Integrated　aerodynamic　optimization　for　both　blade　and　non-axisysmmetric　endwalls　of　a　low　aspect　ratio　turbine　vane　is　carried　out,　by　using　a　blade　multidisciplinary　design　optimization　platform　with　an　in-house　code.　The　performance　of　reference　and　optimal　cascades　are　tested　by　blowing　experiment　on　a　subsonic　wind　tunnel.　The　numerical　results　and　experimental　data　for　both　reference　and　optimal　designs　are　in　well　agreement.　Both　numerical　and　experimental　results　indicate　that　aerodynamic　performance　of　the　optimal　design　is　significantly　better　than　that　of　the　reference　design.　Thus　the　correctness　and　effectiveness　of　proposed　design　optimization　method　for　both　blade　and　non-axisymmetric　endwall　is　demonstrated.　©　2016,　Science　Press.　All　right　reserved.