导叶非均匀布局对气动激励的影响

A key technique for reducing the aerodynamic excitation of downstream rotor blades is the asymmetry layout of inlet guide vanes. The half and half layout divided can be defined in terms of both the number of blades and the vane spacing. This study derives a theoretical solution to aerodynamic excitation with half and half layout and compares the two design schemes’ differences. We compare the aerodynamic excitation properties under two asymmetry schemes using a 1.5-stage compressor as an example, examine the spectral properties of the aerodynamic forces on the rotor blade surface, investigate the relationship between the excitation properties and the vane spacing, and identify the frequency separation mechanism of the aerodynamic excitation for half and half layout. The findings demonstrate that altering the guide vane row’s vane spacing causes the aerodynamic excitation to be frequency divided, the amplitude distribution of the aerodynamic response of rotor blades is affected by the propagation law of aerodynamic excitation, and that the spatial distribution and frequency domain characteristics of the pneumatic excitation differ between the two asymmetry schemes.