Cooling arrangement for electronics

• US 20080110593A1
• Filed: 10/30/2007
• Published: 05/15/2008
• Est. Priority Date: 11/11/2006
• Status: Abandoned Application

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Handley, Brian A., Parkin, David M., Coney, Michael H., Mullender, Andrew J.
• Application Number:
  US11/978,621
• Publication Number:
  US 20080110593A1
• Time in Patent Office: Days
• US Class Current: 165/80.2
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F02C 7/16 characterised by cooling medium
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

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.