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公开(公告)号：US11248490B2
公开(公告)日：2022-02-15
申请号：US16004687
申请日：2018-06-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nathan K. Galle , Brian C. McLaughlin
Abstract: A thermally responsive flow meter may comprise a coil and a plate coupled to the coil. The plate may define a first airflow aperture. The plate may translate in a circumferential direction in response to a thermal expansion of the coil. The thermally responsive flow meter may regulate the flow of air through a second airflow aperture.
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公开(公告)号：US20210003284A1
公开(公告)日：2021-01-07
申请号：US16585836
申请日：2019-09-27
Applicant: United Technologies Corporation
Inventor： Milton A. Fong , Russell B. Hanson , Eric D. Gray , Michael D. Collier , Nathan K. Galle , Salvatore Siciliano
Abstract: Combustor mounting structures for gas turbine engines are described. The combustor mounting structures include a shell portion defining an outer ring arranged at an outer radius relative to a central axis, a combustor connection element defining an inner ring arranged at an inner radius that is less than the outer radius relative to the central axis, and a plurality of struts extending radially between and connecting the shell portion to the combustor connection element, wherein one or more flow apertures are defined between the shell portion and the combustor connection element in a radial direction and between adjacent struts of the plurality of struts in a circumferential direction.
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公开(公告)号：US11530650B2
公开(公告)日：2022-12-20
申请号：US16034573
申请日：2018-07-13
Applicant: United Technologies Corporation
Inventor： Nathan K. Galle , Steven M. Dvorak
Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section operably coupled to the compressor section. A primary flow path is defined through the compressor section, the combustor section, and the turbine section. An engine case surrounds the compressor section, the combustor section, and the turbine section. The gas turbine engine also includes a means for providing an active variable cooling flow through a bypass duct external to the engine case to a secondary flow cavity of the turbine section.
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公开(公告)号：US20170335707A1
公开(公告)日：2017-11-23
申请号：US15158782
申请日：2016-05-19
Applicant: United Technologies Corporation
Inventor： Nathan K. Galle
CPC classification number: F01D11/08 , F01D25/246 , F02C3/04 , F05D2220/32 , F05D2230/11 , F05D2230/21 , F05D2240/11 , F05D2250/21 , F05D2250/231 , F05D2250/232 , F05D2260/607 , Y02T50/671 , Y02T50/675
Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including a body including a raised material that extends beyond the outer surface of the body and the raised material includes an inlet hole formed through the raised material.
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公开(公告)号：US11021962B2
公开(公告)日：2021-06-01
申请号：US16108763
申请日：2018-08-22
Applicant: United Technologies Corporation
Inventor： Neil L. Tatman , Nathan K. Galle , Richard K. Hayford
Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.
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Patent Agency Ranking
公开(公告)号：US20200063564A1
公开(公告)日：2020-02-27
申请号：US16108763
申请日：2018-08-22
Applicant: United Technologies Corporation
Inventor： Neil L. Tatman , Nathan K. Galle , Richard K. Hayford
Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.
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公开(公告)号：US20200018240A1
公开(公告)日：2020-01-16
申请号：US16034573
申请日：2018-07-13
Applicant: United Technologies Corporation
Inventor： Nathan K. Galle , Steven M. Dvorak
Abstract: A gas turbine engine includes a compressor section, a combustor section, and a turbine section operably coupled to the compressor section. A primary flow path is defined through the compressor section, the combustor section, and the turbine section. An engine case surrounds the compressor section, the combustor section, and the turbine section. The gas turbine engine also includes a means for providing an active variable cooling flow through a bypass duct external to the engine case to a secondary flow cavity of the turbine section.
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公开(公告)号：US10385717B2
公开(公告)日：2019-08-20
申请号：US15291650
申请日：2016-10-12
Applicant: United Technologies Corporation
Inventor： Nathan K. Galle
Abstract: A seal may comprise a first ply including an annular shape and a second ply including a discontinuous annular shape having an axial split. The second ply may be positioned adjacent to a surface of the first ply.
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公开(公告)号：US10344611B2
公开(公告)日：2019-07-09
申请号：US15158782
申请日：2016-05-19
Applicant: United Technologies Corporation
Inventor： Nathan K. Galle
Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals disposed therein, the blade outer air seals each including a body including a raised material that extends beyond the outer surface of the body and the raised material includes an inlet hole formed through the raised material.
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公开(公告)号：US20190128134A1
公开(公告)日：2019-05-02
申请号：US15798763
申请日：2017-10-31
Applicant: United Technologies Corporation
Inventor： Terence P. Tyler , Thurman Carlo Dabbs , Kevin J. Ryan , Nathan K. Galle
Abstract: A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.
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