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公开(公告)号：US20200370445A1
公开(公告)日：2020-11-26
申请号：US16420341
申请日：2019-05-23
Applicant: United Technologies Corporation
Inventor： James D. Adams , Zhijun Zheng
IPC: F01D25/18
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：US20170334566A1
公开(公告)日：2017-11-23
申请号：US15161404
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Robert Goodman , Zhijun Zheng , Michael D. Greenberg
CPC classification number: B64D15/04 , B64D33/02 , B64D2033/0233 , F01D17/141 , F01D25/02 , F01D25/24 , F02C7/047 , F05D2220/323 , F16K17/02 , F16K31/06
Abstract: An assembly includes a first enclosed flexible pressure chamber. A first extension arm extends from a first endwall of the first enclosed flexible pressure chamber. A second enclosed flexible pressure chamber includes a second extension arm extending from a second endwall of the second enclosed flexible pressure chamber. A lever arm is disposed on a pivot. A first end of the lever arm is attached to the first extension arm and a second end of the lever arm is attached to the second extension arm. A variable restriction element is connected to the second end of the lever arm.
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公开(公告)号：US10450955B2
公开(公告)日：2019-10-22
申请号：US15202758
申请日：2016-07-06
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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公开(公告)号：US10421551B2
公开(公告)日：2019-09-24
申请号：US14958994
申请日：2015-12-04
Applicant: United Technologies Corporation
Inventor： Michael D. Greenberg , Zhijun Zheng , David Baszak , Scott W. Simpson
Abstract: An anti-icing system for an aircraft structure includes a cavity that has an exterior surface subject to ice accretion and a bleed source that is configured to provide a fluid to the cavity via a duct. The system includes multiple temperature sensors, disposed at the aircraft structure, with each temperature sensor configured to detect a temperature associated with an aircraft structure location. A controller is in communication with the temperature sensors. The controller is programmed to compare outputs of the temperature sensors and to determine a temperature sensor fault condition.
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公开(公告)号：US09994327B1
公开(公告)日：2018-06-12
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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Patent Agency Ranking
公开(公告)号：US20200003117A1
公开(公告)日：2020-01-02
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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公开(公告)号：US09849992B2
公开(公告)日：2017-12-26
申请号：US15161404
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Robert Goodman , Zhijun Zheng , Michael D. Greenberg
CPC classification number: B64D15/04 , B64D33/02 , B64D2033/0233 , F01D17/141 , F01D25/02 , F01D25/24 , F02C7/047 , F05D2220/323 , F16K17/02 , F16K31/06
Abstract: An assembly includes a first enclosed flexible pressure chamber. A first extension arm extends from a first endwall of the first enclosed flexible pressure chamber. A second enclosed flexible pressure chamber includes a second extension arm extending from a second endwall of the second enclosed flexible pressure chamber. A lever arm is disposed on a pivot. A first end of the lever arm is attached to the first extension arm and a second end of the lever arm is attached to the second extension arm. A variable restriction element is connected to the second end of the lever arm.
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公开(公告)号：US20160167792A1
公开(公告)日：2016-06-16
申请号：US14958994
申请日：2015-12-04
Applicant: United Technologies Corporation
Inventor： Michael D. Greenberg , Zhijun Zheng , David Baszak , Scott W. Simpson
Abstract: An anti-icing system for an aircraft structure includes a cavity that has an exterior surface subject to ice accretion and a bleed source that is configured to provide a fluid to the cavity via a duct. The system includes multiple temperature sensors, disposed at the aircraft structure, with each temperature sensor configured to detect a temperature associated with an aircraft structure location. A controller is in communication with the temperature sensors. The controller is programmed to compare outputs of the temperature sensors and to determine a temperature sensor fault condition.
Abstract translation: 用于飞行器结构的防冰系统包括具有经受积冰的外表面的空腔和被配置为经由导管向腔体提供流体的排泄源。 该系统包括设置在飞机结构处的多个温度传感器，每个温度传感器被配置成检测与飞行器结构位置相关联的温度。 控制器与温度传感器通信。 控制器被编程为比较温度传感器的输出并确定温度传感器故障状况。
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公开(公告)号：US20180010519A1
公开(公告)日：2018-01-11
申请号：US15202758
申请日：2016-07-06
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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公开(公告)号：US20170009653A1
公开(公告)日：2017-01-12
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.
Abstract translation: 提供一种燃气涡轮发动机，其具有构造和布置成产生热空气的机舱和压缩机部分。 一个防冰系统被构造和布置成将热空气从压缩机部分排放到机舱。 防冰阀定位在防冰系统中，并被构造和布置成控制热空气从压缩机部分到机舱的流动。 防冰阀包括部分打开位置，以收缩热空气从压缩机部分到机舱的流动。
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