Bh. Dennis et al., Optimization of turbomachinery airfoils with a genetic/sequential-quadratic-programming algorithm, J PROPUL P, 17(5), 2001, pp. 1123-1128
The objective of this aerodynamic shape design effort is to minimize total
pressure loss across the two-dimensional linear-airfoil cascade row while s
atisfying a number of constraints. They included fixed axial chord, total t
orque, inlet and exit flow angles, and blade cross-section area, while main
taining thickness distribution greater than a minimum specified value. The
aerodynamic shape optimization can be performed by using any available flow
field analysis code. For the analysis of the performance of intermediate ca
scade shapes, we used an unstructured-grid-based compressible Navier-Stokes
flowfield analysis code with a k-epsilon turbulence model. A robust geneti
c optimization algorithm was used for optimization, and a constrained seque
ntial quadratic programming was used for enforcement of certain constraints
. The airfoil geometry was parameterized using conic section parameters and
B-splines, thus keeping the number of geometric design variables to a mini
mum while achieving a high degree of geometric flexibility and robustness.
Significant reductions of the total pressure loss were achieved using this
constrained method for a supersonic exit flow axial turbine cascade.