Gas turbine combustor

A gas turbine combustor comprising:

• a plurality of transition ducts of the gas turbine combustor through which high-temperature combustion gas flows;
• a plurality of aft frames that are placed along a circumferential direction on a downstream side of the respective transition ducts, and connected to an upstream side of a gas turbine, each of the plurality of aft frames including at least one floating seal that seals a first gap between the respective aft frame of the plurality of aft frames and the gas turbine in at least one of inner and outer peripheries of the respective aft frame, and a side seal that seals a second gap between aft frames adjacent to each other in the circumferential direction;
• and
• a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, and is configured to seal air flowing from at least the gap portion into a gas turbine side, and the corner seal is configured to be separately independent of the at least one floating seal and the side seal and the corner seal is fixed to one of the aft frames adjacent to each other in the circumferential direction by welding;
• wherein the corner seal includes at least two shoulder seals, and the at least two shoulder seals are placed opposite to each other in the circumferential direction of the corner portion of each of the aft frames adjacent to each other in the circumferential direction and are fixed respectively to each of the aft frames adjacent to each other in the circumferential direction by welding, and the side seal, extending radially between the aft frames adjacent to each other across the at least two shoulder seals, is placed between the at least two shoulder seals placed opposite to each other in the circumferential direction of the corner portion of each of the aft frames adjacent to each other;
• wherein a first shoulder seal of the at least two shoulder seals placed opposite to each other in the circumferential direction of the corner portion of each of the aft frames adjacent to each other includes a block formed in a T-shape by a straight portion extending in a radial direction and a horizontal portion extending from an end of the straight portion in the circumferential direction, and a fixing portion that fixes the block to the corner portion of the respective aft frame,
• surfaces of the straight portion and the horizontal portion of the T-shape of the block on the gas turbine side are formed in a planar portion, and
• the block includes a first block having a first continuous thickness from the planar portion and formed in a curved shape at an outermost circumferential side on an opposite side of the horizontal portion of the T-shape of the block formed in a plane to the gas turbine side, and a second block formed in a square pillar having a second continuous thickness from the planar portion on an opposite side of the straight portion of the T-shape of the block formed in the plane to the gas turbine side.