公开(公告)号：US10352184B2

公开(公告)日：2019-07-16

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 ,  F01D11/00 ,  F01D11/14 ,  F01D25/14

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：US09708922B1

公开(公告)日：2017-07-18

申请号：US15162082

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Mark J. Rogers ,  Paul M. Lutjen ,  Terence P. Tyler, Jr. ,  Michael J. Bruskotter

IPC: F01D11/00 ,  F16J15/02 ,  F16J15/44 ,  F01D11/08

CPC classification number: F01D11/005 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2250/75 ,  F05D2300/50 ,  F16J15/024 ,  F16J15/0887 ,  F16J15/44

Abstract: A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.

公开(公告)号：US10309253B2

公开(公告)日：2019-06-04

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: F02C7/12 ,  F01D25/12 ,  F02C3/04 ,  F01D5/02 ,  F01D5/12 ,  F01D11/08

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：US10167957B2

公开(公告)日：2019-01-01

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: F01D11/00 ,  F16J15/52 ,  C22C19/05 ,  C22C30/00 ,  F01D11/08 ,  C22C19/07 ,  F16J15/08

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.

公开(公告)号：US10036271B2

公开(公告)日：2018-07-31

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

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.