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公开(公告)号：EP2994385B1
公开(公告)日：2019-07-03
申请号：EP13789669.2
申请日：2013-10-31
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2.发明公开
公开(公告)号：EP2994385A1
公开(公告)日：2016-03-16
申请号：EP13789669.2
申请日：2013-10-31
CPC分类号： F25B11/00 , B64D13/06 , B64D2013/0644 , B64D2013/0648 , B64D2013/0674 , F25B1/005 , F25B1/10 , F25B9/008 , F25B9/06 , F25B29/003 , F25B40/00 , F25B41/00 , F25B2309/061 , F25B2341/0011 , F25B2400/13 , F25B2400/23 , F25B2600/2501 , Y02T50/56
摘要： A cooling system includes a heat exchanger through which a refrigerant flows, and which rejects heat to a fluid, an evaporator, a first circuit having an expansion device, a second circuit having an expansion machine coupled to a compressor, and a set of valves arranged to direct the refrigerant through the first circuit, the second circuit, or both the first and second circuits based on ambient conditions.
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公开(公告)号：EP2920075B1
公开(公告)日：2018-04-04
申请号：EP13786584.6
申请日：2013-10-23
发明人： SNYDER, Douglas, J.
摘要： An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.
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4.发明公开ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS 审中-公开自适应传感器CO2-KÜHLSYSTEMEFÜRLUFT- UND RAUMFAHRTANWENDUNGEN
公开(公告)号：EP2969756A2
公开(公告)日：2016-01-20
申请号：EP13871295.5
申请日：2013-12-28
摘要： A cooling system for an aircraft includes a first cooling circuit having a first evaporator and a second evaporator, and a second cooling circuit having a third evaporator and a fourth evaporator. One of the first and second cooling circuits includes a first set of valves arranged to direct refrigerant through a first cooling sub-circuit, a second cooling sub-circuit, or both the first and second cooling sub-circuits based on ambient conditions. Two of the evaporators are installed on a first side of the aircraft, and the other two of the four evaporators are installed on a second side of the aircraft opposite the first side, and the first and second cooling circuits reject heat, via a heat exchanger, from their respective cooling circuit to air passing into an engine of the aircraft.
摘要翻译： 用于飞行器的冷却系统包括具有第一蒸发器和第二蒸发器的第一冷却回路，以及具有第三蒸发器和第四蒸发器的第二冷却回路。 第一和第二冷却回路中的一个包括第一组阀，其布置成基于环境条件引导制冷剂通过第一冷却子回路，第二冷却子回路或第一和第二冷却子回路。 两个蒸发器安装在飞行器的第一侧上，四个蒸发器中的另外两个安装在与第一侧相对的飞行器的第二侧上，并且第一和第二冷却回路通过热交换器 ，从其各自的冷却回路进入飞行器的发动机的空气。
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5.发明公开AIRCRAFT VEHICLE THERMAL MANAGEMENT SYSTEM AND METHOD 有权WÄRMEVERWALTUNGSSYSTEMUNDERVERHRENFÜRLUFTFAHRZEUGE
公开(公告)号：EP2920075A1
公开(公告)日：2015-09-23
申请号：EP13786584.6
申请日：2013-10-23
发明人： SNYDER, Douglas, J.
摘要： An air vehicle power and thermal management system includes an aircraft controller structured to distribute power provided by a gas turbine engine between a cooling system and an electrically powered load. The controller is configured to direct the power to create a first duration cooling power to the cooling system to cool the engine fuel cooling medium over a first power time period. The controller is configured to shift the power to reduce the first duration cooling power to create a load electrical power to drive the electrically powered load over a second power time period. By operation of the controller to shift the power from the first duration cooling power to the load electrical power a second duration cooling power is provided to the cooling system to cool the electrically powered load using the engine fuel cooling medium that was cooled during the first power time period.
摘要翻译： 一种航空器电力和热管理系统包括飞行器控制器，其被构造成在燃料涡轮发动机在冷却系统和电动负载之间分配动力。 控制器被配置为引导电力以向冷却系统产生第一持续时间的冷却功率，以在第一功率时间段内冷却发动机燃料冷却介质。 控制器被配置为移动功率以减少第一持续时间的冷却功率以产生负载电力以在第二功率时间段内驱动电力负载。 通过控制器的操作，将功率从第一持续时间冷却功率转移到负载电力，第二持续时间将冷却功率提供给冷却系统，以使用在第一功率期间被冷却的发动机燃料冷却介质来冷却电动负载 时间段。
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