Gas turbine engine component with integrated heat pipe

• US 9,909,448 B2
• Filed: 04/15/2015
• Issued: 03/06/2018
• Est. Priority Date: 04/15/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Gerstler, William Dwight, Kostka, James Michael, Rambo, Jeffrey Douglas, Moores, John William
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US14/686,799
• Publication Number:
  US 20160305279A1
• Time in Patent Office: 1,056 Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F01D 5/181 Blades having a closed internal cavity containing a cooling medium, e.g. sodium
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/12 Fluid guiding means, e.g. vanes
• CPC Class Codes: F05D 2260/208 using heat pipes
• CPC Class Codes: F05D 2260/232 characterized by the cooling medium
• CPC Class Codes: F28D 15/046 characterised by the material or the construction of the capillary structure
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A heat transfer apparatus for a gas turbine engine includes: a component having a wall structure defining a flow bounding surface; a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid.

Claims

1. A heat transfer apparatus for a gas turbine engine, comprising:

a component having a wall structure defining a flow bounding surface; and

a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid, wherein

the wall structure comprises a three-dimensional mass having an array of spaced-apart, mutually perpendicular holes passing therethrough.

2. The apparatus of claim 1 wherein the chamber is integrally formed with the wall structure.

3. The apparatus of claim 2 wherein the wall structure transitions from a solid structure at the flow bounding surface to a permeable structure at an inner surface.

4. The apparatus of claim 1 wherein the holes are arranged in two or more layers, the holes of each layer having different diameters.

5. The apparatus of claim 1 wherein the component includes an airfoil having opposed pressure and suction sidewalls, a root, a tip, and spaced-apart leading and trailing edges.

6. The apparatus of claim 5 wherein the chamber extends beyond the root or the tip of the airfoil.

7. The apparatus of claim 5 wherein:

the wicking structure spans the space between the sidewalls; and

a series of spanwise vapor channels extend through the wicking structure.

8. The apparatus of claim 5 wherein:

the wicking structure spans the space between the sidewalls; and

a spanwise vapor channel having an airfoil-shaped cross-section extends through a central portion of the wicking structure.

9. The apparatus of claim 5 wherein:

a plurality of supports extend transversely between the pressure and suction sidewalls; and

at least a portion of at least one of the supports comprises a permeable material defining a part of the wicking structure.

10. An apparatus comprising:

the apparatus of claim 1, wherein a portion of the chamber extends beyond the remainder of the component; and

a sump enclosing the extended portion of the chamber and configured for circulation of a fluid therethrough.

11. The apparatus of claim 1, wherein a portion of the chamber extends beyond the remainder of the component;

and

a fluid conduit is disposed in contact with the extended portion of the chamber.

12. The apparatus of claim 1, wherein a portion of the chamber extends beyond the remainder of the component;

and a stub portion of a fluid conduit is formed as part of a single monolithic structure with the extended portion of the chamber.

13. A heat transfer apparatus for a gas turbine engine, comprising:

a component having a wall structure defining a flow bounding surface; and

a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid, wherein;

a portion of the chamber extends beyond the remainder of the component;

the fluid conduit has an annular outer wall; and

the extended portion of the chamber has a concave saddle shape that contacts the outer wall of the fluid conduit.

14. A heat transfer apparatus for a gas turbine engine, comprising:

a plurality of components arranged in a ring around the engine and extending in a generally radial direction so as to define opposed inboard and outboard ends, each component having;

a wall structure defining a flow bounding surface; and

a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid, wherein the chamber includes an evaporator end and an opposed condenser end;

wherein, for some of the chambers, the evaporator end is positioned at the inboard end of the corresponding component, and for others of the chambers, the evaporator end is positioned at the outboard end of the corresponding component.

15. The apparatus of claim 14 wherein the evaporator end of each chamber is positioned such that gravity will assist fluid flow from the condenser end to the evaporator end, for a predetermined orientation of the engine.

16. The apparatus of claim 14 wherein the components are guide vanes.