Parametric modeling and multidisciplinary design optimization for cooling turbine blade

A multidisciplinary design optimization system for gas turbine blade, which involves structure, aerodynamic, heat transfer, vibration and service life, etc, has been developed, serving the purpose of multidisciplinary design optimization of single-hole thin wall cooling blade. A parametric modeling method was also proposed for single-hole thin wall cooling blade. The blade surface geometry is defined by five-order polynomials, while 3-D coupling analysis was made for aerodynamic and heat transfer. The average temperature and maximum temperature of blade volume were optimized, with aerodynamic, vibration and service life as the constraints. A combined algorithm of annealing simulation and SQP (Sequential Quadratic Programming) was used to optimize the blade parameters. While the flow rate of cooling air was kept unchanged, the cooling effect was improved and the performance requirement on the blade materials was reduced.