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1.发明申请ADDITIVE MANUFACTURED DUCTED HEAT EXCHANGER SYSTEM WITH ADDITIVELY MANUFACTURED HEADER 审中-公开具有附加制造长度的添加剂制造的导热换热器系统公开(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
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。
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公开(公告)号：US10830543B2
公开(公告)日：2020-11-10
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
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.
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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
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.
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公开(公告)号：US11161621B2
公开(公告)日：2021-11-02
申请号：US15874274
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： Joseph Turney
IPC: B01D46/00 , B64D33/10 , F02C7/143 , F02C7/057 , B64D13/00 , F28F19/01 , F28F19/00 , F28D9/00 , F28D21/00 , F28D11/02 , B01D46/18
Abstract: Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.
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Patent Agency Ranking
公开(公告)号：US11255268B2
公开(公告)日：2022-02-22
申请号：US16050409
申请日：2018-07-31
Applicant: United Technologies Corporation
Inventor： Joseph Turney
Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.
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公开(公告)号：US20200040820A1
公开(公告)日：2020-02-06
申请号：US16050409
申请日：2018-07-31
Applicant: United Technologies Corporation
Inventor： Joseph Turney
Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a turbine section, with both the main compressor section and the turbine section housing rotatable components. A first tap taps air compressed by the main compressor section at an upstream location upstream of the downstream most location. The first tap passes through a heat exchanger, and to a cooling compressor. Air downstream of the cooling compressor is selectively connected to reach at least one of the rotatable components. The cooling compressor is connected to rotate at a speed proportional to a rotational speed in one of the main compressor section and the turbine section. A valve system includes a check valve for selectively blocking flow downstream of the cooling compressor from reaching the at least one rotatable component. A dump valve selectively dumps air downstream of the cooling compressor. A method is also disclosed.
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公开(公告)号：US20190217965A1
公开(公告)日：2019-07-18
申请号：US15874274
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： Joseph Turney
CPC classification number: B64D33/10 , B01D46/18 , B64D13/00 , F02C7/057 , F02C7/143 , F28D9/0062 , F28D11/02 , F28D2021/0021 , F28F19/006 , F28F19/01 , F28F2250/106
Abstract: Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.
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公开(公告)号：US20200300169A1
公开(公告)日：2020-09-24
申请号：US16803134
申请日：2020-02-27
Applicant: United Technologies Corporation
Inventor： Joseph Turney
Abstract: A fuel system for a gas turbine engine includes an accessory gearbox driven by a mechanical link to the gas turbine engine, a primary fuel pump providing a first fuel flow during engine operation, and a secondary fuel pump providing a second fuel flow. The primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.
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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
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.
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