For the intergraded design of support plate and outlet guide vane

where it's difficult to apply the three-dimensional blade design

the secondary flow in the outlet guide vane can be controlled by changing S3 area ratio gradient at the trailing edge. The numerical results of inner flow field and aerodynamics performance of three designs were compared in a 15 stage turbine. The results showed that when the gradient reduced from 001 to -005

the overall total pressure recovery coefficient of the outlet guide vane increased from 0979 to 0991

and the S parameter on 5% span reduced from 0011 to 0005. The back-flow zone on the hub endwall and the suction side of the blade disappeared

and the corner separation was effectively controlled. When gradient reduced from -005 to -010

the flow velocity in the corner zone increased

and at the 5% span

corner blockage lessened

axial velocity density ratio (AVDR) increased

total pressure recovery coefficient increased

yet the S parameter didn't change.