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11.发明申请Engine Mount Waiting Fail Safe Lug Joint with Reduced Dynamic Amplification Factor 审中-公开发动机装载等待失效安全接头，减少动态放大系数公开(公告)号：US20150375867A1
公开(公告)日：2015-12-31
申请号：US14769336
申请日：2014-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhijun Zheng , Joseph P. Foster , Stephen P. Dailey , David F. Sandy
CPC classification number: B64D27/26 , B64D2027/266 , B64D2027/268 , F01D25/24 , F01D25/28 , F02C7/20 , F05D2220/32 , F05D2230/60 , F05D2230/642 , F05D2240/90 , F05D2260/311 , F16B5/025 , Y02T50/44 , Y02T50/671
Abstract: An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin.
Abstract translation: 发动机支架可以包括U形夹和限定穿过其中的孔的凸耳。 销可以连接到U形夹，并且可以通过销延伸穿过凸耳的孔，并且凸耳在其间限定了间隙。 触发系统可以设置在凸耳上并且与销可操作地相关联。
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公开(公告)号：US11603889B2
公开(公告)日：2023-03-14
申请号：US16420341
申请日：2019-05-23
Applicant: United Technologies Corporation
Inventor： James D. Adams , Zhijun Zheng
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotatable shaft and a cover substantially covering an end of the rotatable shaft. The cover includes a passageway fluidly coupled from outside the shaft to inside the shaft. The cover further includes a fin configured to prevent oil from entering the passageway.
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公开(公告)号：US11060454B2
公开(公告)日：2021-07-13
申请号：US16567665
申请日：2019-09-11
Applicant: United Technologies Corporation
Inventor： Robert Goodman , Zhijun Zheng , Michael D. Greenberg
Abstract: An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston is positioned in the first direct acting valve. The first control valve assembly is fluidly connected to the first valve. The second direct acting valve includes a second inlet, outlet, valve chamber, and piston. The second piston is positioned in the second direct acting valve. The second direct acting valve is fluidly connected to the first direct acting valve in a series configuration. The second control valve assembly is fluidly connected to the second valve chamber.
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Patent Agency Ranking
公开(公告)号：US10220950B2
公开(公告)日：2019-03-05
申请号：US14769336
申请日：2014-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhijun Zheng , Joseph P. Foster , Stephen P. Dailey , David F. Sandy
Abstract: An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin.
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公开(公告)号：US10190499B2
公开(公告)日：2019-01-29
申请号：US14649064
申请日：2013-12-27
Applicant: United Technologies Corporation
Inventor： Joey Wong , Zhijun Zheng
Abstract: A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.
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公开(公告)号：US10054052B2
公开(公告)日：2018-08-21
申请号：US14793441
申请日：2015-07-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Zhijun Zheng , Michael D. Greenberg
CPC classification number: F02C7/047 , B64D15/04 , F02C6/08 , F05D2270/112
Abstract: A gas turbine engine is provided having a nacelle and a compressor section constructed and arranged to generate hot air. An anti-icing system is constructed and arranged to discharge the hot air from the compressor section to the nacelle. An anti-icing valve is positioned in the anti-icing system and constructed and arranged to control a flow of the hot air from the compressor section to the nacelle. The anti-icing valve includes a partially open position to constrict a flow of the hot air from the compressor section to the nacelle.
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公开(公告)号：US20180162538A1
公开(公告)日：2018-06-14
申请号：US15377287
申请日：2016-12-13
Applicant: United Technologies Corporation
Inventor： Zhijun Zheng , James H. Anderson , Scott David Sanicki
CPC classification number: B64D15/20 , B64D15/00 , B64D15/02 , B64D15/22 , B64D29/00 , B64D2033/0233 , F02C7/047
Abstract: A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.
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公开(公告)号：US20150369131A1
公开(公告)日：2015-12-24
申请号：US14649064
申请日：2013-12-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joey Wong , Zhijun Zheng
CPC classification number: F02C7/20 , F01D25/162 , F01D25/24 , F05D2250/711 , F05D2260/30
Abstract: A gas turbine engine includes a convex case section. The convex case section includes an upstream case portion having a first radius, a downstream case portion having a second radius, and an intermediate case portion between the upstream case portion and the downstream case portion. The intermediate case portion has a third radius larger than the first radius and the second radius. A tension rod extends from the upstream case portion to the downstream case portion.
Abstract translation: 燃气涡轮发动机包括凸壳部。 凸形壳体部分包括具有第一半径的上游壳体部分，具有第二半径的下游壳体部分和在上游壳体部分和下游壳体部分之间的中间壳体部分。 中间壳体部具有大于第一半径和第二半径的第三半径。 张力杆从上游壳体部分延伸到下游壳体部分。
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