Gas turbine combustor structure

A gas turbine combustor structure disposed to penetrate a casing of a gas turbine from a direction perpendicular to an axial direction of a turbine rotor of the gas turbine, the gas turbine combustor structure comprising:

• a plurality of combustors;
• a rear liner which is constituted by a cylinder body provided in a direction perpendicular to the axial direction of the turbine rotor on a downstream side of the plurality of combustors, and gathers a combustion gas discharged from the plurality of combustors and guides the combustion gas to a downstream side;
• and
• a scroll which is connected to a downstream end of the rear liner, and guides the combustion gas discharged from the rear liner in the axial direction of the turbine rotor and guides the combustion gas in a circumferential direction of the turbine rotor, wherein each combustor of the plurality of combustors comprises:
• a combustor liner in a cylindrical shape, which combusts fuel and an oxidant;
• a fuel supply part which is provided at an upstream end of the combustor liner, and supplies the fuel into the combustor liner;
• an oxidant supply part which is provided in an annular shape around the fuel supply part, and supplies a swirling flow of the oxidant into the combustor liner;
• and
• an opposite swirl imparting part which is disposed at an outlet of the combustor liner, and imparts a swirl in an opposite direction to a swirling direction of the swirling flow of the oxidant.

A gas turbine combustor structure disposed to penetrate a casing of a gas turbine from a direction perpendicular to an axial direction of a turbine rotor of the gas turbine, the gas turbine combustor structure comprising:

• a combustor casing;
• a plurality of combustors arranged in the combustor casing;
• a rear liner which is constituted by a cylinder body provided in a direction perpendicular to the axial direction of the turbine rotor on a downstream side of the plurality of combustors, and gathers a combustion gas discharged from the plurality of combustors and guides the combustion gas to a downstream side;
• a scroll which is connected to a downstream end of the rear liner, and guides the combustion gas discharged from the rear liner in the axial direction of the turbine rotor and guides the combustion gas in a circumferential direction of the turbine rotor;
• a cooling medium supply part which supplies a cooling medium into the combustor casing;
• and
• a swirling flow introducing part which imparts a swirl to the cooling medium supplied into the combustor casing and introduces the cooling medium into the rear liner wherein:
• each combustor of the plurality of combustors comprises:
• a combustor liner in a cylindrical shape, which combusts fuel and an oxidant;
• a fuel supply part which is provided at an upstream end of the combustor liner, and supplies the fuel into the combustor liner;
• and
• an oxidant supply part which is provided in an annular shape around the fuel supply part, and supplies a swirling flow of the oxidant into the combustor liner, wherein a swirling direction of a swirling flow caused by the cooling medium introduced from the swirling flow introducing part is an opposite direction to a swirling direction of the swirling flow of the oxidant.