Thermal management system and method of circulating air in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9828914-B2
Application number	US-201514685392-A
Country	US
Kind code	B2
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

A thermal management system and method of circulating air in a gas turbine engine are disclosed. The thermal management system includes a nose cone having an aperture communicating air to an interior space of the nose cone and a fan blade coupled to the nose cone and having a blade passage, wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.

First claim

What is claimed is:

1. A thermal management system for a gas turbine engine comprising:
a nose cone having an aperture communicating air to an interior space of the nose cone;
a fan blade coupled to the nose cone and having a blade passage formed as an internal cavity within the fan blade, wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.

2. The system of claim 1 , wherein the blade passage extends to a blade trailing edge to circulate air from the aperture to the blade trailing edge.

3. The system of claim 2 , wherein the blade passage radially extends from a blade neck to the blade trailing edge to circulate air from the aperture to the blade trailing edge.

4. The system of claim 1 , wherein the nose cone further includes an upstream air pump disposed at the aperture to communicate air to the interior space with rotation of the nose cone.

5. The system of claim 4 , wherein the upstream air pump includes a guide vane disposed in the aperture to communicate air to the interior space.

6. The system of claim 4 , wherein the nose cone includes a plurality of apertures and the upstream air pump includes a plurality of guide vanes disposed in the plurality of apertures to communicate air to the interior space.

7. The system of claim 1 , wherein the nose cone further includes a downstream air pump disposed downstream of a heat exchanger to communicate air to the blade passage with rotation of the nose cone.

8. The system of claim 7 , further comprising a plurality of fan blades, wherein the downstream air pump includes a plurality of blades axially aligned with the plurality of fan blades.

9. The system of claim 1 , further comprising a heat exchanger disposed in the interior space, wherein the heat exchanger is in fluid communication with a lubricant circulation system disposed in a forward portion of the gas turbine engine.

10. The system of claim 9 , wherein the lubricant circulation system includes a lubricant filter disposed in the nose cone.

11. A method of circulating air in a gas turbine engine comprising: providing a nose cone having an aperture and an interior space; providing a fan blade having a blade passage;
rotating the nose cone with the fan blade;
communicating air to the interior space of the nose cone through the aperture; and communicating air from the interior space to the blade passage, wherein in the blade passage is formed as an internal cavity within the fan blade.

12. The method of claim 11 , further comprising:
providing a blade trailing edge at a downstream end of the blade passage; and circulating air from the aperture to the blade trailing edge.

13. The method of claim 11 , further comprising:
providing a blade neck at an upstream end of the blade passage; and
circulating air radially outward from the blade neck through the blade passage.

14. The method of claim 11 , further comprising: providing an upstream air pump at the aperture; and pumping air to the interior space with rotation of the nose cone.

15. The method of claim 14 , wherein the upstream air pump includes a guide vane disposed in the aperture to pump air to the interior space.

16. The method of claim 15 , wherein the nose cone includes a plurality of apertures and the upstream air pump includes a plurality of guide vanes disposed in the plurality of apertures to communicate air to the interior space.

17. The method of claim 11 , further comprising:
providing a heat exchanger in the interior space, wherein the nose cone further includes a downstream air pump disposed downstream of the heat exchanger to communicate air to the blade passage with rotation of the nose cone.

18. The method of claim 17 , further comprising: providing a plurality of fan blades;
providing a plurality of blades in the downstream air pump axially aligned with the plurality of fan blades; and
communicating air to the blade passage with the rotation of the nose cone.

19. The method of 11 , further comprising: providing a heat exchanger in the interior space;
providing a lubricant circulation system in fluid communication with the heat exchanger and disposed in a forward portion of the gas turbine engine; and
circulating lubricant through the heat exchanger and the lubricant circulation system.

20. The method of claim 19 , further comprising:
providing a lubricant filter in the lubricant circulation system; and circulating lubricant through the lubricant filter.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• F01D25/12 Primary

  Cooling · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• B64C11/14

  Spinners · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title