公开(公告)号：US20240117754A1

公开(公告)日：2024-04-11

申请号：US17961987

申请日：2022-10-07

Applicant: Raytheon Technologies Corporation

Inventor： Connor C. Perry ,  Xiaomei Fang ,  Bradley L. Paquin ,  Jacob Yochimowitz ,  Sushruth G. Kamath ,  Jun Cao

IPC: F01D25/00 ,  F01D9/02 ,  F01D25/08 ,  F01D25/14

CPC classification number: F01D25/005 ,  F01D9/02 ,  F01D25/08 ,  F01D25/145 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/10 ,  F05D2240/128 ,  F05D2240/14 ,  F05D2240/15 ,  F05D2260/231 ,  F05D2300/211

Abstract: A gas turbine engine component includes a structural component having a surface, the structural component having an organic matrix composite material; and a cured thermal barrier layer on the surface, wherein the cured thermal barrier layer is a pre-ceramic layer including inorganic matrix containing silicon oxides reinforced with glass or quartz fibers.