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Abstract

This article presents a Pareto approach to design for the optimal performance of four configurations of turboprop engines matching the power requirements of a class of propeller-driven aircrafts. In these bi-objective optimizations of the thermal cycle parameters, the power-specific fuel consumption is minimized and the specific power is maximized while maintaining the power levels and limiting the temperature of the power turbine blades. For this purpose, a multi-objective evolutionary optimization algorithm called non-dominated sorting genetic algorithm is used. To avoid engine performance deterioration and constraint violation at extreme operating conditions, the objective functions and constraints are evaluated at both design and off-design conditions. The trade-off surfaces representing the sets of alternative solutions are obtained based on the Pareto optimality. By considering additional subjective criteria, three design points are proposed for each engine configuration.

Keywords

turboprop propulsion cycle performance bi-objective optimization Pareto front non-dominated sorting genetic algorithm

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Optimizations of turboprop engines using the non-dominated sorting genetic algorithm

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