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公开(公告)号：US20180023474A1
公开(公告)日：2018-01-25
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
CPC classification number: F02C7/18 , B64D27/20 , F02C3/04 , F05D2220/323 , F05D2250/51 , F05D2260/232 , Y02T50/676
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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22.发明申请公开(公告)号：US20140321970A1
公开(公告)日：2014-10-30
申请号：US14325583
申请日：2014-07-08
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
IPC: F02C9/18
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
Abstract translation: 用于燃气涡轮发动机系统的机舱包括具有压力侧和吸力侧的壳体。 通道在压力侧和吸力侧之间延伸，以允许从压力侧到吸力侧的气流。 通道包括在压力侧具有入口的第一弯曲部分。 线性部分与第一弯曲部分连接。 第二弯曲部分与线性部分连接并且在吸力侧具有出口。 出口的横截面积小于线性部分的横截面面积。
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公开(公告)号：US20210158792A1
公开(公告)日：2021-05-27
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
IPC: G10K11/168 , B32B3/26 , B32B3/12 , B32B5/02
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：US10767596B2
公开(公告)日：2020-09-08
申请号：US15660656
申请日：2017-07-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dmitriy B. Sidelkovskiy , Steven H. Zysman
IPC: F02K1/72 , B64D27/16 , F02K3/06 , F02K1/80 , B64D29/00 , B64D29/06 , B64D33/02 , B64D33/04 , F01D25/24 , F02C3/04
Abstract: A nacelle may comprise an inlet cowling defining an inlet of the nacelle, wherein the inlet cowling comprises an inlet cowling maximum point and an inlet cowling aft edge, wherein the inlet cowling aft edge comprises an aft edge length; and a boat tail cowling disposed aft of the inlet cowling, wherein the boat tail cowling comprises a boat tail cowling forward edge having a forward edge length, and wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be smaller than the aft edge length, forming a step, the step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge.
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公开(公告)号：US20190017470A1
公开(公告)日：2019-01-17
申请号：US16031202
申请日：2018-07-10
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Oleg Petrenko , Robert E. Malecki , Steven H. Zysman
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：US20170335771A1
公开(公告)日：2017-11-23
申请号：US15161953
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Keith A. Post , Daniel W. Shannon , Steven H. Zysman , Mark Zsurka , Diego H. de la Riva , Sudarshan N. Koushik
CPC classification number: F02C7/24 , B64C23/06 , B64D29/00 , B64D33/00 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2260/96
Abstract: Aspects of the disclosure are directed to a system associated with an engine of an aircraft comprising: a duct, an inlet coupled to the duct, and a fence coupled to the inlet or located upstream of the inlet. In some embodiments, the system further comprises a valve body coupled to the duct. In some embodiments, the valve body includes at least one valve that is configured to rotate between a closed state and an open state.
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公开(公告)号：US20170190438A1
公开(公告)日：2017-07-06
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
CPC classification number: B64D33/02 , B64D27/10 , B64D29/00 , B64D2033/0273 , B64D2033/0286 , F01D25/24 , F02C7/04 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2230/70 , F05D2240/303 , F05D2250/51 , F05D2250/711
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：US09644535B2
公开(公告)日：2017-05-09
申请号：US14325583
申请日：2014-07-08
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Wesley K. Lord , Robert M. Miller , Oliver V. Atassi
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0226 , F02C7/045 , F05D2250/324 , F05D2250/71 , F05D2270/17 , Y10T137/0536
Abstract: A nacelle for a gas turbine engine system includes a housing that has a pressure side and a suction side. A passage extends between the pressure side and the suction side for permitting airflow from the pressure side to the suction side. The passage includes a first curved section that has an inlet at the pressure side. A linear section is connected with the first curved section. A second curved section is connected with the linear section and has an outlet at the suction side. The outlet has a cross sectional area smaller than a cross sectional area of the linear section.
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公开(公告)号：US20160237856A1
公开(公告)日：2016-08-18
申请号：US14621456
申请日：2015-02-13
Applicant: United Technologies Corporation
Inventor： Dmitriy B. Sidelkovskiy , Steven H. Zysman , Robert E. Malecki
CPC classification number: F01D25/28 , B64D29/00 , B64D29/06 , F01D25/24 , F02C7/20 , F02K1/52 , F02K1/72 , F05D2240/55
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.
Abstract translation: 本公开总体上涉及在发动机舱上使用的空气动力学轨道整流罩组件，轨道整流罩组件可定位在发动机舱的后部，气动履带整流罩组件包括朝向后部的后部的后端延伸的上部 所述发动机舱，朝向所述发动机舱的后部的后端延伸的底部，所述底部固定到所述上部以在其间形成轨道腔;以及整流罩，其布置在所述轨道腔内并固定到所述底部 部分。
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公开(公告)号：US20160153363A1
公开(公告)日：2016-06-02
申请号：US14954603
申请日：2015-11-30
Applicant: United Technologies Corporation
Inventor： Steven H. Zysman , Aleksandar Ratajac
CPC classification number: F02C9/18 , B01D45/04 , B01D45/16 , F02C3/04 , F02C7/05 , F02C7/06 , F02C7/18 , F05D2250/323 , F05D2250/51 , F05D2260/609 , F05D2260/98 , Y02T50/675
Abstract: An air scoop includes a base which is attachable to a nacelle of a turbomachine, an air outlet defined in the base, and a scoop body disposed on the base and defining a scoop inlet. The scoop inlet is in fluid communication with the air outlet to supply scoop air to the air outlet. The air scoop also includes separator lip extending from the base to the scoop inlet which spaces the scoop inlet apart from the base to raise the scoop body above liquids streaking along the base.
Abstract translation: 空气勺包括可附接到涡轮机的机舱的基座，限定在基座中的空气出口以及设置在基座上并限定勺入口的勺体。 勺子入口与出气口流体连通，以将舀出的空气供应到出气口。 空气铲还包括从基座延伸到铲斗入口的分离器唇缘，其将铲斗入口与基座隔开，以将勺体升高到沿着基部的条纹上方的勺体。
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