Gas turbine combustor flame holder

1. A combustor comprising:

a first nozzle which extends along an axis and injects fuel toward a downstream side;

a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and

a plurality of second nozzles arranged at first intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer,

wherein the flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion,

wherein a penetrating portion which penetrates the flange portion in an axial direction is formed in at least the flange portion,

wherein the combustor further comprises:

an adjustment plate which covers the penetrating portion from the downstream side, and

wherein an adjusting penetration portion having an opening area smaller than an opening area of the penetrating portion and communicating with the penetrating portion is formed in the adjustment plate.

2. The combustor according to claim 1 , further comprising:

a plurality of extension tubes each provided on the downstream side of each of the second nozzles and having a tubular shape extending in the axial direction, and arranged at the first intervals in the circumferential direction around the axis,

wherein a position in the circumferential direction where the penetrating portion is provided on the flange portion is between a pair of extension tubes adjacent to each other.

3. The combustor according to claim 1 ,

wherein the penetrating portion includes:

a flange-portion slit extending toward the inside from the outside in the radial direction of the flange portion, and

a cone-portion slit communicating with the flange-portion slit and formed in an area which includes the downstream-side end portion of the cone portion.

4. The combustor according to claim 1 ,

wherein the penetrating portion is a hole which penetrates the flange portion in the axial direction.

5. The combustor according to claim 1 ,

wherein a plurality of penetrating portions including the penetrating portion are formed at second intervals in the circumferential direction around the axis in at least the flange portion.

6. A gas turbine comprising:

a compressor which generates high-pressure air;

the combustor according to claim 1 , which generates a combustion gas by mixing the high-pressure air and the fuel and burning the mixture; and

a turbine which is driven by the combustion gas.