期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2016
卷号：5
期号：8
页码：15211
DOI：10.15680/IJIRSET.2016.0508079
出版社：S&S Publications
摘要：The performance of transonic aircraft majorly depends on the compressor rotor blade efficiency andengine weight. To increase rotor blade efficiency flow separation over rotor blade must be prevented and controlled.The aim was to modify and control the flow behaviour over compressor rotor blade by using combination of suctionand blowing boundary layer control method.Rotor blade geometry has been modelled in CATIA V5 and then one suction surface and one blowing surface has beencreated on the blade surface. These geometries have been imported to ANSYS CFX 14.5 for computational simulationand analysis of rotor blade flow with and without boundary layer control technique. Suction slot has been applied at thetrailing edge of the suction surface and blowing slot has been applied at 55% of the blowing surface and shear stresstransport model has been used for computational analysis.Two mass flow rates of 1kg/s and 1.5kg/s have been used here for boundary layer control method and boundary layerseparation effects have been observed and this could be readily seen as the reattachment of velocity vectors whichprevented the flow separation and increment in pressure ratio has been found to be 0.12.
