Flow modifier for combustor fuel nozzle tip

Patent metadata

Field	Value
Publication number	US-9400104-B2
Application number	US-201213630439-A
Country	US
Kind code	B2
Filing date	Sep 28, 2012
Priority date	Sep 28, 2012
Publication date	Jul 26, 2016
Grant date	Jul 26, 2016

Abstract

A fuel injector nozzle assembly includes a body extending along an axis and a core swirl plug positioned at least partially within the body. The core swirl plug has a flow modifying structure configured to swirl fuel at a location upstream from a distal end of the nozzle assembly.

First claim

The invention claimed is:

1. A fuel injector nozzle assembly comprising:
a body extending along an axis;
a support having a support body abutting the body and configured to carry fuel to the body;
a core swirl plug positioned at least partially within the body, the core swirl plug having a central passage for a first fuel flow, a fuel flow path along an outer surface of the core swirl plug for a second fuel flow, and a flow modifying structure configured to swirl the second fuel flow at a location upstream from a distal end of the nozzle assembly, wherein a portion of the flow modifying structure is positioned proximate to the support body, and wherein the flow modifying structure extends along a majority of the body in an axial direction; and
a heat shield sleeve positioned concentrically between the body and the core swirl plug, wherein the heat shield sleeve does not contact the support, and the core swirl plug does not contact the body or the support,
wherein the flow modifying structure is a rib.

2. The assembly of claim 1 , wherein the rib is a helical rib.

3. The assembly of claim 2 , wherein the helical rib has a frustum cross-sectional shape.

4. The assembly of claim 1 , wherein the core swirl plug and the body are spaced from each other.

5. The assembly of claim 1 and further comprising:
a fuel outlet passage that extends through the body at an angle relative to the axis to permit fuel injection in a generally radial direction.

6. The assembly of claim 1 , wherein said fuel flow path along the outer surface is a helical channel having multiple turns.

7. The assembly of claim 6 , wherein said helical channel is adjacent to said distal end of the fuel injector nozzle assembly.

8. The assembly of clam 1 , wherein said body includes a multiple of radial orifices.

9. The assembly of claim 1 , further comprising an outer sleeve that at least partially surrounds said heat shield sleeve.

10. The assembly of claim 9 , wherein said first fuel flow is a primary fuel flow, said second fuel flow is a secondary fuel flow, and said fuel flow path along the outer surface is a helical channel having multiple turns.

11. A combustor assembly for a gas turbine engine combustor, the assembly comprising:
a combustion chamber;
a first fuel injector nozzle configured to inject fuel into the combustion chamber,
the first fuel injector nozzle including:
a body extending along an axis and having a fuel outlet passage that extends through the body at an angle to permit fuel injection into the combustion chamber in a generally radial direction;
a support having a support body and a tube configured to carry fuel, wherein the support body abuts the body;
a core swirl plug positioned at least partially within the body, the core swirl plug having a central passage for a first fuel flow, a fuel flow path along an outer surface of the core swirl plug for a second fuel flow, and a flow modifying structure, wherein the flow modifying structure is a rib that extends along a majority of the body in an axial direction; and
a heat shield sleeve positioned concentrically between the body and the core swirl plug of the first fuel injector nozzle, wherein the heat shield sleeve does not contact the support, and the core swirl plug does not contact the body or the support.

12. The assembly of claim 11 , wherein the rib a helical rib.

13. The assembly of claim 12 , wherein the helical rib has a frustum cross-sectional shape.

14. The assembly of claim 11 , wherein the core swirl plug and the body are spaced from each other, and wherein the core swirl plug and the body each define portions of a boundary of the fuel flow path along the outer surface.

15. The assembly of claim 11 , further comprising:
a second fuel injector nozzle configured to inject fuel into the combustion chamber,
the second fuel injector nozzle having a duplex configuration and including:
a second body extending along an second axis; and
a second core swirl plug positioned at least partially within the second body, the second core swirl plug having a second flow modifying structure and a second passage, wherein a fuel flow path passes along an outer surface of the second core swirl plug adjacent to the second flow modifying structure and another fuel flow path passes through the second core swirl plug along the second passage.

16. The assembly of claim 11 , wherein the flow modifying structure is configured to swirl the second fuel flow along a majority of an axially extending portion of the first fuel injector nozzle.

17. The assembly of claim 11 , wherein the heat shield sleeve contacts the flow modifying structure of the core swirl plug of the first fuel injector nozzle.

18. The assembly of claim 15 , wherein the second body of the second fuel injector nozzle has a common configuration with the body of the first fuel injector nozzle.

19. The assembly of claim 11 , wherein said fuel flow path along the outer surface is a helical channel having multiple turns.

20. The assembly of claim 19 , wherein a portion of said helical channel is adjacent to said fuel outlet passage of the first fuel injector nozzle.

21. The assembly of clam 11 , wherein said body includes a multiple of radial orifices.

22. The assembly of claim 11 , further comprising an outer sleeve that at least partially surrounds said heat shield sleeve.

23. The assembly of claim 22 , wherein said first fuel flow is a primary fuel flow, said second fuel flow is a secondary fuel flow and said fuel flow path along the outer surface is helical channel haying multiple turns.

24. A method for injecting fuel into the combustor assembly of the gas turbine engine combustor according to claim 11 , the method comprising:
delivering the second fuel flow to the fuel flow path along the outer surface;
moving the second fuel flow along the fuel flow path along the outer surface;
ejecting the second fuel flow at a downstream end of the first fuel injector nozzle in a generally radially outward direction; and
swirling the second fuel flow moving along the fuel flow path along the outer surface upstream from the downstream end of the first fuel injector nozzle to help reduce fuel coking, and wherein the rib is helical.

25. The method of claim 24 , and further comprising:
shielding the support from thermal energy transfer with the heat shield sleeve.

26. The method of claim 24 and further comprising:
moving the first fuel flow along the central passage radially inward from the fuel flow path along the outer surface.

27. The method of claim 26 and further comprising:
ejecting the first fuel flow moving along the central passage from the downstream end of the first fuel injector nozzle along the axis.

Assignees

• Low Kevin Joseph
• Hoke James B
• Kojovic Aleksandar
• Manninen Andrew
• Niemeyer Sander
• United Technologies Corp
• Woodward Inc

Inventors

• Low Kevin Joseph
• Hoke James B
• Kojovic Aleksandar
• Manninen Andrew
• Niemeyer Sander

Classifications

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23D11/383 Primary

  with swirl means · CPC title

• F23D2900/00016

  Preventing or reducing deposit build-up on burner parts, e.g. from carbon · CPC title

• F23R2900/00004

  Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title