Session: 31-13 Flow Control

Paper Number: 128721

128721 - Mechanism Study of Stator Suction Slots to Inhibit the Boundary Layer Separation in a Single-Stage Axial Flow Compressor 

Abstract: High-loaded compressor have become an important development in the field of compressor design and flow control. During the operation of a high-loaded compressor, there is a high probability of flow phenomena in which the boundary layer separates at the leading edge of the blades. For the flow phenomenon of boundary layer separation that occurs at the leading edge of the blade, this paper took the transonic single-stage axial compressor NASA Stage35 as the research object and set three Suction-Slots with different axial positions on the stator, to investigate the effect of different axial positions on the boundary layer separation. Numerical calculation results point out that the different Suction-Slot schemes improve the compressor total performance under small and medium mass flow rate conditions. The scheme with double Suction-Slot located at 15% Ca and 50% Ca increasing the compressor efficiency by 1.8% at near-stall conditions. The flow field analysis shows that at 99% blade span, the Suction-Slot directly opposite the center of the separation vortex plays a key role in suppressing the boundary layer separation and eliminating the low-velocity fluids. This is because suction in this position requires minimal angle deflection of the airflow to complete and the airflow can easily enter the Suction-Slot. However, there is an increase in the thickness of the boundary layer at the lower blade span, which is because the Suction-Slot redistributes the distribution of the mass flow rate along the radial direction, the mass flow rate in the lower blade span is reduced, and the angle of attack is increased.

Presenting Author: Hao Wang School of Power and Energy, Northwestern Polytechnical University

Presenting Author Biography: Wang Hao, a master's student at School of Power and Energy, Northwestern Polytechnical University, engaged in turbomachinery aerothermodynamics related research.

Authors:

Haoguang Zhang School of Power and Energy, Northwestern Polytechnical University
Hao Wang School of Power and Energy, Northwestern Polytechnical University
Yiming Feng School of Power and Energy, Northwestern Polytechnical University
Jinhang Xiao School of Power and Energy, Northwestern Polytechnical University
Wuli Chu School of Power and Energy, Northwestern Polytechnical University