公开(公告)号：US11920487B1

公开(公告)日：2024-03-05

申请号：US17956877

申请日：2022-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Andrew E. Breault

IPC: F01D25/14 ,  F01D11/00 ,  F02C7/18 ,  F02C7/28

CPC classification number: F01D25/14 ,  F01D11/005 ,  F02C7/18 ,  F02C7/28 ,  F05D2250/75 ,  F05D2260/232 ,  F05D2260/31 ,  F05D2260/37

Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is positioned radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features. A bifurcation feature is positioned downstream of the first seal. The bifurcation feature is configured to direct a portion of an airflow through the first seal into a cooling air passage. A second seal contacts the bifurcation and the first seal, such that fluid radially inward of the bifurcation feature.

公开(公告)号：US20220307382A1

公开(公告)日：2022-09-29

申请号：US17212333

申请日：2021-03-25

Applicant: Raytheon Technologies Corporation

Inventor： Carson A. Roy Thill ,  Thomas E. Clark ,  Danielle Mahoney ,  Andrew D. Keene

IPC: F01D11/02

Abstract: A component for a gas turbine engine includes a component body formed of ceramic matrix composite lamina and has at least one hook. The at least one hook has an attachment region radially inward of the at least one hook. The attachment region is radially thinner from a hook end of the at least one hook to a remote end, and then becomes radially thicker. A slot is formed through a radial thickness of the at least one hook from the hook end in a remote direction, such that there are two sections of the attachment region. A gas turbine engine is also disclosed.

公开(公告)号：US11421558B2

公开(公告)日：2022-08-23

申请号：US17329510

申请日：2021-05-25

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Ken F. Blaney

IPC: F01D11/08 ,  F01D25/28

Abstract: A seal assembly includes at least one blade outer air seal (BOAS) including a base portion that extends between a leading edge and a trailing edge. A forward wall and an aft wall extend radially outward from the base portion to a radially outer portion. The radially outer portion is spaced from the base portion and at least partially defines a passage with the forward wall, aft wall, and base portion. At least one attachment body is located at least partially within the passage. The at least one attachment body includes a leading edge connected to a trialing edge by a radially inner surface and a radially outer surface. The radially outer surface includes at least one blade outer air seal attachment surface for engaging the at least one BOAS. At least one post extends from the radially outer surface and has a blade outer air seal guide surface.

公开(公告)号：US20230407757A1

公开(公告)日：2023-12-21

申请号：US17843113

申请日：2022-06-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Dean Johnson ,  Thomas E. Clark

IPC: F01D11/12 ,  F01D11/24

CPC classification number: F01D11/125 ,  F05D2240/55 ,  F05D2300/6033 ,  F01D11/24

Abstract: A seal system for a gas turbine engine includes a ceramic matrix composite (CMC) seal arc segment and a carrier supporting the CMC seal arc segment. The CMC seal arc segment defines radially inner and outer sides and has an abradable layer disposed on the radially outer side. There is a cooling cavity radially between the carrier and the abradable layer. The carrier includes a ridge that projects into a groove in the abradable layer and provides a labyrinth seal that partitions the cooling cavity into sub-cavities.

公开(公告)号：US20230151740A1

公开(公告)日：2023-05-18

申请号：US18097397

申请日：2023-01-16

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney ,  Kathryn S. Read ,  Andrew J. Lazur ,  William M. Barker

IPC: F01D11/12 ,  B28B1/00 ,  F01D25/12

CPC classification number: F01D11/12 ,  B28B1/002 ,  F01D25/12 ,  F05D2230/20 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2300/20

Abstract: A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

公开(公告)号：US20240410587A1

公开(公告)日：2024-12-12

申请号：US18208113

申请日：2023-06-09

Applicant: Raytheon Technologies Corporation

Inventor： William K. Ackermann ,  Andrew E. Breault ,  Thomas E. Clark ,  Daniel B. Kupratis

IPC: F02C7/22

Abstract: A gas turbine engine having an axial centerline is provided that includes compressor, combustor, and turbine sections, a tangential on board injector (TOBI) system, and an HPC leakage guide structure. The compressor section has a high pressure compressor (HPC) that includes an HPC aft hub. The TOBI system extends circumferentially around the engine axial centerline, and has a plurality of nozzles and an inner radial flange. The HPC leakage guide structure has forward and aft ends. The forward end is disposed and configured to receive a leakage flow from the HPC and the aft end is engaged with the TOBI inner radial flange. The HPC leakage guide structure and the HPC aft hub define an HPC aft hub cavity. The HPC aft hub cavity extends between the forward and aft ends and has a flow area that is non-decreasing in a direction from the forward end to the aft end.

公开(公告)号：US12018568B2

公开(公告)日：2024-06-25

申请号：US18097397

申请日：2023-01-16

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Daniel J. Whitney ,  Kathryn S. Read ,  Andrew J. Lazur ,  William M. Barker

IPC: F01D11/12 ,  B28B1/00 ,  F01D25/12

CPC classification number: F01D11/12 ,  B28B1/002 ,  F01D25/12 ,  F05D2230/20 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2300/20

Abstract: A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

公开(公告)号：US11913340B2

公开(公告)日：2024-02-27

申请号：US17843113

申请日：2022-06-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Dean Johnson ,  Thomas E. Clark

IPC: F01D11/12 ,  F01D11/00 ,  F01D11/02 ,  F01D11/24 ,  F01D25/00 ,  F01D25/12

CPC classification number: F01D11/125 ,  F01D11/005 ,  F01D11/02 ,  F01D11/24 ,  F01D25/12 ,  F01D25/005 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/6033

Abstract: A seal system for a gas turbine engine includes a ceramic matrix composite (CMC) seal arc segment and a carrier supporting the CMC seal arc segment. The CMC seal arc segment defines radially inner and outer sides and has an abradable layer disposed on the radially outer side. There is a cooling cavity radially between the carrier and the abradable layer. The carrier includes a ridge that projects into a groove in the abradable layer and provides a labyrinth seal that partitions the cooling cavity into sub-cavities.

公开(公告)号：US11624292B2

公开(公告)日：2023-04-11

申请号：US17573921

申请日：2022-01-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Thomas E. Clark ,  William M. Barker

IPC: F01D11/08 ,  F02C3/04 ,  F02C7/28 ,  F16J15/34 ,  F01D11/00 ,  F01D5/28

Abstract: A blade outer air seal assembly includes a support structure and a blade outer air seal having a plurality of segments extending circumferentially about an axis and mounted to the support structure. At least two segments have a base portion extending from a first circumferential side to a second circumferential side, a first protrusion extending from the first circumferential side and having a first slot, and a second protrusion extending from the second circumferential side and having a second slot. A feather seal is arranged in the first slot and the second slot between the at least two segments such that the feather seal is pivotable between first and second positions in response to relative movement between the first and second protrusions.

公开(公告)号：US11371376B2

公开(公告)日：2022-06-28

申请号：US16795738

申请日：2020-02-20

Applicant: Raytheon 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.