公开(公告)号：US10473117B2

公开(公告)日：2019-11-12

申请号：US14805536

申请日：2015-07-22

Applicant: United Technologies Corporation

Inventor： Albert Veninger ,  Conway Chuong

IPC: F02C3/14 ,  F04D29/54 ,  F01D25/28 ,  F23R3/26

Abstract: A turbine engine includes a diffuser connecting a compressor section and a turbine section. The diffuser includes a diffuser frame and multiple diffuser case sections are connected to the diffuser frame.

公开(公告)号：US10006306B2

公开(公告)日：2018-06-26

申请号：US14758367

申请日：2013-12-19

Applicant: United Technologies Corporation

Inventor： Jonathan Ariel Scott ,  Albert Veninger

IPC: F01D25/14 ,  F01D9/04 ,  F01D25/16 ,  F01D25/00 ,  F01D9/02 ,  F01D25/12 ,  F01D9/06 ,  F01D25/30 ,  F01D25/24

CPC classification number: F01D25/145 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/005 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/231 ,  Y02T50/673 ,  Y02T50/675

Abstract: A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts.

公开(公告)号：US20170023015A1

公开(公告)日：2017-01-26

申请号：US14805536

申请日：2015-07-22

Applicant: United Technologies Corporation

Inventor： Albert Veninger ,  Conway Chuong

IPC: F04D29/54 ,  F01D25/28 ,  F23R3/26

CPC classification number: F04D29/547 ,  F01D9/02 ,  F01D9/023 ,  F01D25/243 ,  F01D25/285 ,  F02C3/14 ,  F05D2230/72 ,  F05D2240/35 ,  F23R3/04 ,  F23R3/26 ,  F23R3/60

Abstract: A turbine engine includes a diffuser connecting a compressor section and a turbine section. The diffuser includes a diffuser frame and multiple diffuser case sections are connected to the diffuser frame.

Abstract translation: 涡轮发动机包括连接压缩机部分和涡轮部分的扩散器。 扩散器包括扩散器框架，并且多个扩散器壳体部分连接到扩散器框架。

公开(公告)号：US20150330250A1

公开(公告)日：2015-11-19

申请号：US14758367

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ariel Scott ,  Albert Veninger

IPC: F01D25/14 ,  F01D9/02 ,  F01D25/12 ,  F01D25/00 ,  F01D25/30 ,  F01D25/24

CPC classification number: F01D25/145 ,  F01D9/02 ,  F01D9/041 ,  F01D9/065 ,  F01D25/005 ,  F01D25/12 ,  F01D25/125 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/231 ,  Y02T50/673 ,  Y02T50/675

Abstract: A turbine exhaust case (28) for a gas turbine engine (10) comprises a frame (100), a vane fairing (108), a heat shield (124, 126, 128), and a serpentine cooling path. The frame has an outer ring (102) and an inner ring (104) connected by a hollow strut (106) with a radial service line passage (132). The vane fairing is disposed between the inner ring and the outer ring to define a core airflow path. The heat shield is disposed between the vane fairing and the frame. The serpentine cooling flow path passes through and around the outer ring, the inner ring, and the plurality of struts

Abstract translation: 用于燃气涡轮发动机（10）的涡轮机排气箱（28）包括框架（100），叶片整流罩（108），隔热罩（124,126,128）和蛇形冷却路径。 框架具有通过中空支柱（106）与径向服务线通道（132）连接的外环（102）和内环（104）。 叶片整流罩设置在内环和外圈之间以限定芯气流路径。 隔热罩设置在叶片整流罩和框架之间。 蛇形冷却流路穿过外环，内环和多个支柱