公开(公告)号：WO2015112227A3

公开(公告)日：2015-10-22

申请号：PCT/US2014064213

申请日：2014-11-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BERMAN RUSSELL J ,  WU CHARLES C ,  BARTLING BRETT ALAN

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D9/06 ,  F01D9/041 ,  F01D11/001 ,  F01D11/04 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/81

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Abstract translation: 叶片包括从径向外部平台延伸到径向内部平台的翼型件。 一对腿从径向内部平台径向向内延伸，并且空气流动通道穿过径向外部平台延伸通过翼型件，并进入限定在该对腿部之间的腔室中。 一对腿中的一个包括多个喷射器孔，其构造成允许来自径向外平台的空气通过孔的外部。 还公开了一种燃气涡轮发动机。

公开(公告)号：EP3068996A4

公开(公告)日：2016-11-16

申请号：EP14879596

申请日：2014-11-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BERMAN RUSSELL J ,  WU CHARLES C ,  BARTLING BRETT ALAN

IPC: F01D11/00 ,  F01D11/04

CPC classification number: F01D9/06 ,  F01D9/041 ,  F01D11/001 ,  F01D11/04 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/81

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

公开(公告)号：EP2971673A4

公开(公告)日：2016-11-09

申请号：EP14774334

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MOSLEY JOHN H ,  CHRISIKOS JAMES P ,  GATES ROGER ,  O'CONNOR JOHN J ,  WU CHARLES C ,  GLASSPOOLE DAVID

IPC: F01D5/08

CPC classification number: F02C9/18 ,  F01D5/082 ,  F02C7/18 ,  F05D2220/3215 ,  Y02T50/673 ,  Y02T50/676

Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.