Aero-engine blade fault analysis control method

Abstract

The invention discloses an aero-engine blade fault analysis control method. The method comprises the following steps that a data set of engine blades is obtained; according to the size data of the shoulder of the fault-free engine, determining the distribution numbers of the normal distribution center u value of the width of the shoulder of the fault-free engine and the shoulder size x in the interval f (-sigma-+ sigma), f (x > + sigma) and f (x <-sigma), and determining the upper limit value, the middle limit value and the lower limit value of the shoulder size; the shoulder size data of the blades machined in the same batch are obtained, and the shoulder size data of the blades machined in the same batch are detected and analyzed according to the distribution numbers of the shoulder size x in the interval f (-sigma-+ sigma), f (x > + sigma) and f (x <-sigma) and the upper limit value, the middle limit value and the lower limit value of the shoulder size. Quality detection in the repairing process can be achieved, and the malposition and lap joint fault risks of the engine shoulder blade in the using process are reduced.

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