公开(公告)号：US20170198599A1

公开(公告)日：2017-07-13

申请号：US14994208

申请日：2016-01-13

Applicant: United Technologies Corporation

Inventor： Kevin J. Ryan ,  Terence P. Tyler, JR. ,  Ken F. Blaney

IPC: F01D11/08 ,  F02C7/18 ,  F01D25/12 ,  F02C3/04

CPC classification number: F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

公开(公告)号：US20170335705A1

公开(公告)日：2017-11-23

申请号：US15162183

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Terence P. Tyler, JR. ,  Timothy M. Davis ,  Jeremy Drake ,  Jose R. Paulino ,  Jaimie Schweitzer

IPC: F01D11/00 ,  F16J15/02 ,  F01D11/02 ,  F01D11/08

CPC classification number: F01D11/005 ,  F01D11/02 ,  F01D11/08 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/56 ,  F16J15/025 ,  Y02T50/672

Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.

公开(公告)号：US20170198603A1

公开(公告)日：2017-07-13

申请号：US14994186

申请日：2016-01-13

Applicant: United Technologies Corporation

Inventor： Kevin J. Ryan ,  Terence P. Tyler, JR. ,  Ken F. Blaney

IPC: F01D25/12 ,  F01D11/08 ,  F01D5/12 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08 ,  F01D25/246 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2250/232 ,  F05D2260/202 ,  Y02T50/676

Abstract: A blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas flow, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, and a plurality of film cooling holes disposed on at least one of the gas path surface. The first side and the second side, the film cooling holes are disposed at locations described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin. A gas turbine engine is also disclosed.

公开(公告)号：US20180119560A1

公开(公告)日：2018-05-03

申请号：US15339581

申请日：2016-10-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jose R. Paulino ,  Ken F. Blaney ,  Terence P. Tyler, JR. ,  Daniel S. Rogers ,  Anthony B. Swift ,  Thomas E. Clark

IPC: F01D11/10 ,  F01D9/02 ,  F01D25/24

CPC classification number: F01D11/10 ,  F01D9/02 ,  F01D11/003 ,  F01D11/14 ,  F01D25/14 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/55 ,  Y02T50/672 ,  Y02T50/675

Abstract: A seal assembly includes a blade outer air seal, a downstream vane, and a pressure wall, according to various embodiments. The blade outer air seal may include a radially outer surface and the downstream vane may be coupled to the blade outer air seal via a fluid sealing engagement. The pressure wall may be coupled to the blade outer air seal and may define a metering orifice. In various embodiments, the metering orifice of the pressure wall is configured to meter air flow from a first plenum upstream of the pressure wall to a second plenum downstream of the pressure wall. In various embodiments, at least a preponderance of the radially outer surface of the blade outer air seal at least partially defines the first plenum and the fluid sealing engagement at least partially defines the second plenum.

公开(公告)号：US20170343112A1

公开(公告)日：2017-11-30

申请号：US15169197

申请日：2016-05-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： TIMOTHY M. DAVIS ,  Terence P. Tyler, JR. ,  Jose R. Paulino ,  Paul M. Lutjen

IPC: F16J15/52 ,  F01D11/00 ,  C22C19/05 ,  F01D11/08 ,  C22C30/00

CPC classification number: F16J15/52 ,  C22C19/056 ,  C22C19/07 ,  C22C30/00 ,  F01D11/005 ,  F01D11/08 ,  F05D2240/55 ,  F05D2250/75 ,  F05D2300/175 ,  F16J15/0887

Abstract: A metal gasket bellows seal includes a first ply comprised of a first material having a first yield strength. The metal gasket bellows seal also includes a second ply positioned adjacent to the first ply and comprised of a second material having a second yield strength that is less than the first yield strength.