公开(公告)号：US09810081B2

公开(公告)日：2017-11-07

申请号：US12813658

申请日：2010-06-11

申请人： Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

发明人： Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

IPC分类号： F01D9/02 ,  F23R3/06 ,  F02K1/82 ,  F23R3/00 ,  F23M20/00

CPC分类号： F01D9/023 ,  F02K1/822 ,  F05D2250/13 ,  F05D2250/324 ,  F05D2260/202 ,  F23M20/005 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00014 ,  F23R2900/03042 ,  Y02T50/675

摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.

公开(公告)号：US09546558B2

公开(公告)日：2017-01-17

申请号：US12832116

申请日：2010-07-08

申请人： Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

发明人： Ching-Pang Lee ,  Danning You ,  Reinhard Schilp ,  Chander Prakash

IPC分类号： F02C7/12 ,  F01D9/02 ,  F23R3/06

CPC分类号： F01D9/023 ,  F02C7/12 ,  F05D2260/96 ,  F23R3/06 ,  F23R2900/00014

摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.

摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的峰（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。

公开(公告)号：US09410484B2

公开(公告)日：2016-08-09

申请号：US13945983

申请日：2013-07-19

申请人： Reinhard Schilp

发明人： Reinhard Schilp

IPC分类号： F23R3/00 ,  F02C7/12 ,  F01D9/02

CPC分类号： F02C7/12 ,  F01D9/023 ,  F05D2260/963 ,  F23R3/002 ,  F23R2900/00014

摘要： A cover (54, 54A-B) enclosing with clearance (65) an acoustic damping resonator (24) on a working gas path liner (22) of a gas turbine component (28). The cover includes a coolant inlet chamber (56, 56B) with a top wall (58, 58B) that is closer to the liner than a top wall (32) of the resonator, and extends upstream from the resonator relative to the working gas flow (48). Compressed air (26) surrounds the cover at a higher pressure than the working gas and flows (44) into and through the coolant inlet chamber, then through holes (34) in the resonator, then exits through holes (38) the liner into the working gas. The coolant inlet chamber directs the flow of compressed air over a weld (50) of the upstream wall (40) of the resonator to cool it. The cover may be formed as a box (57) or a sleeve (69).

摘要翻译： 在燃气轮机部件（28）的工作气体通道衬套（22）上包围有间隙（65）的声阻尼谐振器（24）的盖（54,5A-B）。 所述盖包括具有顶壁（58,58B）的冷却剂入口室（58,58B），所述顶壁（58,58B）比所述谐振器的顶壁（32）更靠近所述衬套，并且相对于所述工作气体流在所述谐振器的上游延伸 （48）。 压缩空气（26）在比工作气体高的压力下围绕盖并且流入（44）进入冷却剂入口室，然后通过谐振器中的通孔（34），然后通过孔（38）将衬管排出到 工作气体 冷却剂入口室将压缩空气流引导到谐振器的上游壁（40）的焊缝（50）上以使其冷却。 盖可以形成为盒（57）或套（69）。

公开(公告)号：US09291102B2

公开(公告)日：2016-03-22

申请号：US13226529

申请日：2011-09-07

申请人： Timothy A. Fox ,  Reinhard Schilp

发明人： Timothy A. Fox ,  Reinhard Schilp

IPC分类号： F23R3/28 ,  F02C7/22 ,  F23R3/32

CPC分类号： F02C7/222 ,  F23R3/286 ,  F23R3/32

摘要： A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.

摘要翻译： 一种燃气轮机燃烧器组件，包括燃烧器衬套和布置成在燃烧器衬套内延伸的环形阵列的多个燃料喷嘴组件。 燃料喷嘴组件各自包括与旋流器组件一体的燃料喷嘴体，并且旋流器组件各自包括喇叭口结构，以将空气径向向内转动以通过旋流器组件。 每个喇叭口结构的径向外部去除部分限定了与燃烧器衬套的内表面间隔开的周向直径，并且设置在燃烧器衬套和钟形结构的外围直径的去除部分之间延伸的界面环。

公开(公告)号：US20120198854A1

公开(公告)日：2012-08-09

申请号：US13023710

申请日：2011-02-09

申请人： Reinhard Schilp ,  Muzaffer Sutcu

发明人： Reinhard Schilp ,  Muzaffer Sutcu

IPC分类号： F23R3/46

CPC分类号： F23R3/06 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00014 ,  F23R2900/03042 ,  F23R2900/03044

摘要： A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator.

摘要翻译： 燃烧器衬套具有形成在其上的多个谐振器。 每个谐振器具有径向外壁和至少一个侧壁。 外壁可以没有孔。 每个谐振器具有限定在外壁，至少一个侧壁和衬套的外周表面之间的内腔。 每个谐振器的至少一个侧壁围绕基本上径向延伸穿过衬垫的多个孔的子集。 多个冷却通道在衬套内大致纵向延伸。 每个冷却通道具有与衬套的外部流体连通的入口和与相应一个谐振器的内腔流体连通的出口。 诸如压缩机空气的冷却剂可以沿着冷却通道进入和流动，从而冷却衬管并吹扫谐振器的内腔。

公开(公告)号：US20100319350A1

公开(公告)日：2010-12-23

申请号：US12489775

申请日：2009-06-23

申请人： Kyle L. Landry ,  Reinhard Schilp

发明人： Kyle L. Landry ,  Reinhard Schilp

IPC分类号： F02C7/22

CPC分类号： F02C7/22 ,  F23R3/14 ,  F23R3/286 ,  F23R3/343

摘要： A fuel injector assembly includes a fuel injector that provides fuel to be mixed with air for ignition in a combustor. The fuel injector assembly includes a fuel shroud and a plurality of spanning members. The spanning members are spaced circumferentially on the fuel shroud between the fuel shroud and a base plate assembly, which supports the fuel injector assembly within the combustor. The spanning members space the fuel shroud from the base plate assembly such that an annular gap is formed therebetween. The gap permits a flow of purge air therethrough to be mixed with compressed air entering the fuel shroud and with fuel provided by the fuel injector. The spanning members comprise elongate members having upstream ends that are circumferentially offset from opposed downstream ends so that the spanning members provide tangential velocity to the purge air flowing through the annular gap.

摘要翻译： 燃料喷射器组件包括燃料喷射器，其提供与空气混合的燃料以在燃烧器中点火。 燃料喷射器组件包括燃料罩和多个跨接构件。 跨越构件在燃料罩之间的燃料罩上周向间隔开，燃料罩与底板组件之间，燃料喷射器组件支撑燃烧器内的燃料喷射器组件。 跨越构件将燃料罩从基板组件中间隔开，使得它们之间形成环形间隙。 间隙允许吹扫空气流过其中以与进入燃料罩的压缩空气和由燃料喷射器提供的燃料混合。 跨越构件包括细长构件，其具有周向地从相对的下游端偏移的上游端，使得跨越构件向流过环形间隙的吹扫空气提供切向速度。

公开(公告)号：US20100071374A1

公开(公告)日：2010-03-25

申请号：US12236667

申请日：2008-09-24

申请人： Timothy Fox ,  Reinhard Schilp

发明人： Timothy Fox ,  Reinhard Schilp

IPC分类号： F02C7/22 ,  B05B1/00

CPC分类号： F02C7/22 ,  F05D2250/25 ,  F05D2260/20 ,  F23R3/28 ,  F23R3/34

摘要： A fuel nozzle for delivery of fuel to a gas turbine engine. The fuel nozzle includes an outer nozzle wall and a center body located centrally within the nozzle wall. A gap is defined between an inner wall surface of the nozzle wall and an outer body surface of the center body for providing fuel flow in a longitudinal direction from an inlet end to an outlet end of the fuel nozzle. A turbulating feature is defined on at least one of the central body and the inner wall for causing at least a portion of the fuel flow in the gap to flow transverse to the longitudinal direction. The gap is effective to provide a substantially uniform temperature distribution along the nozzle wall in the circumferential direction.

摘要翻译： 一种用于将燃料输送到燃气涡轮发动机的燃料喷嘴。 燃料喷嘴包括位于喷嘴壁中心的外喷嘴壁和中心体。 在喷嘴壁的内壁表面和中心体的外表面之间限定了间隙，用于在燃料喷嘴的入口端到出口端的纵向方向上提供燃料流。 在中心体和内壁中的至少一个上限定了一个紊流特征，用于使间隙中的燃料流的至少一部分横向于纵向方向流动。 该间隙有效地沿圆周方向沿着喷嘴壁提供基本均匀的温度分布。