Session: 31-02 Transonic Flow

Paper Number: 126225

126225 - Investigation on the Interaction of Tip Leakage Flow/ Shock Wave/ Boundary Layer in a Transonic Compressor Stage 

The performance of transonic compressor blades is significantly influenced by the interaction among blade tip leakage flow, shockwaves, and boundary layers at their tips. In this study, a numerical investigation was conducted on a transonic compressor stage with and without shrouded rotor blades. Key factors affecting rotor tip performance were identified, including tip leakage flow/shock wave interaction and shock wave/boundary layer interaction. Observations also indicated that tip leakage flow played a mitigating role in reducing flow separation. Based on these findings, a design approach involving part-shrouded rotor blades was proposed. The optimal shrouded region of the rotor extends from the leading edge to slightly upstream the location of shock wave under near stall condition. Controlling the location of the tip leakage flow mitigates the interaction between tip leakage flow and shock waves, as well as the flow separation resulting from shock wave/boundary layer interactions, thus improving the stage performance. The 20% shrouded rotors exhibits an improvement in stall margin by 1.24% without any efficiency loss.

Title: Investigation on the Interaction of Tip Leakage Flow/ Shock Wave/ Boundary Layer in a Transonic Compressor Stage

Keywords: Tip leakage flow; Shock wave; Shock wave/boundary layer interaction; transonic compressor.

Presenting Author: Jianci Ma Tsinghua University

Presenting Author Biography: Jianci Ma received the B.S. degree in Flight Vehicle Design & Engineering from Beijing Institute of Technology, Beijing, China, in 2018 and the M.S. degree in Aeronautical and Astronautical Science and Technology from Beijing Institute of Technology, Beijing, China, in 2021. He is currently working toward the Ph.D. degree in Aeronautical and Astronautical Science and Technology with the Institute for Aeroengine, Tsinghua University, Beijing, China. His research interests include axial flow fan/compressor design and flow control.

Authors:

Jianci Ma Tsinghua University
Jiabin Li Tsinghua University
Lucheng Ji Tsinghua University