Development of a method for destroying the rotor blades of a high-pressure compressor at a given frequentation of rotation

The design of gas turbine engines (GTE) is inextricably linked with a large amount of work on numerical modeling. With the help of numerical modeling, it is possible to predict the behavior of the part when the engine is operating in various modes. In addition, when modeling, it is possible to predict modes, design load, conditions for engineering tests. This paper presents an approach to modeling an engineering test for the breakage of the rotor blade (RB) of a high-pressure compressor (HPC) to confirm the impenetrability of the housing. By calculation, the amount of cutting of the RB HPC for breakage at a given rotor speed is determined. The approach is to implement a combination of two factors: 1) the calculation of the blade strength using the deformation criterion prevented the blade breakage at a lower rotational speed, with the necessary maintenance of operation in the design mode close to the ultimate strength; 2) computational and experimental work to determine the resonance allowed to increase the variable component of stresses for blade breakage at a given frequentation of rotation. It was also possible to model the direction of crack growth numerically.