Fuel/air premixing system for turbine engine

Patent metadata

Field	Value
Publication number	US-8925323-B2
Application number	US-201213460700-A
Country	US
Kind code	B2
Filing date	Apr 30, 2012
Priority date	Apr 30, 2012
Publication date	Jan 6, 2015
Grant date	Jan 6, 2015

Abstract

A system includes a fuel nozzle. The fuel nozzle includes a center body configured to receive a first portion of air and to deliver the air to a combustion region. The fuel nozzle also includes a swirler configured to receive a second portion of air and to deliver the air to the combustion region. The swirler includes an outer shroud wall, an inner hub wall, and a swirl vane. The swirl vane includes a radial swirl profile at a downstream edge of the swirl vane. The radial swirl profile includes a region extending from the outer shroud wall to a first transition point and a second region extending from the transition point to the inner hub wall. At least one of the first and second regions is substantially straight and at least one of the first and second regions is arcuate.

First claim

The invention claimed is:

1. A system, comprising:
a fuel nozzle, comprising:
a center body configured to receive a first portion of air and to deliver the air to a combustion region; and
a swirler configured to receive a second portion of air and to deliver the air to the combustion region, wherein the swirler comprises:
an outer shroud wall;
an inner hub wall comprising a fuel supply port; and
a swirl vane with a radial swirl profile at a downstream edge of the swirl vane, wherein the radial swirl profile comprises a first region extending from the outer shroud wall to a transition point and a second region extending from the transition point to the inner hub wall, and the first region is substantially straight and the second region is arcuate, and wherein the swirl vane comprises a fuel injection port in fluid communication with the fuel supply port.

2. The system of claim 1 , wherein the center body includes a diffusion swirler configured to induce a swirl to a subportion of the first portion of air.

3. The system of claim 1 , wherein the radial swirl profile forms a first swirl angle at the outer shroud wall and the radial swirl profile forms a second swirl angle at the inner hub wall, and the first swirl angle is greater than the second swirl angle.

4. The system of claim 3 , wherein the first swirl angle is between approximately 40 degrees and approximately 60 degrees.

5. The system of claim 3 , wherein the second swirl angle is below approximately 20 degrees.

6. The system of claim 1 , wherein the ratio of the first portion of air relative to the second portion of air is approximately 0.05 to approximately 0.25.

7. The system of claim 1 , wherein the transition point is disposed proximate to a center of the radial swirl profile.

8. The system of claim 1 , comprising a gas turbine comprising the combustor and the fuel nozzle.

9. The system of claim 1 , wherein the center body comprises a plurality of swirler vanes configured to induce a swirl angle of the first portion of air exiting the center body at an angle between approximately 30 degrees and approximately 50 degrees.

10. A method, comprising:
directing a first portion of air through a center body of a fuel nozzle, wherein the first portion of air exits the center body with a first swirl angle near a hub wall of the fuel nozzle; and
directing a second portion of air through a swirler of the fuel nozzle, wherein the second portion of air exits the swirler with a second swirl angle near a shroud wall of the fuel nozzle, the second portion of air exits the swirler with a third swirl angle near the hub wall of the fuel nozzle, and the second swirl angle is greater than the third swirl angle
wherein the swirler has a swirl vane with a radial swirl profile at a downstream edge of the swirl vane, the radial swirl profile comprises a first region extending from the outer shroud wall to a transition point and a second region extending from the transition point to the inner hub wall, the first region is substantially straight and the second region is arcuate, wherein the inner hub wall comprises a fuel supply port, and the swirl vane comprises a fuel injection port in fluid communication with the fuel supply port.

11. The method of claim 10 , wherein the ratio of the first portion of air relative to the second portion of air is approximately 0.05 to approximately 0.25.

12. The method of claim 10 , comprising inducing the first swirl angle of the first portion of air exiting the center body at an angle between approximately 30degrees and approximately 50 degrees.

13. The method of claim 10 , comprising inducing the second swirl angle of the second portion of air exiting the swirler near the shroud wall at an angle between approximately 40 degrees and approximately 60 degrees.

14. The method of claim 10 , comprising inducing the third swirl angle of the second portion of air exiting the swirler near the hub wall at an angle below approximately 20 degrees.

15. A system, comprising:
a fuel nozzle swirler, comprising:
an outer shroud wall;
an inner hub wall comprising a fuel supply port; and
a swirl vane with a radial swirl profile at a downstream edge of the swirl vane, wherein the radial swirl profile comprises a first region extending from the outer shroud wall to a transition point and a second region extending from the transition point to the inner hub wall, and the first region comprises a substantially constant swirl angle and the second region comprises a decreasing swirl angle toward the hub wall, and wherein the swirl vane comprises a fuel injection port in fluid communication with the fuel supply port.

16. The system of claim 15 , wherein the radial swirl profile forms a first swirl angle of the first region at the outer shroud wall, the radial swirl profile forms a second swirl angle of the second region at the inner hub wall, and the first swirl angle is greater than the second swirl angle.

17. The system of claim 16 , wherein the first swirl angle is between approximately 40 degrees and approximately 60 degrees.

18. The system of claim 16 , wherein the second swirl angle is below approximately 20 degrees.

19. The system of claim 15 , wherein the transition point is disposed proximate to a center of the radial swirl profile.

Assignees

• Zuo Baifang
• Gen Electric

Inventors

• Zuo Baifang

Classifications

• F23C2900/07001

  Air swirling vanes incorporating fuel injectors · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title

• F23R3/286

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