Heat transfer system and method for turbine engine using heat pipes

• US 7,823,374 B2
• Filed: 08/31/2006
• Issued: 11/02/2010
• Est. Priority Date: 08/31/2006
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Stephenson, Justin P., Moniz, Thomas Ory, Venkataramani, Kattalaicheri Srinivasan, Bailey, William Andrew
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US11/469,234
• Publication Number:
  US 20080053100A1
• Time in Patent Office: 1,524 Days
• Field of Search: 60/390.93, 60/398.3, 602/261, 165/104.26
• US Class Current: 60/39.093
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F05D 2260/208 using heat pipes
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A heat transfer system is provided for a turbine engine of the type including an annular inlet cowling. The heat transfer system includes at least one heat pipe disposed in contact with an interior of the casing. The heat pipe is thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe and into the inlet cowling.

Claims

1. A heat transfer system for a turbine engine including an inlet cowling, the heat transfer system comprising:

an annular fan casing terminating at a first end in an annular inlet cowling;

a heat exchanger having a heat source passing therethrough disposed about a second end of the fan casing and mounted to an exterior surface thereof; and

a plurality of heat pipes each extending between the heat exchanger and an interior of the inlet cowling, each of the heat pipes having an aft section extending in an axial direction across the exterior surface of the fan casing and terminating at one end within an interior cavity defined within the heat exchanger, a transition section extending along at least a portion of a circumferential surface of the first end of the fan casing, and a forward section terminating in generally axially extending portions connected through an arcuate portion, the forward section extending along the interior of the inlet cowling;

wherein the forward sections of each of the heat pipes are radially spaced around the interior of the inlet cowling.

2. The heat transfer system of claim 1 wherein the forward section of each of the plurality of heat pipes is generally U-shaped.

3. The heat transfer system of claim 1 wherein the inlet cowling has a generally U-shaped cross-section.

4. The heat transfer system of claim 3 wherein the transition section of each of the plurality of heat pipes extends at least partially in a circumferential direction.

5. The heat transfer system of claim 1 wherein the plurality of heat pipes are disposed in contact with the interior of the inlet cowling, and each of the heat pipes are thermally coupled to the heat exchanger.

6. The heat transfer system of claim 1 wherein at least one of the aft and transition sections of each of the plurality of heat pipes are insulated and the forward sections of each of the plurality of heat pipes are uninsulated.

7. The heat transfer system of claim 1 wherein each of the plurality of heat pipes includes an elongated outer wall with closed ends defining a cavity that contains a working fluid.

8. The heat transfer system of claim 1 wherein the heat transfer system facilitates at least one of preventing ice formation on the inlet cowling and removing ice which has formed on the inlet cowling.

9. The heat transfer system of claim 1 wherein the heat source is engine oil from the turbine engine, and the heat transfer system facilitates maintaining the engine oil at an acceptable working temperature.

10. The heat transfer system of claim 1 wherein each of the plurality of heat pipes has a non-circular cross-sectional shape.

11. A method for transferring heat in a turbine engine having an inlet cowling, said method comprising:

providing an annular fan casing terminating at a first end in an annular inlet cowling;

providing a heat source about a second end of the fan casing and mounted to an exterior surface thereof;

providing a plurality of heat pipes each extending between the heat source and an interior of the inlet cowling, each of the heat pipes having an aft section extending in an axial direction across the exterior surface of the fan casing and terminating at one end within an interior cavity defined within the heat exchanger, a transition section extending along at least a portion of a circumferential surface of the first end of the fan casing, and a forward section terminating in generally axially extending portions connected through an arcuate portion, the forward section extending along the interior of the inlet cowling; and

thermally coupling the plurality of heat pipes to the heat source and thermally coupling the forward section of each of the plurality of heat pipes to the interior of the inlet cowling.

12. The method of claim 11 wherein sufficient heat is transferred to the inlet cowling so as to achieve at least one of preventing ice formation on the inlet cowling and removing ice which has formed on the inlet cowling.

13. The method of claim 11 wherein the heat source is engine oil from the turbine engine, and sufficient heat is removed from the engine oil to maintain the cooling oil at an acceptable working temperature.