Aerodynamic optimization of high-pressure turbine blades based on radial basis function deformation method

Aiming at the issues of numerous optimization design variables and slow optimization efficiency in turbine aerodynamic optimization, this paper proposes a turbine blade geometric deformation method based on radial basis function (RBF) interpolation. The method establishes the mapping relationship between control points and the spatial positions of blade geometric vertices through RBF interpolation, enabling three-dimensional geometric deformation of turbine blades by adjusting control points. This effectively reduces the number of optimization variables. Meanwhile, a response surface metamodel is constructed, and the sequential quadratic programming (SLSQP) algorithm is employed to optimize the aerodynamic performance. The results show that after optimization, the total pressure loss coefficient of the turbine guide vane is reduced by 11.2%, with the flow rate variation within 2%. The secondary flow vortex structure on the suction surface of the blade is suppressed, and the flow loss on the suction surface of the guide vane is effectively reduced. The optimization method combining geometric deformation and response surface modeling not only reduces the number of optimization variables and computational samples for turbine blades but also improves optimization efficiency, enabling rapid full three-dimensional optimization design of turbine blades.