Aeroacoustic Simulation for NASA CC3 Centrifugal Compressor Operating at off Design Condition

¹ Mechanical and Industrial Engineering Department Collage of Engineering, Qatar University, Doha (2713), Qatar
² Mechanical Engineering Department, Shoubra faculty of Engineering, Benha University, Egypt
³ Mechanical Engineering Department, UBC-University of British Columbia, Vancouver, BC, Canada
⁴ Mechanical Engineering Department, the French University in Egypt, Al-Shorouk City, New Cairo

Abstract

This paper covers the characterization of the acoustic noise and the unsteady flow field of a high speed centrifugal compressor NASA CC3. In order to accurately predict the noise, all analyses are carried out through the use of Large Eddy Simulation and Ffowcs Williams–Hawkings model for noise prediction. The relative effect of hub cavity on flow characteristics and sound levels is investigated, for a compressor stage with a total pressure ratio equal to 4, working from surge to near choke condition. In comparison with the experimental results from literature, the predicted compressor performance and flow field are predicted well. The hub cavity flow effect on the compressor aeroacoustic generated noise is shown in the paper. The unsteady static pressure and sound pressure levels are compared not only at different location but also for design and off design operating points. The internal flow results inside the hub cavity are presented at surge, design and near choke points. The conclusion is that the cavity effect of the centrifugal compressor cannot be ignored in the numerical prediction of aerodynamic generated noise. The impeller back plate of the rotor experiences a strong pressure fluctuation, which is maxima at the impeller outer radius for all operating point, but higher pressure values at the surge point.