Combined application of passive and active boundary layer aspiration in a transonic compressor rotor for shock wave/boundary layer interaction control

Abstract

Shock wave/boundary layer interaction (SWBLI) is one of the key factors that limits the improvement of aerodynamic performance and stability for supersonic/transonic compressors. In this research, a combined flow control device (CFCD) was designed for controlling SWBLI in the NASA transonic compressor Rotor 35. The original flow fields for Rotor 35 were numerically analyzed first. The results show that the SWBLI is severe, resulting in much flow loss and partly leading to the compressor instability. Based on this phenomenon, the CFCD was designed with a novel three-dimensional passive self-recirculation flow channel and an active suction slot. The flow channel is mounted on the rotor blade suction surface to connect the low- and high-pressure regions ahead of and behind the shock, respectively. The effect of the CFCD on the rotor performance and corresponding working mechanism are then researched as well. With the help of CFCD, the rotor-achieved total pressure ratio (TPR) is maximally increased by 3.0%, and the stall margin (SM) is improved by 4.1% as well. But the rotor isentropic efficiency (IE) considering additional energy expenditure caused by active suction flow has the maximum increment at choke point of 0.27% and highest reduction at near-stall point of 0.54%. The working mechanisms of CFCD include two aspects: one is forming a stable and low-entropy generated lambda shock wave and the other one is reducing the magnitude of flow separation. The dominant mechanism varies with the rotor working condition and depends on whether the leading-edge shock moves upstream of the passive bleed slot.

Effects of Perforated Plates on Shock Structure Alteration for NACA0012 Airfoils

“…12), from lowest to highest, is as follows: A1, 'no control', A2, A5, A3, A4, and A6. According to the literature [14], the introduction of passive control with a perforated plate tends to limit local acceleration, resulting in slightly higher static pressure in the control region compared to the baseline 'no control' case. This effect is also observed in the current study, with the values summarized in Table 2.…”

“…One such study conducted by Genç et al [13] focuses on passive flow control methods for UAVs and MAVs operating at low Reynolds numbers, aiming to address issues related to SWBLI. Another investigation by Zhou et al [14] targets SWBLI in supersonic/transonic compressors, proposing a Combined Flow Control Device (CFCD) to mitigate its effects. By stabilizing shock waves and reducing flow separation, the CFCD enhances rotor performance.…”