A new multidisciplinary design optimization procedure, integrating aerodynamic, heat transfer, modal and structural design criteria along with various mechanical and geometric constraints, has been developed for the design of turbomachinery blades. The Kreisselmeier-Steinhauser (K-S) function approach is used to efficiently integrate the multiple objective functions and constraints.; Two types of blade models have been considered. For both the blade models external cooling is enabled through film cooling ports on the surface of the blade. The first blade model is a two-dimensional (2-D) blade in which the airfoil surface is represented using cubic splines. For the 2-D airfoil, two types of internal coolant passages have been studied. In the first type, the internal passages are elliptically shaped, whereas the second type uses trapezoidal shaped passages. A thin layer Navier-Stokes solver is used for the external flow calculations. The blade interior temperatures are evaluated using the finite element method. The multiobjective optimization procedure is used to maximize kinetic energy efficiency and minimize total pressure loss, average temperature, and maximum temperature of the blade.; The second blade model that is considered is a three-dimensional (3-D) blade. The blade is divided into numerous spanwise sections and each section is represented as a Bezier-Bernstein polynomial. Trapezoidal shaped internal coolant passages are used for internal cooling. A 3-D Navier-Stokes solver is used to evaluate the external flow field, and the finite element procedure is used at each spanwise section to obtain the blade interior temperature distribution. The structural and modal analyses of the blade are performed using the ANSYS software. The blade average and maximum temperatures at each spanwise section and the blade weight are minimized. Numerical results are presented showing significant improvements, after optimization, compared to reference designs.; A continuous sensitivity analysis procedure has been developed for calculating aerodynamic design sensitivities for high speed wing body configurations. The procedure has been developed in conjunction with a parabolized Navier Stokes (PNS) solver, UPS3D. Representative results compare well with those obtained using the finite element approach and the Automatic Differentiation In FORtran (ADIFOR) software and establish the computational efficiency and accuracy of the continuous procedure.
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