A turbine blade includes cooling passages formed inside the blade and extending in a blade height direction, blade surfaces on a suction side and a pressure side being covered with thermal barrier coating, a design point on a suction side being set on the blade surface on the suction side of each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, and to a position in front of and not including a tailing end of a final cooling passage. Thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.
1. A turbine blade comprising:
at least one cooling passage that is formed in the blade and extends in a blade height direction, wherein the at least one cooling passage comprises a final cooling passage that is closest to a blade trailing edge, and the final cooling passage communicates with a trailing edge discharge passage which is adapted to discharge air that has flowed through the final cooling passage,
wherein blade surfaces on a suction side and a pressure side are covered with thermal barrier coating,
wherein a design point on the suction side is set on the blade surface on the suction side in each blade section perpendicular to the blade height direction within a range from a position on a back side of and including a throat position, at which a distance between turbine blades is a global minimum, to a position in front of and not including a position of a tailing end of the final cooling passage, and
wherein thickness distribution of the thermal barrier coating on the suction side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from a blade leading edge to the design point and gradually reduces from the design point toward the back side up to the blade trailing edge.
2. The turbine blade according to claim 1 , further comprising:
at least one array of film cooling holes on the suction side, which are formed in the blade surface and the thermal barrier coating on the suction side and communicate with the cooling passage,
wherein film cooling holes on the suction side in a final array that is the closest to the blade trailing edge among the at least one array of film cooling holes on the suction side are present within the range from a position on the back side of and including the throat position, and to a position in front of and not including the position of the tailing end of the final cooling passage, and
wherein the design point is set within a range from a position on the back side of and including the position of the film cooling holes on the suction side in the final array, and to a position in front of and not including the position of the tailing end of the final cooling passage on the blade surface on the suction side in each blade section.
3. The turbine blade according to claim 1 ,
wherein a design point on the pressure side is set so as to be symmetric with the design point on the suction side with respect to a camber line as an axis of symmetry on the blade surface on the pressure side in each blade section, and
wherein thickness distribution of the thermal barrier coating on the pressure side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from the blade leading edge to the design point on the pressure side and gradually reduces from the design point on the pressure side toward the back side up to the blade trailing edge.
4. The turbine blade according to claim 1 ,
wherein thickness distribution of the thermal barrier coating on the pressure side of each blade section is configured such that a thickness of the thermal barrier coating is uniform from the blade leading edge to the blade trailing edge.