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公开(公告)号：US20150345405A1
公开(公告)日：2015-12-03
申请号：US14761073
申请日：2014-02-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Paul W. Duesler
CPC classification number: F02C9/18 , F01D5/08 , F01D19/00 , F01D25/10 , F02C3/06 , F02C7/28 , F05D2220/32 , F05D2230/642 , F05D2240/30 , F05D2260/232 , Y02T50/676
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.
Abstract translation: 燃气涡轮发动机具有带有叶片和盘的压缩机转子。 孔被径向向内限定在盘的内部。 燃烧器包括燃烧器喷嘴。 分接头敲击已经通过阀在燃烧器部分中燃烧并进入盘的孔中的空气。 还公开了一种方法。
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公开(公告)号：US11408300B2
公开(公告)日：2022-08-09
申请号：US16207669
申请日：2018-12-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Merry , Paul W. Duesler
Abstract: A gas turbine engine may include a rotor overspeed protection (ROP) assembly. The ROP assembly may include an annular blade outer air seal (BOAS) assembly including a ROP segment. The ROP assembly may include a stator vane coupled with the BOAS assembly/. The stator vane may include a stator flange disposed about a forward edge portion of the stator vane. The ROP segment may include a ROP flange extending in an axially aft direction from a main body of the ROP segment toward the stator vane, wherein the ROP flange is disposed radially inward of the stator flange.
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公开(公告)号：US11041677B2
公开(公告)日：2021-06-22
申请号：US14987393
申请日：2016-01-04
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Joseph W. Bridges, Jr.
Abstract: Aspects of the disclosure are directed to a heat exchanger comprising: a first plurality of channels configured to convey a first medium at a first set of temperatures along a first span of the first plurality of channels, the first set of temperatures including a first inlet temperature and a first outlet temperature, a second plurality of channels configured to convey a second medium at a second set of temperatures along a second span of the second plurality of channels, the second set of temperatures being at least partially different from the first set of temperatures and including a second inlet temperature and a second outlet temperature, and a core region where the first plurality of channels and the second plurality of channels are co-mingled with respect to one another.
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公开(公告)号：US10526916B2
公开(公告)日：2020-01-07
申请号：US15138727
申请日：2016-04-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Paul W. Duesler
IPC: F01D17/10 , F01D25/12 , F01D25/24 , F02C7/18 , F02K3/115 , F02K9/64 , F28D1/047 , F28D7/16 , F28F21/08 , F28F9/00 , F28F9/007 , F28F9/013 , F28F9/02 , F04D29/32 , F01D5/02
Abstract: A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.
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公开(公告)号：US20190218974A1
公开(公告)日：2019-07-18
申请号：US16364524
申请日：2019-03-26
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.
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Patent Agency Ranking
公开(公告)号：US10060353B2
公开(公告)日：2018-08-28
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.
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公开(公告)号：US20170268426A1
公开(公告)日：2017-09-21
申请号：US15074829
申请日：2016-03-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Duesler , Frederick M. Schwarz
CPC classification number: F02C7/32 , F02C6/08 , F02C7/141 , F02C7/185 , F02K3/115 , F04D29/5826 , F05D2260/213 , F05D2300/175 , F28D7/06 , F28D2021/0026 , F28F9/002 , F28F9/0246 , F28F2255/02 , F28F2265/26 , F28F2280/00 , Y02T50/675
Abstract: A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.
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公开(公告)号：US20170191762A1
公开(公告)日：2017-07-06
申请号：US14987393
申请日：2016-01-04
Applicant: United Technologies Corporation
Inventor： Paul W. Duesler , Joseph W. Bridges, JR.
CPC classification number: F28D7/0016 , B23P15/26 , F02C7/12 , F05D2260/213 , F28D7/0033 , F28D7/022 , F28D7/024 , F28D2021/0026 , Y02T50/671 , Y02T50/676
Abstract: Aspects of the disclosure are directed to a heat exchanger comprising: a first plurality of channels configured to convey a first medium at a first set of temperatures along a first span of the first plurality of channels, the first set of temperatures including a first inlet temperature and a first outlet temperature, a second plurality of channels configured to convey a second medium at a second set of temperatures along a second span of the second plurality of channels, the second set of temperatures being at least partially different from the first set of temperatures and including a second inlet temperature and a second outlet temperature, and a core region where the first plurality of channels and the second plurality of channels are co-mingled with respect to one another.
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公开(公告)号：US09632004B2
公开(公告)日：2017-04-25
申请号：US14423671
申请日：2013-10-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Duesler , Paul Filewich
CPC classification number: G01M7/08 , B23K26/356 , B23K2101/001 , C21D10/005 , C22F1/18
Abstract: A method for testing an edge of a rotor blade that has been hardened is disclosed. A shallow notch is created in the edge of the blade using a laser and the blade is then tested using an HCF process. If the blade passes the test, a deeper notch is imparted into the edge of the blade and the blade is retested. If the blade passes the second test, a third notch may be imparted into the edge of the blade and the blade is tested again. Any test failure may provide assistance in modifying the parameters used to harden the blade. The blade may be initially hardened using an LSP process.
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公开(公告)号：US11492973B2
公开(公告)日：2022-11-08
申请号：US16364524
申请日：2019-03-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul W. Duesler , Frederick M. Schwarz
IPC: F28F7/00 , F02C7/18 , F02K3/115 , F02C7/141 , F02C7/20 , F04D29/58 , F28D1/047 , F28D7/06 , F28F21/08 , F28F9/013 , 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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