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21. 发明申请

US20130058756A1 FLOW DISCOURAGER INTEGRATED TURBINE INTER-STAGE U-RING 有权
标题翻译：流量传感器集成涡轮机内部U形环
公开(公告)号：US20130058756A1
公开(公告)日：2013-03-07
申请号：US13226547
申请日：2011-09-07
申请人： Kok-Mun THAM , Ching-Pang LEE , Abdullatif M. CHEHAB , Gm Salam AZAD , Shantanu P. MHETRAS , Manjit SHIVANAND , Vincent P. LAURELLO , Christopher RAWLINGS
发明人： Kok-Mun THAM , Ching-Pang LEE , Abdullatif M. CHEHAB , Gm Salam AZAD , Shantanu P. MHETRAS , Manjit SHIVANAND , Vincent P. LAURELLO , Christopher RAWLINGS
IPC分类号： F04D29/58 , F01D1/02
CPC分类号： F01D11/001 , F01D11/04
摘要： A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).
摘要翻译：一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。转子凸缘（41i，41o）从转子盘（9-1）延伸。内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。

22. 发明申请

US20120007318A1 SEAL INCLUDING FLEXIBLE SEAL STRIPS 有权
标题翻译：密封包括柔性密封条
公开(公告)号：US20120007318A1
公开(公告)日：2012-01-12
申请号：US12832141
申请日：2010-07-08
申请人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
发明人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
IPC分类号： F02F11/00 , F16J15/44
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译：一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。密封构件包括多个柔性密封条。每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的轴。密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

23. 发明申请

US20110247346A1 COOLING FLUID METERING STRUCTURE IN A GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机冷却流量计结构
公开(公告)号：US20110247346A1
公开(公告)日：2011-10-13
申请号：US12758069
申请日：2010-04-12
申请人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
发明人： Keith D. Kimmel , Vincent P. Laurello , Todd Ebert
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/081 , F05D2260/221
摘要： A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, structure defining at least one bypass passage in fluid communication with the supply of cooling fluid for supplying cooling fluid from the supply of cooling fluid, and metering structure located at an outlet of the at least one bypass passage. The metering structure includes at least one flow passageway extending therethrough at an angle to a central axis of the engine for permitting cooling fluid in the bypass passage to pass into a turbine rim cavity. The cooling fluid flowing out of the flow passageway has a velocity component in a direction tangential to the circumferential direction in the same direction as a rotation direction of the shaft.
摘要翻译：燃气涡轮发动机包括冷却流体供应源，旋转轴结构，其限定至少一个旁路通道，其与冷却流体供应流体连通，用于从冷却流体供应源供应冷却流体;以及计量结构，位于出口处所述至少一个旁通通道。计量结构包括至少一个流动通道，其以与发动机的中心轴线成一定角度的方式延伸，以允许旁路通道中的冷却流体进入涡轮机边缘腔。从流动通道流出的冷却流体在与轴的旋转方向相同的方向上具有与圆周方向相切的方向的速度分量。

24. 发明授权

US4648792A Stator vane support assembly 失效
标题翻译：定子叶片支撑组件
公开(公告)号：US4648792A
公开(公告)日：1987-03-10
申请号：US728951
申请日：1985-04-30
申请人： Walter J. Baran, Jr. , Gary F. Chaplin , Vincent P. Laurello
发明人： Walter J. Baran, Jr. , Gary F. Chaplin , Vincent P. Laurello
IPC分类号： F01D11/08 , F01D25/24 , F01D25/28
CPC分类号： F01D11/08 , F01D25/246 , F05D2240/11
摘要： A stage of circumferentially disposed turbine stator vane clusters and arcuate, circumferentially disposed segments of a rotor outer air seal disposed on one side of the stator stage is secured to an annular attachment ring which is integral with a surrounding turbine case. The outer seal segments are trapped axially between stator vane clusters and the radially inner ends of arcuate support segments, and are also radially supported thereby. The radially inner ends of the support segments are trapped axially between the stator vane clusters and the annular attachment ring, and are also supported radially thereby. This boltless attachment reduces the number of parts while providing strong radially support and accurate radial location for the seal segments.
摘要翻译：设置在定子台一侧的转子外部空气密封件的周向布置的涡轮机定子叶片组和圆弧形周向设置的段被固定到与周围涡轮壳体成一体的环形附接环。外部密封段被轴向地夹在定子叶片组和弧形支撑段的径向内端之间，并由此径向支撑。支撑段的径向内端被轴向地捕获在定子叶片簇和环形附接环之间，并且也被径向支撑。这种无螺栓附件减少了部件数量，同时为密封段提供了强大的径向支撑和精确的径向位置。

25. 发明授权

US4236869A Gas turbine engine having bleed apparatus with dynamic pressure recovery 失效
标题翻译：具有动压回收的排放装置的燃气涡轮发动机
公开(公告)号：US4236869A
公开(公告)日：1980-12-02
申请号：US864192
申请日：1977-12-27
申请人： Vincent P. Laurello
发明人： Vincent P. Laurello
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/081 , Y02T50/676
摘要： A gas turbine engine has conduits leading from the compressor to the turbine for bleeding a portion of compressor air through the turbine blades for cooling or other purposes. A radial pump in the conduits formed by a tangential accelerator and a rotating diffuser transmits the air from the non-rotating environment in the engine to the rotating environment of the turbine rotor. The tangential accelerator accelerates the bleed air to a tangential speed higher than that of the rotor, and the radial diffuser is designed to recover the dynamic pressure or relative velocity of the air over the rotor.
摘要翻译：燃气涡轮发动机具有从压缩机引导到涡轮机的导管，用于使一部分压缩机空气通过涡轮机叶片用于冷却或其它目的。由切向加速器和旋转扩散器形成的导管中的径向泵将空气从发动机中的非旋转环境传递到涡轮转子的旋转环境。切向加速器将排气加速到比转子高的切向速度，并且径向扩散器被设计成恢复转子上的空气的动态压力或相对速度。

26. 发明授权

US09494081B2 Turbine engine shutdown temperature control system with an elongated ejector 有权
标题翻译：涡轮发动机关闭温度控制系统带有细长的喷射器
公开(公告)号：US09494081B2
公开(公告)日：2016-11-15
申请号：US13890297
申请日：2013-05-09
申请人： Vincent P. Laurello
发明人： Vincent P. Laurello
IPC分类号： F02C7/18 , F02C7/24 , F02C7/16 , F01D25/12 , F01D25/14
CPC分类号： F02C7/24 , F01D25/12 , F01D25/14 , F02C7/16 , F02C7/18 , F05D2260/231 , F05D2260/608
摘要： A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.
摘要翻译：公开了一种涡轮发动机关闭温度控制系统，其被配置成在压缩机和涡轮叶片组件周围的空腔内促进恒定的空气温度，以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。涡轮发动机关闭温度控制系统可以包括一个或多个壳体温度控制壳体，其沿壳体的外表面在外壳的外径处和壳体的上侧区域沿着内表面延伸。上侧区域可以位于壳体的水平延伸的中心线上方。流体可以从壳体温度控制壳体中的一个或多个排气槽排出，以将燃气涡轮发动机关闭之后的壳体的上侧区域与壳体内的热气体的浮力影响隔离。

27. 发明授权

US08939711B2 Outer rim seal assembly in a turbine engine 有权
标题翻译：涡轮发动机中的外轮缘密封组件
公开(公告)号：US08939711B2
公开(公告)日：2015-01-27
申请号：US13768561
申请日：2013-02-15
申请人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, Jr.
发明人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, Jr.
IPC分类号： F01D25/12 , F01D5/08 , F01D11/04
CPC分类号： F01D25/12 , F01D5/081 , F01D11/001 , F01D11/04 , F01D11/122 , F05D2260/202
摘要： A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.
摘要翻译：在涡轮发动机中的热气体路径和盘腔之间的密封组件包括不可旋转的叶片组件，其包括一排叶片和内部护罩，与叶片组件相邻的可旋转刀片组件，并且包括一排叶片和形成涡轮机转子的一部分的涡轮盘，以及径向位于热气路径和盘腔之间的环形翼部件。翼构件大致轴向地从叶片组件延伸到叶片组件，并且包括从其径向内表面延伸到其径向外表面的多个周向间隔开的流动通道。在发动机运行期间，流动通道将冷却流体从盘腔抽吸到热气路径。

28. 发明申请

US20140331637A1 TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH AN ELONGATED EJECTOR 有权
标题翻译：涡轮发动机关闭温度控制系统
公开(公告)号：US20140331637A1
公开(公告)日：2014-11-13
申请号：US13890297
申请日：2013-05-09
申请人： VINCENT P. LAURELLO
发明人： VINCENT P. LAURELLO
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F01D25/12 , F01D25/14 , F02C7/16 , F02C7/18 , F05D2260/231 , F05D2260/608
摘要： A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.
摘要翻译：公开了一种涡轮发动机关闭温度控制系统，其被配置成在压缩机和涡轮叶片组件周围的空腔内促进恒定的空气温度，以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。涡轮发动机关闭温度控制系统可以包括一个或多个壳体温度控制壳体，其沿壳体的外表面在外壳的外径处和壳体的上侧区域沿着内表面延伸。上侧区域可以位于壳体的水平延伸的中心线上方。流体可以从壳体温度控制壳体中的一个或多个排气槽排出，以将燃气涡轮发动机关闭之后的壳体的上侧区域与壳体内的热气体的浮力影响隔离。

29. 发明申请

US20140311157A1 VANE CARRIER TEMPERATURE CONTROL SYSTEM IN A GAS TURBINE ENGINE 有权
标题翻译：气动涡轮发动机中的VANE载体温度控制系统
公开(公告)号：US20140311157A1
公开(公告)日：2014-10-23
申请号：US13719269
申请日：2012-12-19
申请人： Vincent P. Laurello , Kok-Mun Tham
发明人： Vincent P. Laurello , Kok-Mun Tham
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F02C6/08
摘要： A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air.
摘要翻译：用于燃气涡轮发动机的叶片载体温度控制系统包括第一冷却空气源，第二冷却空气源和空气温度控制系统。第一冷却空气源将从发动机的压缩机部分提取的叶片载体冷却空气的第一部分提供给在发动机的涡轮部分内支撑多排叶片的叶片载体的第一部分。第二冷却空气源将从压缩机部分抽出的叶片载体冷却空气的第二部分提供给沿着由通过涡轮部分的热作业气体流动的方向限定的轴向方向与第一部分间隔开的叶片载体的第二部分。空气温度控制系统控制叶片承载件冷却空气的第一和第二部分中的至少一个的温度。

30. 发明申请

US20140234076A1 OUTER RIM SEAL ASSEMBLY IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机中的外部密封组件
公开(公告)号：US20140234076A1
公开(公告)日：2014-08-21
申请号：US13768561
申请日：2013-02-15
申请人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, JR.
发明人： Ching-Pang Lee , Kok-Mun Tham , Manjit Shivanand , Vincent P. Laurello , Gm Salam Azad , Nicholas F. Martin, JR.
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/081 , F01D11/001 , F01D11/04 , F01D11/122 , F05D2260/202
摘要： A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.
摘要翻译：在涡轮发动机中的热气体路径和盘腔之间的密封组件包括不可旋转的叶片组件，其包括一排叶片和内部护罩，与叶片组件相邻的可旋转刀片组件，并且包括一排叶片和形成涡轮机转子的一部分的涡轮盘，以及径向位于热气路径和盘腔之间的环形翼部件。翼构件大致轴向地从叶片组件延伸到叶片组件，并且包括从其径向内表面延伸到其径向外表面的多个周向间隔开的流动通道。在发动机运行期间，流动通道将冷却流体从盘腔抽吸到热气路径。

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