Combustor

Patent metadata

Field	Value
Publication number	US-9464807-B2
Application number	US-201514601418-A
Country	US
Kind code	B2
Filing date	Jan 21, 2015
Priority date	Jan 24, 2014
Publication date	Oct 11, 2016
Grant date	Oct 11, 2016

Abstract

Provided is a combustor including a support shaft, a wing portion provided on the support shaft and configured to swirl a first fluid around the support shaft, and a cover housing enclosing the support shaft and the wing portion and includes a space enlarging portion provided at a downstream of of the wing portion, where a distance of the space enlarging portion from an outer surface of the support shaft is different from distances of other portions of the cover housing from the outer surface of the support shaft.

First claim

What is claimed is:

1. A combustor comprising:
a support shaft;
a wing portion provided on the support shaft and configured to swirl a first fluid around the support shaft; and
a cover housing enclosing the support shaft and the wing portion and comprising a space enlarging portion provided at a downstream side of the wing portion along a flow direction of the first fluid,
wherein a distance between the space enlarging portion and an outer surface of the support shaft is different from distances between other portions of the cover housing and the outer surface of the support shaft, and
wherein the space enlarging portion extends spirally with respect to a longitudinal direction of the support shaft.

2. The combustor of claim 1 , further comprising a guide housing enclosing the cover housing.

3. The combustor of claim 1 , wherein the space enlarging portion extends in a predetermined angle with respect to a longitudinal direction of the support shaft.

4. The combustor of claim 1 , wherein the space enlarging portion comprises:
a fluid injection hole configured to inject a second fluid at a first angle with respect to the flow direction of the first fluid; and
a fuel injection hole configured to inject a fuel at a second angle with respect to the flow direction of the first fluid.

5. The combustor of claim 4 , wherein the second fluid and the fuel are configured to circulate in the space enlarging portion after being injected into the space enlarging portion through the fluid injection hole and the fuel injection hole, respectively.

6. The combustor of claim 4 , wherein the fluid injection hole comprises a plurality of fluid injection holes provided at different heights of the space enlarging portion.

7. The combustor of claim 1 , wherein a cross-sectional area of the space enlarging portion varies along a circumferential direction of the space enlarging portion.

8. The combustor of claim 6 , wherein the plurality of fluid injection holes are provided at different heights with respect to a radial direction of the space enlarging portion.

9. The combustor of claim 4 , wherein the first angle and the second angle are different from each other.

10. A combustor comprising:
a support plate;
a support shaft provided on the support plate;
a wing portion radially extending from the support plate and configured to swirl a first fluid toward a center of the support plate; and
a cover housing enclosing the support shaft and the wing portion and comprising a space enlarging portion provided at a downstream side of the wing portion along a flow direction of the first fluid,
wherein a distance between the space enlarging portion and an outer surface of the support shaft is different from distances between other portions of the cover housing and the outer surface of the support shaft, and
wherein the space enlarging portion extends spirally with respect to a longitudinal direction of the support shaft.

11. The combustor of claim 10 , further comprising a guide housing enclosing the cover housing.

12. The combustor of claim 10 , wherein the space enlarging portion extends at a predetermined angle with respect to a longitudinal direction of the support shaft.

13. The combustor of claim 10 , wherein the space enlarging portion comprises:
a fluid injection hole configured to inject a second fluid at a first angle with respect to the flow direction of the first fluid; and
a fuel injection hole configured to inject a fuel at a second angle with respect to the flow direction of the first fluid.

14. The combustor of claim 13 , wherein the second fluid and the fuel are configured to circulate inside the space enlarging portion after being injected into the space enlarging portion through the fluid injection hole and the fuel injection hole, respectively.

15. The combustor of claim 13 , wherein the fuel injection hole comprises a plurality of fluid injection holes provided at different heights of the space enlarging portion.

16. The combustor of claim 10 , wherein a cross-sectional area of the space enlarging portion varies along a circumferential direction of the space enlarging portion.

17. The combustor of claim 15 , wherein the plurality of fluid injection holes are provided at different heights with respect to a radial direction of the space enlarging portion.

18. The combustor of claim 13 , wherein the first angle and the second angle are different from each other.

Assignees

• Hanwha Techwin Co Ltd

Inventors

• Kim Sinhyun
• Jung Seungchai
• Yang Siwon

Classifications

• F23R3/34

  Feeding into different combustion zones · CPC title

• F23R3/286

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

• F23R2900/00015

  Trapped vortex combustion chambers · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title