Calculation of the forced oscillations of rotor compressor blades at aviation gas-turbine engine, arising from action of circumferential non-uniformity of gas stream

In article approaches to calculation of forced oscillations of rotor axial compressor blades at gas-turbine engines are described. The circumferential non-uniformity of a stream causing forced oscillations of blades is defined by CFD calculation. Modal calculation and calculation of blades forced oscillations in ANSYS program are carried out. Resonance frequencies and tension are defined. Recommendations about decrease of resonance tension level are made.