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公开(公告)号：US11078837B2
公开(公告)日：2021-08-03
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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公开(公告)号：US11046445B2
公开(公告)日：2021-06-29
申请号：US15660687
申请日：2017-07-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy B. Sidelkovskiy , Steven H. Zysman
Abstract: A nacelle may comprise an inlet cowling comprising an inlet cowling aft edge having an aft edge length; a boat tail cowling comprising a boat tail cowling forward edge having a forward edge length, wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be shorter than the aft edge length, forming a step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge. The nacelle may further comprise a transition fairing coupled to the boat tail cowling, wherein the transition fairing comprises a fairing forward edge disposed adjacent to the inlet cowling aft edge and a fairing ramp surface spanning between the inlet cowling aft edge and a boat tail cowling external surface.
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公开(公告)号：US10557416B2
公开(公告)日：2020-02-11
申请号：US15620284
申请日：2017-06-12
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman
IPC: F01D9/06 , F02C3/04 , F02K3/06 , F02C7/18 , F24F13/10 , F02C7/14 , F01D17/14 , F02C6/08 , F16K1/20 , F01D25/12 , F24F13/14 , F02K3/115
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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公开(公告)号：US10479519B2
公开(公告)日：2019-11-19
申请号：US15378300
申请日：2016-12-14
Applicant: United Technologies Corporation
Inventor： Yuan J. Qiu , Steven H. Zysman , Robert E. Malecki , Wesley K. Lord
Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.
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公开(公告)号：US10371092B2
公开(公告)日：2019-08-06
申请号：US14817611
申请日：2015-08-04
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Oleg Petrenko , Robert E. Malecki , Steven H. Zysman
IPC: F02K1/78 , B64D29/00 , F02K1/40 , F02K1/52 , F02K1/00 , F02K1/82 , F02K1/36 , F02K3/077 , F02C3/04 , F02K3/06 , B64D29/02 , B64D29/04
Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.
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Patent Agency Ranking
公开(公告)号：US09506353B2
公开(公告)日：2016-11-29
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：US20160195038A1
公开(公告)日：2016-07-07
申请号：US14817611
申请日：2015-08-04
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Oleg Petrenko , Robert E. Malecki , Steven H. Zysman
CPC classification number: F02K1/78 , B64D29/00 , B64D29/02 , B64D29/04 , F02C3/04 , F02K1/00 , F02K1/36 , F02K1/40 , F02K1/52 , F02K1/82 , F02K3/06 , F02K3/077
Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.
Abstract translation: 用于燃气涡轮发动机的机舱包括限定中心轴线并具有径向向外表面和径向向内表面的环形主体。 径向向内表面的后部包括轴向延伸的收敛发散出口。 轴向延伸的二次管道穿过会聚发散出口喷嘴中的机舱。 轴向延伸的次级管道包括在收敛发散出口喷嘴的收敛部分处的入口和在会聚发散出口喷嘴的发散部分处的出口。
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公开(公告)号：US12109793B2
公开(公告)日：2024-10-08
申请号：US16690519
申请日：2019-11-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Kenneth Holland , Bruce L Morin , Michael Joseph Murphy , Steven H. Zysman
CPC classification number: B32B38/10 , B24C1/045 , B32B3/12 , B32B3/266 , B32B5/02 , B32B37/146 , B32B37/18 , G10K11/168 , B32B2262/101 , B32B2262/106 , B32B2305/02 , B32B2315/00 , B32B2419/04
Abstract: A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.
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公开(公告)号：US10570852B2
公开(公告)日：2020-02-25
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 the 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 reduce an amount of reverse thrust necessary.
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公开(公告)号：US10450898B2
公开(公告)日：2019-10-22
申请号：US14621456
申请日：2015-02-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy B. Sidelkovskiy , Steven H. Zysman , Robert E. Malecki
Abstract: The present disclosure relates generally to an aerodynamic track fairing assembly used on an engine nacelle, the track fairing assembly positionable on the aft section of the engine nacelle, the aerodynamic track fairing assembly including: an upper section extending toward an aft end of the aft section of the engine nacelle; a bottom section extending toward the aft end of the aft section of the engine nacelle, the bottom section affixed to the upper section to form a track cavity therebetween; and a fairing fitting disposed within the track cavity and affixed to the bottom section.
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