| 摘要 |
<p>A blade assembly, for example, for a gas turbine engine, is produced by mounting blades 42 e.g. turbine blades on a rotor 40 in a number of radial stages. Sacrificial supports 58 are then placed on the blades 42. Guide vanes 46 e.g. stators, are then placed on the sacrificial supports 58. The rotor 40 is then introduced into a casing 44, and the guide vanes 46 are connected to the casing 44. Upon initial rotation of the rotor 40, the sacrificial supports 58 break up and are ejected.</p> |
