Gas turbine combustor

Patent metadata

Field	Value
Publication number	US-10060625-B2
Application number	US-201314772535-A
Country	US
Kind code	B2
Filing date	Mar 13, 2013
Priority date	Mar 13, 2013
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

In a perforated coaxial jet burner implemented by a lot of air-fuel coaxial jets, a swirl plate ( 33 ) as an end face of the burner on the combustion chamber's side has a lot of air holes for supplying unburned premixed gas of fuel and air to the combustion chamber. Grooves ( 36 ) are formed downstream of the air holes of the swirl plate. Adhesion of flame to the swirl plate is inhibited by feeding part of the unburned premixed gas to the grooves. Further, the width of each remaining part ( 37 ) between adjacent grooves is set at several millimeters that is approximately equal to the flame quenching distance, by which adhesion of flame to the remaining parts is also prevented. With this configuration, both stable combustion and low NOx combustion can be achieved irrespective of the load condition.

First claim

The invention claimed is:

1. A gas turbine combustor comprising:
a combustion chamber in which fuel is burned with air to generate combustion gas;
a fuel header having a plurality of fuel nozzles for discharging fuel;
an air hole plate provided with a plurality of air holes in rows formed by arranging the plurality of air holes in a circumferential direction of the air hole plate through which fuel discharged from the plurality of fuel nozzles and air are injected into the combustion chamber; and
a plurality of grooves formed on a surface of the air hole plate on a side of the combustion chamber, the plurality of grooves being connected with the plurality of air holes; wherein
each of the plurality of grooves is provided at least for each of the rows.

2. The gas turbine combustor according to claim 1 , wherein:
each of the air holes is formed obliquely in the air hole plate, each air hole having its central axis extending at a predetermined angle with respect to an axial direction of a combustor liner, and
the plurality of grooves are formed to be situated on a downstream side in regard to an air discharge direction from the air holes.

3. The gas turbine combustor according to claim 2 , wherein each of the plurality of grooves is formed for each of the air holes in a one-to-one correspondence.

4. A gas turbine combustor comprising:
a combustion chamber in which fuel is burned with air to generate combustion gas;
a fuel header having a plurality of fuel nozzles for discharging fuel;
an air hole plate provided with a plurality of air holes through which fuel discharged from the plurality of fuel nozzles and air are injected into the combustion chamber; and
a groove formed on a surface of the air hole plate on a side of the combustion chamber, the groove being connected with the plurality of air holes;
wherein:
the groove is one of a plurality of grooves formed on the air hole plate, and
a dimension of a gap formed by two adjacent ones of the plurality of grooves is set less than or equal to a flame quenching distance.

5. The gas turbine combustor according to claim 4 , wherein:
the plurality of grooves are concentric circumferential grooves differing in a radius; and
a dimension of the gap between two of the plurality of grooves adjacent to each other in a radial direction is set less than or equal to the flame quenching distance.

6. The gas turbine combustor according to claim 5 , wherein:
none of the grooves are formed in a first region where a radial distance from a center of the air hole plate is less than a predetermined value, the first region including the air holes each having its open end on the combustion chamber's side situated on the air hole plate;
the grooves are formed in a second region where the radial distance from the center of the air hole plate is the predetermined value or more, the second region including the air holes each having its open end on the combustion chamber's side situated at a bottom of the grooves; and
the air holes in the second region are larger in diameter than those of the air holes in the first region.

7. A gas turbine combustor comprising:
a combustion chamber in which fuel is burned with air to generate combustion gas;
a fuel header having a plurality of fuel nozzles for discharging fuel;
an air hole plate provided with a plurality of air holes through which fuel discharged from the plurality of fuel nozzles and air are injected into the combustion chamber; and
a groove formed on a surface of the air hole plate on a side of the combustion chamber, the groove being connected with the plurality of air holes;
wherein:
each of the fuel nozzles is provided with a corresponding one of the air holes which is arranged downstream of the fuel nozzle in an axial direction of the fuel nozzle; and
the fuel discharged from the each of the fuel nozzles and the air flowing through the corresponding one of the air holes form a coaxial jet.

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Abe Kazuki
• Koganezawa Tomomi
• Miura Keisuke

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

• F23R3/12 Primary

  inducing a vortex · CPC title

• F23R3/32

  being tubular · CPC title

• F23R3/286

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

• F23R3/30

  comprising fuel prevapourising devices · CPC title