The effects of modeling design on compressor aerodynamic noise were studied by numerical method

the calculation results of the three-dimensional flow field indicated that the modeling designed compressors and the original model satisfied the similarity criterion

and the relative error of the global performance parameters were less than 2%. The analysis of compressor flow structure further confirmed that the flow field of the modeling designed compressor was similar to that of the original model. The compressor aerodynamic noise was investigated by a hybrid computational aero-acoustic method

which combined unsteady Reynolds averaged Navier-Stokes equations and boundary element method. The results showed that the compressor aerodynamic noise was mainly composed of discrete tones and broadband noise

and the discrete tones dominated in the spectrum. The total sound pressure level of modeling designed compressor gradually reduced with the decreasing scale factor

the peaks of modeling designed compressor discrete tones were slightly lower than those of the original model

but the broadband noise was greatly enlarged. Compressor aerodynamic noise showed obvious acoustic directivity in the inlet duct nozzle

the sound pressure amplitude and directivity of the modeling designed compressor was weaker than the original model

and the trend was proportional to the scale factor.