Rotor having improved structure, and turbine and gas turbine including the same

A turbine through which flows a combustion gas supplied from a combustor and which is cooled by compressed air supplied from a compressor, the turbine comprising:

• a stator that includes a casing and a vane installed on an inner surface of the casing;
• and
• a rotor installed in the casing and rotated by the flow of combustion gas and cooled by the compressed air, the rotor comprising:
• a disk having an outer circumferential surface;
• a platform installed on the outer circumferential surface of the disk;
• and
• a blade airfoil formed on an upper surface of the platform, the blade airfoil having an airfoil end situated opposite to the platform, the airfoil end having an upstream side and a downstream side with respect to a flow direction of the combustion gas,
• wherein the blade airfoil is formed so that the downstream side of the airfoil end is closer to the inner surface of the casing than the upstream side of the airfoil end.

A gas turbine comprising:

• a compressor that sucks and compresses air;
• a combustor that produces a combustion gas by burning fuel and the compressed air;
• and
• a turbine that generates power by passing the combustion gas and includes
• a stator that includes a casing and a vane installed on an inner surface of the casing;
• and
• a rotor installed in the casing and rotated by the combustion gas and cooled by the compressed air, the rotor comprising a disk having an outer circumferential surface;
• a platform installed on the outer circumferential surface of the disk;
• and a blade airfoil formed on an upper surface of the platform, the blade airfoil having an airfoil end situated opposite to the platform, the airfoil end having an upstream side and a downstream side with respect to a flow direction of the combustion gas, wherein the blade airfoil is formed so that the downstream side of the airfoil end is closer to the inner surface of the casing than the upstream side of the airfoil end.