Technological residual deformations calculating for aviation parts subjected to shot peeneng strenghtening

Ensuring the geometric accuracy of critical parts is an actual problem for aviation industry enterprises. The blades of gas turbine engines are particularly critical and technologically complex parts. In most cases, the interlocks of the blades, as well as the blade, are subjected to surface shot peening. Residual stresses are the first cause of the appearance of technological residual deformations. It is the residual deformations caused by the action of residual stresses that in most cases are the cause of critical defects of parts. Thus, the development of scientifically based approaches to modeling residual stresses and calculating technological residual deformations is an actual task. The paper presents an approach that allows at the stage of machining to take into account the deformations that can be obtained at the final stages of manufacturing parts after shot peening strengthening. The approach is based on preliminary computational prediction of technological residual deformations from the action of residual stresses based on analytical and finite element methods. The implementation of the approach is shown on the example of a compressor blade of a gas turbine engine, subjected to hardening by shot peening over the entire surface of the part.