| 摘要 |
A turbine blade for a gas turbine mounted to a rotor disk comprising: a support structure comprising a base defining a curved root of said blade and a framework extending radially outwardly from said base; a skin coupled to said support structure framework, said framework and said skin defining a curved airfoil of said blade; and at least one curved platform section located adjacent to said airfoil and coupled to said rotor disk. |
