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    Gas turbine engine with improved cooling between turbine rotor disk elements
    1.
    发明授权
    Gas turbine engine with improved cooling between turbine rotor disk elements 有权
    涡轮发动机具有改进的涡轮转子盘元件之间的冷却

    公开(公告)号：US09017013B2

    公开(公告)日：2015-04-28

    申请号：US13367728

    申请日：2012-02-07

    申请人： Vincent P. Laurello ,  Kok-Mun Tham

    发明人： Vincent P. Laurello ,  Kok-Mun Tham

    IPC分类号： F01D5/14 ,  F04D31/00 ,  F01D25/24 ,  F01D5/08

    CPC分类号： F01D5/087 ,  F01D5/3038 ,  F01D11/001 ,  F01D11/006

    摘要： A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component.

    摘要翻译： 提供一种燃气涡轮发动机，包括能够旋转的前转子盘和叶片组件; 能够旋转的后转子盘和叶片组件; 以及位于前转子盘和叶片组件和后转子盘和叶片组件之间的一排叶片。 叶片排和前转子盘和叶片组件可以限定前腔。 叶片排可以包括至少一个定子叶片，其包括：主体和包括盖的内护罩结构。 盖可以包括接收冷却空气的第一内腔。 盖子还可以包括至少一个冷却流道。 从冷却流路流动的冷却空气具有切向速度分量。

    Flow discourager integrated turbine inter-stage U-ring
    4.
    发明授权
    Flow discourager integrated turbine inter-stage U-ring 有权
    整流式涡轮机级U型环

    公开(公告)号：US09062557B2

    公开(公告)日：2015-06-23

    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： F01D1/02 ,  F01D11/00 ,  F01D11/04

    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）。

    GAS TURBINE ENGINE WITH IMPROVED COOLING BETWEEN TURBINE ROTOR DISK ELEMENTS
    5.
    发明申请
    GAS TURBINE ENGINE WITH IMPROVED COOLING BETWEEN TURBINE ROTOR DISK ELEMENTS 有权
    在涡轮转子盘元件之间改进冷却的气体涡轮发动机

    公开(公告)号：US20130202408A1

    公开(公告)日：2013-08-08

    申请号：US13367728

    申请日：2012-02-07

    申请人： Vincent P. Laurello ,  Kok-Mun Tham

    发明人： Vincent P. Laurello ,  Kok-Mun Tham

    IPC分类号： F01D9/04 ,  F01D25/12

    CPC分类号： F01D5/087 ,  F01D5/3038 ,  F01D11/001 ,  F01D11/006

    摘要： A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component.

    摘要翻译： 提供一种燃气涡轮发动机，包括能够旋转的前转子盘和叶片组件; 能够旋转的后转子盘和叶片组件; 以及位于前转子盘和叶片组件和后转子盘和叶片组件之间的一排叶片。 叶片排和前转子盘和叶片组件可以限定前腔。 叶片排可以包括至少一个定子叶片，其包括：主体和包括盖的内护罩结构。 盖可以包括接收冷却空气的第一内腔。 盖子还可以包括至少一个冷却流道。 从冷却流路流动的冷却空气具有切向速度分量。

    SEAL INCLUDING FLEXIBLE SEAL STRIPS
    6.
    发明申请
    SEAL INCLUDING FLEXIBLE SEAL STRIPS 有权
    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。

    Seal including flexible seal strips
    7.
    发明授权
    Seal including flexible seal strips 有权
    密封包括柔性密封条

    公开(公告)号：US09206904B2

    公开(公告)日：2015-12-08

    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： F16J15/32 ,  F01D11/02

    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。

    Finned seal assembly for gas turbine engines
    8.
    发明授权
    Finned seal assembly for gas turbine engines 有权
    燃气涡轮发动机的翅片密封组件

    公开(公告)号：US09121298B2

    公开(公告)日：2015-09-01

    申请号：US13534060

    申请日：2012-06-27

    申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    IPC分类号： F04D11/00 ,  F01D11/00

    CPC分类号： F01D11/001

    摘要： A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

    摘要翻译： 设置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从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片 从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。 翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。 在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中 密封组装。

    Gas turbine compressor with bleed path
    9.
    发明授权
    Gas turbine compressor with bleed path 有权
    带排气路的燃气轮机压缩机

    公开(公告)号：US09032738B2

    公开(公告)日：2015-05-19

    申请号：US13455509

    申请日：2012-04-25

    申请人： Vincent P. Laurello ,  Kok-Mun Tham

    发明人： Vincent P. Laurello ,  Kok-Mun Tham

    IPC分类号： F02C6/08 ,  F02C6/04

    CPC分类号： F02C6/08 ,  F04D29/321

    摘要： A gas turbine engine includes a compressor for generating compressed air. The compressor includes a rotor defined by a plurality of axial disks including a first disk and a second disk. A first row of blades extends radially outwardly from the first disk, and a second row of blades extends radially outwardly from the second disk. A row of cantilevered vanes is located at an axial location between the first row of blades and the second row of blades. A bleed path extends at least partially through the second disk and includes an entrance at an axial location between the first row of blades and at least a portion of the row of cantilevered vanes. The entrance communicates with a compressed air flowpath through the compressor.

    摘要翻译： 燃气涡轮发动机包括用于产生压缩空气的压缩机。 压缩机包括由包括第一盘和第二盘的多个轴向盘限定的转子。 第一排叶片从第一盘径向向外延伸，并且第二排叶片从第二盘径向向外延伸。 一排悬臂叶片位于第一排叶片与第二排叶片之间的轴向位置。 排放路径至少部分延伸穿过第二盘，并且包括位于第一排叶片与至少一部分悬臂叶片的至少一部分之间的轴向位置处的入口。 入口与通过压缩机的压缩空气流路相通。

    Outer rim seal assembly in a turbine engine
    10.
    发明授权
    Outer rim seal assembly in a turbine engine 有权
    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。