| 摘要 |
PURPOSE:To reduce thermeal stress to be occurred inside a blade and to contrive improvement of reliability of a heat shielding coating, by forming thickness of a coated layer so that a coefficient of heat transmission becomes even, in a cooling blade of a turbine. CONSTITUTION:A heat resistant alloy metal blade 40 taking the thickness distribution tc of heat shielding coating into consideration is prepared through either precision casting or forging. Thickness of a coated layer 60 is formed on the surface of its profile 41 so that a coefficient of heat transfer is adjusted to the coefficient of heat transfer alphaq70 of a high temperature gas side and a coefficient of heat transmission becomes even, and a profile 63 is made so that it is made into a designed aerodynamical profile. In this manner, thermal stress to be occurred inside a blade can be reduced, reliability of the heat shielding coating is improved and a life of the blade can be made longer as a thermal load distribution on the surface of a cooling blade can be made even. |
