公开(公告)号：US20160201485A1

公开(公告)日：2016-07-14

申请号：US14593886

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Richard M. Salzillo, JR. ,  Jeffrey J. Degray

IPC: F01D9/02 ,  F01D25/28 ,  F01D9/04

CPC classification number: F01D9/023 ,  F01D9/04 ,  F01D9/06 ,  F01D25/28 ,  F05D2240/81 ,  Y02T50/676

Abstract: An airfoil of a turbine engine may have internal passages to permit the travel of cooling air through the airfoil. Multiple airfoils may be formed together in a stator vane assembly, and cooling air may be directed through the stator vane assembly. The stator vane assembly may be mounted to an engine structure to carry structural loads experienced by the stator vane assembly. Buttresses may be formed in the stator vane assembly, such as beneath each airfoil of the stator vane assembly, and extending into a passage permitting the travel of cooling air through the airfoil. The buttresses may enhance the strength and stability of the stator vane assembly by facilitating the transmission of structural loads to an engine structure. A channel may be defined through one or more buttress to enable the passage of cooling air into the airfoils, and yet allow the buttresses to carry structural loads.

Abstract translation: 涡轮发动机的翼型件可以具有允许冷却空气通过翼型的行进的内部通道。 多个翼型件可以一起形成在定子叶片组件中，并且冷却空气可以被引导通过定子叶片组件。 定子叶片组件可以安装到发动机结构以承载由定子叶片组件经受的结构负载。 支撑件可以形成在定子叶片组件中，例如在定子叶片组件的每个翼型件下面，并且延伸到允许冷却空气通过翼型件的行进的通道中。 支撑件可以通过促进将结构载荷传递到发动机结构来增强定子叶片组件的强度和稳定性。 通道可以通过一个或多个支撑件来限定，以使冷却空气能够进入翼型件，并允许支撑架承载结构载荷。

公开(公告)号：US10072517B2

公开(公告)日：2018-09-11

申请号：US14769210

申请日：2014-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark A. Boeke ,  Kevin Rajchel ,  Richard M. Salzillo ,  Jeffrey J. Degray ,  Allison Mainelli

IPC: F01D11/00 ,  F01D9/04

CPC classification number: F01D11/005 ,  F01D9/041 ,  F05D2240/11 ,  F05D2240/57

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

公开(公告)号：US09752446B2

公开(公告)日：2017-09-05

申请号：US14593886

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Richard M. Salzillo, Jr. ,  Jeffrey J. Degray

IPC: F01D9/06 ,  F01D9/02 ,  F01D25/28 ,  F01D9/04

CPC classification number: F01D9/023 ,  F01D9/04 ,  F01D9/06 ,  F01D25/28 ,  F05D2240/81 ,  Y02T50/676

Abstract: An airfoil of a turbine engine may have internal passages to permit the travel of cooling air through the airfoil. Multiple airfoils may be formed together in a stator vane assembly, and cooling air may be directed through the stator vane assembly. The stator vane assembly may be mounted to an engine structure to carry structural loads experienced by the stator vane assembly. Buttresses may be formed in the stator vane assembly, such as beneath each airfoil of the stator vane assembly, and extending into a passage permitting the travel of cooling air through the airfoil. The buttresses may enhance the strength and stability of the stator vane assembly by facilitating the transmission of structural loads to an engine structure. A channel may be defined through one or more buttress to enable the passage of cooling air into the airfoils, and yet allow the buttresses to carry structural loads.