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。

公开(公告)号：US11149649B2

公开(公告)日：2021-10-19

申请号：US16104281

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  John P. Virtue

IPC: F02C7/268 ,  B64D27/24 ,  B64D33/00 ,  F02C9/26 ,  F02C9/54 ,  F02K5/00 ,  B64D27/02 ,  F02C6/14 ,  B64D27/10 ,  B64D31/06

Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine, an electric motor operable to perform an electric taxiing of the hybrid electric aircraft, and a controller. The controller is operable to prevent fuel flow to the gas turbine engine during at least a portion of the electric taxiing and monitor for a powered warm-up request during the electric taxiing. A powered warm-up state of the gas turbine engine is initiated based on detecting the powered warm-up request. The powered warm-up state adds heat to one or more components of the gas turbine engine prior to transitioning to a takeoff power state. The gas turbine engine transitions from the powered warm-up state to the takeoff power state after reaching a target temperature of the one or more components in the powered warm-up state.

公开(公告)号：US20200056549A1

公开(公告)日：2020-02-20

申请号：US16104579

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  John P. Virtue

IPC: F02C9/18 ,  F02C6/14 ,  F02C7/275

Abstract: An embodiment of an engine assembly includes a plurality of offtakes powered by a combustion turbine engine having a high spool and at least one lower spool, and a controller configured to operate the combustion turbine engine through a range between a first low-idle mode, a second high idle mode, and a maximum takeoff power rating mode. The controller operates the engine in the low-idle mode by directing at least a first portion of power from the at least one lower spool to the plurality of offtakes, and wherein the controller operates the engine in the high idle mode by increasing a speed of the high spool relative to a speed of the high spool in the low-idle mode, thereby increasing a compressor outlet (T3) temperature in the high idle mode relative to a T3 temperature in the low-idle mode.

公开(公告)号：US20200056546A1

公开(公告)日：2020-02-20

申请号：US16104281

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  John P. Virtue

IPC: F02C7/268 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  B64D33/00 ,  F02C9/26

Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine, an electric motor operable to perform an electric taxiing of the hybrid electric aircraft, and a controller. The controller is operable to prevent fuel flow to the gas turbine engine during at least a portion of the electric taxiing and monitor for a powered warm-up request during the electric taxiing. A powered warm-up state of the gas turbine engine is initiated based on detecting the powered warm-up request. The powered warm-up state adds heat to one or more components of the gas turbine engine prior to transitioning to a takeoff power state. The gas turbine engine transitions from the powered warm-up state to the takeoff power state after reaching a target temperature of the one or more components in the powered warm-up state.

公开(公告)号：US10995674B2

公开(公告)日：2021-05-04

申请号：US16104579

申请日：2018-08-17

Applicant: United Technologies Corporation

Inventor： Neil Terwilliger ,  John P. Virtue

IPC: F02C7/32 ,  F02C6/14 ,  F02C7/275 ,  F02C7/36 ,  F02C9/28 ,  F02C9/18

Abstract: An embodiment of an engine assembly includes a plurality of offtakes powered by a combustion turbine engine having a high spool and at least one lower spool, and a controller configured to operate the combustion turbine engine through a range between a first low-idle mode, a second high idle mode, and a maximum takeoff power rating mode. The controller operates the engine in the low-idle mode by directing at least a first portion of power from the at least one lower spool to the plurality of offtakes, and wherein the controller operates the engine in the high idle mode by increasing a speed of the high spool relative to a speed of the high spool in the low-idle mode, thereby increasing a compressor outlet (T3) temperature in the high idle mode relative to a T3 temperature in the low-idle mode.