公开(公告)号：US11713679B1

公开(公告)日：2023-08-01

申请号：US17585760

申请日：2022-01-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D5/28 ,  F01D5/14

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

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：US20250027418A1

公开(公告)日：2025-01-23

申请号：US18353196

申请日：2023-07-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christian X. Campbell ,  Aaron Tomich ,  Peter J. Rosenfeld

IPC: F01D5/28 ,  C04B35/80 ,  D03D1/00 ,  D03D3/00 ,  D03D25/00

Abstract: An airfoil wall that includes a wishbone-shaped fiber layup structure that has first and second arms that merge into a single leg. The leg includes fiber tows from each of the arms and the tows are interwoven in the leg. Each of the arms includes a first section that is distal from the leg and a second section that is proximal to the leg. The first section defines a first thickness and a first fiber tow count. The second section defines a second thickness that is greater than the first thickness and a second fiber tow count that is greater than the first fiber tow count. The single leg defines a third thickness that is greater than the second thickness and a third fiber tow count that is greater than the second fiber tow count.

公开(公告)号：US20240376017A1

公开(公告)日：2024-11-14

申请号：US18196594

申请日：2023-05-12

Applicant: Raytheon Technologies Corporation

Inventor： Christian X. Campbell ,  Kathryn S. Read ,  James T. Roach ,  Robert A. White, III ,  Daniel Josiah Whitney

IPC: C04B35/80 ,  C04B35/628 ,  C04B35/64 ,  C04B35/657

Abstract: A method of forming a ceramic matrix composite includes fabricating a space filling insert by assembling the space filling insert from a fibrous ceramic material, placing the space filling insert into a tooling fixture, the tooling fixture having an internal shape complementary to a shape of the insert, and infiltrating the space filling insert with a first ceramic material. The method further includes forming a preform by laying up a plurality of fibrous ceramic plies and inserting the infiltrated space filling insert into a void defined by the plurality of plies. The method further includes infiltrating the preform with a second ceramic material.

公开(公告)号：US20240342954A1

公开(公告)日：2024-10-17

申请号：US18300863

申请日：2023-04-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christian X. Campbell ,  Robert A. White, III

IPC: B28B21/48 ,  B28B21/86 ,  B28B21/92 ,  F01D5/28

CPC classification number: B28B21/48 ,  B28B21/86 ,  B28B21/925 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/6033

Abstract: A method of fabricating an airfoil includes providing an airfoil core tube that is made of a rigidized ceramic fabric, using the airfoil core tube as a mandrel by braiding a plurality of ceramic fiber tows around the airfoil core tube to form one or more braided layers, where the airfoil core tube and the one or more braided layers forming an airfoil preform, and densifying the airfoil preform with a ceramic matrix material to thereby form a ceramic matrix composite airfoil.

公开(公告)号：US12078083B2

公开(公告)日：2024-09-03

申请号：US18084935

申请日：2022-12-20

Applicant: Raytheon Technologies Corporation

Inventor： Christian X. Campbell

IPC: F01D9/04 ,  B32B5/02 ,  B32B5/26 ,  B32B38/08

CPC classification number: F01D9/041 ,  B32B5/02 ,  B32B5/26 ,  B32B38/08 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/105 ,  B32B2305/076 ,  B32B2315/02 ,  B32B2603/00 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A method of forming a ceramic matrix composite (CMC) vane comprises drawing a continuous fiber sheet over at least one contoured surface to form a single-folded sheet. The single-folded sheet comprises an airfoil portion, a first platform at a first end of the airfoil portion, and an integral transition region between the airfoil portion and the first platform. The method further comprises mounting the airfoil portion on a mandrel, attaching a second platform to a second, opposing end of the airfoil portion to form a vane preform, and densifying the vane preform.