专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08528348B2 Cooling system for cooling heat loads on board an aircraft and method for operating such a cooling system 有权
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：US08528348B2
公开(公告)日：2013-09-10
申请号：US12438489
申请日：2007-08-17
申请人： Wolfgang Ebigt , Wilson Willy Casas Noriega , Andreas Frey , Dirk Kastell
发明人： Wolfgang Ebigt , Wilson Willy Casas Noriega , Andreas Frey , Dirk Kastell
IPC分类号： F25B7/00
CPC分类号： F25B25/005 , B64D13/06 , B64D2013/0629 , B64D2013/064 , B64D2013/0674 , Y02T50/44 , Y02T50/56
摘要： An aircraft cooling system for cooling heat loads on board an aircraft includes a cold producing device, a first cold carrier fluid circuit thermally coupled to the cold producing device and connected to a first heat load in order to carry off heat from the first heat load, a second cold carrier fluid circuit connected to a second heat load in order to carry off heat from the second heat load, a heat exchanger disposed in the second cold carrier fluid circuit and configured to thermally couple the second cold carrier fluid circuit to an ambient temperature surrounding the aircraft, and a coupling system configured to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit.
摘要翻译：用于冷却飞机上的热负荷的飞行器冷却系统包括冷产生装置，第一冷载体流体回路，其热连接到冷产生装置并连接到第一热负载以便从第一热负荷传送热量，第二冷载体流体回路，连接到第二热负荷以便从第二热负荷传递热量;热交换器，设置在第二冷载体流体回路中并且构造成将第二冷载体流体回路热耦合到环境温度围绕飞行器以及耦合系统，其被配置为选择性地将第一冷载体流体回路耦合到第二冷载体流体回路，或者使其与第二冷载体流体回路热分解。

2. 发明申请

US20090321062A1 COOLING SYSTEM FOR COOLING HEAT LOADS ON BOARD AN AIRCRAFT AND METHOD FOR OPERATING SUCH A COOLING SYSTEM 有权
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：US20090321062A1
公开(公告)日：2009-12-31
申请号：US12438489
申请日：2007-08-17
申请人： Wolfgang Ebigt , Wilson Willy Casas Noriega , Andreas Frey , Dirk Kastell
发明人： Wolfgang Ebigt , Wilson Willy Casas Noriega , Andreas Frey , Dirk Kastell
IPC分类号： F28F27/00
CPC分类号： F25B25/005 , B64D13/06 , B64D2013/0629 , B64D2013/064 , B64D2013/0674 , Y02T50/44 , Y02T50/56
摘要： A cooling system for cooling heat loads on board an aircraft comprises a cold producing device, a first cold carrier fluid circuit, which is thermally coupled to the cold producing device and is connected to a first heat load in order to carry off heat from the first heat load, and a second cold carrier fluid circuit, which is connected to a second heat load in order to carry off heat from the second heat load. A coupling system of the cooling system is adapted to selectively thermally couple the first cold carrier fluid circuit to the second cold carrier fluid circuit or thermally uncouple it from the second cold carrier fluid circuit. In a method for operating such a cooling system for cooling heat loads on board an aircraft, the first cold carrier fluid circuit is selectively thermally coupled to the second cold carrier fluid circuit or thermally uncoupled from the second cold carrier fluid circuit by means of the coupling system.
摘要翻译：用于冷却飞机上的热负荷的冷却系统包括冷产生装置，第一冷载体流体回路，其与冷产生装置热耦合并连接到第一热负荷，以便从第一热负载和第二冷载体流体回路，其连接到第二热负荷以便从第二热负荷传递热量。冷却系统的联接系统适于选择性地将第一冷载体流体回路耦合到第二冷载体流体回路，或者使其与第二冷载体流体回路热分离。在用于操作用于冷却飞机上的热负荷的这种冷却系统的方法中，第一冷载体流体回路选择性地热耦合到第二冷载体流体回路，或者通过耦合与第二冷载体流体回路热分离系统。

3. 发明授权

US08752398B2 Refrigerating device, in particular for aircraft 有权
标题翻译：制冷装置，特别适用于飞机
公开(公告)号：US08752398B2
公开(公告)日：2014-06-17
申请号：US12790284
申请日：2010-05-28
申请人： Wilson Willy Casas Noriega , Stefan Wischhusen , Wolfgang Ebigt , Dirk Kastell
发明人： Wilson Willy Casas Noriega , Stefan Wischhusen , Wolfgang Ebigt , Dirk Kastell
IPC分类号： F25B41/00 , F25B49/00
CPC分类号： F25B41/00 , B64D13/08 , B64D2013/0674 , F25B2400/0401 , F25B2400/0411 , F25B2600/0251 , F25B2700/2106 , F25B2700/2116 , Y02T50/56
摘要： The invention relates to a refrigerating device (10), in particular for an aircraft, having a refrigerant circuit, in which a refrigerant container (12), an expansion valve (14), an evaporator (16), a compressor (20) and a condenser (22) are disposed. To save energy during operation and to increase the reliability and availability of the refrigerating device (10), in the refrigerant circuit there is a compressor bypass line (26), in which a bypass valve (18) is disposed, and a refrigerant pump (30) that is disposed downstream of the condenser (22) and upstream of the evaporator (16). It is possible to dispense with the refrigerant pump (30) if the condenser (22) is disposed at a higher level than the evaporator (16) in the refrigerant circuit.
摘要翻译：本发明涉及具有制冷剂回路的制冷装置（10），特别是用于航空器的制冷装置（10），其中制冷剂容器（12），膨胀阀（14），蒸发器（16），压缩机（20）和设置冷凝器（22）。为了节省运转时的能量，提高制冷装置（10）的可靠性和可利用性，在制冷剂回路中设置有配置有旁通阀（18）的压缩机旁通管路（26）和制冷剂泵 30），其设置在冷凝器（22）的下游和蒸发器（16）的上游。如果冷凝器（22）设置在比制冷剂回路中的蒸发器（16）更高的高度，则可以省略制冷剂泵（30）。

4. 发明申请

US20100326105A1 REFRIGERATING DEVICE, IN PARTICULAR FOR AIRCRAFT 有权
标题翻译：制冷装置，特别是飞机
公开(公告)号：US20100326105A1
公开(公告)日：2010-12-30
申请号：US12790284
申请日：2010-05-28
申请人： Wilson Willy Casas Noriega , Stefan Wischhusen , Wolfgang Ebigt , Dirk Kastell
发明人： Wilson Willy Casas Noriega , Stefan Wischhusen , Wolfgang Ebigt , Dirk Kastell
IPC分类号： F25B49/02 , F25B1/00
CPC分类号： F25B41/00 , B64D13/08 , B64D2013/0674 , F25B2400/0401 , F25B2400/0411 , F25B2600/0251 , F25B2700/2106 , F25B2700/2116 , Y02T50/56
摘要： The invention relates to a refrigerating device (10), in particular for an aircraft, having a refrigerant circuit, in which a refrigerant container (12), an expansion valve (14), an evaporator (16), a compressor (20) and a condenser (22) are disposed. To save energy during operation and to increase the reliability and availability of the refrigerating device (10), in the refrigerant circuit there is a compressor bypass line (26), in which a bypass valve (18) is disposed, and a refrigerant pump (30) that is disposed downstream of the condenser (22) and upstream of the evaporator (16). It is possible to dispense with the refrigerant pump (30) if the condenser (22) is disposed at a higher level than the evaporator (16) in the refrigerant circuit.
摘要翻译：本发明涉及具有制冷剂回路的制冷装置（10），特别是用于航空器的制冷装置（10），其中制冷剂容器（12），膨胀阀（14），蒸发器（16），压缩机（20）和设置冷凝器（22）。为了节省运转时的能量，提高制冷装置（10）的可靠性和可利用性，在制冷剂回路中设置有配置有旁通阀（18）的压缩机旁通管路（26）和制冷剂泵 30），其设置在冷凝器（22）的下游和蒸发器（16）的上游。如果冷凝器（22）设置在比制冷剂回路中的蒸发器（16）更高的高度，则可以省略制冷剂泵（30）。

5. 发明授权

US09145210B2 Redundant aircraft cooling system for redundant aircraft components 有权
标题翻译：用于冗余飞机部件的冗余飞机冷却系统
公开(公告)号：US09145210B2
公开(公告)日：2015-09-29
申请号：US12518374
申请日：2007-12-03
申请人： Wilson Willy Casas Noriega , Wolfgang Ebigt , Andreas Frey
发明人： Wilson Willy Casas Noriega , Wolfgang Ebigt , Andreas Frey
IPC分类号： F28D15/00 , F28F7/00 , B64D13/00 , B64D13/06 , F25B25/00
CPC分类号： B64D13/00 , B64D13/06 , B64D2013/0614 , B64D2013/0674 , F25B25/005 , F25B2500/06 , Y02T50/56
摘要： An aircraft cooling system includes a first coolant stream which cools at least one first heat load and a second coolant stream which cools at least one second heat load. The aircraft cooling system is formed such that the first heat load and the second heat load are thermally coupled together. The first heat load and the second heat load can be formed by two mutually redundant aircraft components. A third coolant stream thermally couples the first heat load and the second heat load together. The third coolant stream can be cooled by a heat sink, such as the outer skin of the aircraft in a bilge region.
摘要翻译：飞机冷却系统包括冷却至少一个第一热负荷的第一冷却剂流和冷却至少一个第二热负荷的第二冷却剂流。飞机冷却系统形成为使得第一热负荷和第二热负荷热耦合在一起。第一热负荷和第二热负荷可以由两个相互冗余的飞行器部件形成。第三冷却剂流将第一热负荷和第二热负荷热耦合在一起。第三冷却剂流可以由散热器（例如在舱底区域中的飞行器的外皮）来冷却。

6. 发明申请

US20100132920A1 Redundant Aircraft Cooling System For Redundant Aircraft Components 有权
标题翻译：用于冗余飞机部件的冗余飞机冷却系统
公开(公告)号：US20100132920A1
公开(公告)日：2010-06-03
申请号：US12518374
申请日：2007-12-03
申请人： Wilson Willy Casas Noriega , Wolfgang Ebigt , Andreas Frey
发明人： Wilson Willy Casas Noriega , Wolfgang Ebigt , Andreas Frey
IPC分类号： F28D15/00 , F28F7/00
CPC分类号： B64D13/00 , B64D13/06 , B64D2013/0614 , B64D2013/0674 , F25B25/005 , F25B2500/06 , Y02T50/56
摘要： An aircraft cooling system (1) according to the invention comprises a first coolant stream (4a) which cools at least one first heat load (2a), and a second coolant stream (4b) which cools at least one second heat load (2b), wherein the aircraft cooling system (1) is formed such that the first heat load (2a) and the second heat load (2b) are thermally coupled together. The first heat load (2a) and the second heat load (2b) can be formed by two mutually redundant aircraft components. A third coolant stream (12) can thermally couple the first heat load (2a) and the second heat load (2b) together. The third coolant stream (12) can be cooled by a heat sink (16).
摘要翻译：根据本发明的飞机冷却系统（1）包括冷却至少一个第一热负荷（2a）的第一冷却剂流（4a）和冷却至少一个第二热负荷（2b）的第二冷却剂流（4b），其中所述飞行器冷却系统（1）形成为使得所述第一热负荷（2a）和所述第二热负荷（2b）热耦合在一起。第一热负荷（2a）和第二热负荷（2b）可以由两个相互冗余的飞行器部件形成。第三冷却剂流（12）可以将第一热负荷（2a）和第二热负荷（2b）热耦合在一起。第三冷却剂流（12）可以被散热器（16）冷却。

7. 发明申请

US20110300786A1 System And Method For Ventilating Explosive Regions Of An Aircraft 有权
标题翻译：飞机爆炸区通风系统及方法
公开(公告)号：US20110300786A1
公开(公告)日：2011-12-08
申请号：US12867634
申请日：2009-02-11
申请人： Dirk Kastell , Wilson Willy Casas Noriega
发明人： Dirk Kastell , Wilson Willy Casas Noriega
IPC分类号： B64D13/00
CPC分类号： B64D37/32 , B64D13/08 , B64D2013/0618 , Y02T50/44 , Y02T50/56
摘要： A system (10) for ventilating an explosion hazard region (12) of an aircraft comprises a ram-air channel (16), which has an air inlet for feeding ambient air into the ram-air channel (16) as well as an air outlet (18). The ram-air channel (16) is devised to feed air to a device that is to be cooled on board the aircraft. A ventilation line (22) has an air inlet (24) for feeding air flowing through the ram-air channel (16) into the ventilation line (22) as well as an air outlet (26). The ventilation line (22) is devised to feed air to a region (12) of the aircraft that is to be ventilated. An accumulator (28) is disposed between the ram-air channel (16) and the air inlet (24) of the ventilation line (22) and is devised to convert the dynamic pressure of the air flow conveyed through the ram-air channel (16) at least partially into static pressure.
摘要翻译：用于对飞机的爆炸危险区域（12）进行通风的系统（10）包括冲击空气通道（16），其具有用于将环境空气供入冲击空气通道（16）的空气入口以及空气出口（18）。冲压空气通道（16）设计成将空气送入飞机上要冷却的装置。通风管路（22）具有用于将流过冲压空气通道（16）的空气进入通气管线（22）的空气入口（24）以及空气出口（26）。通风线（22）被设计成将空气供给到要通风的飞行器的区域（12）。蓄压器（28）设置在冲压空气通道（16）和通风管线（22）的空气入口（24）之间，并被设计成转换通过冲压空气通道传送的气流的动态压力 16）至少部分地进入静压。

8. 发明授权

US08721406B2 Air duct for supplying ambient air in an aircraft 有权
标题翻译：用于在飞机上提供环境空气的空气管道
公开(公告)号：US08721406B2
公开(公告)日：2014-05-13
申请号：US13001353
申请日：2009-06-23
申请人： Dirk Kastell , Sebastian Roering , Wilson Willy Casas Noriega
发明人： Dirk Kastell , Sebastian Roering , Wilson Willy Casas Noriega
IPC分类号： B64D13/00
CPC分类号： B64D13/00 , B64D2241/00 , Y02T50/56
摘要： An air duct for supplying ambient air in an aircraft includes an air inlet, a flow duct portion and a feed device that is devised to feed ambient air through the air inlet and the flow duct portion. A flow control flap closes the air inlet in a first position, releases a first flow cross-section of the air inlet in a second position and releases a larger second flow cross-section of the air inlet in a third position. The flow control flap is designed to not increase drag significantly in the second position while still enabling flow through the flow duct portion, while increasing drag to increase air fow through the flow duct portion in the third position.
摘要翻译：用于在飞行器中供应环境空气的空气管道包括空气入口，流动管道部分和进给装置，其被设计成通过空气入口和流动管道部分供给环境空气。流动控制翼将空气入口封闭在第一位置，将空气入口的第一流动横截面释放在第二位置，并在第三位置释放空气入口的较大的第二流动横截面。流量控制挡板被设计成在第二位置中不会显着地增加阻力，同时仍然允许流过流道部分，同时增加阻力以增加通过第三位置中的流动管道部分的气流。

9. 发明申请

US20110151764A1 Air Duct for Supplying Ambient Air in an Aircraft 有权
标题翻译：用于在飞机上供应环境空气的空气管道
公开(公告)号：US20110151764A1
公开(公告)日：2011-06-23
申请号：US13001353
申请日：2009-06-23
申请人： Dirk Kastell , Sebastian Roering , Wilson Willy Casas Noriega
发明人： Dirk Kastell , Sebastian Roering , Wilson Willy Casas Noriega
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 flow duct portion (16) extending downstream of the air inlet (12) and a feed device (22) that is devised to feed ambient air through the air inlet (12) and the flow duct portion (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 so designed and disposed that a first surface portion (28) of the flow control flap (24), in the second position of the flow control flap (24), is aligned in the region of the air inlet (12) substantially parallel to an aircraft outer skin portion (18) is surrounding the air inlet (12), and that the first surface portion (28) of the flow control flap (24), in the third position of the flow control flap (14), is aligned in the region of the air inlet (12) at an angle to the aircraft outer skin portion (18) surrounding the air inlet (12).
摘要翻译：本发明涉及一种用于在飞行器中提供环境空气的空气管道（10），包括空气入口（12），在空气入口（12）的下游延伸的流动管道部分（16）和进料装置（22）被设计成通过空气入口（12）和流动管道部分（16）供给环境空气。流动控制翼片（24）在第一位置关闭空气入口（12），将空气入口（12）的第一流动横截面释放在第二位置，并释放空气入口的第二流动横截面 12），其大于第一流动横截面，在第三位置。流动控制翼片（24）被设计和设置成使得在流动控制翼片（24）的第二位置处的流量控制翼片（24）的第一表面部分（28）在空气的区域中对准基本上平行于飞行器外皮部分（18）的入口（12）围绕空气入口（12），并且流量控制翼片（24）的第一表面部分（28）处于流量控制翼片（14）在空气入口（12）的区域中与围绕空气入口（12）的飞行器外皮部分（18）成一定角度排列。

10. 发明授权

US08584485B2 Aircraft cooling system evaporator arrangement for two independent coolant circuits 有权
标题翻译：飞机冷却系统蒸发器布置用于两个独立的冷却剂回路
公开(公告)号：US08584485B2
公开(公告)日：2013-11-19
申请号：US12675496
申请日：2008-09-01
申请人： Wolfgang Ebigt , Wilson Willy Casas Noriega
发明人： Wolfgang Ebigt , Wilson Willy Casas Noriega
IPC分类号： F25B7/00
CPC分类号： B64D11/04 , B64D2013/0629 , B64D2013/0674 , F25B5/02 , Y02T50/46
摘要： An aircraft cooling system evaporator arrangement has an evaporation device including four evaporators that are hydraulically separate from each other with respect to coolant flow. Refrigerant flows from a feed line into first and second evaporators, from the first evaporator into and through a third evaporator, and from the second evaporator into and through a fourth evaporator. The first and third evaporators define a first pair of evaporators arranged parallel to a second pair of evaporators defined by the second and fourth evaporators. First and second coolant supply lines of a first coolant circuit supply coolant to one of the evaporators in each of the first and second pair of evaporators respectively, and first and second coolant supply lines of a second, independent coolant circuit supply coolant to the other of the evaporators in each of the first and second pair of evaporators respectively.
摘要翻译：飞机冷却系统蒸发器装置具有蒸发装置，其包括相对于冷却剂流在液压上彼此分离的四个蒸发器。制冷剂从进料管线流入第一和第二蒸发器，从第一蒸发器进入并通过第三蒸发器，并且从第二蒸发器流入并通过第四蒸发器。第一和第三蒸发器限定了平行于由第二和第四蒸发器限定的第二对蒸发器布置的第一对蒸发器。第一冷却剂回路的第一和第二冷却剂供应管线分别向第一和第二对蒸发器中的每个蒸发器中的一个蒸发器供应冷却剂，第二独立冷却剂回路的第一和第二冷却剂供应管路将冷却剂供给到另一个蒸发器分别在第一和第二对蒸发器中。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式