公开(公告)号：US11053808B2

公开(公告)日：2021-07-06

申请号：US16790890

申请日：2020-02-14

Applicant: United Technologies Corporation

Inventor： Russell J. Bergman ,  Charles C. Wu ,  Brett Alan Bartling

IPC: F01D9/06 ,  F01D11/00 ,  F01D11/04 ,  F01D5/08 ,  F01D9/04 ,  F01D25/12

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：US10072585B2

公开(公告)日：2018-09-11

申请号：US14769591

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John H. Mosley ,  James P. Chrisikos ,  John J. O'Connor ,  Charles C. Wu ,  David Glasspoole ,  Roger Gates

IPC: F02C9/18 ,  F01D5/08 ,  F02C7/18

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.

公开(公告)号：US20160312631A1

公开(公告)日：2016-10-27

申请号：US15103561

申请日：2014-11-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Russell J. Bergman ,  Charles C. Wu ,  Brett Alan Bartling

IPC: F01D9/06 ,  F01D25/12 ,  F01D9/04 ,  F01D11/04 ,  F01D11/00

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：US20160003166A1

公开(公告)日：2016-01-07

申请号：US14769591

申请日：2014-03-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John H. Mosley ,  James P. Chrisikos ,  Roger Gates ,  John J. O'Connor ,  Charles C. Wu ,  David Glasspoole

IPC: F02C9/18 ,  F01D5/08 ,  F02C7/18

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.

Abstract translation: 用于燃气涡轮发动机涡轮部分的冷却系统包括支撑具有冷却通道的叶片的转子。 盘相对于转子固定，并且在转子和盘之间形成空腔。 排气源与空腔流体连通。 在空腔内布置有叶轮。 叶轮被构造成增加空腔内的流体压力以驱使排放空气源的排出空气，从而向冷却通道提供加压的冷却流体。