公开(公告)号：US20200072127A1

公开(公告)日：2020-03-05

申请号：US16122431

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/16

Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.

公开(公告)号：US20200072071A1

公开(公告)日：2020-03-05

申请号：US16122553

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Paul M. Lutjen ,  Thomas E. Clark

IPC: F01D11/08

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. The blade outer air seal has a lip at an axial end engaged with the support structure. A seal structure has a seal portion and a wear liner portion joined by a radially extending portion. The seal portion is radially outward of the lip and the wear liner is radially inward of the lip.

公开(公告)号：US20200072069A1

公开(公告)日：2020-03-05

申请号：US16116140

申请日：2018-08-29

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Winston Gregory Smiddy ,  Daniel J. Whitney ,  William M. Barker

IPC: F01D11/08

Abstract: A method of forming a gas turbine engine component includes the steps of (a) forming an intermediate portion, (b) forming cooling circuit structure into at least an outer layer of the intermediate portion, (c) providing an outer layer over the formed cooling circuits to close off the cooling circuits, such that there are laminate on both a radially inner and a radially outer side of the cooling circuits, and (d) forming an inlet and an outlet to the cooling circuits through the outer layer. A gas turbine engine is also disclosed.

公开(公告)号：US20200072067A1

公开(公告)日：2020-03-05

申请号：US16122525

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D11/00 ,  F01D25/24 ,  F01D11/08

Abstract: A blade outer air seal assembly includes a support structure. A blade outer air seal extends circumferentially about an axis and is mounted in the support structure. A flow guide has a plurality of flow guide segments arranged between the blade outer air seal and the support structure. An intersegment seal is at a circumferential end of at least one of the flow guide segments.

公开(公告)号：US10563542B2

公开(公告)日：2020-02-18

申请号：US15161716

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Brian C. McLaughlin

IPC: F01D25/28 ,  F01D25/24 ,  F23R3/60 ,  F01D5/02 ,  F02C3/04 ,  F02C3/14 ,  F01D9/02

Abstract: A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

公开(公告)号：US20200040751A1

公开(公告)日：2020-02-06

申请号：US16050625

申请日：2018-07-31

Applicant: United Technologies Corporation

Inventor： William M. Barker ,  Thomas E. Clark

IPC: F01D11/00 ,  F01D11/08

Abstract: A gas turbine engine includes a turbine section having a turbine rotor and at least one blade extending outwardly of the turbine rotor. The turbine rotor rotates about an axis of rotation. A blade outer air seal is positioned radially outward of the at least one blade. The blade outer air seal has an axially forward hook and an axially aft hook supported to static structure. An axial seal is attached to static structure forward of the forward hook, and has a sealing portion extending in an aft direction. A sealing surface member is positioned intermediate an aft end of the axial seal and a forward end of the forward hook to provide a sealing surface for sealing between the seal and the blade outer air seal.

公开(公告)号：US20200025029A1

公开(公告)日：2020-01-23

申请号：US16042096

申请日：2018-07-23

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F01D25/14 ,  F01D25/12 ,  F01D11/12

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one turbine rotor having a radially extending turbine blade. The turbine section is rotatable about an axis of rotation. A blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade. The blade outer air seal has axially spaced forward and aft portions and a central web between the axially spaced portions. An attachment block is supported on structure within the engine. The attachment block mounts the blade outer air seal. A passage extends into a chamber within the attachment block, and communicates to circumferential edges of the attachment block to direct cooling air along the central web of the blade outer air seal. A blade outer air seal assembly is also disclosed.

公开(公告)号：US20200003077A1

公开(公告)日：2020-01-02

申请号：US16019972

申请日：2018-06-27

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Ken F. Blaney

IPC: F01D25/28 ,  F01D11/08

Abstract: An attachment body for a blade outer air seal includes a leading edge connected to a trialing edge by a radially inner wall and a radially outer wall. At least one forward hook extends from the radially outer wall. At least one aft hook extends from the radially outer wall. At least one post extends from the radially outer surface and has a blade outer air seal (BOAS) guide surface.

公开(公告)号：US10450883B2

公开(公告)日：2019-10-22

申请号：US15339151

申请日：2016-10-31

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Jeremy Drake

IPC: F01D11/00 ,  F01D25/24 ,  F02C7/28 ,  F16J15/08

Abstract: A sealing assembly for a gas turbine engine includes a case, a support arm, a carrier, a vane, a seal, and a gasket. The support arm is connected to and extending radially inward from the case. The carrier is connected to an end of the support arm. A portion of the vane is disposed downstream of the carrier. A portion of the seal is disposed within the carrier. The gasket is disposed adjacent to and abutting the seal. The gasket is also positioned partially between the seal and the carrier and partially between the seal and the vane.

公开(公告)号：US10228023B2

公开(公告)日：2019-03-12

申请号：US15076783

申请日：2016-03-22

Applicant: United Technologies Corporation

Inventor： Thomas E. Clark ,  Eric Charles Mundell ,  Gary L. Grogg

IPC: F16C33/66 ,  F16C27/04 ,  F01D25/16 ,  F16F15/023 ,  F16C19/26 ,  F16C33/58

Abstract: An improved film damper oil delivery pathway from an oil reservoir to a thin film fluidic damper is provided. An oil supply tube may be configured to mate to a bearing outer race. The bearing outer race may comprise internal oil flow circuit(s) configured to supply oil from the oil tube to the thin film damper for improved bearing compartment designs.