Optimal design and control of gas‐turbine engine components: a multicriteria approach

Abstract

Discusses a new approach to solving optimal designing and control problems in aircraft gas‐turbine engine components. This approach is a combination of optimal designing problems with optimal control problems, allowing the formation of a single problem of optimal designing of controllable systems. The solving of this problem would involve simultaneous optimization of both design parameters and control laws. Allows the making of technically correct and substantiated decisions, taking into consideration several efficiency criteria for gas‐turbine engine components; a specific feature being the determination of a set of competitive optimal solutions in terms of different efficiency criteria values. Demonstrates the effectiveness of this approach by an example of multicriteria design optimization of a controllable axial flow compressor. Presents the results of a search of compressor blade rows geometrical parameters sets and of compressor stator blades control laws which are Edgeworth‐Pareto optimal for four operating modes. Shows a possibility of increasing compressor efficiency considerably by choosing the most preferable design parameters set and implementing in airborne digital control system a number of control laws optimal for different operating modes.

Citation

Egorov, I.N., Kretinin, G.V. and Leshchenko, I.A. (1997), "Optimal design and control of gas‐turbine engine components: a multicriteria approach", Aircraft Engineering and Aerospace Technology, Vol. 69 No. 6, pp. 518-526. https://doi.org/10.1108/00022669710185977