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公开(公告)号：EP1108901A2
公开(公告)日：2001-06-20
申请号：EP00311266.1
申请日：2000-12-15
发明人： Rainous, Edward Atwood , Barber, Daniel John , Vickers, Edward Charles , Maue, Gregory Paul , Cody, William Edward , Yee, Sharon Lisa , McMahan, Kevin Weston
IPC分类号： F16B37/08
CPC分类号： F01D25/246 , F01D11/001 , F04D29/164 , F16B5/0241
摘要： A retainer (82), in an exemplary embodiment of the invention, is used in a gas turbine engine inter-stage seal assembly to retain an annular seal ring flange (50) of a seal ring (48) against an annular platform flange (60) extending radially inwardly from an inner platform (30) of an annular nozzle stage having nozzle vanes (26). The retainer includes a body having a central portion (92) through which a bore (88) is formed around a bore axis (89) and a central tab (94) extends radially outwardly from the central portion (92) with respect to the bore axis (89). First and second arms (97 and 98), respectively, extend in opposite respective first and second tangential directions, with respect to the bore axis (89), away from the central portion (92) and each other. Axial spacers (104) extend aftwardly from first and second free ends (106 and 108) of the first and second arms (97 and 98), respectively and anti-rotation feet with rounded ends depend from the first and second free ends (106 and 108) in an opposite direction from which the central tab (94) extends. A pedestal assembly (110) extends aft from the central portion (92) and is located aft of the central tab. The retainer (82) is an integrally cast unit.
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公开(公告)号：EP2592232B1
公开(公告)日：2019-06-26
申请号：EP12182706.7
申请日：2012-09-03
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公开(公告)号：EP2592231B1
公开(公告)日：2019-06-26
申请号：EP12182705.9
申请日：2012-09-03
发明人： Flanagan, James Scott , LeBegue, Jeffrey Scott , McMahan, Kevin Weston , Dillard, Daniel Jackson , Pentecost, Ronnie Ray
IPC分类号： F01D9/02
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公开(公告)号：EP2375163A3
公开(公告)日：2017-11-22
申请号：EP11161159.6
申请日：2011-04-05
摘要： A combustor section (10) is provided and includes a segmented annular manifold (20) mounted upstream from a fuel nozzle support (60) in a section of a passage through which an oxidizer flows, each segment (201,202,203,204) of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.
摘要翻译： 提供燃烧器部分（10），并且包括分段环形歧管（20），所述分段环形歧管安装在氧化剂流过的通道的区段中的燃料喷嘴支撑件（60）的上游，歧管的每个部分（201,202,203,204）基本上轴向地 对齐并且包括内部容纳燃料的主体，所述主体被形成为限定喷射孔，燃料通过所述喷射孔被喷射到氧化剂流过燃料喷嘴支撑件上游的通道中。
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公开(公告)号：EP2500523A3
公开(公告)日：2017-06-14
申请号：EP12158160.7
申请日：2012-03-06
CPC分类号： F01D9/023 , F01D25/12 , F02C7/20 , F05D2260/201 , F05D2260/202 , F05D2260/2322 , F23R3/60 , F23R2900/00012 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： An aft frame (50) and a method for cooling an aft frame (50) are disclosed. In one embodiment, an aft frame (50) for a transition piece (26) in a combustor (16) is disclosed. The combustor (16) includes the transition piece (26) and an impingement sleeve (34) at least partially defining a flow path (36) therebetween. The aft frame (50) includes a body (60) and a generally radially extending cooling passage (70) defined in the body (60), the cooling passage (70) comprising a first end (72) configured to accept a coolant (52). The aft frame (50) further includes an exhaust passage (80) defined in the body (60), the exhaust passage (80) including a first end (82) in communication with the cooling passage (70) and a second end (84) configured for communication with the flow path (36) for flowing the coolant (52) therethrough.
摘要翻译： 公开了一种后架（50）和一种用于冷却后架（50）的方法。 在一个实施例中，公开了用于燃烧器（16）中的过渡件（26）的后架（50）。 燃烧器（16）包括过渡件（26）和至少部分地限定其间的流动路径（36）的冲击套筒（34）。 所述后架（50）包括主体（60）和限定在所述主体（60）中的大致径向延伸的冷却通道（70），所述冷却通道（70）包括第一端部（72），所述第一端部构造成接收冷却剂 ）。 所述后架（50）还包括限定在所述主体（60）中的排气通道（80），所述排气通道（80）包括与所述冷却通道（70）连通的第一端部（82）和第二端部 ），其被构造用于与流动路径（36）连通以使冷却剂（52）流过其中。
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26.发明授权Can-annular combustor array for a gas turbine having oval or elliptical can heads twisted among themselves 有权管环形燃烧室对于具有相互捻卵形或椭圆形燃烧器头的燃气涡轮
公开(公告)号：EP2733421B1
公开(公告)日：2017-03-15
申请号：EP13184858.2
申请日：2013-09-17
CPC分类号： F02C7/24 , F23C5/08 , F23R3/46 , F23R2900/00014
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公开(公告)号：EP2660519B1
公开(公告)日：2015-12-16
申请号：EP13157044.2
申请日：2013-02-27
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公开(公告)号：EP2530247A3
公开(公告)日：2014-06-04
申请号：EP12170622.0
申请日：2012-06-01
CPC分类号： F01D9/023 , F05D2240/35 , F05D2250/42 , F05D2260/30 , F23R3/60
摘要： A mount device (100) and mounting assembly (102) for a turbine system (10) are disclosed. The mounting assembly (102) includes a transition duct (50) extending between a fuel nozzle and a turbine section. The transition duct (50) has an inlet (52), an outlet (54), and a passage (56) extending between the inlet (52) and the outlet (54) and defining a longitudinal axis (90), a radial axis (94), and a tangential axis (92). The outlet (54) of the transition duct (50) is offset from the inlet (52) along the longitudinal axis (90) and the tangential axis (92). The mounting assembly (102) further includes a mount device (100) connecting the transition duct (50) to the turbine section. The mount device (100) is configured to allow movement of the outlet (54) about at least two axes.
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29.发明公开Combustor assembly for use in a turbine engine and methods of fabricating same 有权一种用于在燃气涡轮发动机及其制造方法使用的燃烧室组件及其
公开(公告)号：EP2489937A3
公开(公告)日：2013-11-27
申请号：EP12155362.2
申请日：2012-02-14
CPC分类号： F23R3/002 , F01D9/023 , F05D2260/202 , F23R3/60 , F23R2900/03042 , Y02T50/676 , Y10T29/49346
摘要： A combustor assembly (26) includes a combustor liner (38) defining a combustion chamber (36) there within, and a transition piece (64) including a forward portion (76) coupled to the combustion liner and an aft portion (68) extending from the forward portion, the aft portion including a transition piece frame (66). The transition piece frame includes an upstream surface (98), a downstream surface (100), and a radially inner surface (102) extending between the upstream and downstream surfaces, the radially inner surface comprises a leading edge (110) extending between the radially inner surface and the upstream surface, and a plurality of first cooling passages (132) extending from the upstream surface to the downstream surface, each of the first cooling passages oriented obliquely with respect to the leading edge from the upstream surface towards the downstream surface.
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公开(公告)号：EP2657608A2
公开(公告)日：2013-10-30
申请号：EP13156623.4
申请日：2013-02-25
摘要： A combustor includes an end cap (52) that extends radially across at least a portion of the combustor, wherein the end cap (52) comprises an upstream surface (64) axially separated from a downstream surface (66). A shroud (68) circumferentially surrounds at least a portion of the end cap (52), wherein the shroud (68) at least partially defines a fuel plenum (70) between the upstream surface (64) and the downstream surface (66). A combustion chamber (38) downstream from the end cap (52) defines a longitudinal axis. A plurality of tubes (50) extend from the upstream surface (64) through the downstream surface (66) of the end cap (52) to provide fluid communication through the end cap (52) to the combustion chamber (38). A transition duct (40) circumferentially surrounds at least a portion of the combustion chamber (38) downstream from the end cap (52) and curves tangentially from the longitudinal axis.
摘要翻译： 燃烧器包括径向延伸穿过燃烧器的至少一部分的端盖（52），其中端盖（52）包括与下游表面（66）轴向分离的上游表面（64）。 护罩（68）周向地围绕端盖（52）的至少一部分，其中护罩（68）至少部分地限定在上游表面（64）和下游表面（66）之间的燃料增压室（70）。 端盖（52）下游的燃烧室（38）限定纵向轴线。 多个管（50）从上游表面（64）延伸穿过端盖（52）的下游表面（66），以提供通过端盖（52）到燃烧室（38）的流体连通。 过渡管道（40）周向地围绕端盖（52）下游的燃烧室（38）的至少一部分并且与纵向轴线相切地弯曲。
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