Turbine blade, turbine including same turbine blade, and gas turbine including same turbine

A turbine for generating driving force to be used for generation of electric power by passing a combustion gas supplied from a combustor, the turbine comprising:

• a turbine casing in which the combustion gas flows;
• and
• a turbine rotor rotatable inside the turbine casing, the turbine rotor including a plurality of turbine disks and a plurality of turbine blades coupled to an outer surface of each of the plurality of turbine disks, wherein a turbine blade of the plurality of turbine blades comprises:
• an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the trailing-edge portion including first and second sides opposing each other and forming an open end linked to the leading-edge portion and a closed end having a streamlined shape, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion;
• a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas;
• and
• a generally U-shaped barrier wall portion configured to prevent formation of a gap between the open end of the trailing-edge portion and either of a first side surface of the leading-edge portion and a second side surface of the leading-edge portion, the generally U-shaped barrier wall portion comprising:
• a first wall having an upstream portion exposed to the combustion gas and protruding axially from the first side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a first distal end and inner and outer surfaces joined at the first distal end, the outer surface of the first wall configured to contact an inside surface of the first side of the trailing-edge portion;
• and
• a second wall having an upstream portion exposed to the combustion gas and protruding axially from the second side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a second distal end and inner and outer surfaces joined at the second distal end, the outer surface of the second wall configured to contact an inside surface of the second side of the trailing-edge portion.

A gas turbine comprising:

• a compressor to produce compressed air by taking in air and compressing the intake air;
• a combustor to produce combustion gas by burning a mixture of fuel and the compressed air supplied from the compressor;
• and
• a turbine rotatable by the combustion gas supplied from the combustor, the turbine comprising:
• a turbine casing in which the combustion gas flows;
• and
• a turbine rotor rotatable inside the turbine casing, the turbine rotor including a plurality of turbine disks and a plurality of turbine blades coupled to an outer surface of each of the plurality of turbine disks,
• wherein a turbine blade of the plurality of turbine blades comprises an airfoil including as separate bodies a trailing-edge portion and a leading-edge portion being linked to the trailing-edge portion and disposed upstream of the trailing-edge portion, the trailing-edge portion including first and second sides opposing each other and forming an open end linked to the leading-edge portion and a closed end having a streamlined shape, the leading-edge portion including a front surface arranged on an upstream side of the leading-edge portion;
• a rotary unit connected to the leading-edge portion and configured to rotate the leading-edge portion according to an inflow angle of the combustion gas such that the front surface faces a flow of the combustion gas;
• and
• a generally U-shaped barrier wall portion configured to prevent formation of a gap between the open end of the trailing-edge portion and either of a first side surface of the leading-edge portion and a second side surface of the leading-edge portion, the generally U-shaped barrier wall portion comprising:
• a first wall having an upstream portion exposed to the combustion gas and protruding axially from the first side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a first distal end and inner and outer surfaces joined at the first distal end, the outer surface of the first wall configured to contact an inside surface of the first side of the trailing-edge portion;
• and
• a second wall having an upstream portion exposed to the combustion gas and protruding axially from the second side surface of the leading-edge portion toward the open end of the trailing-edge portion and including a second distal end and inner and outer surfaces joined at the second distal end, the outer surface of the second wall configured to contact an inside surface of the second side of the trailing-edge portion.