Oblong swirler assembly for combustors

Patent metadata

Field	Value
Publication number	US-9404656-B2
Application number	US-201213717232-A
Country	US
Kind code	B2
Filing date	Dec 17, 2012
Priority date	Dec 17, 2012
Publication date	Aug 2, 2016
Grant date	Aug 2, 2016

Abstract

In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

First claim

What is claimed is:

1. A swirler, comprising:
a first swirler comprising:
an outer shroud and inner shroud, the inner shroud positioned radially inside the outer shroud, at least one of the outer and inner shroud having a major diameter which is greater than a minor diameter such that the inner and outer shroud define an oblong, the swirler having a first end and a second end, the inner shroud defining a first oblong shape at one or more of the first end and the second end and the outer shroud defining a second oblong shape at one or more of the first end and the second end; and
a plurality of radial swirler vanes positioned between the inner and outer shroud.

2. The swirler of claim 1 , wherein the plurality of radial swirler vanes are positioned between the inner and outer shroud in a third oblong shape.

3. The swirler of claim 1 , wherein both the inner and outer shroud are oblong shaped.

4. The swirler of claim 1 , wherein the first swirler is oblong shaped at a proximal end, circular shaped at a distal end, and the first swirler transitions from being oblong shaped at the proximal end to being circular shaped at the distal end, the proximal end being the first end and the distal end being the second end.

5. The swirler of claim 1 , wherein the first swirler is oblong shaped at a distal end, circular shaped at a proximal end, and the first swirler transition from being circular shaped at the proximal end to being oblong shaped at the distal end, the distal end being the first end and the proximal end being the second end.

6. The swirler of claim 1 , further comprising a second swirler positioned around the first swirler.

7. The swirler of claim 6 , wherein the second swirler is oblong shaped.

8. The swirler of claim 1 , wherein the swirler is a component of a swirler assembly, the swirler assembly comprising a plurality of swirlers having oblong, circular, or a mixture of oblong and circular shapes.

9. A gas turbine engine, comprising:
a compressor;
a combustor axially behind the compressor and having at least one swirler positioned through a forward bulkhead, each swirler including an outer shroud and an inner shroud, the inner shroud positioned radially inside the outer shroud, at least one of the inner and outer shroud being oblong shaped, the swirler having a first end and a second end, the inner shroud defining a first oblong shape at one or more of the first end and the second end and the outer shroud defining a second oblong shape at one or more of the first end and the second end, and a plurality of radial swirler vanes positioned between the inner and outer shroud; and
a turbine axially behind the combustor and connected to the compressor by a rotatable shaft.

10. The gas turbine engine of claim 9 , wherein the plurality of radial swirler vanes are positioned between the inner and outer shrouds in a third oblong shape.

11. The gas turbine engine of claim 9 , wherein both the inner and outer shrouds are a oblong shaped.

12. The gas turbine engine of claim 9 , wherein the at least one swirler is oblong shaped at a proximal end, circular shaped at a distal end, and the at least one swirler transitions from being oblong shaped at the proximal end to being circular shaped at the distal end, the proximal end being the first end and the distal end being the second end.

13. The gas turbine engine of claim 9 , wherein the at least one swirler is oblong shaped at a distal end, circular shaped at a proximal end, and the at least one swirler transitions from being circular shaped at the proximal end to being oblong shaped at the distal end, the distal end being the first end and the proximal end being the second end.

14. The gas turbine engine of claim 9 , wherein the combustor has an annular shape and a circumferential diameter of the at least one swirler with respect to the combustor is greater than a radial diameter of the at least one swirler with respect to the combustor.

15. The gas turbine engine of claim 14 , wherein the at least one swirler is symmetric about a centerline of the forward bulkhead.

16. The gas turbine engine of claim 9 , further comprising an outer swirler radially surrounding the at least one swirler, wherein both the at least one swirler and the outer swirlers are oblong shaped.

17. The gas turbine engine of claim 9 , wherein the at least one swirler is a component of a swirler assembly which includes a plurality of swirlers, each swirler having an oblong shape, a circular shape, or a mixture of oblong and circular shapes.

18. A method of mixing air and fuel with an oblong swirler thereby creating an air-fuel mixture, comprising:
injecting fuel into a housing of the oblong swirler by a fuel injection system; and
creating a mixing turbulence with air flowing through a plurality of air passages between a plurality of radial swirler vanes disposed in the housing of the oblong swirler and arranged in a first oblong shape, the housing of the oblong swirler including an outer shroud and an inner shroud, the inner shroud positioned radially inside the outer shroud, the inner shroud defining a second oblong shape at one or more of a first end of the oblong swirler and a second end of the oblong swirler and the outer shroud defining a third oblong shape at one or more of the first end and the second end.

19. The method of claim 18 , further comprising providing a preferential premixing of the air and fuel with the housing of the oblong swirler having an oblong shaped proximal end.

20. The method of claim 18 , further comprising dispersing the air-fuel mixture into a combustion chamber in a preferential air-fuel flow distribution by the housing of the swirler having an oblong shaped distal end.

Assignees

• United Technologies Corp

Inventors

• Burd Steven W

Classifications

• F23R3/28 Primary

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

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title