Combustor of gas turbine

A combustor of a gas turbine, the combustor comprising:

• a combustion chamber;
• a swirler including an outer peripheral surface and an injection port directed to the combustion chamber;
• a bulkhead fitted to the outer peripheral surface of the swirler;
• a panel located outside the swirler in a radial direction of the swirler so as to cover the bulkhead from the combustion chamber while being spaced apart from the outer peripheral surface of the swirler in the radial direction by a radial gap and spaced apart from the bulkhead in an axial direction of the swirler by an axial gap, a coefficient of thermal expansion of the panel being smaller than each of a coefficient of thermal expansion of the swirler and a coefficient of thermal expansion of the bulkhead;
• and
• a seal ring that is fitted to the outer peripheral surface of the swirler in the axial gap and is in contact with the panel in the axial direction, wherein:
• the bulkhead includes a cooling air hole that is open toward the axial gap;
• and
• the panel includes a cooling air hole which is located outside the seal ring in the radial direction, is open to the axial gap, and makes the axial gap communicate with the combustion chamber.