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    FUEL TANK INERTING APPARATUS FOR AIRCRAFT
    12.
    发明申请
    FUEL TANK INERTING APPARATUS FOR AIRCRAFT 审中-公开
    燃油箱燃油装置

    公开(公告)号：US20160362188A1

    公开(公告)日：2016-12-15

    申请号：US14734051

    申请日：2015-06-09

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Louis J. Bruno ,  Christina W. Millot ,  Harold W. Hipsky

    IPC: B64D37/32 ,  B64D13/06

    CPC classification number: B64D37/32 ,  B64D13/02 ,  B64D13/06 ,  B64D2013/0648 ,  B64D2013/0677 ,  Y02T50/56

    Abstract: A system includes a first flow path fluidly connecting a first supply to an inerting apparatus. A second flow path connects a second supply to a turbine of a compressor device. A first valve, located within the first flow path, is configured to be open in a first state and closed in a second state. The first valve is configured to allow a supply of air from the first supply to an inerting apparatus directly. A second valve, located within the second flow path, is configured to be closed in the first state and open in the second state. The second valve is configured to allow a supply of air from the second supply to drive the turbine of the compressor device. When in the second state, the compressor device is operated to compress air from the first supply prior to the air being supplied to the inerting apparatus.

    Abstract translation: 系统包括将第一供应流体地连接到惰性装置的第一流路。 第二流路将第二供应件连接到压缩机装置的涡轮机。 位于第一流路内的第一阀构造成在第一状态下打开并在第二状态下关闭。 第一阀被构造成允许从第一供应源供给到惰化装置的空气。 位于第二流路内的第二阀配置成在第一状态下被关闭并在第二状态下打开。 第二阀构造成允许来自第二供应源的空气供应来驱动压缩机装置的涡轮机。 当处于第二状态时，压缩机装置在空气被供给到惰化装置之前被操作以从第一供给部压缩空气。

    Air compressor backing plate
    15.
    发明授权
    Air compressor backing plate 有权
    空压机背板

    公开(公告)号：US08979026B2

    公开(公告)日：2015-03-17

    申请号：US13909377

    申请日：2013-06-04

    Applicant: Hamilton Sundstrand Corporation

    Inventor： David A. Dorman ,  Harold W. Hipsky ,  Peter A. Wierzbowski ,  Eric Chrabascz ,  Brian Cabello

    IPC: B64D11/00 ,  F01D9/04

    CPC classification number: F01D9/04 ,  F04D29/444 ,  F04D29/681 ,  F05D2250/52

    Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.5% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

    Abstract translation: 一种用于对飞行器内的空气流进行加压的压缩机，包括提供空气流到压缩机的入口。 出口在压缩机加压之后提供空气流到飞行器的腔室。 扩散器组件设置在入口和出口之间。 扩散器组件包括一个或多个叶片，其至少部分地阻碍通过扩散器组件的空气流。 背板包括具有邻近一个或多个叶片的表面。 表面包括使空气绕过一个或多个叶片的浮雕特征。 浮雕特征具有通过扩散器组件的流动通道的宽度的约0.5％至2.5％的轴向深度或背衬板的凸缘的厚度的约0.5％至5％。 还包括操作压缩机的方法。

    Dual Action Check Valve
    16.
    发明申请
    Dual Action Check Valve 审中-公开
    双作用止回阀

    公开(公告)号：US20140199931A1

    公开(公告)日：2014-07-17

    申请号：US13743373

    申请日：2013-01-17

    Applicant: HAMILTON SUNDSTRAND CORPORATION

    Inventor： Harold W. Hipsky

    IPC: B64D13/06 ,  G05D7/01

    CPC classification number: B64D13/06 ,  B64D13/08 ,  F04D27/009 ,  F16K15/033 ,  F16K15/035 ,  F16K17/196 ,  G05D7/01

    Abstract: A combination includes a selectively driven fan and a bypass flow passage for bypassing the fan. The bypass flow passage communicates with a first check valve to allow air to flow from the bypass passage to a downstream location. A second check valve allows air driven by the fan to pass into a return passage and return to an inlet of the fan in the event that the discharge pressure from the fan overcomes a spring force associated with the second check valve. A heat exchanger pack and an environmental control system for use on an aircraft, and a method are all also disclosed.

    Abstract translation: 组合包括用于绕过风扇的选择性驱动的风扇和旁路流动通道。 旁通流路与第一止回阀连通，以允许空气从旁路通道流到下游位置。 如果来自风扇的排出压力克服与第二止回阀相关联的弹簧力，则第二止回阀允许由风扇驱动的空气进入返回通道并返回到风扇的入口。 一种用于飞机的热交换器组件和环境控制系统以及一种方法也被公开。

    Particle separation system
    19.
    发明授权
    Particle separation system 有权

    公开(公告)号：US10369503B2

    公开(公告)日：2019-08-06

    申请号：US15176970

    申请日：2016-06-08

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Dilip Prasad ,  Harold W. Hipsky ,  Thomas M. Zywiak

    IPC: B01D46/00 ,  B01D45/06 ,  B01D45/12 ,  B01D45/02 ,  B01D45/04 ,  B01D45/16 ,  B64D13/00 ,  B01D53/26

    Abstract: A particle separation device to remove particulate matter from an exterior air flow for use with an environmental control system includes a curved airflow path with an inner radius and an outer radius, the curved air flow path to receive the exterior air flow, a particle passage disposed along at least one of the inner radius and the outer radius to receive the particulate matter from the exterior air flow, a circumferential volute to receive the particulate matter from the particle passage, and a duct to transport the particulate matter from the circumferential volute to a downstream region.

    Dual action check valve with combined return and bypass passages
    20.
    发明授权
    Dual action check valve with combined return and bypass passages 有权

    公开(公告)号：US10144518B2

    公开(公告)日：2018-12-04

    申请号：US13743373

    申请日：2013-01-17

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Harold W. Hipsky

    IPC: B64D13/06 ,  G05D7/01 ,  B64D13/08 ,  F16K15/03 ,  F04D27/00 ,  F16K17/196

    Abstract: A combination includes a selectively driven fan and a bypass flow passage for bypassing the fan. The bypass flow passage communicates with a first check valve to allow air to flow from the bypass passage to a downstream location. A second check valve allows air driven by the fan to pass into a return passage and return to an inlet of the fan in the event that the discharge pressure from the fan overcomes a spring force associated with the second check valve. A heat exchanger pack and an environmental control system for use on an aircraft, and a method are all also disclosed.

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