Abstract
Rotor stator interaction (RSI) is an important phenomenon influencing performances in the pump, turbine, and compressor. In this paper, the correlation-based transition model is used to study the RSI phenomenon between a translational cascade of airfoils and a flat plat. A comparison was made between computational results and experimental results. The computational boundary layer velocity is in reasonable agreement with the experimental velocity. The thickness of boundary layer decreases as the RSI frequency increases and it increases as the fluid flows downstream. The spectral plots of velocity fluctuations at leading edge x/c = 2 under RSI partial flow condition f = 20 Hz and f = 30 Hz are dominated by a narrowband component. RSI frequency mainly affects the turbulence intensity in the freestream region. However, it has little influence on the turbulence intensity of boundary layer near the wall. A secondary vortex is induced by the wake–boundary layer interaction and it leads to the formation of a thickened laminar boundary layer. The negative-vorticity wake also facilitates the formation of a thickened boundary layer while the positive-vorticity wake has a similar effect, like a calmed region which makes the boundary layer thinner.
Highlights
Rotor stator interaction (RSI) is a common phenomenon in pumps and turbomachines, especially in the case of multistage compressors
Wissink [26] deliberated the effect of wake turbulence intensity on transition in a compressor cascade by using Direct numerical simulation (DNS), and the results indicated that the separation was intermittently inhibited due to the intense wake reaction as the periodically passing wakes tried to induce turbulent spots upstream of separation point
Layersis made with results obtained from multiple periodic cycles
Summary
Rotor stator interaction (RSI) is a common phenomenon in pumps and turbomachines, especially in the case of multistage compressors. Many works have been carried out to investigate the influence of RSI on energy calculation [1], pressure fluctuation [2], internal fluid flow [3], noise [4], and machine vibration for turbomachines [5]. The unsteady interaction changes the local pressure distribution, the inverse pressure gradient, and viscous effects may lead to the separation of the boundary layer where a back-flow region is generated, which makes the energy loss increase and the efficiency decrease. In order to improve the efficiency and control the blade load, it makes sense to carry out an investigation of the mechanism by which RSI influences the boundary layer and how the boundary layer develops with the interaction
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