Gas turbine combustor

A gas turbine combustor comprising:

• a tubular body that defines a combustion chamber, extends from a first side to a second side in an axial direction, and defines a discharge port located at the second side in the axial direction;
• an air passage through which air is supplied to the combustion chamber;
• a straightening plate;
• and
• at least one resonator including
• at least one opening that is open toward the air passage and
• a resonance chamber that communicates with the opening, wherein:
• the air passage includes
• an upstream region that extends along an outer peripheral surface of the tubular body,
• a downstream region that extends along an inner peripheral surface of the tubular body, is located at the first side of the combustion chamber in the axial direction, and communicates with the combustion chamber, and
• a direction change region that connects the upstream region to the downstream region in a radial direction of the tubular body and is adjacent to the upstream region such that an area of a section of the air passage which is orthogonal to the axial direction changes at a position between the upstream region and the direction change region;
• the opening of the resonator is open toward a space of the air passage which is located downstream of the upstream region;
• the at least one resonator comprises a first resonator located at the tubular body and including an outer peripheral surface extending in a circumferential direction extending circumferentially around an axis of the tubular body;
• and
• the opening of the first resonator is open toward the downstream region of the air passage;
• the straightening plate is annular such that a circumference of the straightening plate is adjacent to the tubular body and
• the outer peripheral surface of the first resonator is located, in the radial direction, outside a portion of the outer peripheral surface of the tubular body which is adjacent to the first resonator in the axial direction.