公开(公告)号：US20180112597A1

公开(公告)日：2018-04-26

申请号：US15334804

申请日：2016-10-26

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Dennis M. Moura

IPC: F02C7/18 ,  F02C7/28 ,  F01D9/04

Abstract: A combustor seal for use in a combustor of a gas turbine engine including a seal with a multiple of slots that correspond with a multiple of 1st HPT vanes. A method of cooling within a gas turbine engine including communicating cooling air through combustor seal toward each of a multiple of 1st HPT vanes.

公开(公告)号：US20170184306A1

公开(公告)日：2017-06-29

申请号：US14982642

申请日：2015-12-29

Applicant: United Technologies Corporation

Inventor： John S. Tu ,  James B. Hoke ,  Jonathan Jeffery Eastwood ,  Kevin Joseph Low ,  Sean D. Bradshaw

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/005 ,  F23R3/002 ,  F23R3/06 ,  F23R3/26 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03043

Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.