公开(公告)号：US20230055197A1

公开(公告)日：2023-02-23

申请号：US17977093

申请日：2022-10-31

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：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：US20220003126A1

公开(公告)日：2022-01-06

申请号：US17476566

申请日：2021-09-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Carson A. Roy Thill ,  Jaime A. Arbona ,  Justin K. Bleil ,  Andrew D. Keene ,  Danielle Mahoney

IPC: F01D11/08

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. The first and second rails include respective first and seconds pairs of hooks dimensioned to mount the seal arc segment to an engine static structure in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.

公开(公告)号：US11624291B2

公开(公告)日：2023-04-11

申请号：US17476566

申请日：2021-09-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Carson A. Roy Thill ,  Jaime A. Arbona ,  Justin K. Bleil ,  Andrew D. Keene ,  Danielle Mahoney

IPC: F01D11/08

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. The first and second rails include respective first and seconds pairs of hooks dimensioned to mount the seal arc segment to an engine static structure in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.

公开(公告)号：US20210254488A1

公开(公告)日：2021-08-19

申请号：US16903509

申请日：2020-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Carson A. Roy Thill ,  Jaime A. Arbona ,  Justin K. Bleil ,  Andrew D. Keene ,  Danielle Mahoney

IPC: F01D11/08

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. Each of the first and second rails includes at least one interface bore dimensioned to receive a retention pin such that the seal arc segment is carried by the retention pin in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.

公开(公告)号：US11519283B2

公开(公告)日：2022-12-06

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 ,  F01D11/08

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：US11143050B2

公开(公告)日：2021-10-12

申请号：US16903509

申请日：2020-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Carson A. Roy Thill ,  Jaime A. Arbona ,  Justin K. Bleil ,  Andrew D. Keene ,  Danielle Mahoney

IPC: F01D11/08 ,  F01D25/00

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment including a sealing portion, and a first rail and a second rail opposed to the first rail. The sealing portion extends in a circumferential direction between opposed mate faces and extends in an axial direction between a leading edge and a trailing edge. Each of the first and second rails extend outwardly in a radial direction from the sealing portion to respective first and second edge faces, and the sealing portion has a sealing face dimensioned to bound a gas path and includes a backside face opposed to the sealing face. Each of the first and second rails includes at least one interface bore dimensioned to receive a retention pin such that the seal arc segment is carried by the retention pin in an installed position. The seal arc segment is radially opposed to the sealing face between the first and second edge faces establishing a first region. The seal arc segment is radially opposed to the sealing face between the leading and trailing edges establishing a second region. A method of sealing for a gas turbine engine is also disclosed.