPANY
发明人： Richard Martin DiCintio
IPC分类号： F23R3/48 , B23P11/00 , F23R3/60
CPC分类号： F23R3/48 , F16L37/088 , F23C6/02 , F23R3/60 , Y10T29/49323
摘要： According to one aspect of the invention, a combustor assembly for a pair of adjacent combustors includes a first passage formed in a liner of a first combustor and a flow sleeve disposed outside the liner of the first combustor, wherein the flow sleeve includes a window and a second passage aligned with the first passage. The assembly also includes a cross-fire tube disposed in the first passage to provide fluid communication between the first combustor and a second combustor and a retention clip disposed through the window to urge the cross-fire tube against an outer surface of the liner to enable the cross-fire tube to receive fluid through the first passage.
摘要翻译：根据本发明的一个方面，用于一对相邻的燃烧器的燃烧器组件包括形成在第一燃烧器的衬套中的第一通道和设置在第一燃烧器的衬套外部的流动套筒，其中流动套筒包括窗口和与第一通道对准的第二通道。组件还包括布置在第一通道中的交叉火管，以在第一燃烧器和第二燃烧器之间提供流体连通，以及通过窗口设置的保持夹，以将交叉火管推压到衬套的外表面上以使得能够交叉火焰管通过第一通道接收流体。

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