公开(公告)号：US20160265371A1

公开(公告)日：2016-09-15

申请号：US15029474

申请日：2014-10-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Timothy Dale ,  Swati G. Bhanderi

IPC: F01D9/02 ,  F23R3/10

Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.

Abstract translation: 燃气涡轮发动机的燃烧器部分具有扩散器壳体，其具有可变壁厚度的结构锥体，其具有可定位的位置，用于减小锥体中的局部应力。

公开(公告)号：US10533437B2

公开(公告)日：2020-01-14

申请号：US15029474

申请日：2014-10-31

Applicant: United Technologies Corporation

Inventor： Timothy Dale ,  Swati G. Bhanderi

IPC: F01D9/02 ,  F01D25/30 ,  F01D25/24 ,  F23R3/04 ,  F23R3/50 ,  F23R3/10

Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.