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1. 发明申请

WO2011038889A8 SYSTEM AND METHOD FOR COOLING AND/OR HEATING AIRCRAFT DEVICES 审中-公开
公开(公告)号：WO2011038889A8
公开(公告)日：2011-09-01
申请号：PCT/EP2010005913
申请日：2010-09-28
申请人： AIRBUS OPERATIONS GMBH , HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
发明人： HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
IPC分类号： B64D13/08
CPC分类号： B64D13/08 , B64D13/00 , B64D2013/0655 , F25B49/02 , Y02T50/44 , Y02T50/56
摘要： A system (10) for cooling and/or heating aircraft devices to be cooled and/or heated comprises a first individual cooling and/or heating system (20, 22) associated with a first aircraft device (12, 14) to be cooled and/or heated, and a second individual cooling and/or heating system (24, 26) associated with a second aircraft device (16, 18) to be cooled and/or heated. The system (10) further comprises a cooling and/or heating energy supply apparatus (28) which is designed to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) to the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated. A control device (30) is designed to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system (20, 22, 24, 26). The control device (30) is further designed to control, on the basis of said signals, the operation of the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) and/or the supply of cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) to the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated.

2. 发明申请

WO2011038889A3 SYSTEM AND METHOD FOR COOLING AND/OR HEATING AIRCRAFT DEVICES 审中-公开
标题翻译：用于冷却和/或加热飞机设备的系统和方法
公开(公告)号：WO2011038889A3
公开(公告)日：2011-07-14
申请号：PCT/EP2010005913
申请日：2010-09-28
申请人： AIRBUS OPERATIONS GMBH , HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
发明人： HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
IPC分类号： B64D13/08
CPC分类号： B64D13/08 , B64D13/00 , B64D2013/0655 , F25B49/02 , Y02T50/44 , Y02T50/56
摘要： A system (10) for cooling and/or heating aircraft devices to be cooled and/or heated comprises a first individual cooling and/or heating system (20, 22) associated with a first aircraft device (12, 14) to be cooled and/or heated, and a second individual cooling and/or heating system (24, 26) associated with a second aircraft device (16, 18) to be cooled and/or heated. The system (10) further comprises a cooling and/or heating energy supply apparatus (28) which is designed to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) to the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated. A control device (30) is designed to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system (20, 22, 24, 26). The control device (30) is further designed to control, on the basis of said signals, the operation of the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) and/or the supply of cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system (20, 22, 24, 26) to the first and/or the second aircraft device (12, 14, 16, 18) to be cooled and/or heated.
摘要翻译：一种用于冷却和/或加热系统（10）被冷却和/或加热的空气的车载设备包括具有Einzelkühl-和/或加热模块（20相关联的第一，第一被冷却和/或加热的空气的车辆设备（12，14）， 22）以及与独立冷却和/或加热系统（24,26）相关联的第二待冷却和/或加热飞行器装置（16,18）。该系统（10）还包括冷却和/或加热能量供给装置，其适于通过所述第一和/或第二Einzelkühl-和/或加热单元产生的（28）（20，22，24，26）的冷却和/或第一和/或第二要被冷却和/或加热的飞行器装置（12,14,16,18）供给的能量。的控制装置（30），适合于接收和所需的第一和/或第二的冷却和/或加热需求的过程信号被冷却和/或加热的空气的车辆设备（12，14，16，18）和第一和/或第二单个冷却和/或加热系统（20,22,24,26）的负载状况是特征性的。另外，控制装置（30）适于将这些信号的第一和/或第二Einzelkühl-和/或-heizsystems的操作（20，22，24，26）和/或冷却的供给的基础上和/ 或者从所述第一和/或第二Einzelkühl-和/或产生的热能-heizsysteme（20，22，24，26）到所述第一和/或第二被冷却和/或（被加热的空气的车辆设备12， 14，16，18）。

3. 发明申请

WO2011038888A3 SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT COOLING SYSTEM 审中-公开
标题翻译：用于控制飞机冷却系统的系统和方法
公开(公告)号：WO2011038888A3
公开(公告)日：2011-07-14
申请号：PCT/EP2010005912
申请日：2010-09-28
申请人： AIRBUS OPERATIONS GMBH , HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
发明人： HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
IPC分类号： B64D13/08
CPC分类号： B64D13/08 , B64D13/00 , B64D2013/0655 , F25B49/02 , Y02T50/44 , Y02T50/56
摘要： A system (10) for controlling a cooling system (100) for use especially on board an aircraft comprises a operating state detection unit (30) that is designed to detect operating state signals characteristic of the operating state of the cooling system (100) and/or the operating state of a plurality of cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100). The control system (10) further comprises a database (38) in which priority data that is dependent on the operating state and is characteristic of the priority to be given to the cooling energy consumers (16a-d, 18a-d, 20a-d) in terms of the cooling energy to be supplied in various operating states of the cooling system (100) and/or of the cooling energy consumers (16a-d, 18a-d, 20a-d), is stored for a plurality of cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100). A control signal generation unit (40) of the control system (10) is designed to generate control signals that control the supply of cooling energy to the cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100) in accordance with the operating state signals detected by the operating state detection unit (30) and the priority data stored in the database (38).
摘要翻译：一种用于控制特定的系统（10），用于在船上使用航空器冷却系统（100）包括适于检测用于冷却系统的操作条件（100）和/或操作状态的操作状态信号的运转状态检测单元（30）由冷却系统（100）供应冷却能量的多个冷却能量消耗装置（16a-d，18a-d，20a-d）是特征性的。此外，控制系统（10）包括在其中具有冷却能量冷却能量消耗（16A-d，图18a-d，20a至d）被供给通过所述冷却系统（100）的多个数据的基础（38）的操作相关的条件优先级数据被存储时，用于冷却能量消耗（16A-d，图18a-d，20a至d）中的冷却系统（100）和/或冷却能量消耗（16A-d，图18a-d，20a至d）特性在供应einzuräumende冷却能量优先的各种操作条件是。控制系统的控制信号产生单元（40）（10）适于通过所述冷却系统（100）来控制冷却功率到与冷却能量冷却能量消耗（16A-d，图18a-d，20a至d）控制的控制信号作为操作状态检测单元的功能被提供（30）生成检测到的操作状态信号和存储在数据库（38）中的优先级数据。

4. 发明申请

WO2011038888A8 SYSTEM AND METHOD FOR CONTROLLING AN AIRCRAFT COOLING SYSTEM 审中-公开
标题翻译：系统和方法控制飞机冷却系统
公开(公告)号：WO2011038888A8
公开(公告)日：2011-09-01
申请号：PCT/EP2010005912
申请日：2010-09-28
申请人： AIRBUS OPERATIONS GMBH , HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
发明人： HOELLING MARC , ROTHAMMER WERNER , DITTMAR JAN , COLBERG CARSTEN , CASAS NORIEGA WILSON WILLY , ULUC OZAN , ROERING SEBASTIAN , WOLF HOLGER
IPC分类号： B64D13/08
CPC分类号： B64D13/08 , B64D13/00 , B64D2013/0655 , F25B49/02 , Y02T50/44 , Y02T50/56
摘要： A system (10) for controlling a cooling system (100) for use especially on board an aircraft comprises a operating state detection unit (30) that is designed to detect operating state signals characteristic of the operating state of the cooling system (100) and/or the operating state of a plurality of cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100). The control system (10) further comprises a database (38) in which priority data that is dependent on the operating state and is characteristic of the priority to be given to the cooling energy consumers (16a-d, 18a-d, 20a-d) in terms of the cooling energy to be supplied in various operating states of the cooling system (100) and/or of the cooling energy consumers (16a-d, 18a-d, 20a-d), is stored for a plurality of cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100). A control signal generation unit (40) of the control system (10) is designed to generate control signals that control the supply of cooling energy to the cooling energy consumers (16a-d, 18a-d, 20a-d) to be supplied with cooling energy by the cooling system (100) in accordance with the operating state signals detected by the operating state detection unit (30) and the priority data stored in the database (38).
摘要翻译：一种用于控制特定的系统（10），用于在船上使用航空器冷却系统（100）包括适于检测用于冷却系统的操作条件（100）和/或操作状态的操作状态信号的运转状态检测单元（30）与冷却能量冷却能量消耗（16A-D，18A-D，20A-D）是特性被供应的多个贯通的冷却系统（100）。此外，控制系统（10）包括在其中具有冷却能量冷却能量消耗（16A-D，18A-D，20A-D）被供给通过所述冷却系统（100）的多个数据的基础（38）的操作相关的条件优先级数据被存储时，用于冷却能量消耗（16A-D，18A-D，20A-D）在所述冷却系统（100）和/或冷却能量消耗（16A-D，18A-D，20A-D）特性在供应einzuräumende冷却能量优先的各种操作条件是。控制系统的控制信号产生单元（40）（10）适于通过所述冷却系统（100）来控制冷却功率到与冷却能量冷却能量消耗（16A-D，18A-D，20A-D）控制的控制信号作为操作状态检测单元的功能被提供（30）运行状态信号中检测并存储在数据库（38），以产生优先级数据。

5. 发明申请

WO2009156120A8 AIR DUCT FOR SUPPLYING AMBIENT AIR IN AN AIRCRAFT 审中-公开
公开(公告)号：WO2009156120A8
公开(公告)日：2010-07-15
申请号：PCT/EP2009004513
申请日：2009-06-23
申请人： AIRBUS OPERATIONS GMBH , KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
发明人： KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
IPC分类号： B64D33/02
CPC分类号： B64D13/00 , B64D2241/00 , Y02T50/56
摘要： The invention relates to an air duct (10) for supplying ambient air in an aircraft, comprising an air inlet (12), a duct channel section (16) extending downstream of the air inlet (12) and an air conveying device (22) which is adapted to convey ambient air through the air inlet (12) and the duct channel section (16). A flow control flap (24) closes the air inlet (12) in a first position, releases a first flow cross-section of the air inlet (12) in a second position and releases a second flow cross-section of the air inlet (12), which is larger than the first flow cross-section, in a third position. The flow control flap (24) is designed and arranged in such a manner that a first surface section (28) of the flow control flap (24) is oriented substantially parallel to an aircraft shell section (18) surrounding the air inlet (12) in the area of the air inlet (12) in the second position of the flow control flap (24) and that the first surface section (28) of the flow control flap (24) is oriented at an angle with respect to the aircraft shell section (18) surrounding the air inlet (12) in an area of the air inlet (12) in the third position of the flow control flap (14).

6. 发明申请

WO2009156120A4 AIR DUCT FOR SUPPLYING AMBIENT AIR IN AN AIRCRAFT 审中-公开
标题翻译：空气管道，用于环境的空气供应在飞机
公开(公告)号：WO2009156120A4
公开(公告)日：2010-05-20
申请号：PCT/EP2009004513
申请日：2009-06-23
申请人： AIRBUS OPERATIONS GMBH , KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
发明人： KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
IPC分类号： B64D33/02
CPC分类号： B64D13/00 , B64D2241/00 , Y02T50/56
摘要： The invention relates to an air duct (10) for supplying ambient air in an aircraft, comprising an air inlet (12), a duct channel section (16) extending downstream of the air inlet (12) and an air conveying device (22) which is adapted to convey ambient air through the air inlet (12) and the duct channel section (16). A flow control flap (24) closes the air inlet (12) in a first position, releases a first flow cross-section of the air inlet (12) in a second position and releases a second flow cross-section of the air inlet (12), which is larger than the first flow cross-section, in a third position. The flow control flap (24) is designed and arranged in such a manner that a first surface section (28) of the flow control flap (24) is oriented substantially parallel to an aircraft shell section (18) surrounding the air inlet (12) in the area of the air inlet (12) in the second position of the flow control flap (24) and that the first surface section (28) of the flow control flap (24) is oriented at an angle with respect to the aircraft shell section (18) surrounding the air inlet (12) in an area of the air inlet (12) in the third position of the flow control flap (14).
摘要翻译：用于在飞行器中环境空气供应的空气通道（10）包括延伸所述空气入口的下游，其通过空气入口（12）和适于将环境空气的空气入口（12）（12）的流动通道段（16）和一个输送器（22）以促进所述流动通道部分（16）。一种流量控制翼片（24）在第一位置关闭所述空气入口（12）处于第二位置的空气入口（12）自由的第一流动横截面，并且在第三位置中，一个相对于该第一流动横截面放大的第二流动空气入口的横截面（12）自由，流动控制翼片（24）被设计和布置成使得在空气入口（12）的区域中的流量控制阀（24）的第二位置的流控制翼片（24）的第一表面部分（28），其与进气口平行基本上包围（12）飞机外蒙皮部分（18）对准，并且成角度地围绕所述空气入口（12）的飞机外蒙皮部分的区域中的空气入口（12）的区域中的流量控制阀（24）的第三位置时，流量控制翼片（24）的第一表面部分（28）（18 ）对齐。

7. 发明申请

WO2009156120A2 AIR DUCT FOR SUPPLYING AMBIENT AIR IN AN AIRCRAFT 审中-公开
标题翻译：空气管道，用于环境的空气供应在飞机
公开(公告)号：WO2009156120A2
公开(公告)日：2009-12-30
申请号：PCT/EP2009004513
申请日：2009-06-23
申请人： AIRBUS OPERATIONS GMBH , KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
发明人： KASTELL DIRK , ROERING SEBASTIAN , CASAS NORIEGA WILSON WILLY
IPC分类号： B64D13/00
CPC分类号： B64D13/00 , B64D2241/00 , Y02T50/56
摘要： The invention relates to an air duct (10) for supplying ambient air in an aircraft, comprising an air inlet (12), a duct channel section (16) extending downstream of the air inlet (12) and an air conveying device (22) which is adapted to convey ambient air through the air inlet (12) and the duct channel section (16). A flow control flap (24) closes the air inlet (12) in a first position, releases a first flow cross-section of the air inlet (12) in a second position and releases a second flow cross-section of the air inlet (12), which is larger than the first flow cross-section, in a third position. The flow control flap (24) is designed and arranged in such a manner that a first surface section (28) of the flow control flap (24) is oriented substantially parallel to an aircraft shell section (18) surrounding the air inlet (12) in the area of the air inlet (12) in the second position of the flow control flap (24) and that the first surface section (28) of the flow control flap (24) is oriented at an angle with respect to the aircraft shell section (18) surrounding the air inlet (12) in an area of the air inlet (12) in the third position of the flow control flap (14).
摘要翻译：用于在飞行器中环境空气供应的空气通道（10）包括延伸所述空气入口的下游，其通过空气入口（12）和适于将环境空气的空气入口（12）（12）的流动通道段（16）和一个输送器（22）以促进所述流动通道部分（16）。一种流量控制翼片（24）在第一位置关闭所述空气入口（12）处于第二位置的空气入口（12）自由的第一流动横截面，并且在第三位置中，一个相对于该第一流动横截面放大的第二流动空气入口的横截面（12）自由，流动控制翼片（24）被设计和布置成使得在空气入口（12）的区域中的流量控制阀（24）的第二位置的流控制翼片（24）的第一表面部分（28），其与进气口平行基本上包围（12）飞机外蒙皮部分（18）对准，并且成角度地围绕所述空气入口（12）的飞机外蒙皮部分的区域中的空气入口（12）的区域中的流量控制阀（24）的第三位置时，流量控制翼片（24）的第一表面部分（28）（18 ）对齐。

8. 发明申请

WO2009100897A1 SYSTEM AND METHOD FOR VENTILATING EXPLOSIVE REGIONS OF AN AIRCRAFT 审中-公开
标题翻译： SYSTEM AND METHOD FOR FAN飞机的危险区
公开(公告)号：WO2009100897A1
公开(公告)日：2009-08-20
申请号：PCT/EP2009000955
申请日：2009-02-11
申请人： AIRBUS OPERATIONS GMBH , KASTELL DIRK , CASAS NORIEGA WILSON WILLY
发明人： CASAS NORIEGA WILSON WILLY
IPC分类号： B64D37/32 , B60K15/035 , B64D13/08
CPC分类号： B64D37/32 , B64D13/08 , B64D2013/0618 , Y02T50/44 , Y02T50/56
摘要： The invention relates to a system (10) for ventilating an explosive region (12) of an aircraft, comprising a ram air channel (16), which has an air inlet for supplying ambient air into the ram air channel (16), and an air outlet (18). The ram air channel (16) is configured to supply air to a device to be cooled on board of the aircraft. A ventilation line (22) has an air inlet (24) for supplying air flowing from the ram air channel (16) into the ventilation line (22), and an air outlet (26). The ventilation line (22) is configured to supply air to a region (12) of the aircraft to be ventilated. A reservoir (28) is disposed between the ram air channel (16) and the air inlet (24) of the ventilation line (22), said reservoir being configured to convert the dynamic pressure of the air flow directed through the ram air channel (16) at least partially into static pressure.
摘要翻译：一种用于通风飞行器的危险区域（12）的系统（10）包括具有用于供给环境空气的进入冲压空气通道（16）和空气出口（18）的空气入口冲压空气管道（16）。冲压空气通道（16）被配置为提供要在板冷却飞行器空气的装置。排气管线（22）具有用于供给所述冲压空气管道（16）通过在通气管路（22）和空气出口（26）流动的空气的空气入口（24）。排气管线（22）适于施加在飞机的空气的通风区域（12）。冲压空气管道（16）之间，并且所述通气导管（22）的空气入口（24）中设置有存储器（28），其适于将出动态压力通过冲压空气管中的静压力（16）的空气流至少部分地。

9. 发明申请

WO2008025462A8 COOLING SYSTEM FOR COOLING HEAT LOADS ON BOARD AN AIRCRAFT AND METHOD FOR OPERATING SUCH A COOLING SYSTEM 审中-公开
标题翻译：用于冷却飞机上的热负荷的冷却系统和用于操作这种冷却系统的方法
公开(公告)号：WO2008025462A8
公开(公告)日：2008-05-29
申请号：PCT/EP2007007295
申请日：2007-08-17
申请人： AIRBUS GMBH , EBIGT WOLFGANG , CASAS NORIEGA WILSON WILLY , FREY ANDREAS , KASTELL DIRK
发明人： EBIGT WOLFGANG , CASAS NORIEGA WILSON WILLY , FREY ANDREAS , KASTELL DIRK
IPC分类号： B64D13/00 , B64D13/06
CPC分类号： F25B25/005 , B64D13/06 , B64D2013/0629 , B64D2013/064 , B64D2013/0674 , Y02T50/44 , Y02T50/56
摘要： A cooling system (10) for cooling heat loads (28, 34) on board an aircraft comprises a cold producing device (12), a first cold carrier fluid circuit (24), which is thermally coupled to the cold producing device (12) and is connected to a first heat load (28) in order to carry off heat from the first heat load (28), and a second cold carrier fluid circuit (30), which is connected to a second heat load (34) in order to carry off heat from the second heat load. A coupling system of the cooling system (10) is adapted to selectively thermally couple the first cold carrier fluid circuit (24) to the second cold carrier fluid circuit (30) or thermally uncouple it from the second cold carrier fluid circuit (30). In a method for operating such a cooling system (10) for cooling heat loads (28, 34) on board an aircraft, the first cold carrier fluid circuit (24) is selectively thermally coupled to the second cold carrier fluid circuit (30) or thermally uncoupled from the second cold carrier fluid circuit (30) by means of the coupling system.
摘要翻译：用于冷却飞机上的热负荷（28,34）的冷却系统（10）包括冷产生装置（12），与冷产生装置（12）热耦合的第一冷载体流体回路（24）并连接到第一热负荷（28）以便从第一热负荷（28）传出热量;以及第二冷载体流体回路（30），其依次连接到第二热负荷（34）以从第二热负荷中传出热量。冷却系统（10）的联接系统适于选择性地将第一冷载体流体回路（24）热耦合到第二冷载体流体回路（30），或者使其与第二冷载体流体回路（30）热分离。在用于操作用于冷却飞机上的热负荷（28,34）的这种冷却系统（10）的方法中，第一冷载体流体回路（24）选择性地热耦合到第二冷载体流体回路（30）或通过耦合系统与第二冷载体流体回路（30）热耦合。

10. 发明申请

WO2009030449A8 AIRCRAFT COOLING SYSTEM EVAPORATOR ARRANGEMENT FOR TWO INDEPENDENT COOLANT CIRCUITS 审中-公开
标题翻译：两台几个独立的冰箱电路的飞机冰箱组装
公开(公告)号：WO2009030449A8
公开(公告)日：2009-06-18
申请号：PCT/EP2008007129
申请日：2008-09-01
申请人： AIRBUS GMBH , EBIGT WOLFGANG , CASAS NORIEGA WILSON WILLY
发明人： EBIGT WOLFGANG , CASAS NORIEGA WILSON WILLY
IPC分类号： B64D11/04 , F25B5/02
CPC分类号： B64D11/04 , B64D2013/0629 , B64D2013/0674 , F25B5/02 , Y02T50/46
摘要： The invention relates to an aircraft cooling system evaporator arrangement (10) comprising an evaporation apparatus (20) for exchanging heat between a cooling agent and a coolant, said evaporation apparatus (20) comprising at least four evaporators (24a, 24b, 24c, 24d) that are hydraulically separated from each other in relation to the coolant flow. Said evaporation apparatus (10) also comprises at least one supply line (26) for feeding cooling agent to the evaporation apparatus (20). The evaporators (24a, 24b, 24c, 24d) are arranged in such a way that cooling agent fed to the evaporator (22) by means of the supply line (26) flows through two evaporators (24a, 24b, 24c, 24d) in a parallel manner. Furthermore, two independent circuits (16, 17) for a coolant are provided, each coolant circuit comprising at least two hydraulically separated supply lines (34a, 34c; 36b, 36d) for feeding coolant to one respective evaporator (24a, 24b, 24c, 24d). Each of at least two evaporators (24a, 24d; 24b, 24c), through both of which the cooling agent flows in parallel, is connected to a coolant supply line (34a, 36d; 36b, 34c) of another coolant circuit (16, 17).
摘要翻译：本发明涉及一种飞机用的蒸发装置（20），用于在制冷剂和二次制冷剂之间进行热交换，其中，所述蒸发装置（20）的至少四个蒸发器（24A，24B，24C，24D），其相对于制冷剂流的液压彼此分离冷却系统的蒸发器组件（10）是。蒸发器组件（10）还包括用于向蒸发器（20）供应制冷剂的至少一个供应管线（26）。蒸发器（24A，24B，24C，24D）被布置为使得蒸发器;通过进料管线（26）供给至所述蒸发器（24A，24D 24B，24C）（22）的制冷剂通过平行成对流动。此外，提供了用于冷却介质，其中，每个冷却剂回路的至少两个液压地彼此设置的供给线分离的两个独立的电路（16，17）（34A，34C; 36B，36D）（用于向蒸发器中的每一个图24A，24B，24C供给制冷剂，24d）。（16，17），其连接在此，另一制冷剂回路的至少两对流经由制冷剂的蒸发器平行（24A，24D; 24B，24C），每个具有制冷剂供给管（36B，34C，34A，36D）。

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