A coupled EulerianLagrangian method based on Nav i erStokes equation and freewake model is established for impulsive airloadi ngs prediction during interaction. The noise prediction is based on the wellknown FWH equation for acoustic pressure. By the method, aiming at the noise abatem e nt, a parametric study is performed to examine the effects of blade geometry parameters such as sweeptback,sweepforward,taper and anhedr al tip on bladevortex interaction(BVI) noise of AH1/OLS rotor. The results i ndicate that the BVI noise c an be reduced by the blade geometry of anhedral tip and sweepforward, while the blade geometry (i.e. taper and sweepback) adopted by helicopter widely has fini te influence on the reduction of BVI noise even the unfavourable infl uence.