公开(公告)号：US09732620B2

公开(公告)日：2017-08-15

申请号：US14339019

申请日：2014-07-23

Applicant: United Technologies Corporation

Inventor： Matthew A. Hough

IPC: F01D11/00 ,  F01D5/22 ,  F01D5/30 ,  F01D5/32

CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D5/3007 ,  F01D5/323 ,  F05D2260/96

Abstract: A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface. The second turbine blade includes a second platform with a second underplatform surface. The first underplatform surface and the second underplatform surface at least partially defines a cavity. A damper with a platform rub surface is included adjacent the first underplatform surface and the second underplatform surface. A seal is included with a forward portion, an aft portion, and a damper interface portion therebetween. The damper interface portion extends along a damper underside and the forward portion and the aft portion adjacent the first underplatform surface and the second underplatform surface.

公开(公告)号：US10036503B2

公开(公告)日：2018-07-31

申请号：US14685118

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Anthony P. Cherolis ,  Alexander Broulidakis ,  Matthew A. Hough ,  Jonathan Lemoine ,  Christopher Treat

IPC: F16L55/00 ,  F01D9/06 ,  F16L21/035

CPC classification number: F16L55/00 ,  F01D9/065 ,  F05D2240/58 ,  F05D2300/43 ,  F16L21/035

Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.

公开(公告)号：US20160298472A1

公开(公告)日：2016-10-13

申请号：US14685118

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Anthony P. Cherolis ,  Alexander Broulidakis ,  Matthew A. Hough ,  Jonathan Lemoine ,  Christopher Treat

IPC: F01D9/06 ,  F01D25/12 ,  F01D25/24 ,  F16L55/00

CPC classification number: F16L55/00 ,  F01D9/065 ,  F05D2240/58 ,  F05D2300/43 ,  F16L21/035

Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.

Abstract translation: 本公开的方面针对被配置为传送流体，发动机的凸台和联接到管和凸起中的至少一个的垫片的飞行器的发动机的管，所述垫被配置为保持间隙 管和发动机组装时的老板。

公开(公告)号：US09932834B2

公开(公告)日：2018-04-03

申请号：US14775179

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： Matthew A. Hough ,  Jeffrey S. Beattie

IPC: F01D5/14 ,  F01D5/22 ,  F01D5/30

CPC classification number: F01D5/141 ,  F01D5/147 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/14 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/941

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.

公开(公告)号：US20160153303A1

公开(公告)日：2016-06-02

申请号：US14339019

申请日：2014-07-23

Applicant: United Technologies Corporation

Inventor： Matthew A. Hough

IPC: F01D11/00 ,  B23P15/04 ,  F01D5/22

CPC classification number: F01D11/006 ,  F01D5/22 ,  F01D5/3007 ,  F01D5/323 ,  F05D2260/96

Abstract: A turbine assembly includes a first turbine blade circumferentially adjacent to a second turbine blade. The first turbine blade includes a first platform with a first underplatform surface. The second turbine blade includes a second platform with a second underplatform surface. The first underplatform surface and the second underplatform surface at least partially defines a cavity. A damper with a platform rub surface is included adjacent the first underplatform surface and the second underplatform surface. A seal is included with a forward portion, an aft portion, and a damper interface portion therebetween. The damper interface portion extends along a damper underside and the forward portion and the aft portion adjacent the first underplatform surface and the second underplatform surface.

Abstract translation: 涡轮组件包括与第二涡轮机叶片周向相邻的第一涡轮机叶片。 第一涡轮叶片包括具有第一底板平台表面的第一平台。 第二涡轮机叶片包括具有第二平台下表面的第二平台。 第一底板下表面和第二平台下表面至少部分地限定空腔。 具有平台摩擦表面的阻尼器包括在第一底板表面和第二平台下表面附近。 密封件包括在其间的前部，后部和阻尼器接口部分。 阻尼器接口部分沿着阻尼器下侧延伸，并且前部和后部与第一底板平面和第二平台下表面相邻。

公开(公告)号：US10941669B2

公开(公告)日：2021-03-09

申请号：US16228994

申请日：2018-12-21

Applicant: United Technologies Corporation

Inventor： Matthew A. Hough ,  Russell B. Hanson ,  John S. Tu ,  Paul F. Croteau ,  Paul K. Sanchez ,  Stephen C. Harmon ,  Joshua C. Rathgeb

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/24

Abstract: A diffuser case support structure for a gas turbine engine is disclosed. The diffuser case support structure includes a fairing disposed circumferentially about a longitudinal axis. The fairing forms at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. The fairing defines a plurality of apertures extending through the fairing. At least one spoke extends through at least one respective aperture of the plurality of apertures. The at least one spoke is configured to couple an inner diffuser case and an outer diffuser case of the gas turbine engine.

公开(公告)号：US20160032727A1

公开(公告)日：2016-02-04

申请号：US14775179

申请日：2014-03-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Hough ,  Jeffrey S. Beattie

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/147 ,  F01D5/22 ,  F01D5/3007 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/80 ,  F05D2250/14 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/941

Abstract: A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.

Abstract translation: 用于涡轮发动机的转子叶片包括连接到基座的翼型件。 底座包括平台，颈部和圆角。 圆角沿平台和颈部之间的交叉点的至少一部分延伸。 圆角的半径随着圆角从平台延伸到颈部而基本上连续变化。