| 摘要 |
An aircraft electrical component cooling arrangement comprises at least one electrical component ( 40 ) housed in a body ( 38 ), for example an engine's electronic controller, characterised in that fuel is passed through the body ( 38 ) and directly over the component ( 40 ). Advantageously, this maintains a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness over convention air cooled systems.
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