公开(公告)号：US09062557B2

公开(公告)日：2015-06-23

申请号：US13226547

申请日：2011-09-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Abdullatif M. Chehab ,  Gm Salam Azad ,  Shantanu P. Mhetras ,  Manjit Shivanand ,  Vincent P. Laurello ,  Christopher Rawlings

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Abdullatif M. Chehab ,  Gm Salam Azad ,  Shantanu P. Mhetras ,  Manjit Shivanand ,  Vincent P. Laurello ,  Christopher Rawlings

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

CPC classification number: F01D11/001 ,  F01D11/04

Abstract: 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).

Abstract translation: 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）。

公开(公告)号：US08939711B2

公开(公告)日：2015-01-27

申请号：US13768561

申请日：2013-02-15

Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Manjit Shivanand ,  Vincent P. Laurello ,  Gm Salam Azad ,  Nicholas F. Martin, Jr.

Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Manjit Shivanand ,  Vincent P. Laurello ,  Gm Salam Azad ,  Nicholas F. Martin, Jr.

IPC: F01D25/12 ,  F01D5/08 ,  F01D11/04

CPC classification number: F01D25/12 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F01D11/122 ,  F05D2260/202

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20140234076A1

公开(公告)日：2014-08-21

申请号：US13768561

申请日：2013-02-15

Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  Manjit Shivanand ,  Vincent P. Laurello ,  Gm Salam Azad ,  Nicholas F. Martin, JR.

Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  Manjit Shivanand ,  Vincent P. Laurello ,  Gm Salam Azad ,  Nicholas F. Martin, JR.

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/081 ,  F01D11/001 ,  F01D11/04 ,  F01D11/122 ,  F05D2260/202

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20120183389A1

公开(公告)日：2012-07-19

申请号：US13005752

申请日：2011-01-13

Applicant: Shantanu P. Mhetras ,  Manjit Shivanand ,  Abdullatif M. Chehab ,  Ching-Pang Lee

Inventor： Shantanu P. Mhetras ,  Manjit Shivanand ,  Abdullatif M. Chehab ,  Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/3015

Abstract: A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.

Abstract translation: 公开了一种用于燃气涡轮发动机中的转子组件的密封系统。 密封系统可以包括由侧块形成的密封件和上密封件，其密封位于轴向延伸的第二转子供应通道的入口处的转子组件中的径向向外延伸的第一转子供应通道之间的间隙，该第二转子供应通道处于流体连通 具有涡轮叶片的内部叶片冷却系统。 密封件可以包括增强冷却流体超过常规结构的流动的部件。 在另一个实施例中，密封系统可以包括集成密封块，其被配置为在第一和第二转子供应通道之间的交叉处密封相邻涡轮叶片之间的间隙。 集成密封块可以由径向向内延伸的腿和中心体形成。

公开(公告)号：US08985949B2

公开(公告)日：2015-03-24

申请号：US13872229

申请日：2013-04-29

Applicant: Ching-Pang Lee ,  Ralph W. Matthews ,  Gm Salam Azad ,  Manjit Shivanand

Inventor： Ching-Pang Lee ,  Ralph W. Matthews ,  Gm Salam Azad ,  Manjit Shivanand

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/304 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/294 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

Abstract translation: 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和冷却系统。 外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。 冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。 冷却系统接收来自冷却流体腔的冷却流体，用于冷却外壁的后缘部分，并且包括由相对的第一和第二侧壁限定的冷却流体室，该第一和第二侧壁包括相应的交替成角度的部分，这些部分为冷却流体室提供Z字形 。

公开(公告)号：US20140321980A1

公开(公告)日：2014-10-30

申请号：US13872229

申请日：2013-04-29

Applicant: Ching-Pang Lee ,  Ralph W. Matthews ,  Gm Salam Azad ,  Manjit Shivanand

Inventor： Ching-Pang Lee ,  Ralph W. Matthews ,  Gm Salam Azad ,  Manjit Shivanand

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/304 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2250/294 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a cooling system. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling system receives cooling fluid from the cooling fluid cavity for cooling the trailing edge portion of the outer wall and includes a cooling fluid chamber defined by opposing first and second sidewalls that include respective alternating angled sections that provide the cooling fluid chamber with a zigzag shape.

Abstract translation: 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和冷却系统。 外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。 冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。 冷却系统接收来自冷却流体腔的冷却流体，用于冷却外壁的后缘部分，并且包括由相对的第一和第二侧壁限定的冷却流体室，该第一和第二侧壁包括相应的交替成角度的部分，这些部分为冷却流体室提供Z字形 。

公开(公告)号：US20130058756A1

公开(公告)日：2013-03-07

申请号：US13226547

申请日：2011-09-07

Applicant: Kok-Mun THAM ,  Ching-Pang LEE ,  Abdullatif M. CHEHAB ,  Gm Salam AZAD ,  Shantanu P. MHETRAS ,  Manjit SHIVANAND ,  Vincent P. LAURELLO ,  Christopher RAWLINGS

Inventor： Kok-Mun THAM ,  Ching-Pang LEE ,  Abdullatif M. CHEHAB ,  Gm Salam AZAD ,  Shantanu P. MHETRAS ,  Manjit SHIVANAND ,  Vincent P. LAURELLO ,  Christopher RAWLINGS

IPC: F04D29/58 ,  F01D1/02

CPC classification number: F01D11/001 ,  F01D11/04

Abstract: 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).

Abstract translation: 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）。