公开(公告)号：US11661865B2

公开(公告)日：2023-05-30

申请号：US17866855

申请日：2022-07-18

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Ken F. Blaney

IPC: F01D11/08 ,  F01D25/28

CPC classification number: F01D25/28 ,  F01D11/08 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/20

Abstract: A method of assembling a blade outer air seal assembly includes engaging a first blade outer air seal with a first attachment surface on a first attachment body. The first blade outer air seal includes a first attachment body passage for accepting the first attachment body. A second blade outer air seal is engaged with a second attachment surface on the first attachment body. The second blade outer air seal includes a second attachment body passage for accepting the first attachment body. Rotation is prevented of the first attachment body relative to the first blade outer air seal with a first post engaging the first blade outer air seal. Rotation is prevented of the first attachment body relative to the second blade outer air seal with a second post engaging the second blade outer air seal.

公开(公告)号：US20230100487A1

公开(公告)日：2023-03-30

申请号：US17858287

申请日：2022-07-06

Applicant: Raytheon Technologies Corporation

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: B29C43/36 ,  F01D9/04 ,  F01D11/08 ,  F01D9/06 ,  B29L31/00

Abstract: A mandrel for a molding process includes a first portion and a second portion that form a mandrel having a channel between the first and second portions. At least one locking pin is configured to urge the first and second portions away from each other to establish a gap in response to inserting the locking pin into the channel along a respective end of the mandrel. A molding apparatus and method of forming a matrix composite component are also disclosed.

公开(公告)号：US20220364483A1

公开(公告)日：2022-11-17

申请号：US17866855

申请日：2022-07-18

Applicant: Raytheon Technologies Corporation

Inventor： Thomas E. Clark ,  Ken F. Blaney

IPC: F01D25/28 ,  F01D11/08

Abstract: A method of assembling a blade outer air seal assembly includes engaging a first blade outer air seal with a first attachment surface on a first attachment body. The first blade outer air seal includes a first attachment body passage for accepting the first attachment body. A second blade outer air seal is engaged with a second attachment surface on the first attachment body. The second blade outer air seal includes a second attachment body passage for accepting the first attachment body. Rotation is prevented of the first attachment body relative to the first blade outer air seal with a first post engaging the first blade outer air seal. Rotation is prevented of the first attachment body relative to the second blade outer air seal with a second post engaging the second blade outer air seal.

公开(公告)号：US20200284152A1

公开(公告)日：2020-09-10

申请号：US16879274

申请日：2020-05-20

Applicant: Raytheon Technologies Corporation

Inventor： Ken F. Blaney ,  Richard K. Hayford

IPC: F01D5/16 ,  B22F3/105 ,  B22F5/04 ,  B23K26/342 ,  B23K15/00 ,  F01D5/18 ,  F01D9/04 ,  F01D25/06 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54

Abstract: An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

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：US11668197B2

公开(公告)日：2023-06-06

申请号：US16879274

申请日：2020-05-20

Applicant: Raytheon Technologies Corporation

Inventor： Ken F. Blaney ,  Richard K. Hayford

IPC: F01D5/16 ,  B22F5/04 ,  F04D29/66 ,  B22F10/28 ,  B23K26/342 ,  B23K15/00 ,  F01D5/18 ,  F01D9/04 ,  F01D25/06 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  B22F10/25

CPC classification number: F01D5/16 ,  B22F5/04 ,  B22F10/28 ,  B23K15/0086 ,  B23K26/342 ,  F01D5/18 ,  F01D9/041 ,  F01D25/06 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/668 ,  B22F10/25 ,  F05D2220/30 ,  F05D2220/36 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2260/96 ,  Y02P10/25

Abstract: An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

公开(公告)号：US10883426B2

公开(公告)日：2021-01-05

申请号：US16730466

申请日：2019-12-30

Applicant: Raytheon Technologies Corporation

Inventor： Ken F. Blaney ,  Todd M. LaPierre ,  Richard K. Hayford

IPC: F16H57/025 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F16H1/46 ,  F16H57/028

Abstract: A planetary gear system for a turbomachine includes a forward planetary gear assembly including a plurality of forward planet gears meshed to a forward sun gear disposed on a power shaft and a forward ring gear meshed to the forward planet gears and an aft planetary gear assembly aft of the forward planetary assembly including a plurality of aft planet gears meshed to an aft sun gear disposed on the power shaft and an aft ring gear meshed to the aft planet gears. The system also includes a gear housing disposed between the forward planetary gear assembly and the aft planetary gear assembly. The gear housing includes a stationary carrier, wherein the forward and aft planet gears are rotatably mounted to the stationary carrier, and a mount extending radially from the stationary carrier that is connectable to a stationary portion of the turbomachine.

公开(公告)号：US11215119B2

公开(公告)日：2022-01-04

申请号：US16814159

申请日：2020-03-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Ken F. Blaney ,  Thomas E. Clark

IPC: F02C7/18 ,  F02C3/04 ,  F02C9/16

Abstract: A blade outer air seal assembly includes a support structure arranged about an axis. At least one blade outer air seal segment is mounted in the support structure. A flow guide is arranged between the support structure and the at least one blade outer air seal segment defining a passage between the flow guide and the blade outer air seal segment. The passage extends in a generally axial direction.