| 摘要 |
<p>The invention relates to a method for producing a gas turbine rotor comprising integral hollow blades, said method containing the following steps: a) provision of an in particular disc-type base body (10) for the gas turbine rotor; b) processing of the base body on its outer surface to produce several protuberances that are distributed around the circumference and form connection zones (12) for hollow blades. Said protruding connection zones (12) define a respective partial contour of a cavity (17) of the hollow blade that is to be connected to the respective connection zone; c) creation of vane contours for the hollow blades on the respective connection zones (12) of the latter by laser powder welding; d) machining of the created vane contours to provide blade surfaces that satisfy the demands of flow technology.</p> |
