公开(公告)号：US20190162121A1

公开(公告)日：2019-05-30

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.

公开(公告)号：US20160231068A1

公开(公告)日：2016-08-11

申请号：US14615732

申请日：2015-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John T. Schmitz ,  Neal R. Herring ,  John H. Whiton ,  Joseph Turney ,  Brian St. Rock ,  Michael K. Ikeda

IPC: F28F9/02 ,  B23P15/26

CPC classification number: F28F9/026 ,  B23P15/26 ,  B33Y80/00 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28F9/02 ,  F28F9/0265 ,  F28F2255/18

Abstract: A heat exchanger system includes an additively manufactured inlet header upstream of, and in fluid communication with, the heat exchanger core and an additively manufactured exit header downstream of, and in fluid communication with, the heat exchanger core. A method of manufacturing a header for a ducted heat exchanger system for a gas turbine engine includes additively manufacturing a header with respect to a desired airflow therethrough.

Abstract translation: 热交换器系统包括在热交换器芯的上游并与之流体连通的加法制造的入口集管以及与热交换器芯下游并与热交换器芯流体连通的相加制造的出口集管。 一种制造用于燃气涡轮发动机的管道式热交换器系统的集管的方法包括相对于所需的气流相加地制造集管。

公开(公告)号：US11203977B2

公开(公告)日：2021-12-21

申请号：US16739598

申请日：2020-01-10

Applicant: United Technologies Corporation

Inventor： Joseph Turney ,  Michael K. Ikeda

IPC: F02C7/00 ,  F02C7/232 ,  F02C7/143 ,  F16K17/20

Abstract: A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.

公开(公告)号：US20200300168A1

公开(公告)日：2020-09-24

申请号：US16803095

申请日：2020-02-27

Applicant: United Technologies Corporation

Inventor： Neal R. Herring ,  Michael K. Ikeda ,  Peter Cocks

IPC: F02C7/236

Abstract: A fuel system for a gas turbine engine includes a primary fuel pump providing fuel flow during engine operation and a primary electric motor coupled to the primary fuel pump for driving the primary fuel pump during engine operation. A secondary system provides fuel flow in the absence of fuel flow from the primary fuel pump.

公开(公告)号：US20210079848A1

公开(公告)日：2021-03-18

申请号：US16815737

申请日：2020-03-11

Applicant: United Technologies Corporation

Inventor： Peter Cocks ,  Michael K. Ikeda

IPC: F02C7/236 ,  F02C9/26 ,  F02C3/13 ,  F02C7/36 ,  F04D13/06

Abstract: A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.

公开(公告)号：US10914242B2

公开(公告)日：2021-02-09

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00 ,  F02C7/14 ,  F02C7/32 ,  F02C7/224 ,  F02C3/04 ,  F02C7/22 ,  B64D13/06

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.

公开(公告)号：US20200232389A1

公开(公告)日：2020-07-23

申请号：US16739598

申请日：2020-01-10

Applicant: United Technologies Corporation

Inventor： Joseph Turney ,  Michael K. Ikeda

IPC: F02C7/232 ,  F02C7/143 ,  F16K17/20

Abstract: A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.