Gas turbine combustor, manufacturing method for gas turbine and gas turbine combustor

1. A method of manufacturing a gas turbine combustor configured to mix fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supply the generated combustion gas to a turbine, the gas turbine combustor including

an inner cylinder configured to form a combustion chamber thereinside,

an outer cylinder configured to cover the inner cylinder and form, between the outer cylinder and the inner cylinder, an annular outer peripheral flow path through which the compressed air flows,

an end cover configured to close an end of the outer cylinder on a side opposite the turbine,

an air hole plate that is inserted into the inner cylinder from an end cover side of the inner cylinder and that has a plurality of air holes guiding the compressed air that has passed through the outer peripheral flow path, and which has been dammed by the end cover into the combustion chamber,

a plurality of fuel nozzles disposed on the end cover side with respect to the air hole plate so as to each inject the fuel into the combustion chamber through each associated air hole among the plurality of air holes, and

a spring seal provided between the air hole plate and the inner cylinder, the method comprising:

producing a component including a cylindrical portion constituting a part of the inner cylinder, a turn guide provided at an end of the cylindrical portion, on an end cover side of the cylindrical portion, and a plurality of cooling air holes provided in the cylindrical portion; and

joining the component to the end of the inner cylinder after adjusting a length of the inner cylinder such that the plurality of cooling air holes are positioned between a portion of the spring seal which contacts the inner cylinder and a turbine side of the inner cylinder, the turn guide protruding from the inner cylinder such that an interference surface of the turn guide rises from an outer peripheral surface of the inner cylinder toward the outer cylinder and is connected to an inner peripheral surface of the inner cylinder by a curved surface of the turn guide,

wherein the outer peripheral surface extends substantially axially along a longitudinal axis of the inner cylinder, the interference surface extends substantially radially relative to the longitudinal axis of the inner cylinder, and

a plurality of cooling air holes are provided in the inner cylinder along the interference surface of the turn guide, the plurality of cooling air holes being defined in part by the inner cylinder and in part by the interference surface.

2. A gas turbine combustor configured to mix fuel with compressed air guided from a compressor to burn the fuel mixed with the compressed air to generate a combustion gas and supply the generated combustion gas to a turbine, the gas turbine combustor comprising:

an inner cylinder configured to form a combustion chamber thereinside;

an outer cylinder configured to cover the inner cylinder and form, between the outer cylinder and the inner cylinder, an annular outer peripheral flow path through which the compressed air flows;

an end cover configured to close an end of the outer cylinder a side opposite the turbine; and

a turn guide provided at an end of the inner cylinder, on an end cover side of the inner cylinder, an interference surface of the turn guide protruding from an outer peripheral surface of the inner cylinder toward the outer cylinder and connected to an inner peripheral surface of the inner cylinder by a curved surface of the turn guide, wherein

the outer peripheral surface extends substantially axially along a longitudinal axis of the inner cylinder, the interference surface extends substantially radially relative to the longitudinal axis of the inner cylinder, and

a plurality of cooling air holes are provided in the inner cylinder along the interference surface of the turn guide, the plurality of cooling air holes being defined in part by the inner cylinder and in part by the interference surface.

3. The gas turbine combustor according to claim 2 , further comprising:

an air hole plate that is inserted into the inner cylinder from the end cover side and that has a plurality of air holes configured to guide the compressed air that has passed through the outer peripheral flow path, and which has been dammed by the end cover into the combustion chamber; and

a plurality of fuel nozzles disposed on the end cover side with respect to the air hole plate so as to each inject the fuel into the combustion chamber through each associated air hole among the plurality of air holes.

4. The gas turbine combustor according to claim 3 , further comprising:

a spring seal provided between the air hole plate and the inner cylinder, wherein the plurality of cooling air holes are located at a first position between a portion of the spring seal which contacts the inner cylinder and a turbine side of the inner cylinder.

5. The gas turbine combustor according to claim 4 , wherein a part of the turn guide is located at the first position.

6. The gas turbine combustor according to claim 2 , further comprising:

a turn vane disposed between the turn guide and the end cover.

7. The gas turbine combustor according to claim 2 , further comprising:

a plurality of straightening guides arranged side by side in a circumferential direction on the outer peripheral surface of the inner cylinder.

8. The gas turbine combustor according to claim 2 , wherein

a distance from the outer peripheral surface of the inner cylinder to an outer peripheral surface of the turn guide varies.

9. A gas turbine comprising:

a compressor air and the compressed air;

the gas turbine combustor according to claim 2 , the combustor being configured to mix fuel with the compressed air guided from the compressor and being configured to burn the fuel mixed with the compressed air to generate a combustion gas; and

a turbine configured to be driven by the combustion gas generated by the gas turbine combustor.