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公开(公告)号：US10794288B2
公开(公告)日：2020-10-06
申请号：US14793119
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Paul W. Duesler
IPC: F02C7/18 , F02K3/06 , F02C7/141 , F02C9/18 , F02K3/075 , F02C7/042 , F02C7/16 , F02C7/04 , F02K3/02
Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.
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公开(公告)号：US10287982B2
公开(公告)日：2019-05-14
申请号：US14826905
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
IPC: F02C7/18 , F02K3/115 , F02C7/141 , F02C7/20 , F04D29/58 , F28D1/047 , F28D7/06 , F28D21/00 , F04D19/02 , F28F9/22
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.
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公开(公告)号：US10253695B2
公开(公告)日：2019-04-09
申请号：US15062400
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
IPC: F02C7/18 , F28F9/02 , F02K3/115 , F02C7/141 , F04D29/58 , F28F9/24 , F28D7/06 , F28D1/047 , F28D21/00
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.
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公开(公告)号：US10094296B2
公开(公告)日：2018-10-09
申请号：US14761073
申请日：2014-02-11
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Paul W. Duesler
Abstract: A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.
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公开(公告)号：US20180058328A1
公开(公告)日：2018-03-01
申请号：US15244025
申请日：2016-08-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Paul W. Duesler
CPC classification number: F02C7/141 , F02C7/18 , F02C7/185 , F02C9/18 , F05C2201/90 , F05D2260/213 , F05D2300/1723 , F05D2300/176 , Y02T50/676
Abstract: A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.
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Patent Agency Ranking
公开(公告)号：US20170307311A1
公开(公告)日：2017-10-26
申请号：US15138491
申请日：2016-04-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Paul W. Duesler
CPC classification number: F28F21/087 , F01D9/065 , F02C7/185 , F02K3/02 , F05D2260/213 , F05D2300/175 , F05D2300/182 , F28D1/0475 , F28D7/12 , F28F1/28 , F28F1/40 , Y02T50/676
Abstract: A heat exchanger system for use in a gas turbine engine has a plurality of circumferentially spaced heat exchangers. The spaced heat exchangers are formed of a nickel alloy material including more than 50-percent by volume gamma-prime intermetallic phase material. A gas turbine engine is also disclosed.
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公开(公告)号：US20170204787A1
公开(公告)日：2017-07-20
申请号：US15000618
申请日：2016-01-19
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.
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公开(公告)号：US20170044983A1
公开(公告)日：2017-02-16
申请号：US14826905
申请日：2015-08-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/185 , F02C7/141 , F02C7/18 , F02C7/20 , F02K3/115 , F04D19/02 , F04D29/5826 , F05D2260/213 , F28D1/0475 , F28D7/06 , F28D2021/0026 , F28F2009/222 , F28F2245/00 , F28F2250/06 , F28F2255/00 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 HEX可以包括中央歧管，其包括入口部分，第一出口部分和第二出口部分。 HEX还可以包括耦合到中央歧管的多个管，多个管包括至少第一管，第二管，第三管和第四管，至少部分地封装所述多个管的护罩， 以及由所述护罩，所述多个管和所述中央歧管的外表面中的至少一个限定的冷却空气流动路径，其中所述冷却空气流动路径与所述多个管正交。
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公开(公告)号：US20170044982A1
公开(公告)日：2017-02-16
申请号：US14826871
申请日：2015-08-14
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/185 , F01D25/12 , F02C7/141 , F02C7/32 , F05D2220/32 , F05D2240/91 , F05D2250/42 , F05D2260/213 , F05D2260/232 , F05D2260/30 , F05D2260/941 , F28F9/002 , F28F2265/26 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise an intake manifold in fluid communication with a compressor section and configured to receive air from the compressor section, an outtake manifold in fluid communication with the intake manifold via a tube, and a cooling air flow path defined by at least one of an outer surface of the tube, an outer surface of the intake manifold, and an outer surface of the outtake manifold, wherein the cooling air flow path is orthogonal to said tube. The air from the intake manifold may travel through the tube to the outtake manifold and from the outtake manifold to a portion of the gas turbine engine.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 HEX可以包括与压缩机部分流体连通并被配置为从压缩机部分接收空气的进气歧管，经由管与进气歧管流体连通的出口歧管和由至少一个 管的外表面，进气歧管的外表面和出口歧管的外表面，其中冷却空气流动路径与所述管正交。 来自进气歧管的空气可以通过管移动到出口歧管，并且从出口歧管移动到燃气涡轮发动机的一部分。
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公开(公告)号：US20170044980A1
公开(公告)日：2017-02-16
申请号：US15062400
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/18 , F02C7/141 , F02K3/115 , F04D29/5826 , F05D2260/213 , F28D1/0475 , F28D7/06 , F28D2021/0021 , F28D2021/0026 , F28F9/0268 , F28F9/24 , Y02T50/675
Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.
Abstract translation: 提供一种用于在燃气涡轮发动机中冷却空气的热交换器（HEX）。 提供可调节阻尼器。 可调阻尼器可以用于阻止HEX相对于气体涡流发动机的运动。 可调节阻尼器可以包括：第一管; 至少部分地位于第一管内的第二管; 联接到所述第二管的壳体; 可移动构件，所述可移动构件包括与所述第二管接触的接触表面; 可调节地联接到所述壳体的调节构件; 以及位于所述可移动构件和所述调节构件之间的弹簧构件，所述弹簧构件构造成响应于调节构件相对于所述壳体移动而被压缩或减压中的至少一个。
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