| 摘要 |
<p>The method involves providing vane blanks (12), and joining the vane blanks to a guide vane assembly (10) for a gas turbine. The joined assembly is reprocessed via electro-chemical spark machining and milling. The assembly is reprocessed in a flow mechanical relevant area of the assembly and in transient area (20) between vanes, and the blanks are forged. The blanks are welded together at the assembly. The flow mechanical relevant area is formed by a radial outer lying surface of a covering band section (18), vane blade section (14) and a radial inner lying surface of a vane neck section (16).</p> |
