According to the thermeset coupling analysis and approach of turbine blade optimization based on genetic-finite element method
an optimization design method about the integration of thermeset of turbine cooling blade was persented.By modeling the rotor blade of gas engine turbine
the influence of the position
shape(circle and rectanglar)
size and number of cooling holes on thermal stress and cooling effect of turbine blade were investigated.It is proved that the developed method can effectively reduce the stress of turbine blade
and rectangular cooling hole has more cooling effect and smaller stress
the higher temperature of blade is decreased with the increase of size and number
Synthetical optimization design of rotor airfoil by genetic algorithm
Optimization design of shroud configuration of transporter based on surrogate model
Aerodynamic optimization method for duct design
Optimization design of spiral bevel gear's dynamic characteristics based on genetic algorithm
Optimization design of crystallographic orientation in single crystal turbine blade
Related Author
WANG Qing
ZHAO Qi-jun
MA Yang
WANG Dan-dan
YANG Tao
FENG Zhi-wei
ZHANG Qing-bin
YE Kun
Related Institution
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics
College of Aerospace Science and Engineering, National University of Defense Technology
Beijing Institute of Astronautical Systems Engineering, China Academy of Launch Vehicle Technology
School of Aeronautics, Northwestern Polytechnical University
School of Mechanical Engineering,Northwestern Polytechnical University