公开(公告)号：US12292193B2

公开(公告)日：2025-05-06

申请号：US18343198

申请日：2023-06-28

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas Banhos ,  James T. Roach ,  Russell Kim ,  Raymond Surace

IPC: F23R3/00 ,  B32B3/10 ,  B32B3/26 ,  B32B5/02 ,  B32B5/26

Abstract: A combustor includes a combustion chamber and a liner that bounds at least a portion of the combustion chamber. The liner includes a first side facing the combustion chamber and a second side facing away from the combustion chamber. The liner is formed of a lay-up of ceramic matrix composite (CMC) plies that have a first CMC ply on the first side, a second CMC ply on the second side, and intermediate CMC plies between the first and second CMC plies. At least one of the intermediate CMC plies has a pattern of voids that define cooling channels in the combustor panel. The cooling channels are bound on lateral channel sides by the at least one of the intermediate CMC plies.

公开(公告)号：US12196095B2

公开(公告)日：2025-01-14

申请号：US18071121

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： James T. Roach ,  Jonas Banhos ,  Russell Kim

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02

Abstract: A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.

公开(公告)号：US11905851B2

公开(公告)日：2024-02-20

申请号：US18126556

申请日：2023-03-27

Applicant: Raytheon Technologies Corporation

Inventor： Russell Kim ,  James T. Roach ,  Jonas Banhos

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/284 ,  F05D2230/31 ,  F05D2240/122 ,  F05D2250/75 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  F05D2300/6034

Abstract: A method of forming a ceramic matrix composite airfoil includes forming a fibrous ceramic preform by laying up a plurality of plies to form a hollow core cavity, overwrapping the plurality of plies of the core cavity with a first overwrap layer, weaving together a tows of first free portion and tows of a second free portion of the first overwrap layer to form a cross brace, overwrapping the plurality of plies of the core cavity and the first overwrap layer with a second overwrap layer, and consolidating the first free portion and the second free portion of the first overwrap layer and a third free portion and a fourth free portion of the second overwrap layer to form a trailing edge.

公开(公告)号：US11905847B1

公开(公告)日：2024-02-20

申请号：US17970917

申请日：2022-10-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas Banhos ,  James T. Roach ,  Cheng Gao

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2300/603

Abstract: An airfoil includes an airfoil wall that has a span between first and second radial ends and that defines leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity. The internal cavity is divided into at least first and second sub-cavities extending over the span. The first sub-cavity defines a venturi tube.

公开(公告)号：US20230313692A1

公开(公告)日：2023-10-05

申请号：US18126556

申请日：2023-03-27

Applicant: Raytheon Technologies Corporation

Inventor： Russell Kim ,  James T. Roach ,  Jonas Banhos

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/284 ,  F01D5/147 ,  F05D2300/6034 ,  F05D2300/6033 ,  F05D2230/31 ,  F05D2240/122 ,  F05D2250/75 ,  F05D2300/6012 ,  F05D2300/2261

Abstract: A method of forming a ceramic matrix composite airfoil includes forming a fibrous ceramic preform by laying up a plurality of plies to form a hollow core cavity, overwrapping the plurality of plies of the core cavity with a first overwrap layer, weaving together a tows of first free portion and tows of a second free portion of the first overwrap layer to form a cross brace, overwrapping the plurality of plies of the core cavity and the first overwrap layer with a second overwrap layer, and consolidating the first free portion and the second free portion of the first overwrap layer and a third free portion and a fourth free portion of the second overwrap layer to form a trailing edge.