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公开(公告)号：US08850793B2
公开(公告)日：2014-10-07
申请号：US14102764
申请日：2013-12-11
Applicant: United Technologies Corporation
Inventor： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz
CPC classification number: F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.
Abstract translation: 涡轮风扇发动机被公开并且包括与风扇部分连通的风扇和压缩机，燃烧器，涡轮机和联接到风扇并由涡轮机旋转的减速机构。 涡轮机包括包括三级或更多级的第一涡轮机部分和包括至少两级的第二涡轮部分。 第一涡轮部分中的翼型件与旁路区域的比例小于约170。
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52.发明授权公开(公告)号：US11015550B2
公开(公告)日：2021-05-25
申请号：US15887183
申请日：2018-02-02
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.
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公开(公告)号：US10934938B2
公开(公告)日：2021-03-02
申请号：US15217108
申请日：2016-07-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Steven H. Zysman
Abstract: A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.
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公开(公告)号：US10830148B2
公开(公告)日：2020-11-10
申请号：US15978455
申请日：2018-05-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine includes a main compressor. A tap is fluidly connected downstream of the main compressor. A heat exchanger is fluidly connected downstream of the tap. An auxiliary compressor unit is fluidly connected downstream of the heat exchanger. The auxiliary compressor unit is configured to compress air cooled by the heat exchanger with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US10718272B2
公开(公告)日：2020-07-21
申请号：US15490155
申请日：2017-04-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Matthew R Feulner , Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine comprises a housing having an inlet leading to a fan rotor. A bypass door is mounted upstream of the inlet to the fan rotor, and is moveable away from a non-bypass position to a bypass position to selectively bypass boundary layer air vertically beneath the engine. An aircraft is also disclosed.
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Patent Agency Ranking
公开(公告)号：US10718268B2
公开(公告)日：2020-07-21
申请号：US15807911
申请日：2017-11-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses cooling air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US10655538B2
公开(公告)日：2020-05-19
申请号：US16143662
申请日：2018-09-27
Applicant: United Technologies Corporation
Inventor： Jonathan Gilson , Bruce L. Morin , Ramons A. Reba , David A. Topol , Wesley K. Lord
Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
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公开(公告)号：US10563585B2
公开(公告)日：2020-02-18
申请号：US15058229
申请日：2016-03-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Nathan Snape , Gabriel L. Suciu
Abstract: A gas turbine engine component includes a heat exchange structure having an upstream end and a downstream end. A diffusing duct is associated with the upstream end. A throttle member controls air flow through the heat exchange structure, wherein the throttle member: (a) has a non-circular cross section; and (b) is mounted to the downstream end of the heat exchange structure or is mounted between the upstream end and the diffusing duct.
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59.发明申请公开(公告)号：US20200025036A1
公开(公告)日：2020-01-23
申请号：US16391476
申请日：2019-04-23
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Robert E. Malecki , Yuan J. Qiu , Becky E. Rose , Jonathan Gilson
Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.
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公开(公告)号：US10421553B2
公开(公告)日：2019-09-24
申请号：US14600946
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler
Abstract: An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.
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