Numerical Simulation of the Influence of Helicopter Rotor Downwash on Turboshaft Engine Inlet
The influence of the rotor downwash on the turboshaft engine inlet was studied.The numerical simulation of the rotor flow field adopts the method of solving Navier-Stokes equation based on sliding mesh technology,and the method of imposing boundary conditions is adopted for the turboshaft engine simulation.Through the integrated flow field simulation of the inlet and exhaust of the helicopter rotor/airframe/engine,the flow field characteristics of the turboshaft engine inlet under different flight conditions are obtained,and the effect of the rotor downwash on the the total pressure loss coefficient and total pressure distortion index of the turboshaft engine inlet is analyzed.The results show that,compared with the forward flight state and the oblique descent state,the turboshaft engine inlet is most affected by the rotor downwash in the hovering state,and the total pressure distortion index of the inlet is the highest,and the total pressure loss coefficient is the largest;As the downwash speed increases,the total pressure loss coefficient and total pressure distortion index of the inlet also slightly increase,and the performance of the inlet decreases.
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