公开(公告)号：US09850771B2

公开(公告)日：2017-12-26

申请号：US14603414

申请日：2015-01-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D. Porter ,  John T. Ols

IPC: F01D11/00 ,  F02C7/28 ,  F01D9/02 ,  F01D9/04 ,  F01D9/06 ,  F01D25/26 ,  F02C3/04

CPC classification number: F01D11/005 ,  F01D9/02 ,  F01D9/041 ,  F01D9/06 ,  F01D25/26 ,  F02C3/04 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/58 ,  F05D2240/80

Abstract: A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.

公开(公告)号：US20160177755A1

公开(公告)日：2016-06-23

申请号：US14862351

申请日：2015-09-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D. Porter ,  John T. Ols ,  Kyle C. Lana

IPC: F01D9/02 ,  F01D1/04

CPC classification number: F01D9/02 ,  F01D1/04 ,  F01D5/081 ,  F01D11/001 ,  F05D2240/80 ,  Y02T50/676

Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.

Abstract translation: 提供燃气涡轮发动机。 燃气涡轮发动机包括具有后叶片平台的高压涡轮机。 静态结构可以设置在高压涡轮机的后方并且靠近由后叶片平台限定的空腔。 静态结构的叶片可以具有叶片平台，其具有延伸到空腔中的成形尖端。

公开(公告)号：US20160153296A1

公开(公告)日：2016-06-02

申请号：US14900737

申请日：2014-06-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Ols ,  Richard N Allen ,  Paul K. Sanchez ,  Steven D. Porter ,  Jonathan Lemoine

IPC: F01D9/04 ,  F01D11/02

CPC classification number: F01D9/041 ,  F01D5/082 ,  F01D11/003 ,  F01D11/02 ,  F05D2240/12 ,  F05D2240/80

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract translation: 燃气涡轮发动机内的界面包括由叶片平台的一部分限定的密封表面。 密封件与所述密封表面接触。 屏障横向于密封表面。