公开(公告)号：US11982187B1

公开(公告)日：2024-05-14

申请号：US18085864

申请日：2022-12-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel S. Rogers ,  Joseph Micucci ,  Peter J. Rosenfeld ,  Giovanni Lawrence ,  Aaron Tomich

IPC: F01D11/08 ,  F01D5/28

CPC classification number: F01D11/08 ,  F01D5/282 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2300/6033 ,  F05D2300/6034

Abstract: A blade outer air seal arc segment includes a ceramic matrix composite body that defines a core gaspath side, a non-core gaspath side opposite the core gaspath side, a forward end, an aft end, and circumferential sides. The ceramic matrix composite body has first and second flanges on the non-core gaspath side. The ceramic matrix composite body is comprised of fiber plies disposed in a ceramic matrix. The fiber plies include flange fiber plies that have a +/−15-75 degree ply layup arrangement.

公开(公告)号：US20240167391A1

公开(公告)日：2024-05-23

申请号：US17990244

申请日：2022-11-18

Applicant: Raytheon Technologies Corporation

Inventor： Daniel S. Rogers ,  Joseph Micucci

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F05D2220/32 ,  F05D2240/55

Abstract: A blade outer air seal has seal mount hooks on both a leading edge of the central web and a trailing edge of the central web. The seal mount hooks have a generally radially outward extending section extending to a generally axially extending section. The seal mount hooks have a support face which is to be supported on a support mount hook. The support face is generally formed about a single radius of curvature over at least 50% of a circumferential length defined from a radially inner end of the support face to a radially outer end of the support face. A radius of curvature of the inner support surface is greater than or equal to 0.150 inch and less than or equal to 0.300 inch. A blade outer air seal and a gas turbine engine are also disclosed.

公开(公告)号：US11879340B1

公开(公告)日：2024-01-23

申请号：US17957438

申请日：2022-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Daniel S. Rogers ,  Timothy J. Harding ,  Joseph Micucci ,  Paul M. Lutjen

IPC: F01D11/12 ,  F01D25/00

CPC classification number: F01D11/12 ,  F01D25/005 ,  F05D2240/56 ,  F05D2250/38 ,  F05D2260/30 ,  F05D2300/6033

Abstract: There is a blade outer air seal positioned to be radially outward of blades in the rotating blade row relative to the rotational axis. There is at least one brush seal having bristles extending from a mount location radially inward to contact a sealing surface on the blade outer air seal. An angle is defined between the bristles and relative to the sealing surface having a radially inward extending component, and with an axial component in a direction toward a leading edge attachment feature and a trailing edge attachment feature, and the angle is less than 90° on a side of the brush seal opposite the leading edge and trailing edge mount hooks. A gas turbine engine component is also disclosed.