Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors

摘要: The tip clearance flows of transonic compressor rotors are important because they have a significant impact on rotor and stage performance. A wall-bounded shear layer formed by the relative motion between overtip leakage flow shroud wall is found to major influence development field. This which has not been recognized earlier investigators, impacts stable operating range rotor. Simulation accuracy dependent ability numerical code resolve this layer. While simulations these quite sophisticated, seldom verified through rigorous comparisons measured data kinds measurements rare in detail necessary be useful high-speed machines. In paper we compare tip-clearance details (e.g., trajectory radial extent) with corresponding obtained from simulation. Laser-Doppler Velocimeter (LDV) acquired rotor, NASA Rotor 35, used. field simulated using Navier-Stokes turbomachinery solver that incorporates an advanced k-e turbulence model derived for local equilibrium. simple method presented determining when component