公开(公告)号：US10605121B2

公开(公告)日：2020-03-31

申请号：US16005118

申请日：2018-06-11

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce High Temperature Composites, Inc.

Inventor： Daniel K. Vetters ,  Todd Engel ,  Robert J. Shinavski

IPC: F01D25/24

Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.

公开(公告)号：US10989060B2

公开(公告)日：2021-04-27

申请号：US16845820

申请日：2020-04-10

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Daniel K. Vetters ,  David J. Thomas ,  Ted Freeman ,  Joseph Lamusga ,  Rick Uskert ,  Douglas D. Dierksmeier ,  Jun Shi ,  Todd Engel ,  Matt Brandt

IPC: F01D11/08 ,  F01D9/04 ,  F01D25/24 ,  F01D11/02

Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

公开(公告)号：US20200025012A1

公开(公告)日：2020-01-23

申请号：US16189648

申请日：2018-11-13

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

IPC: F01D11/12 ,  F01D25/24 ,  F01D9/02

Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

公开(公告)号：US20180328213A1

公开(公告)日：2018-11-15

申请号：US16042809

申请日：2018-07-23

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Ted Freeman ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

IPC: F01D11/08 ,  F01D25/24 ,  F01D9/04 ,  F01D25/00

CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D25/005 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2300/6033

Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.

公开(公告)号：US20180291769A1

公开(公告)日：2018-10-11

申请号：US16005118

申请日：2018-06-11

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce High Temperature Composites, Inc.

Inventor： Daniel K. Vetters ,  Todd Engel ,  Robert J. Shinavski

IPC: F01D25/24

Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.