Cooling arrangement for electronics

Abstract

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.

1 . An aircraft electrical component cooling arrangement comprises at least one electrical component housed in a body characterised in that fuel is passed through the body and directly over the component. 
   
   
       2 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the component and body are of an engine's electronic control unit. 
   
   
       3 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the body defines an inlet gallery and an outlet gallery for distribution of the fuel over the at least one electrical component. 
   
   
       4 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the aircraft comprises a fuel supply pipe extending between a fuel tank and a combustor assembly, an inlet pipe connects from the fuel supply pipe to the body and the outlet pipe connects the body to the supply pipe. 
   
   
       5 . An aircraft electrical component cooling arrangement as claimed in  claim 4  wherein a Venturi flow meter is provided in the supply pipe, the Venturi flow meter comprising a throat to which the outlet pipe is connected. 
   
   
       6 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the arrangement comprises a pump and a fuel supply pipe extending from an aircraft fuel tank to the body. 
   
   
       7 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the arrangement comprises a controllable valve for metering the flow of fuel into the body and temperature gauge for measuring the temperature of the components, the valve being controlled to maintain a desired temperature of the components. 
   
   
       8 . An aircraft electrical component cooling arrangement as claimed in  claim 1  wherein the body is completely filled with fuel. 
   
   
       9 . A method of operating an aircraft electrical component cooling arrangement comprising at least one electrical component housed in a body, the body connected to a fuel supply pipe, method is characterised by passing fuel through the body directly over the component to cool the component.