Thermal adjustment member for a fuel nozzle of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9739202-B2
Application number	US-201514710308-A
Country	US
Kind code	B2
Filing date	May 12, 2015
Priority date	May 12, 2015
Publication date	Aug 22, 2017
Grant date	Aug 22, 2017

Abstract

A fuel nozzle for use in a gas turbine engine is provided. The fuel nozzle has a fuel nozzle tip with an outer tip housing. The tip housing has a recess formed at an inner surface of the tip housing. A shim is disposed within the recess and a surface of the shim contacts a diaphragm of the fuel nozzle tip. A thermal adjustment member is disposed within the recess against the shim. The tip housing, diaphragm and shim are formed of a base material having a coefficient of thermal expansion (α 1 ) and the thermal adjustment member is formed of a different material having a coefficient of thermal expansion (α 2 ) higher than the coefficient of thermal expansion (α 1 ) of the base material.

First claim

What is claimed is:

1. A fuel nozzle for use in a gas turbine engine, comprising:
a fuel nozzle tip having an outer tip housing, wherein the outer tip housing has a recess formed at an inner surface of the outer tip housing;
a shim disposed within the recess, wherein a surface of the shim contacts a diaphragm of the fuel nozzle tip; and
a thermal adjustment member disposed within the recess against the shim, wherein the outer tip housing, diaphragm and shim are formed of a base material having a linear coefficient of thermal expansion (α 1 ) and the thermal adjustment member is formed of a different material having a linear coefficient of thermal expansion (α 2 ) higher than the linear coefficient of thermal expansion (α 1 ) of the base material.

2. The fuel nozzle of claim 1 wherein the thermal adjustment member has a length that extends from the shim to a wall of the inner surface of the outer tip housing.

3. The fuel nozzle of claim 2 wherein the thermal adjustment member is a cylindrical ring.

4. The fuel nozzle of claim 3 wherein the cylindrical ring is disposed between the shim and the wall of the outer tip housing such that a face of the cylindrical ring contacts the shim and an opposing face of the cylindrical ring contacts the wall of the inner surface of the outer tip housing.

5. The fuel nozzle of claim 2 wherein the thermal adjustment member is a metal component formed from at least one of: cobalt, cobalt alloys and stainless steel.

6. The fuel nozzle of claim 5 wherein the base material is formed from at least one of: nickel and nickel alloys.

7. The fuel nozzle of claim 1 further comprising a seat wherein the seat contacts the diaphragm proximate a pilot orifice of the fuel nozzle tip.

8. The fuel nozzle of claim 7 wherein the seat further contacts an end of the outer tip housing such that the diaphragm, shim and thermal adjustment member are enclosed within an interior of the fuel nozzle tip.

9. The fuel nozzle of claim 1 wherein the thermal adjustment member is tuned to counter fueling shifts due to changes in a modulus of elasticity of the diaphragm when the fuel nozzle tip is operating at high metal temperatures ranging from approximately 500° F. to approximately 1400° F.

10. The fuel nozzle of claim 9 wherein the material and length of the thermal adjustment member are preselected to provide for thermal growth such that the thermal adjustment member offsets loss in diaphragm preload due to a lower modulus of elasticity.

11. The fuel nozzle of claim 1 further comprising a heat shield wherein the heat shield is in substantially parallel alignment with at least a portion of the length of the thermal adjustment member.

12. The fuel nozzle of claim 11 wherein the heat shield is secured to the outer tip housing and is spaced apart from the thermal adjustment member to provide thermal management of the thermal adjustment member.

13. The fuel nozzle of claim 1 further comprising at least one channel extending through the outer tip housing, wherein one end of the channel is at an exterior of the outer tip housing and another end of the channel is at an interior of the outer tip housing proximate the thermal adjustment member such that the channel enables air to flow along the thermal adjustment member to provide heat transfer.

14. A fuel nozzle for use in a gas turbine engine comprising:
a fuel nozzle tip having an outer tip housing, wherein the outer tip housing has a recess formed at an inner surface of the outer tip housing;
a shim disposed within the recess wherein a surface of the shim contacts a diaphragm of the fuel nozzle tip; and
a thermal adjustment member of the shim disposed within the recess and in contact with the outer tip housing, wherein the shim and the thermal adjustment member comprise a single piece component, and wherein the outer tip housing and diaphragm are formed of a base material having a linear coefficient of thermal expansion (α 1 ) and the shim having the thermal adjustment member is formed of a different material having a linear coefficient of thermal expansion (α 2 ) higher than the linear coefficient of thermal expansion (α 1 ) of the base material.

15. The fuel nozzle of claim 14 wherein the thermal adjustment member has a length that laterally extends within the recess such that a face of the thermal adjustment member contacts a wall of the inner surface of the outer tip housing.

16. The fuel nozzle of claim 15 wherein the thermal adjustment member of the shim is in the shape of a cylindrical ring that extends substantially perpendicular to a body member of the shim.

17. The fuel nozzle of claim 14 wherein the shim having the thermal adjustment member is formed from at least one of: cobalt, cobalt alloys, and stainless steel.

18. The fuel nozzle of claim 17 wherein the base material is formed of at least one of: nickel and nickel alloys.

19. The fuel nozzle of claim 14 further comprising a seat, wherein the seat contacts the diaphragm proximate a pilot orifice of the fuel nozzle tip and wherein the seat further contacts an end of the outer tip housing such that the diaphragm and the shim are enclosed within an interior of the fuel nozzle tip.

20. The fuel nozzle of claim 14 wherein the length of the thermal adjustment member and the material of the shim are preselected to counter fueling shifts due to changes in a modulus of elasticity of the diaphragm when the fuel nozzle tip is operating at high metal temperatures ranging from approximately 500° F. to 1400° F.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Nam Tech Inc

Inventors

• Vetters Daniel K

Classifications

• F02C7/222 Primary

  Fuel flow conduits, e.g. manifolds · CPC title

• F05D2300/50212

  dissimilar · CPC title

• Y02E10/20

  Hydro energy · CPC title