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公开(公告)号：US20170175626A1
公开(公告)日：2017-06-22
申请号：US14974112
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Yuan J. Qiu , Amr Ali , Steven H. Zysman
CPC classification number: F02C7/04 , F02C3/04 , F02C7/045 , F02K3/06 , F04D19/002 , F04D29/384 , F04D29/522 , F05D2220/32 , F05D2240/30 , F05D2250/314 , F05D2250/713 , F05D2250/72 , F05D2260/96
Abstract: A gas turbine engine comprises a nacelle and a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle has inner periphery that is substantially axially symmetric about a center axis of the rotor from either a throat of the nacelle at a substantially bottom dead center location, or a point of inflection at which the inner periphery of the nacelle at substantially bottom dead center merges a convex portion into a concave portion.
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公开(公告)号：US20140169935A1
公开(公告)日：2014-06-19
申请号：US13719821
申请日：2012-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , Michael A. Weisse , Steven H. Zysman
CPC classification number: F01D5/225 , F04D25/028 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2220/36 , F05D2250/14 , Y02T50/671 , Y02T50/673
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan.
Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机尤其包括风扇部分，其包括具有可围绕轴线旋转的多个风扇叶片的风扇。 多个风扇叶片中的每一个包括中跨罩和与风扇连通的变速装置。
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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：US20210003485A1
公开(公告)日：2021-01-07
申请号：US16502242
申请日：2019-07-03
Applicant: United Technologies Corporation
Inventor： Joel H. Wagner , Kevin W. Schlichting , Michael Joseph Murphy , Steven H. Zysman , Nigel David Sawyers-Abbott , Andrew A. Consiglio , Charles Waldo Haldeman, IV
IPC: G01N1/22 , G01N23/223
Abstract: An environmental sampling system includes a passage in an aircraft component and a removable collector disposed in the passage. The passage has an inlet at a first region and an outlet at a second region. When the aircraft component is in operation the first region is at a greater pressure than the second region such that air flows through the passage from the inlet to the outlet. The removable collector is configured to retain constituents from the air and to react with the media designed to mimic corrosion effects seen at higher temperatures on engine parts. The constituents can then be characterized and correlated to engine deterioration to predict maintenance activity.
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公开(公告)号：US20200248620A1
公开(公告)日：2020-08-06
申请号：US16269151
申请日：2019-02-06
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Karl D. Blume , James H. Anderson , Holly Teufel , Jesse W. Clauson , Xiaojun Campbell , William O. Taylor , Graham A. Kaiser , Karl Milenkovic , Michael C. Rhodes , Tsering Dolma
Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.
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Patent Agency Ranking
公开(公告)号：US10730635B1
公开(公告)日：2020-08-04
申请号：US16574424
申请日：2019-09-18
Applicant: United Technologies Corporation
Inventor： Timothy S. Snyder , Steven H. Zysman
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an engine wing. This disclosure also relates to an airplane including an engine wing.
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公开(公告)号：US20200024982A1
公开(公告)日：2020-01-23
申请号：US16038320
申请日：2018-07-18
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman
Abstract: A fan assembly for gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a plurality of fan blades rotatable about a fan rotation axis, each of the plurality of fan blades movable about an axis transverse to the fan rotation axis, a fan nacelle partially surrounding the plurality of fan blades, and a pitch mechanism coupled to the plurality of blades that changes an angle of pitch for each of the plurality of blades corresponding to a circumferential position of the fan blade about the fan rotation axis.
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公开(公告)号：US20190085789A1
公开(公告)日：2019-03-21
申请号：US15711229
申请日：2017-09-21
Applicant: United Technologies Corporation
Inventor： Andre L. Bent , Steven H. Zysman , Nigel David Sawyers-Abbott
Abstract: An exhaust section of a gas turbine engine includes an exhaust plug defining a plurality of exhaust plug apertures circumferentially spaced from each other. Also included is an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. Further included is an exhaust plug liner having a non-uniform outer surface axially aligned with the exhaust plug apertures. The exhaust plug liner is rotatable relative to exhaust plug between a first position and a second position to selectively change a cross-sectional area of the exhaust pathway during thrust reversal operation to increase an amount of reverse thrust.
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公开(公告)号：US20180355821A1
公开(公告)日：2018-12-13
申请号：US15619029
申请日：2017-06-09
Applicant: United Technologies Corporation
Inventor： Andre L. Bent , Steven H. Zysman , Nigel David Sawyers-Abbott
CPC classification number: F02K1/70 , F02C3/04 , F02K1/08 , F02K1/16 , F02K1/72 , F02K3/06 , F05D2260/57 , F05D2270/62 , F05D2270/65
Abstract: An exhaust section of a gas turbine engine includes an exhaust plug, and an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. The exhaust plug is configured for axial translation relative to exhaust nozzle between a first position and a second position to selectably change a cross-sectional area of the exhaust pathway during thrust reversal operation of the gas turbine engine to reduce an amount of reverse thrust necessary. A method of operating a gas turbine engine includes actuating a fan thrust reverser to divert a fan airflow from a fan airflow pathway, and translating an exhaust plug from a first position to a second position, thereby increasing a cross-sectional area of an exhaust pathway to reduce an amount of reverse thrust necessary.
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公开(公告)号：US20180355739A1
公开(公告)日：2018-12-13
申请号：US15620284
申请日：2017-06-12
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman
Abstract: A gas turbine engine includes a fan, a compressor, a combustor, a turbine, a bypass duct downstream of the fan and outward of the compressor, and a cooling system. The cooling system includes an inlet for receiving air from the bypass duct, an outlet for returning air to the bypass duct, a cooling duct, and a heat exchanger and a modulator positioned in the cooling duct. The modulator includes dividers that extend parallel to each other and are arranged across the duct, and each divider includes two flaps that are rotatable about an axis in opposite directions.
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