| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a means for preventing damage of an inner wall surface in a cooling passage by a laser beam penetrating through a gas turbine member when cooling holes are formed by laser working to the gas turbine member having acute corner part, rib and the like in the cooling passage. <P>SOLUTION: In a method for manufacturing the gas turbine member for forming the cooling holes 14 for introducing a cooling gas to the surface 11a of a turbine stationary blade 10 to the turbine stationary blade 10 having the cooling passage in which the cooling gas is circulated in its inner part by the laser working, the laser working is performed in such a state that an extendable and contractive structure body 17 which can absorb the laser beam L and with which at least a part of the cooling passage is filled is disposed in the cooling passage. <P>COPYRIGHT: (C)2012,JPO&INPIT |
