Thesis (Ph.D.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering

A design tool is developed for the preliminary design of transonic compressors using experimental correlations to predict the shock losses, profile losses, deviation angle and the design incidence. The developed tool is used to compute an initial geometry for the numerical simulations. The off design operation of the design shape produced by the preliminary method is performed using the computational fluid dynamics. Then, the design of a transonic fan is optimized using the numerical simulation of the compressible-viscous flow equations and simplex optimization algorithm. The blade geometry is defined in terms of set of geometric groups describing the section chord, stagger angle, staking position, the section thickness and camber distributions. A tip injection flow control technology is applied on the optimized transonic fan rotor in order to enhance the rotor stability parameters

Issued also as CD