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公开(公告)号：US20200230770A1
公开(公告)日：2020-07-23
申请号：US16840687
申请日：2020-04-06
Applicant: United Technologies Corporation
Inventor： Glenn Levasseur , Krzysztof Barnat , Gordon Miller Reed
Abstract: Disclosed is an improved method for cryogenically cooling machining tools where a feedback-controlled system uses temperature, pressure, flow and/or infrared sensors to regulate flow of a cryogenic coolant and functioning of a cutting tool.
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公开(公告)号：US10428765B2
公开(公告)日：2019-10-01
申请号：US15452647
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , Ryan A. Singh
Abstract: Disclosed is a flutter damper, including an acoustic liner in fluid communication with a fluid flow the acoustic liner being configured for peak acoustical energy absorption at a frequency range greater than a frequency range associated with fan flutter, and a plurality of modular chambers configured for peak acoustical energy absorption at a frequency range associated with one or more fan flutter modes, the plurality of modular chambers disposed radially outside the acoustic liner, the plurality of modular chambers including a circumferential gap between proximate circumferential ends of at least one adjacent pair of modular chambers, and the plurality of modular chambers each including a plurality of circumferentially aligned and connected chamber segments, and wherein at least one of the chambers in the plurality of modular chambers has a mutually unique length, width and/or height or shape.
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公开(公告)号：US20180258955A1
公开(公告)日：2018-09-13
申请号：US15452622
申请日：2017-03-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , Ryan A. Singh
CPC classification number: F02K3/06 , F02C7/045 , F05D2220/32 , F05D2260/963 , Y02T50/672
Abstract: Disclosed is a flutter damper, including an acoustic liner in fluid communication with a fluid flow, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, and a plurality of modular chambers, each of the plurality of modular chambers being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and the plurality of modular chambers being disposed radially outside of the acoustic liner, and the plurality of modular chambers including a circumferential gap between proximate circumferential ends of at least one adjacent pair of modular chambers, wherein, the plurality of modular chambers each include a plurality of circumferentially aligned and connected chamber segments.
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公开(公告)号：US20160169783A1
公开(公告)日：2016-06-16
申请号：US14903935
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , James T. Roach , Grant O. Cook, III , Raymond K. Kersey
IPC: G01N3/08
CPC classification number: G06K19/07749 , B29C37/0025 , B29C64/106 , B29C64/124 , B29C64/153 , B29C70/42 , B29C70/54 , B29K2079/08 , B29K2105/0058 , B29K2105/12 , B29K2105/251 , B29K2105/253 , B29K2307/04 , B29K2309/08 , B29L2009/008 , B29L2031/082 , B32B27/08 , B32B27/281 , B32B2250/02 , B32B2255/10 , B32B2255/205 , B32B2262/101 , B32B2262/106 , B32B2603/00 , B33Y10/00 , B33Y70/00 , B33Y80/00 , C23C18/1641 , C23C18/1653 , C23C18/1657 , C23C18/166 , C23C18/22 , C23C18/30 , C23C18/32 , C23C28/021 , C23C28/023 , C25D1/003 , C25D1/02 , C25D1/20 , C25D3/02 , C25D5/06 , C25D5/54 , C25D5/56 , C25D7/00 , C25D7/04 , C25D9/02 , C25D17/12 , G01B7/16 , G01D5/12 , G01N3/08 , G01N2203/026 , G01N2203/0268 , G01N2203/0298
Abstract: A plated polymer test specimen for measuring strain imparted to the plated polymer test specimen includes a polymeric substrate including a top, a bottom, a pair of opposing edges and a pair of opposing end edges, the top and bottom being plated with top and bottom metal layers respectively, the side edges and the end edges being at least substantially free of plating. The substrate includes two spaced-apart holes that extend through the top metal layer, substrate and the bottom metal layer. Alternatively, the substrate may comprise a composite layup structure. A method for testing the strain imparted to a plated polymer test specimen is also disclosed.
Abstract translation: 用于测量赋予镀覆聚合物测试样品的应变的镀覆聚合物测试样品包括聚合物基材，其包括顶部，底部，一对相对的边缘和一对相对的端部边缘，顶部和底部镀有顶部和底部金属 层边缘和端边缘至少基本上没有电镀。 衬底包括延伸穿过顶部金属层，衬底和底部金属层的两个间隔开的孔。 或者，衬底可以包括复合叠层结构。 还公开了一种用于测试赋予镀覆聚合物试样的应变的方法。
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公开(公告)号：US20160144602A1
公开(公告)日：2016-05-26
申请号：US14903913
申请日：2014-07-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , Shari Bugaj , Grant O. Cook
CPC classification number: B32B15/08 , B29B11/06 , B29B11/14 , B29C43/183 , B29C45/14 , B29K2101/10 , B29K2101/12 , B29K2105/20 , B29K2705/00 , B29L2009/00 , B32B2250/02 , B32B2307/558 , B32B2605/00 , C23C18/1605 , C23C26/00 , C25D5/022 , C25D7/04 , E04B1/19 , E04B1/30 , E04B2001/1927
Abstract: An encapsulated polymeric article is disclosed. The encapsulated polymeric article may include a polymer substrate and a metallic outer shell at least partially encapsulating the polymer substrate. The encapsulated polymeric article may be fabricated by a method comprising: 1) providing a mandrel in a shape of the encapsulated polymeric article, 2) shaping the metallic outer shell on the mandrel, 3) removing the mandrel from the metallic outer shell, and 4) molding the polymeric substrate into the metallic outer shell through a port formed in the metallic outer shell to provide the encapsulated polymeric article.
Abstract translation: 公开了一种封装的聚合物制品。 封装的聚合物制品可以包括聚合物基材和至少部分地包封聚合物基材的金属外壳。 封装的聚合物制品可以通过以下方法制造：1）提供具有封装的聚合物制品形状的心轴，2）在心轴上成形金属外壳，3）从金属外壳中去除心轴，4 ）通过形成在金属外壳中的端口将聚合物基材模制成金属外壳，以提供封装的聚合物制品。
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Patent Agency Ranking
公开(公告)号：US11280271B2
公开(公告)日：2022-03-22
申请号：US14433444
申请日：2013-10-03
Applicant: United Technologies Corporation
Inventor： Glenn Levasseur , Gabriel L. Suciu , Gary M. Stetson
Abstract: A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.
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公开(公告)号：US20200317370A1
公开(公告)日：2020-10-08
申请号：US16376294
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A repair system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters wherein each of the gas turbine engine components is an as-run component and has been exposed to a substantially identical general wear pattern. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A repair module is configured to generate a repair formula based on the predictive model. The repair formula is configured to receive a set of measured parameters of an as-run gas turbine engine component and determine a suggested repair capable of repairing the as-run gas turbine engine component.
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公开(公告)号：US20200023982A1
公开(公告)日：2020-01-23
申请号：US16039849
申请日：2018-07-19
Applicant: United Technologies Corporation
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US20180306059A1
公开(公告)日：2018-10-25
申请号：US15495283
申请日：2017-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ram Ranjan , James D. Hill , Glenn Levasseur , Joel H. Wagner
CPC classification number: F01D25/14 , F05D2260/208 , F28D15/0266 , F28D15/0275 , F28D2021/0026
Abstract: A turbine casing may comprise a casing body a heat pipe disposed in the casing body. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be located forward the condensation section. The vaporization section may be located in a high pressure turbine region of the casing body. The condensation section may be located in a low pressure turbine region of the casing body.
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公开(公告)号：US20180216473A1
公开(公告)日：2018-08-02
申请号：US15420882
申请日：2017-01-31
Applicant: United Technologies Corporation
Inventor： James D. Hill , Ram Ranjan , Glenn Levasseur
CPC classification number: F01D5/187 , F01D5/181 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2240/24 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2260/208 , Y02T50/676
Abstract: An airfoil may comprise an airfoil body having a leading edge and a trailing edge. A heat pipe may be disposed within the airfoil. The heat pipe may include a vaporization section and a condensation section. The vaporization section may be disposed within the airfoil body and may be configured to remove heat from the trailing edge. The second cooling apparatus may be disposed within the airfoil body and may be configured to remove heat from the leading edge.
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