Combustor for gas turbine engine
A combustor for a gas turbine engine that is placed in a compressed air chamber of the gas turbine engine to generate combustion gas, the combustor being provided with a liner that defines a combustion chamber therein around a prescribed central axis, the liner comprising a plurality of raised wall portions that extends in a circumferential direction at an angle with respect to the central axis and are arranged at predetermined intervals along the central axis, a plurality of cooling air holes passed through the raised wall portions, and thick wall portions provided circumferentially in parts of the raised wall portions at ends of the cooling air holes.
1 . A combustor for a gas turbine engine that is placed in a compressed air chamber of the gas turbine engine to generate combustion gas, the combustor being provided with a liner that defines a combustion chamber therein around a prescribed central axis, the liner comprising:
a plurality of raised wall portions that extends in a circumferential direction at an angle with respect to the central axis and are arranged at predetermined intervals along the central axis;
a plurality of cooling air holes passed through each of the raised wall portions at a predetermined interval in the circumferential direction; and
thick wall portions provided in parts of each of the raised wall portions at ends of the cooling air holes such that each thick wall portion is formed around an outer periphery of an end of a corresponding one of the cooling air holes,
wherein the thick wall portions are provided at inlets and/or outlets of the cooling air holes, and
the thick wall portions are individually formed in an arcuate shape at the inlets and/or outlets of the cooling air holes such that a recess is defined between each pair of the thick wall portions adjacent to each other in the circumferential direction.
2 . The combustor for a gas turbine engine according to claim 1 , wherein the cooling air holes each include a flared portion that flares from a side of the compressed air chamber to a side of the combustion chamber.
3 . The combustor for a gas turbine engine according to claim 2 , wherein the flared portions are progressively enlarged in a circumferential direction from a side of the compressed air chamber to a side of the combustion chamber.
4 . The combustor for a gas turbine engine according to claim 2 , wherein the flared portions have a trapezoidal cross-sectional shape with a long side thereof located on a radially outer side.
5 . The combustor for a gas turbine engine according to claim 2 , wherein the flared portions have a triangular cross-sectional shape with a base thereof located on a radially outer side.
6 . The combustor for a gas turbine engine according to claim 1 , wherein the liner further includes inclined wall portions that are inclined radially inward along the central axis with respect to a flow direction of the combustion gas so as to alternate with the raised wall portion along the central axis.
7 . The combustor for a gas turbine engine according to claim 6 , wherein the liner further includes cylindrical wall portions that are substantially less inclined than the inclined wall portions and each positioned between one of the raised wall portions and the adjoining inclined wall portion on an upstream side or a downstream side thereof.