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Abstract

This article presents a methodology to design for optimal performance of turboprop engines matching the power requirements for propeller-driven aircrafts. First, the flight performance analyses were used to assess the relatively significant constraints, and then identify the feasible design space and the ideal design point by adopting KSOPT optimizing technique. Second, a multi-objective deterministic algorithm modified method of feasible direction was used for the Pareto approach optimization of the propulsion cycle for three configurations of turboprops. In this optimization problem the maximum specific power and the minimum power specific fuel consumption are the principal figures of merit. The obtained results were based on a created model from the published data of a particular aircraft. This methodology used in the preliminary design phase has shown its effectiveness in rapidly searching for the ideal match point and identifying a candidate turboprop engine, as well as in the development of a derivative engine.

Keywords

turboprop engines flight performance constraints diagram minimum power requirement multi-objective optimization Pareto front propulsion cycle engine performance

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Minimum power requirement for a propeller-driven aircraft and optimum cycle parameters of turboprop engines

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