Gas turbine combustor and gas turbine

Patent metadata

Field	Value
Publication number	US-10094565-B2
Application number	US-201515301812-A
Country	US
Kind code	B2
Filing date	Apr 21, 2015
Priority date	May 23, 2014
Publication date	Oct 9, 2018
Grant date	Oct 9, 2018

Abstract

A gas turbine combustor and a gas turbine include a pilot burner, a plurality of main burners, and a flame stabilizer. A first air ejection portion is adapted to eject first air toward a tip end portion side between the main burners and the flame stabilizer, a second air ejection portion is adapted to circulate second air toward a tip end portion side outside the flame stabilizer and eject the second air toward a radially outward direction, and a change member is adapted to change an ejecting direction of the second air ejected through the second air ejection portion to an axial center direction of the flame stabilizer.

First claim

The invention claimed is:

1. A gas turbine combustor comprising:
a combustion chamber having a cylindrical shape;
a pilot burner in a central portion in the combustion chamber;
a plurality of main burners around the pilot burner in the combustion chamber;
a flame stabilizer covering an outside of a pilot nozzle in the pilot burner and having a tapered cylinder shape where a tip end portion of the flame stabilizer radially expands;
a first air ejection portion adapted to eject first air in a first ejecting direction toward a tip end portion side of the first air ejection portion between one of the main burners and the flame stabilizer,
the first ejecting direction having an axial center direction component and a radial direction component;

a second air ejection portion adapted to circulate second air toward a tip end portion side of the second air ejection portion that is radially outside the flame stabilizer and eject the second air toward a radially outward direction;
and a change member adapted to change a second ejecting direction of the second air ejected through the second air ejection portion to an axial center direction of the flame stabilizer,
wherein the change member is adapted to change the second ejecting direction of the second air ejected through the second air ejection portion in the axial center direction to become an opposite direction to the axial center direction component of the first ejecting direction of the first air ejected through the first air ejection portion.

2. The gas turbine combustor according to claim 1 , wherein:
the second air ejection portion includes:
a first air passage radially outside the flame stabilizer that is adapted to circulate the second air toward a tip end portion side of the first air passage,
a second air passage adapted to circulate the second air from the tip end portion side of the first air passage toward the radially outward direction,
and an air ejection port in a radially outward end of the second air passage,

wherein the change member is in the air ejection port;
the flame stabilizer includes:
a flame stabilizer body having a cylindrical shape,
tapered cylinder portion having a tapered cylinder shape continuing to the tip end portion of the flame stabilizer,
a tapered external cylinder portion radially outside the tapered cylinder portion having a tapered cylinder shape continuing to the tip end portion of the flame stabilizer, and
a predetermined space between the tapered cylinder portion and the tapered external cylinder portion; and

wherein the first air passage, the second air passage, and the air ejection port are between the tapered cylinder portion and the tapered external cylinder portion,
and the change member is positioned in the tapered cylinder portion.

3. The gas turbine combustor according to claim 2 , wherein the change member is in a tip end portion of the tapered cylinder portion.

4. The gas turbine combustor according to claim 2 , wherein at least one of the main burners includes a main burner cylinder, a main nozzle in a central portion of the main burner cylinder, and a swirler vane between the main burner cylinder and the main nozzle; and
the change member extends around a whole circumferential area of the tapered cylinder portion of the flame stabilizer.

5. The gas turbine combustor according to claim 2 , wherein at least one of the main burners includes a main burner cylinder, a main nozzle in a central portion of the main burner cylinder, and a swirler vane between the main burner cylinder and the main nozzle; and
the change member extends along a part of a whole circumferential area of the tapered cylinder portion of the flame stabilizer.

6. The gas turbine combustor according to claim 2 , wherein the tapered cylinder portion is configured such that divided bodies are combined in a cylindrical shape,
and the change member is positioned in at least a partial area of the divided bodies.

7. A gas turbine comprising:
a compressor adapted to compress air;
the gas turbine combustor of claim 1 , adapted to mix and burn compressed air compressed by the compressor with a fuel; and
a turbine adapted to obtain rotary power by expanding a combustion gas generated by the gas turbine combustor.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Tanaka Yusuke
• Takiguchi Satoshi
• Saito Keijiro
• Akamatsu Shinji

Classifications

• 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

• F23R3/18 Primary

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

• F23R3/286

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

• F23R3/26

  Controlling the air flow · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title