公开(公告)号：US09976436B2

公开(公告)日：2018-05-22

申请号：US14779602

申请日：2014-03-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brad Powell

IPC: F01D11/24 ,  F01D11/22 ,  F01D11/20

CPC classification number: F01D11/22 ,  F01D11/20

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

公开(公告)号：US20170002834A1

公开(公告)日：2017-01-05

申请号：US14902373

申请日：2014-07-10

Applicant: United Technologies Corporation

Inventor： Brad Powell ,  Anthony R. Bifulco ,  Paul E. Coderre

IPC: F04D29/58 ,  F04D27/00 ,  F04D29/32 ,  F04D19/02

CPC classification number: F04D29/5826 ,  F01D5/082 ,  F01D5/084 ,  F02C7/185 ,  F04B1/2064 ,  F04B1/324 ,  F04D19/02 ,  F04D27/002 ,  F04D29/321 ,  F04D29/5833 ,  F04D29/584 ,  F05B2220/302

Abstract: An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions. At least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction. An example compressor including the spacer is also disclosed.

Abstract translation: 一种冷却燃气涡轮发动机的压缩机部分的示例性方法包括使来自压缩机的流动通过热交换器转向，该流量从压缩机沿第一方向移动，并且将流体从热交换器移回到压缩机中 第二个方向 用于燃气涡轮发动机的压缩机的示例性间隔件包括第一侧部分，与第一侧部分间隔开的第二侧部以及布置在第一和第二侧部之间的中间腹板。 第一和第二侧部和中间腹板中的至少一个包括至少一个孔，以在不同于芯流路流动方向的方向上传递流。 还公开了包括间隔件的示例性压缩机。

公开(公告)号：US10036278B2

公开(公告)日：2018-07-31

申请号：US14665797

申请日：2015-03-23

Applicant: United Technologies Corporation

Inventor： Brad Powell ,  Chong H. Park

IPC: F01D11/02 ,  F01D25/12 ,  F01D25/14 ,  F01D5/08 ,  F01D11/00 ,  F02C7/24 ,  F01D1/02 ,  F01D5/06

CPC classification number: F01D25/12 ,  F01D1/02 ,  F01D5/06 ,  F01D5/084 ,  F01D11/001 ,  F01D11/02 ,  F01D25/145 ,  F02C7/24 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/12 ,  F05D2240/15 ,  F05D2240/24 ,  F05D2260/231 ,  F05D2260/31 ,  Y02T50/671 ,  Y02T50/676

Abstract: In various embodiments, a high pressure compressor may comprise a thermal shield. The thermal shield may be installed between a first rotor and a second rotor. The thermal shield may also be installed radially inward of a stator. The stator may be a shrouded stator. Moreover, the thermal shield may be configured to thermally isolate and/or reduce the thermal load associated with windage on a rotor hub.

公开(公告)号：US20160047266A1

公开(公告)日：2016-02-18

申请号：US14779602

申请日：2014-03-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brad Powell

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F01D11/20

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

Abstract translation: 根据本公开的一个公开的非限制性实施例的用于燃气涡轮发动机的发动机壳体的叶片顶端间隙控制系统包括发动机壳体内的空气密封段。 驱动连杆延伸穿过发动机外壳，驱动连杆安装在空气密封段上。

公开(公告)号：US20180283196A1

公开(公告)日：2018-10-04

申请号：US15959501

申请日：2018-04-23

Applicant: United Technologies Corporation

Inventor： Brad Powell

IPC: F01D11/22 ,  F01D11/20

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

公开(公告)号：US10605109B2

公开(公告)日：2020-03-31

申请号：US15959501

申请日：2018-04-23

Applicant: United Technologies Corporation

Inventor： Brad Powell

IPC: F01D11/20 ,  F01D11/22 ,  F01D11/14

Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.

公开(公告)号：US10480533B2

公开(公告)日：2019-11-19

申请号：US14916425

申请日：2014-09-08

Applicant: United Technologies Corporation

Inventor： Brad Powell ,  Anthony R. Bifulco ,  Paul E. Coderre ,  John P. Virtue ,  Brian Lucker

IPC: F04D29/58 ,  F01D9/06 ,  F01D25/12 ,  F04D29/54 ,  F02C7/14 ,  F02K3/04 ,  F04D29/32

Abstract: An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.

公开(公告)号：US20160222982A1

公开(公告)日：2016-08-04

申请号：US14916425

申请日：2014-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brad Powell ,  Anthony R. Bifulco ,  Paul E. Coderre ,  John P. Virtue ,  Brian Lucker

IPC: F04D29/58 ,  F02K3/04 ,  F04D29/32

CPC classification number: F04D29/5846 ,  F01D9/065 ,  F01D25/125 ,  F02C7/14 ,  F02K3/04 ,  F04D29/321 ,  F04D29/541 ,  F04D29/5826 ,  F04D29/584 ,  F05D2220/3219 ,  F05D2220/36 ,  F05D2240/127 ,  F05D2260/20 ,  F05D2260/213

Abstract: An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.

Abstract translation: 对燃气轮机的压缩机进行冷却的一个示例性方法包括：将来自压缩机的流转向转向并沿着具有圆周分量和轴向分量的方向的压缩机的流动。