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1. 发明申请

US20100071881A1 COOLING SYSTEM FOR AIRCRAFT ELECTRIC OR ELECTRONIC DEVICES 审中-公开
标题翻译：用于航空电子或电子设备的冷却系统
公开(公告)号：US20100071881A1
公开(公告)日：2010-03-25
申请号：US12540505
申请日：2009-08-13
申请人： Yann MURER , Augustin ZELLER
发明人： Yann MURER , Augustin ZELLER
IPC分类号： F28D15/00 , H05K7/20
CPC分类号： B64D13/00 , B64D2013/0614 , F25B25/005 , Y02T50/56
摘要： A cooling system for cooling the electrical or electronic equipment on board an aircraft is equipped with a main closed circuit. A pump circulates a heat transfer medium through the main closed circuit. A main heat exchanger is thermally coupled with the heat transfer medium. A secondary heat exchanger allows direct thermal coupling of the heat transfer medium to air on the outside of the aircraft. A bypass valve located upstream from the secondary heat exchanger allows to block, at least partially, the circulation of the heat transfer medium towards the secondary heat exchanger. A bypass duct connects the bypass valve to a point on the main closed cooling circuit downstream from the secondary heat exchanger to bypass, at least partially, the heat transfer medium towards the main heat exchanger as a function of a setting of the bypass valve.
摘要翻译：用于冷却飞机上的电气或电子设备的冷却系统配备有主闭路。泵将传热介质循环通过主闭合回路。主热交换器与传热介质热耦合。二次热交换器允许传热介质与飞机外部的空气直接热耦合。位于二次热交换器上游的旁通阀允许至少部分阻止传热介质朝向二次热交换器的循环。旁通管道将旁通阀连接到二次热交换器下游的主闭合冷却回路上的点，至少部分地将传热介质作为旁通阀的设置旁路至主热交换器。

2. 发明申请

US20110108662A1 ATTACHMENT PYLON FOR AN AIRCRAFT TURBO-SHAFT ENGINE WITH CONCENTRIC HOT AIR CHANNELS 有权
标题翻译：具有集中热空气通道的飞机涡轮发动机的附件PYLON
公开(公告)号：US20110108662A1
公开(公告)日：2011-05-12
申请号：US12892374
申请日：2010-09-28
申请人： Lionel Diochon , Yann Murer
发明人： Lionel Diochon , Yann Murer
IPC分类号： B64D27/14
CPC分类号： B64D15/04 , B64D27/14 , B64D29/04 , B64D2027/005 , B64D2027/026 , Y02T50/66 , Y10T137/85938
摘要： The invention relates to a pylon (14) for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge (16), as well as a first hot air distribution channel (30) passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel (36) belonging to a system for supplying pressurised air to the aircraft.According to the invention the second channel (36) is housed inside the first channel (30).
摘要翻译：本发明涉及一种用于连接设计成侧向偏移在飞行器结构的后部上的涡轮轴飞机发动机的塔架（14），其中塔架具有包括前缘（16）的空气动力学特性，以及第一热空气分配通道（30），其沿着前缘通过以提供防冰，其中该发动机附接塔还包括属于用于向飞行器供应加压空气的系统的第二热空气通道（36）。根据本发明，第二通道（36）容纳在第一通道（30）内。

3. 发明申请

US20100084118A1 COOLING SYSTEM FOR AIRCRAFT ELECTRIC OR ELECTRONIC DEVICES 审中-公开
标题翻译：用于航空电子或电子设备的冷却系统
公开(公告)号：US20100084118A1
公开(公告)日：2010-04-08
申请号：US12540512
申请日：2009-08-13
申请人： Yann MURER , Augustin ZELLER
发明人： Yann MURER , Augustin ZELLER
IPC分类号： F28D15/00 , F28F27/02
CPC分类号： B64D13/00 , B64D2013/0614 , F25B25/005 , Y02T50/56
摘要： In a cooling system for the electrical or electronic equipment on board an aircraft, a heat transfer medium circulates through a main closed cooling circuit. A liquid coolant circulates through a secondary closed cooling circuit. A first heat exchanger makes it possible to transfer the heat from the heat transfer medium circulating through the main closed cooling circuit to the liquid coolant circulating through the secondary closed cooling circuit, by evaporation of the liquid coolant circulating through the secondary closed cooling circuit. A second heat exchanger makes possible the condensation of the liquid coolant circulating through the secondary closed cooling circuit. The second heat exchanger cools the liquid coolant by thermal coupling to the outside ambient air.
摘要翻译：在用于飞机上的电气或电子设备的冷却系统中，传热介质通过主闭合冷却回路循环。液体冷却剂循环通过次级封闭冷却回路。第一热交换器通过蒸发通过二级封闭冷却回路循环的液体冷却剂，可以将循环通过主闭合冷却回路的传热介质的热量传递到循环通过次级封闭冷却回路的液体冷却剂。第二个热交换器可使通过次级封闭冷却回路循环的液体冷却剂冷凝。第二热交换器通过热耦合到外部环境空气来冷却液体冷却剂。

4. 发明授权

US08459588B2 Attachment pylon for an aircraft turbo-shaft engine with concentric hot air channels 有权
标题翻译：具有同心热风通道的飞机涡轮轴发动机的附件塔
公开(公告)号：US08459588B2
公开(公告)日：2013-06-11
申请号：US12892374
申请日：2010-09-28
申请人： Lionel Diochon , Yann Murer
发明人： Lionel Diochon , Yann Murer
IPC分类号： B64D15/04 , B64D27/26 , F16L41/00
CPC分类号： B64D15/04 , B64D27/14 , B64D29/04 , B64D2027/005 , B64D2027/026 , Y02T50/66 , Y10T137/85938
摘要： A pylon for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge, as well as a first hot air distribution channel passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel belonging to a system for supplying pressurized air to the aircraft. The second channel is housed inside the first channel.
摘要翻译：一种用于附接涡轮轴飞机发动机的塔架，其设计成侧向偏移在飞行器结构的后部，其中塔架具有包括前缘的空气动力学特性，以及沿着前导的第一热空气分配通道边缘以提供防冰，其中该发动机附接塔还包括属于用于向飞行器供应加压空气的系统的第二热空气通道。第二个通道位于第一个通道内。

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