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.