公开(公告)号：WO2014175969A3

公开(公告)日：2015-01-08

申请号：PCT/US2014023949

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WANG CHENG-ZHANG ,  GLAHN JORN A ,  CLOUD DAVID F ,  MUNSELL PETER M ,  CRAWLEY CLIFTON J JR ,  NEWMAN ROBERT ,  STEARNS MICHELLE DIANA

IPC: F01D25/24 ,  F01D25/12 ,  F02C7/12 ,  F04D29/52 ,  F04D29/58

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F02C7/18 ,  F05D2240/14 ,  F05D2260/14 ,  F05D2260/20 ,  F05D2260/2212 ,  F05D2260/97 ,  Y02T50/676

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Abstract translation: 涡轮发动机包括具有低压涡轮机的涡轮机部分和围绕轴线布置的涡轮机壳体。 框架组件限定外腔和内腔，其中外腔包括构造并适于将冷却空气与涡轮机壳连通的至少一个开口。 传送管设置在外腔内并且被配置和适于接收冷却空气。 传送管包括弯曲部，该弯曲部被配置为向外腔内的冷却空气赋予圆周速度。

公开(公告)号：WO2014084951A2

公开(公告)日：2014-06-05

申请号：PCT/US2013059202

申请日：2013-09-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： RONAN MICHAEL ,  CARMINATI DANIEL ,  WANG CHENG-ZHANG

CPC classification number: F02C6/08 ,  F04D27/023 ,  F04D29/522 ,  Y02T50/671

Abstract: An example turbomachine structure includes a case having a radially extending port, and at least one rib configured to direct flow through and past the port.

Abstract translation: 一种示例涡轮机械结构包括具有径向延伸端口的壳体以及被配置为引导流动通过并经过端口的至少一个肋。

公开(公告)号：EP2898190A4

公开(公告)日：2015-10-14

申请号：EP13859392

申请日：2013-09-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： RONAN MICHAEL ,  CARMINATI DANIEL ,  WANG CHENG-ZHANG

IPC: F01D25/24 ,  F02C7/12 ,  F04D29/52

CPC classification number: F02C6/08 ,  F04D27/023 ,  F04D29/522 ,  Y02T50/671

公开(公告)号：EP2971612A4

公开(公告)日：2017-01-04

申请号：EP14787748

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WANG CHENG-ZHANG ,  GLAHN JORN A ,  CLOUD DAVID F ,  MUNSELL PETER M ,  CRAWLEY CLIFTON J JR ,  NEWMAN ROBERT ,  STEARNS MICHELLE DIANA

IPC: F01D25/24 ,  F01D9/04 ,  F01D9/06 ,  F01D25/12 ,  F01D25/16 ,  F02C7/12 ,  F02C7/18 ,  F04D29/52 ,  F04D29/58

CPC classification number: F01D25/24 ,  F01D9/041 ,  F01D9/065 ,  F01D25/162 ,  F02C7/18 ,  F05D2240/14 ,  F05D2260/14 ,  F05D2260/20 ,  F05D2260/2212 ,  F05D2260/97 ,  Y02T50/676

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

公开(公告)号：EP2875222A4

公开(公告)日：2016-03-02

申请号：EP13820243

申请日：2013-07-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DOUGAN DONALD ,  CARMINATI DANIEL ,  WANG CHENG-ZHANG

IPC: F02C7/00 ,  F02C7/20 ,  F02C7/32

CPC classification number: F01D25/243 ,  F01D25/12 ,  F02C6/08 ,  F04D29/522 ,  F05D2240/12 ,  F05D2260/606 ,  Y02T50/671

Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.

公开(公告)号：EP2812548A4

公开(公告)日：2015-10-21

申请号：EP13747274

申请日：2013-02-05

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WANG CHENG-ZHANG ,  PHILLIPS THOMAS G ,  CLOUD DAVID F ,  MUNSELL PETER M

IPC: F02C3/04 ,  F01D9/02 ,  F01D9/06 ,  F02C6/08 ,  F02C7/04 ,  F02C7/18 ,  F02C9/18 ,  F02K3/00

CPC classification number: F02C6/08 ,  F01D9/023 ,  F01D9/065 ,  F02C7/185 ,  F02C9/18 ,  F05D2260/601 ,  F05D2270/17 ,  F05D2270/301 ,  Y02T50/675

Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.