Gas Turbine Combuster
A gas turbine combustor with a relatively simple structure is configured to attenuate pressure fluctuation owing to combustion oscillation while securing mechanical reliability. The gas turbine combustor includes a combustion liner that forms a combustion chamber for generating combustion gas, a combustion casing disposed at an outer circumferential side of the combustion liner, and a burner for supplying air flowing between the combustion liner and the combustion casing, and fuel to be supplied from a fuel supply system to the combustion chamber. The combustor further includes a vane disposed at the outer circumferential side of the combustion liner, a plurality of supports disposed at an inner side of the combustion casing for fixing the vane, and a pressure dynamics damping hole formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.
1 . A gas turbine combustor including a combustion liner that forms a combustion chamber for generating combustion gas, a combustion casing disposed at an outer circumferential side of the combustion liner, and a burner for supplying air flowing between the combustion liner and the combustion casing, and fuel to be supplied from a fuel supply system to the combustion chamber, the gas turbine combustor comprising:
a vane disposed at the outer circumferential side of the combustion liner;
a plurality of supports disposed at an inner side of the combustion casing for fixing the vane; and
a pressure dynamics damping hole formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.
2 . The gas turbine combustor according to claim 1 , wherein the support has a streamlined cross section.
3 . The gas turbine combustor according to claim 1 , wherein gaps formed between the outer circumferential surface of the combustion liner and an inner circumferential surface of the vane are made different from each other in a circumferential direction of the combustion liner.
4 . The gas turbine combustor according to claim 1 , wherein a gap formed between the outer circumferential surface of the combustion liner and an inner circumferential surface of the vane at one side of the support is different from a gap formed between the outer circumferential surface of the combustion liner and the inner circumferential surface of the vane at the other side of the support.
5 . The gas turbine combustor according to claim 4 , wherein four pieces of the supports are disposed at equal intervals at the inner side of the combustion casing.
6 . A gas turbine combustor including a combustion liner that forms a combustion chamber for generating combustion gas, a combustion casing disposed at an outer circumferential side of the combustion liner, and a burner for supplying air flowing between the combustion liner and the combustion casing, and fuel to be supplied from a fuel supply system to the combustion chamber, the gas turbine combustor comprising:
a flow sleeve disposed at the outer circumferential side of the combustion liner; and
a pressure dynamics damping hole formed in the combustion liner at a position corresponding to the flow sleeve for communication with the combustion chamber.
7 . The gas turbine combustor according to claim 6 , further comprising a rib formed as an annular member at the outer circumferential side of the combustion liner downstream from the pressure dynamics damping hole.