公开(公告)号：US11143048B2

公开(公告)日：2021-10-12

申请号：US16750636

申请日：2020-01-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexander MirzaMoghadam ,  Hasham Hamzamiyan Chougule ,  Abhay Naik

IPC: F01D11/02 ,  F01D11/12 ,  F16J15/447 ,  F01D5/02 ,  F01D9/02

Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is less than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.

公开(公告)号：US20200157960A1

公开(公告)日：2020-05-21

申请号：US16750636

申请日：2020-01-23

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexander MirzaMoghadam ,  Hasham Hamzamiyan Chougule ,  Abhay Naik

IPC: F01D11/02 ,  F01D9/02 ,  F01D5/02 ,  F16J15/447 ,  F01D11/12

Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is less than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.

公开(公告)号：US20150300192A1

公开(公告)日：2015-10-22

申请号：US14257485

申请日：2014-04-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  Bradley Reed Tucker ,  Ardeshir Riahi ,  Ed Zurmehly ,  Alexander MirzaMoghadam

IPC: F01D11/00 ,  F01D9/04 ,  B22D19/00 ,  B22D25/02 ,  B22D25/06 ,  F01D1/06 ,  F01D25/12

CPC classification number: F01D11/005 ,  B22D19/00 ,  B22D25/02 ,  B22D25/06 ,  F01D1/06 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/941

Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.

Abstract translation: 提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。 在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。 该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽 壁。 应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。

公开(公告)号：US10598038B2

公开(公告)日：2020-03-24

申请号：US15819473

申请日：2017-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexander MirzaMoghadam ,  Hasham Hamzamiyan Chougule ,  Abhay Naik

IPC: F01D11/02 ,  F01D11/12 ,  F16J15/447 ,  F01D5/02 ,  F01D9/02

Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is different than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.

公开(公告)号：US20190153884A1

公开(公告)日：2019-05-23

申请号：US15819473

申请日：2017-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Alexander MirzaMoghadam ,  Hasham Hamzamiyan Chougule ,  Abhay Naik

IPC: F01D11/02 ,  F01D9/02 ,  F01D5/02

CPC classification number: F01D11/02 ,  F01D5/02 ,  F01D9/02 ,  F01D11/122 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/18 ,  F16J15/4472

Abstract: A labyrinth seal for a gas turbine engine is provided. The labyrinth seal includes a stator and a rotor spaced apart from the stator. The rotor includes a first tooth at a first side having a first radial height, and a second tooth between the first tooth and a second side. The second tooth has a second radial height that is different than the first radial height. The rotor includes a third tooth between the first tooth and the second side having a third radial height that is substantially the same as the first radial height. A first clearance between a first tip of the first tooth and the stator is different than a second clearance between a second tip of the second tooth and the stator, and a third clearance between a third tip of the third tooth and the stator is substantially the same as the first clearance.

公开(公告)号：US09506365B2

公开(公告)日：2016-11-29

申请号：US14257485

申请日：2014-04-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jason Smoke ,  Bradley Reed Tucker ,  Ardeshir Riahi ,  Ed Zurmehly ,  Alexander MirzaMoghadam

IPC: F01D11/00 ,  B23D19/00 ,  F01D1/06 ,  F01D9/04 ,  F01D25/12 ,  B22D25/02 ,  B22D25/06 ,  B22D19/00

CPC classification number: F01D11/005 ,  B22D19/00 ,  B22D25/02 ,  B22D25/06 ,  F01D1/06 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/55 ,  F05D2260/20 ,  F05D2260/941

Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.

Abstract translation: 提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。 在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。 该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽 壁。 应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。