Systems and methods for thermally integrating oil reservoir and outlet guide vanes using heat pipes

Patent metadata

Field	Value
Publication number	US-2017314471-A1
Application number	US-201615141253-A
Country	US
Kind code	A1
Filing date	Apr 28, 2016
Priority date	Apr 28, 2016
Publication date	Nov 2, 2017
Grant date	—

Abstract

A fluid cooling system for a gas turbine engine having a core engine and an annular fan casing. The fluid cooling system includes a fluid reservoir positioned within the gas turbine engine and configured to contain a fluid. The system also includes a cold sink positioned within the gas turbine engine and having a lower temperature than the fluid. The system further includes a heat pipe including a first end, a second end, and a conduit extending therebetween, the second end thermally coupled to the cold sink, and the first end thermally coupled to the fluid, where the heat pipe facilitates a transfer of a quantity of heat from the fluid to the cold sink.

First claim

What is claimed is:

1 . A fluid cooling system for a gas turbine engine, the gas turbine engine including a core engine and an annular fan casing, said fluid cooling system comprising:
a fluid reservoir positioned within the gas turbine engine and configured to contain a fluid; a cold sink positioned within the gas turbine engine and having a lower temperature than said fluid; and a heat pipe comprising a first end, a second end, and a conduit extending therebetween, said second end thermally coupled to said cold sink, said first end thermally coupled to said fluid, wherein said heat pipe facilitates a transfer of a quantity of heat from said fluid to said cold sink.

2 . The fluid cooling system in accordance with claim 1 , wherein said fluid reservoir comprises an oil tank.

3 . The fluid cooling system in accordance with claim 1 , wherein said fluid comprises a lubricating oil.

4 . The fluid cooling system in accordance with claim 1 , wherein said fluid reservoir is further positioned on a radially outward portion of the annular fan casing.

5 . The fluid cooling system in accordance with claim 1 further comprising at least one condenser thermally coupled to and between said second end and said cold sink.

6 . The fluid cooling system in accordance with claim 1 further comprising at least one evaporator thermally coupled to and between said first end and said fluid.

7 . The fluid cooling system in accordance with claim 1 , wherein said cold sink comprises the annular fan casing, an annular inner housing, an outlet guide vane (OGV), and a thrust link support.

8 . The fluid cooling system in accordance with claim 1 , wherein said cold sink comprises an outlet guide vane (OGV), said OGV comprising a cavity defined therewithin, said cavity configured to facilitate positioning said heat pipe within said OGV.

9 . The fluid cooling system in accordance with claim 1 , wherein said first end comprises an increased surface area.

10 . A gas turbine engine comprising:
a core engine; an annular fan casing; a fluid cooling system comprising:
a fluid reservoir positioned within said gas turbine engine and configured to contain a fluid;
a cold sink positioned with said gas turbine engine and having a lower temperature than said fluid;
a heat pipe comprising a first end, a second end, and a conduit extending therebetween, said second end thermally coupled to said cold sink, said first end thermally coupled to said fluid, wherein said heat pipe facilitates transfer of a quantity of heat from said fluid to said cold sink.

11 . The gas turbine engine in accordance with claim 10 , wherein said fluid reservoir comprises an oil tank, and said fluid comprises a lubricating oil.

12 . The gas turbine engine in accordance with claim 10 , wherein said fluid reservoir is further positioned on a radially outward portion of said annular fan casing.

13 . The gas turbine engine in accordance with claim 10 further comprising at least one condenser thermally coupled to and between said second end and said cold sink.

14 . The gas turbine engine in accordance with claim 10 further comprising at least one evaporator thermally coupled to and between said first end and said fluid.

15 . The gas turbine engine in accordance with claim 10 , wherein said cold sink comprises said annular fan casing, an annular inner housing, an outlet guide vane (OGV), and a thrust link support.

16 . The gas turbine engine in accordance with claim 10 , wherein said cold sink comprises an outlet guide vane (OGV), said OGV comprising a cavity defined therewithin, said cavity configured to facilitate positioning said heat pipe within said OGV.

17 . A method of cooling a fluid in a gas turbine engine, the gas turbine engine including a core engine, a fluid reservoir configured to contain a fluid, and a cold sink having a lower temperature than the fluid, said method comprising:
selecting a heat pipe having performance parameters to facilitate following a predetermined heat transfer characteristic including a thermal resistance between the fluid and the cold sink;
thermally coupling a first end of the heat pipe to the fluid;
thermally coupling a second end of the heat pipe to the cold sink;
receiving heat into the first end from the fluid; and
transferring heat through the heat pipe to the cold sink.

18 . The method in accordance with claim 17 , wherein said thermally coupling a first end of the heat pipe to the fluid comprises defining an increased surface area in the first end to facilitate said transferring heat through the heat pipe to the cold sink.

19 . The method in accordance with claim 17 , wherein said thermally coupling a second end of the heat pipe to the cold sink comprises thermally coupling the second end to an annular fan casing, an annular inner housing, an outer guide vane, and a thrust link support.

20 . The method in accordance with claim 17 further comprising:
thermally coupling an evaporator to and between the first end and the fluid; and
thermally coupling a condenser to and between the second end and the cold sink.

Assignees

• Gen Electric

Inventors

• Sennoun Mohammed El Hacin

Classifications

• F02C7/14 Primary

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title