Optimisation Techniques Applied to the Design of Gas Turbine Blades Cooling Systems

Abstract

This paper addresses the methodology used to design the layout of the tip cooling nozzles of a high pressure rotor blade turbine. The methodology used is through a complete CAE approach, by means of a parametric CFD model which is run several times for the exploration of several designs by an optimizer. Hence the design is carried out automatically by parallel computations, with the optimization algorithms taking the decisions rather than the design engineer. The engineer instead takes decision regarding the physical settings of the CFD model to employ, the number and the extension of the geometrical parameters of the blade tip holes and the optimization algorithms to be employed. From CFD validation the final design of the tip cooling geometry found by the optimizer has proved to be better than the base design, which used mean values of all input parameters, and than the design proposed by an experienced heat transfer AVIO engineer, who used standard best practice methods. Furthermore the large number of experiences gained by the simulations run by the optimizer allowed the designer to find laws, functions and correlation between input parameters and performance output, with a further and deeper insight on this specific design problem.

Impact of Aerodynamic Performance by the Heat Value of Fuel Change on the Turbine Cascade of Ground Heavy Duty Gas Turbine

“…In order to study the impact to the ground heavy duty gas turbine performance of heat value changes, this paper conducts onedimensional and quasi-three-dimensional calculation on the GE 9FA, a preliminary analysis of the fuel heat value changes in flow rate changes on turbine design. Turbine design has basically established a complete design system [6][7][8][9][10][11][12][13][14][15] , the establishment of F-class turbine technology for the middle and low heat value fuel, turbine parts design is a very important part. The purpose of this study, refer to the general F-class turbine aerodynamic design experience, to discuss gas turbine design on how to choose one dimensional, quasi threedimensional parameters, and optimized, so as to provide cascade reference to the engineering design.…”

Application of evaluationary approach to thermo-mechanical optimization of gas turbine airfoil cooling configuration

“…The results showed large potential hidden in a cooling system; appropriate size and location of channels had a great influence on the coolant usage, thermal stress level and in consequence lifetime of the component. Bucchieri et al [1] presented a paper dealing with optimization of the tip cooling holes of a gas turbine rotor blade. The design process aimed to find such a configuration of cooling passages which provided, on one hand the minimum coolant usage and wall heat flux and, on the other, maximum blade efficiency.…”