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    Integrated fuel cell aircraft pressurization and cooling system
    3.
    发明授权
    Integrated fuel cell aircraft pressurization and cooling system 有权

    公开(公告)号：US10224556B2

    公开(公告)日：2019-03-05

    申请号：US14969184

    申请日：2015-12-15

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Charles E. Lents ,  Jonathan Rheaume

    IPC: H01M8/04111 ,  B64D13/06 ,  B64D15/04 ,  B64D37/32 ,  F04D25/04 ,  F04D25/06 ,  F04D29/28 ,  H01M8/04082 ,  B64D13/02 ,  H01M8/04089 ,  B64D41/00

    Abstract: According to one embodiment of this disclosure an integrated fuel cell and environmental control system includes a turbo-compressor. The turbo-compressor includes a rotatable shaft, a compressor rotatable with the shaft to generate a flow of compressed air, a motor connected to the shaft, and a turbine connected to the shaft. The system further includes a fuel cell connected to the compressor by a first compressed air supply line that supplies a first portion of the flow of compressed air to the fuel cell. The fuel cell is connected to the turbine by a fuel cell exhaust line that supplies a flow of fuel cell exhaust to the turbine and causes the turbine to rotate. The system further includes an environmental control system connected to the compressor by a second compressed air supply line that supplies a second portion of the flow of compressed air to the environmental control system.

    THERMAL REGULATION OF BATTERIES
    8.
    发明申请
    THERMAL REGULATION OF BATTERIES 审中-公开

    公开(公告)号：US20200303789A1

    公开(公告)日：2020-09-24

    申请号：US16449146

    申请日：2019-06-21

    Applicant: Hamilton Sundstrand Corporation

    Inventor： Malcolm Macdonald ,  Charles E. Lents

    IPC: H01M10/63 ,  F28F27/02 ,  B64D37/00 ,  H01M10/625 ,  H01M10/48 ,  H01M10/613 ,  H01M10/6561

    Abstract: A battery thermal management system for an air vehicle includes a first heat exchange circuit, a battery in thermal communication with the first heat exchange circuit, and a heat exchanger positioned on the first heat exchange circuit. The heat exchanger is operatively connected to a second heat exchange circuit. The system includes a controller operatively connected to the second heat exchange circuit. The controller is configured to variably select whether heat will be rejected to the second heat exchange circuit. A method for controlling a thermal management system for an air vehicle includes determining an expected fluid temperature of fluid in a fluid heat exchange circuit. The method includes commanding a flow restrictor at least partially closed or commanding the flow restrictor at least partially open.

    AIRCRAFT HEAT EXCHANGE SYSTEM INCLUDING A THERMOELECTRIC DEVICE
    10.
    发明申请
    AIRCRAFT HEAT EXCHANGE SYSTEM INCLUDING A THERMOELECTRIC DEVICE 审中-公开
    包括热电装置的飞机热交换系统

    公开(公告)号：US20170027082A1

    公开(公告)日：2017-01-26

    申请号：US14808523

    申请日：2015-07-24

    Applicant: Hamilton Sundstrand Corporation

    Inventor： William E. Rhoden ,  Charles E. Lents

    IPC: H05K7/20 ,  B64D37/34 ,  B64D37/02

    CPC classification number: H05K7/20272 ,  B64D37/02 ,  B64D37/34 ,  H01L35/30 ,  H05K7/20281

    Abstract: A heat exchange system for an aircraft includes an aircraft controller for controlling an operation of an aircraft, a thermoelectric device having a low temperature side and a high temperature side, an inlet line that carries fluid through the low temperature side of the thermoelectric device and to the aircraft controller; and an outlet line that carrier the fluid away from the and aircraft controller through the high temperature side of the thermoelectric device. Heat is transferred away from the inlet line to the outlet line through the thermoelectric device when a predetermined condition is met.

    Abstract translation: 用于飞行器的热交换系统包括用于控制飞行器的操作的飞行器控制器，具有低温侧和高温侧的热电装置，将流体通过热电装置的低温侧运送的入口管线，以及 飞机控制器; 以及出口管线，其通过热电装置的高温侧将流体从飞行器控制器运送离开飞行器控制器。 当满足预定条件时，热量通过热电装置从入口管线转移到出口管线。

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