Focusing on the transient state of aviation turbine engines components

a method based on dynamic boundaries and a two-way fluid-structure interaction(FSI) method were used to calculate the acceleration process of the transonic compressor NASA Rotor 67.The curve of the compressor transient process considering the blade deformation was calculated

and the influences of the aeroelastic deformation of the blade on the aerodynamic parameters during the acceleration process and the shock wave structure and evolution process in the flow field were studied.And the deformation distribution of the blade in acceleration process under unsteady aerodynamic load and centrifugal load was also studied.The results showed that: with the increase of the rotational speed

the influence of the blade deformation on the total pressure ratio parameter and the total temperature ratio parameter was more obvious.The structure and evolution of the shock wave in the flow path when considering blade deformation were slightly different with those without blade deformation in the acceleration process of the transonic compressor.The transient load caused the gradual increase of blade deformation during the acceleration process.The blade deformation was mainly concentrated in the upper half of the blade

and mainly caused by centrifugal load

which was dominated by bending deformation

and caused the torsion phenomenon at the leading edge of the tip to cause change of aerodynamic performance.