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：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.

公开(公告)号：US20230235673A1

公开(公告)日：2023-07-27

申请号：US17585760

申请日：2022-01-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christian X. Campbell ,  Howard J. Liles ,  Russell Kim

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/141 ,  F01D5/282 ,  F05D2220/32 ,  F05D2300/6033 ,  F05D2250/71

Abstract: A gas turbine engine includes a turbine section that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.

公开(公告)号：US20230184136A1

公开(公告)日：2023-06-15

申请号：US17549168

申请日：2021-12-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Russell Kim ,  James T. Roach

IPC: F01D25/28 ,  F01D25/24

CPC classification number: F01D25/28 ,  F01D25/24

Abstract: An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.