公开(公告)号：US11041391B2

公开(公告)日：2021-06-22

申请号：US16852728

申请日：2020-04-20

Applicant: Raytheon Technologies Corporation

Inventor： Steven D. Porter ,  Shawn M. McMahon ,  Kevin Zacchera ,  Noah Wadsworth ,  Christopher Whitfield ,  Sean D. Bradshaw ,  Dennis M. Moura ,  David Bitzko ,  Alex J. Schneider

IPC: F01D9/02 ,  F01D11/00 ,  F01D25/12 ,  F01D9/04

Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.