Effects of Rotor-Stator Interaction on Static Aeroelasticity of a Transonic Compressor Blade

In order to research the effects of rotor-stator interaction on static aeroelasticity of a compressor blade, a time domain two-way fluid-structure interaction numerical calculation method was applied to study the deformation process of a 1.5-stage transonic compressor rotor blade under aerodynamic and centrifugal forces, and the characteristic of deformation and its effects on the aerodynamic performance were analyzed in the design condition. The results show that the passage shockwave position and strength are altered due to the blade static deformation, the time-averaged peak efficiency increases by 0.45% compared with cold blade, and the choking flow rate increases by 0.7%, as a result, the aerodynamic characteristic map is shifted to a large mass flow direction. Aerodynamic and centrifugal forces have a major influence on the axial component and circumferential component, the axial spacing shortened between rotor and IGV blade rows can enlarge the unsteady effects, the pressure fluctuation amplitude increases by 12.3% on rotor blade leading edge, the circumferential deformation causes the inlet angle increasing, which changes the static pressure distribution on up half spanwise locations. The high-performance compressor design in industrial practice should consider the effects of blade static aeroelastic deformation on aerodynamic performance.