TURBINE BLADE AND GAS TURBINE

摘要

Provided are a turbine blade and a gas turbine, wherein the flow rate of a cooling fluid at the inlet of a pin fit area can be improved to improve a cooling capability at the rear edge of the turbine blade. The turbine blade is comprised of a wing profile portion (11); a supply passage (15) which extends in the span direction swithin the wing profile portion (11), and through which a cooling fluid passes; a pin fin massage (18) which extends from the supply passage (15) toward the rear edge (TE) of the wing profile portion (11) along the center line (CL) of the wing profile portion (11), and opens to the outside of the wing profile portion (11) in the rear edge (TE); a plurality of discontinuous pin fins (19) which are projected from a pair of opposed inner walls which define the pin fin passage (18) on the area of the pin fin passage (18) adjacent to the supply passage (15), and define a space extending in the span direction; a pin fin (20) which connects a pair of opposed inner walls to each other on the area of the pin fin passage (18) adjacent to the rear edge (TE); and an insertion portion (22) which is disposed in the space, and reduces the passage area of the cooling fluid in the area of the pin fin massage (18) adjacent to the supply passage (15).