Gas turbine combustor

1. A gas turbine combustor comprising:

a combustor basket in which combustion gas flows, the combustion gas being produced by combustion of fuel injected from at least one nozzle; and

a plurality of acoustic liners each including a housing mounted on an outer surface of the combustor basket, the housings of the plurality of the acoustic liners being separate from each other so that each of the housings together with the outer surface of the combustor basket forms an individual resonance space for each of the acoustic liners,

wherein each housing is mounted to an outer surface of a diverging portion of the combustor basket,

wherein the plurality of the acoustic liners includes:

a first acoustic liner disposed on an upstreammost side in terms of a flow direction of the combustion gas; and

a second acoustic liner for damping combustion oscillation of a frequency higher than the first acoustic liner, the second acoustic liner being mounted on the outer surface of the combustor basket so as to be disposed on a downstream side from the first acoustic liner in a flow of the combustion gas,

wherein the individual resonance space of each of the acoustic liners communicates with an interior space of the combustor basket via at least one acoustic hole formed through the combustor basket.

2. The gas turbine combustor according to claim 1 ,

wherein the first and second acoustic liners are disposed in a flat region of the outer surface of the combustion basket, and

wherein a relationship of h 1 >h 2 is satisfied, where h 1 is a height of the resonance space of the first acoustic liner defined by a maximum distance between an interior surface of the housing of the first acoustic liner and the flat region of the outer surface, and h 2 is a height of the resonance space of the second acoustic liner defined by a maximum distance between an interior surface of the housing of the second acoustic liner and the flat region of the outer surface.

3. The gas turbine combustor according to claim 1 ,

wherein the at least one nozzle includes a pilot nozzle arranged on a center axis of the combustor basket and a plurality of main nozzles arranged on an outer circumference of the pilot nozzle, and

wherein a relationship of 0.8≦L 2 /D 2 ≦1.1 is established where D 2 is a diameter of the combustor basket at a mounting position of the second acoustic liner and L 2 is a distance between a downstream end of a main-nozzle external cylinder surrounding the main nozzle and the mounting position of the second acoustic liner.

4. The gas turbine combustor according to claim 1 ,

wherein the housing of each of the first and second acoustic liners has a purging hole for introducing compressed air from outside of the combustor basket into the resonance space of said each of the first and second acoustic liners.

5. The gas turbine combustor according to claim 1 , further comprising:

a transition piece for introducing the combustion gas produced in the combustor basket to a turbine, the transition piece being arranged so that an upstream end of the transition piece overlaps an outer periphery of a downstream end of the combustor basket,

wherein the second acoustic liner is disposed in an area where the downstream end of the combustor basket and the upstream end of the transition piece overlaps with each other.

6. The gas turbine combustor according to claim 1 , wherein the plurality of the acoustic liners are disposed so that the shorter a distance between a mount position of each of the acoustic liners and a down-stream end of the gas turbine combustor is, the higher the frequency of the combustion oscillation each of the acoustic liners is configured to damp is.

7. A gas turbine combustor comprising:

a combustor basket in which combustion gas flows, the combustion gas being produced by combustion of fuel injected from at least one nozzle; and

a first resonance device; and

a second resonance device for damping combustion oscillation of a frequency higher than the first resonance device, the second resonance device being mounted on the outer surface of the combustor basket so as to be disposed on a downstream side from the first resonance device in a flow of the combustion gas,

wherein the first resonance device and the second resonance device are acoustic liners each having a housing mounted to the outer surface of the combustor basket, and

wherein a resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket,

wherein the gas turbine combustor further comprising:

a transition piece for introducing the combustion gas produced in the combustor basket to a turbine, the transition piece being arranged so that an upstream end of the transition piece overlaps an outer periphery of a downstream end of the combustor basket;

a spring clip for connecting the upstream end of the transition piece and the downstream end of the combustor basket to each other by elastic force; and

a baggy clip for pressing the spring clip toward the upstream end of the transition piece,

wherein the second resonance device is housed in a space surrounded by the baggy clip and the outer surface of the downstream end of the combustor basket.

8. The gas turbine combustor according to claim 7 ,

wherein a height of the resonance space of the second resonance device is lower than a height of the resonance space of the first resonance device.

9. A gas turbine combustor comprising:

a combustor basket in which combustion gas flows, the combustion gas being produced by combustion of fuel injected from at least one nozzle; and

a first resonance device; and

a second resonance device for damping combustion oscillation of a frequency higher than the first resonance device, the second resonance device being mounted on the outer surface of the combustor basket so as to be disposed on a downstream side from the first resonance device in a flow of the combustion gas,

wherein the first resonance device and the second resonance device are acoustic liners each having a housing mounted to the outer surface of the combustor basket, and

wherein a resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket,

wherein a relationship of 0.05≦W 2 /D 2 ≦0.3 is established where D 2 is a diameter of the combustor basket at a mounting position of the second resonance device and W 2 is a width of the resonance space of the second resonance device in a longitudinal direction of the combustor basket.

10. A gas turbine combustor comprising:

a combustor basket in which combustion gas flows, the combustion gas being produced by combustion of fuel injected from at least one nozzle; and

a first resonance device; and

a second resonance device for damping combustion oscillation of a frequency higher than the first resonance device, the second resonance device being mounted on the outer surface of the combustor basket so as to be disposed on a downstream side from the first resonance device in a flow of the combustion gas,

wherein the first resonance device and the second resonance device are acoustic liners each having a housing mounted to the outer surface of the combustor basket, and

wherein a resonance space surrounded by the housing and the outer surface of the combustor basket communicates with an interior space of the combustor basket via a plurality of acoustic holes formed in the combustor basket,

wherein a relationship of 0.005≦h 2 /d 2 ≦0.02 is established where d 2 is a diameter of the combustor basket at a mounting position of the second resonance device and h 2 is a height of the resonance space of the second resonance device.