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Optimization of Turbofan Propulsion Cycle Using a Genetic Algorithm

[+] Author Affiliations
Adel Ghenaiet

EMP, Algiers, Algeria

Paper No. GT2010-22420, pp. 595-607; 13 pages
doi:10.1115/GT2010-22420
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 3: Controls, Diagnostics and Instrumentation; Cycle Innovations; Marine
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4398-7 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

This paper presents an evolutionary approach as the optimization framework to design for the optimal performance of a high-bypass unmixed turbofan to match with the power requirements of a commercial aircraft. The parametric analysis had the objective to highlight the effects of the principal design parameters on the propulsive performance in terms of specific fuel consumption and specific thrust. The design optimization procedure based on the genetic algorithm PIKAIA coupled to the developed engine performance analyzer (on-design and off-design) aimed at finding the propulsion cycle parameters minimizing the specific fuel consumption, while meeting the required thrusts in cruise and takeoff and the restrictions of temperatures limits, engine size and weight as well as pollutants emissions. This methodology does not use engine components’ maps and operates on simplifying assumptions which are satisfying the conceptual or early design stages. The predefined requirements and design constraints have resulted in an engine with high mass flow rate, bypass ratio and overall pressure ratio and a moderate turbine inlet temperature. In general, the optimized engine is fairly comparable with available engines of equivalent power range.

Copyright © 2010 by ASME

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