Multidisciplinary design optimization of film‐cooled gas turbineblades

Abstract

Design optimization of a gas turbine blade geometry for effective film cooling toreduce the blade temperature has been done using a multiobjective optimization formulation. Three optimization formulations have been used. In the first, the average blade temperature is chosen as the objective function to be minimized. An upper bound constraint has been imposed on the maximum blade temperature. In the second, the maximum blade temperature is chosen as the objective function to be minimized with an upper bound constraint on the average blade temperature. In the third formulation, the blade average and maximum temperatures are chosen as objective functions. Shape optimization is performed using geometric parameters associated with film cooling and blade external shape. A quasi-three-dimensional Navier–Stokes solver for turbomachinery flows is used to solve for the flow field external to the blade with appropriate modifications to incorporate the effect of film cooling. The heat transfer analysis for temperature distribution within the blade is performed by solving the heat diffusion equation using the finite element method. The multiobjective Kreisselmeier–Steinhauser function approach has been used in conjunction with an approximate analysis technique for optimization. The results obtained using both formulations are compared with reference geometry. All three formulations yield significant reductions in blade temperature with the multiobjective formulation yielding largest reduction in blade temperature.

Fluid-Thermal-Structural Coupled Analysis of a Radial Inflow Micro Gas Turbine Using Computational Fluid Dynamics and Computational Solid Mechanics

“…They found that the temperature had a notable effect on the overall stresses in the turbine blades. Other relevant works involving multidisciplinary analysis and optimization design of gas turbines can be found in [17][18][19][20][21].…”

Inverse-design and optimization methods for centrifugal pump impellers

“…They applied their method to the design of both compressor rotor blades and turbine stator blades. Talya et al [65] developed a multi-disciplinary optimization method for film-cooled gas turbines, using a quasi three-dimensional Navier-Stokes method. The cost function was based on the blade temperature and a gradient method was used to find the optimum.…”