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The impact of blade untwist on transonic high-bypass-ratio fan performance was studied by using an in-house blade deformation code based on fluid-structure coupling algorithm in which nonlinear effect of unsteady aerodynamic loads were considered.Firstly,the blade shape with centrifugal loads was calculated using ANSYS finite element code starting from the manufacture blade shape (“cold” blade).Secondly,blade running shapes (“hot” blade) under different aerodynamic conditions were worked out through the deformation code.Finally,aerodynamic characteristic lines of the fan obtained with blade running shapes and the fixed design blade shape respectively were generated.The results show that blade untwist determined by aerodynamic loads has effects on the fan aerodynamic performance.The displacements caused by centrifugal and aerodynamic loads counteract each other more or less depending on operation conditions.Blade untwist angles were calculated for different aerodynamic conditions which lead to some changes in stagger angles.Mass flow rate at choke point for the “hot” blade shape is 4kg/s less than that for the design blade shape,and in opposite stall mass flow rate is 2 kg/s more than that for the design shape.