公开(公告)号：US20200224544A1

公开(公告)日：2020-07-16

申请号：US16244409

申请日：2019-01-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William M. Barker ,  Daniel J. Whitney ,  Michael G. McCaffrey ,  Thomas E. Clark

IPC: F01D11/08 ,  F01D25/24

Abstract: A blade outer air seal assembly may comprise a blade outer air seal segment and a blade outer air seal support coupled to the blade outer air seal segment. The blade outer air seal segment may comprise a forward rail and an aft rail. The forward rail may be castellated. The blade outer air seal support may comprise an aft flange and a first forward flange. A pin may be disposed through the aft rail, the aft flange, the first forward flange, and the forward rail.

公开(公告)号：US20200095893A1

公开(公告)日：2020-03-26

申请号：US16142515

申请日：2018-09-26

Applicant: United Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark ,  Daniel J. Whitney

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

Abstract: A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

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.