| 摘要 |
A damaged portion of a superalloy material turbine blade body is removed, forming an excavated recess. A repair splice is formed of a same material with similar mechanical structural properties, having a mating outer profile conforming to the corresponding recess profile. The repair splice is inserted and captured within the recess, so that the blade body and repair splice are mechanically interlocked. Given similarities in mechanical properties of both the blade body and the mechanically interlocked splice the repaired blade's overall mechanical structural properties are similar to those of an undamaged blade. The repair splice is affixed to the blade body so that the interlocking respective portions of each do not separate. Localized affixation and subsequent cosmetic blade surface repair can be performed with softer, low temperature application braze and weld alloys.
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