Influence of inlet Reynolds number and turbulent intensity on the flow mechanism in compressor profiles
To address the problem of decreased aerodynamic performance of unmanned aerial vehicle engine compres-sors at high altitudes,the V103 subsonic compressor blade profile is selected for a numerical study.This study inves-tigates the effects of different inflow turbulence levels(Tu=1%,3%,5%,6%,7.5%,10%)on the internal flow characteristics of the compressor cascade under three Reynolds numbers(Re=1.5×105,4.5×105,1.2×106).The re-lationship between flow separation and transition and the variation in blade profile loss caused by these factors are an-alyzed.The results indicate that when the turbulent intensity remains constant,the length of the separation bubble in-creases with a decrease in the Reynolds number,while the position of the separation point remains unchanged.When the Reynolds number remains constant,the laminar separation point moves forward as the inlet turbulent intensity de-creases.This phenomenon becomes more pronounced under low Reynolds number conditions.When the inlet turbu-lent intensity increases,the separation bubble on the blade surface disappears,but the loss continues to increase.Under different Reynolds number conditions,there exists an inflow turbulence corresponding to the minimum profile loss,and this turbulence increases slightly as the Reynolds number decreases.This paper provides theoretical guid-ance for modifying the compressor profile loss model at low Reynolds numbers and developing a numerical model to predict the compressor's performance at high altitudes with low Reynolds numbers.
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维普
