公开(公告)号：EP3792452A1

公开(公告)日：2021-03-17

申请号：EP20194466.7

申请日：2020-09-03

Applicant: Raytheon Technologies Corporation

Inventor： BARKER, William M. ,  CLARK, Thomas E.

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

Abstract: A blade outer air seal (64) includes a carrier (70), a ceramic seal segment (68), and a face seal (80). The ceramic seal segment (68) is supported on the carrier (70) and has first and second axial ends (68a, 68b), first and second circumferential sides (68c, 68d), an inner side (68e), and an outer side (68f). The face seal (80) is carried on the ceramic seal segment (68) at the first axial end (68a). The face seal (80) has a radial seal wall (82) and a tongue (84) that extends axially from the radial seal wall (82).

公开(公告)号：EP3969246A1

公开(公告)日：2022-03-23

申请号：EP20805586.3

申请日：2020-05-14

Applicant: Raytheon Technologies Corporation

Inventor： CLARK, Thomas E. ,  READ, Karhryn S. ,  BARKER, William M.

IPC: B29C44/32 ,  B29C53/60 ,  B29C53/82 ,  B65H81/08 ,  F16L59/02

公开(公告)号：EP3805530A1

公开(公告)日：2021-04-14

申请号：EP20193968.3

申请日：2020-09-01

Applicant: Raytheon Technologies Corporation

Inventor： BARKER, William M. ,  CLARK, Thomas E. ,  WANGARD III, William ,  MAHONEY, Danielle

IPC: F01D25/24

Abstract: A blade outer air seal (64; 164) includes a carrier (70; 170) that has a dovetail (76; 176) and a ceramic seal segment (68; 168) supported on the dovetail (70; 170). The ceramic seal segment (68; 168) has first and second axial ends (68a, 68b), first and second circumferential sides (68c, 68d), an inner side (68e), an outer side (68f), and first and second inward-facing dovetail hooks (72; 172) that project from the outer side (68f) and define a dovetail key (74). The ceramic seal segment (68; 168) is axially receivable onto the dovetail (70; 170) of the carrier via the dovetail key (74).

公开(公告)号：EP3792454A1

公开(公告)日：2021-03-17

申请号：EP20192953.6

申请日：2020-08-26

Applicant: Raytheon Technologies Corporation

Inventor： THIRUMALAI, Sudarshan ,  BARKER, William M. ,  CLARK, Thomas E.

IPC: F01D11/00 ,  F16J15/08 ,  F01D5/28 ,  F01D11/22

Abstract: A blade outer air seal assembly (104) includes a blade outer air seal (106) that has a plurality of segments (105) that extend circumferentially about an axis and are mounted in a carrier (112). At least two of the plurality of segments (105) have a first wall (120) and a second wall (122) circumferentially spaced from one another and a base portion (124) that extends from the first wall (120) to the second wall (122). The base portion (124) extends circumferentially outward past the first and second walls (120, 122) to form first and second sealing surfaces (125, 127). An intersegment seal (150) has a curved surface (152). The curved surface (152) is engaged with the first and second sealing surfaces (125, 127) between the at least two segments.

公开(公告)号：EP3767077A1

公开(公告)日：2021-01-20

申请号：EP20183256.5

申请日：2020-06-30

Applicant: Raytheon Technologies Corporation

Inventor： BLANEY, Ken F. ,  CLARK, Thomas E.

IPC: F01D11/00 ,  C04B35/80 ,  F01D11/08 ,  F01D25/24

Abstract: A blade outer air seal (106) includes a base portion (124). A first wall (119) and a second wall (121) extend from the base portion (124). The first wall (119) is circumferentially spaced from the second wall (121). The first and second walls (119, 121) extend at an angle less than 90° from the base portion (124). The first and second walls (119, 121) extend towards one another.

公开(公告)号：EP3739168A1

公开(公告)日：2020-11-18

申请号：EP20174478.6

申请日：2020-05-13

Applicant: Raytheon Technologies Corporation

Inventor： CLARK, Thomas E. ,  BARKER, William M. ,  WHITNEY, Daniel J. ,  MAHONEY, Danielle ,  WANGARD III, William

IPC: F01D5/28 ,  F01D11/00 ,  F01D25/24 ,  F01D11/08

Abstract: A blade outer air seal assembly (104) includes a support structure (110). A blade outer air seal (106) has a plurality of segments (105) that extend circumferentially about an axis (A) and mounted in the support structure (110) via a carrier (112; 212). At least one of the plurality of segments (105) has a base portion (124) that extends between a first circumferential side (C1) and a second circumferential side (C2) and from a first axial side (Al) to a second axial side (A2). A first hook (127) extends from the base portion (124) near the first axial side (Al) and faces towards the second axial side (A2). A second hook (126) extends from the base portion (124) near the second axial side (A2) and faces towards the first axial side (Al). A slot (138) is in the second hook (126) configured to receive a pin (150).

公开(公告)号：EP4219128A3

公开(公告)日：2023-09-13

申请号：EP23159233.8

申请日：2019-09-24

Applicant: Raytheon Technologies Corporation

Inventor： BLANEY, Ken F. ,  CLARK, Thomas E.

IPC: B29C53/82 ,  B29C33/48 ,  B29C70/04

Abstract: A mandrel (300) for a molding process that includes a first portion (302) that has a first portion outer surface (306), a first portion inner surface (312), a first portion first end (303), and a first portion second end (305). A thickness (Hi) of the first portion first end (303) is greater than the first portion second end (305). A second portion (304) has a second portion outer surface (310), a second portion inner surface (308), a second portion first end (303), and a second portion second end (305). A thickness (H 2 ) of the second portion first end (303) is smaller than the second portion second end (305). The first portion inner surface (312) engages the second portion inner surface (308) to form a mandrel that has a constant cross-section.

公开(公告)号：EP4219910A1

公开(公告)日：2023-08-02

申请号：EP23166176.0

申请日：2019-12-03

Applicant: Raytheon Technologies Corporation

Inventor： BARKER, William M. ,  CLARK, Thomas E.

IPC: F01D11/12

Abstract: A method of forming a blade outer air seal includes applying a cavity layer (130) that has a plurality of cavities (134) to a radially inner side of a seal body. The cavity layer (130) is coated with an abradable coating (132).

公开(公告)号：EP3971392A1

公开(公告)日：2022-03-23

申请号：EP21207520.4

申请日：2020-02-10

Applicant: Raytheon Technologies Corporation

Inventor： CLARK, Thomas E. ,  WHITNEY, Daniel J. ,  READ, Kathryn S. ,  LAZUR, Andrew J. ,  BARKER, William M.

IPC: F01D5/28 ,  F01D11/08 ,  F01D25/12 ,  B29C70/22 ,  C04B35/628 ,  B32B18/00

Abstract: A fiber-reinforced component for use in a gas turbine engine (20) includes a first braided fiber sleeve (96) forming a cooling channel (90a-90c) and a plurality of fiber plies (98) enclosing the first braided fiber sleeve (96), with the plurality of fiber plies (98) forming first and second walls (106, 108) separated by the first braided fiber sleeve (96). The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve (96) and the plurality of fiber plies (98).

公开(公告)号：EP3792453A2

公开(公告)日：2021-03-17

申请号：EP20194519.3

申请日：2020-09-04

Applicant: Raytheon Technologies Corporation

Inventor： JOHNSON, Dean W. ,  CLARK, Thomas E.

IPC: F01D9/04 ,  F01D11/08

Abstract: A blade outer air seal (106) includes a base portion (124). A first wall (120) and a second wall (122) extend radially from the base portion (124). The first wall (120) is axially spaced from the second wall (122). The first and second walls (120, 122) extend in a circumferential direction. A first hook (121) extends from the first wall (120) and a second hook (123) extends from the second wall (122). The first and second hooks (121, 123) extend in an axial direction towards one another to form a passage (138) that extends in the circumferential direction. The passage (138) is configured to receive a carrier (112). A tab (126) extends radially outward from the second hook (123). The tab (126) is configured to engage with the carrier (112).