Nose cone assembly and method of circulating air in a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10060350-B2
Application number	US-201514685325-A
Country	US
Kind code	B2
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.

First claim

What is claimed is:

1. A nose cone assembly for a gas turbine engine comprising:
a nose cone having an aperture communicating air to an interior space of the nose cone;
a discharge member communicating the air out of the nose cone forward of fan inlet guide vanes when the nose cone assembly is mounted to the gas turbine engine, the discharge member providing a first air passageway configured to communicate air, wherein the discharge member includes a pump that draws the air out of the interior space, and wherein the pump is a centrifugal pump having a rotor surrounded by a forward-swept discharge casing that discharges air axially rearward toward a radially inward portion of the fan inlet guide vanes when the nose cone assembly is mounted to the gas turbine engine; and
a heat exchanger disposed forward of the pump of the discharge member in the interior space, wherein the rotor of the pump is located aft of the heat exchanger and forward of the fan inlet guide vanes.

2. The nose cone assembly of claim 1 , wherein the discharge member discharges the air at a discharge location forward of a fan of the gas turbine engine when the nose cone assembly is mounted to the gas turbine engine.

3. The nose cone assembly of claim 1 , further comprising:
a plurality of heat exchangers disposed forward of the discharge member in the interior space, wherein the plurality of heat exchangers comprises the heat exchanger; and
a plurality of apertures disposed adjacent the plurality of heat exchangers and communicating air to the interior space, wherein the plurality of apertures comprises the aperture.

4. The nose cone assembly of claim 3 , further comprising a guide member disposed in fluid communication between the plurality of heat exchangers and the discharge member to guide the air toward the discharge member.

5. The nose cone assembly of claim 3 , further comprising a plurality of conduits circulating fluid through the discharge member and the plurality of heat exchangers.

6. The nose cone assembly of claim 5 , wherein at least one conduit of the plurality of conduits is in fluid communication with at least two heat exchangers of the plurality of heat exchangers.

7. The nose cone assembly of claim 1 , wherein the pump is driven by a shaft of the gas turbine engine when the nose cone assembly is mounted to the gas turbine engine.

8. A gas turbine engine assembly comprising:
a fan section including a fan and fan inlet guide vanes located forward of the fan;
a nose cone having an aperture communicating air to an interior space of the nose cone;
a discharge member communicating the air out of the nose cone at a discharge location forward of the fan inlet guide vanes and the fan when the nose cone assembly is mounted to the gas turbine engine, the discharge member providing a first air passageway configured to communicate air, wherein the discharge member includes a pump that draws the air out of the interior space, and wherein the pump is a centrifugal pump having a rotor surrounded by a forward-swept discharge casing that discharges air axially rearward toward a radially inward portion of the fan inlet guide vanes; and
a heat exchanger disposed forward of the pump of the discharge member in the interior space, wherein the rotor of the pump is located aft of the heat exchanger and forward of the fan inlet guide vanes.

9. The nose cone assembly of claim 8 , further comprising a plurality of circumferentially spaced heat exchangers disposed forward of the discharge member in the interior space, wherein the plurality of circumferentially spaced heat exchangers comprises the heat exchanger.

10. The nose cone assembly of claim 9 , further comprising a guide member disposed in fluid communication between the plurality of circumferentially spaced heat exchangers and the discharge member to guide the air toward the discharge member.

11. The nose cone assembly of claim 9 , further comprising a plurality of conduits circulating fluid through the discharge member and the plurality of circumferentially spaced heat exchangers.

12. The nose cone assembly of claim 11 , wherein at least one conduit of the plurality of conduits is in fluid communication with at least two heat exchangers of the plurality of circumferentially spaced heat exchangers.

13. The nose cone assembly of claim 8 , wherein the pump is driven by a shaft of the gas turbine engine.

14. A method of circulating air in a gas turbine engine comprising:
providing a nose cone having an aperture and an interior space;
providing a heat exchanger in the interior space;
providing a discharge member, the discharge member providing a first air passageway configured to communicate air, wherein the discharge member includes a centrifugal pump having a rotor surrounded by a forward-swept discharge casing, and wherein the rotor of the centrifugal pump is located aft of the heat exchanger and forward of the fan inlet guide vanes;
circulating air through the aperture;
circulating the air through the heat exchanger in the interior space using the centrifugal pump; and
discharging the air out of the discharge member at a discharge location forward of fan inlet guide vanes, wherein the discharge casing discharges air axially rearward toward a radially inward portion of the fan inlet guide vanes.

15. The method of claim 14 , further comprising:
providing a plurality of heat exchangers in the interior space, wherein the plurality of heat exchangers comprises the heat exchanger; and
circulating the air through the plurality of heat exchangers in the interior space.

16. The method of claim 15 , further comprising circulating oil through the plurality of heat exchangers and the discharge member.

17. The method of claim 15 , further comprising circulating the air through the aperture and the plurality of heat exchangers with a pump.

18. The method of claim 14 , wherein discharging the air comprises discharging the air at a discharge location forward of a fan of the gas turbine engine when the nose cone is mounted to the gas turbine engine.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M
• Hipsky Harold W
• Zywiak Thomas M

Classifications

• F05D2260/213

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

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02C7/14

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

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F01D25/12

  Cooling · CPC title