Combustor and gas turbine

Patent metadata

Field	Value
Publication number	US-9933162-B2
Application number	US-201414762577-A
Country	US
Kind code	B2
Filing date	Jan 10, 2014
Priority date	Feb 1, 2013
Publication date	Apr 3, 2018
Grant date	Apr 3, 2018

Abstract

A combustor includes: a pilot burner; a plurality of main burners, each of which is provided radially and outwardly along a circumferential direction about the pilot burner, and including a main nozzle disposed in a main burner cylinder; and an extension tube provided to extend toward a downstream side from the main burner cylinder of each of the main burners. The extension tube has a circular inlet communicating with the main burner cylinder, and an outlet at the downstream side comprising two radial edges parallel to the radial direction and two circumferential edges formed along the circumferential direction so as to connect both ends of the radial edges. The combustor further includes an air passage formed outside of the main burner cylinder; and an inner communication hole (formed at the side of the inlet of the extension tube and at a position corresponding to the radially and inwardly circumferential edge for allowing communication between the air passage and the inside of the extension tube.

First claim

The invention claimed is:

1. A combustor comprising:
a pilot burner;
a plurality of main burners positioned radially outward of the pilot burner and displaced along a circumferential direction about a longitudinal axis of the pilot burner, each of the main burners including a main nozzle disposed in a main burner cylinder;
a plurality of extension tubes, each of the extension tubes being located at a downstream side of the main burner cylinder of a respective one of the main burners, each of the extension tubes including an upstream circular inlet communicating with the respective main burner cylinder, and including a downstream trapezoidal outlet formed of two radial edges extending in a radial direction and two circumferential edges formed in the circumferential direction so as to connect radial outer ends and radial inner ends of the radial edges; and
an air passage formed outside of the main burner cylinder;
wherein each of the extension tubes has an elongated slit-shaped inner communication hole formed to extend obliquely through a wall on a radially inner side of the upstream circular inlet of the respective extension tube and towards the downstream trapezoidal outlet, the inner communication hole being configured to allow the air passage to communicate with an interior of the respective extension tube at a radially inner circumferential edge of the respective extension tube, and
wherein the inner communication hole is configured such that a center of an arc length of the elongated slit-shaped inner communication hole is shifted circumferentially from a central position of the radially inner circumferential edge.

2. A gas turbine comprising:
a compressor;
the combustor according to claim 1 ; and
a turbine.

3. The combustor according to claim 1 , further comprising:
a plurality of main swirlers radially extending in the main burner cylinder; and
a vane communication hole formed at a position corresponding to a downstream end of the main swirlers to allow communication between the air passage and an interior of the main burner cylinder.

4. The combustor according to claim 1 , wherein the elongated slit-shaped inner communication hole extends more than 30 degrees and less than 180 degrees in the circumferential direction.

5. The combustor according to claim 1 , wherein each of the extension tubes further has a corner communication hole configured to allow the air passage to communicate with the interior of the respective extension tube, the corner communication hole being located at a radially outer circumferential edge of the inlet of the respective extension tube.

6. The combustor according to claim 5 , wherein
the inner communication hole extends in the circumferential direction, and the corner communication hole extends in the circumferential direction.

7. The combustor according to claim 6 , wherein
the inner communication hole is formed to have a larger aperture area than that of the corner communication hole.

8. The combustor according to claim 5 , wherein the inner communication hole extends in the circumferential direction and the corner communication hole is one of a plurality of holes discontinuously arranged in the circumferential direction.

9. The combustor according to claim 5 , wherein the corner communication hole is formed through the wall of the extension tube.

10. A combustor comprising:
a pilot burner;
a plurality of main burners positioned radially outward of the pilot burner and displaced along a circumferential direction about a longitudinal axis of the pilot burner, each of the main burners including a main nozzle disposed in a main burner cylinder;
a plurality of extension tubes, each of the extension tubes being located at a downstream side of the main burner cylinder of a respective one of the main burners, each of the extension tubes including an upstream circular inlet communicating with the respective main burner cylinder, and including a downstream trapezoidal outlet formed of two radial edges extending in a radial direction and two circumferential edges formed in the circumferential direction so as to connect radial outer ends and radial inner ends of the radial edges; and
an air passage formed outside of the main burner cylinder;
wherein each of the extension tubes has an elongated slit-shaped corner communication hole formed to extend obliquely through a wall on a radially outer side of the upstream circular inlet of the respective extension tube and towards the downstream trapezoidal outlet, the corner communication hole being configured to allow the air passage to communicate with an interior of the respective extension tube at a radially outer circumferential edge of the respective extension tube, and
wherein the corner communication hole is configured such that a center of an arc length of the elongated slit-shaped corner communication hole is shifted circumferentially from a central position of the radially outer circumferential edge.

11. The combustor according to claim 10 , further comprising:
An inner communication hole configured to allow the air passage to communicate with the interior of the respective extension tube at the radially inner circumferential edge of the respective extension tube.

12. The combustor according to claim 10 , wherein the elongated slit-shaped corner communication hole extends more than 30 degrees and less than 180 degrees in the circumferential direction.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Inoue Kei
• Saito Keijiro
• KATANO Hikaru
• Nakamura Sosuke
• Isono Mitsunori
• Yuasa Atsushi

Classifications

• F23R2900/03343

  Pilot burners operating in premixed mode · CPC title

• F23R3/18 Primary

  Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title