Effects of Blade Deformation on the Aerodynamic Performance and Hot-to-Cold Transformation Method of a Counter-Rotating Compressor
To clarify the effect of blade deformation on the aerodynamic performance of a highly loaded counter-rotating compressor,a thermal-fluid-structure interaction method is used to analyze the character of the blade deformation and the variation mechanism of aerodynamic performance under centrifugal,aerodynamic,and thermal loads.Additionally,a method for hot-to-cold trans-formation is developed.The results show that the leading edges of the low-pressure rotor deform towards the suction sides,whereas the leading edges of the high-pressure rotor deform towards the pressure sides.This leads to the operating point of the low-pressure rotor moving to the stall bound-ary,and results in the reduction of choke mass flow and peak efficiency of the compressor.By using nonlinear static analysis with inverse solving,the cold blade profile can be generated to achieve the aerodynamic performance of the design point without the need for deformation reverse interpolation and iterative correction.
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