Multidisciplinary design and optimisation of conceptual rotorcraft powerplants for operational performance and environmental impact

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[1] Ali, F.

[2] Tzanidakis, K.

[3] Goulos, I.

[4] Pachidis, V.

[5] D'Ippolito, R.

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| 1600年 / Royal Aeronautical Society卷 / 119期

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This paper demonstrates the application of an integrated rotorcraft multidisciplinary design and optimisation framework; deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for rotorcraft applications. The proposed approach comprises a wide-range of individual modelling theories applicable to rotorcraft flight dynamics; gas turbine engine performance and weight estimation as well as a physics-based stirred reactor model; for the rapid estimation of various gas turbine gaseous emissions. A single-objective Particle Swarm Optimiser is coupled with the aforementioned rotorcraft design framework. The overall methodology is deployed for the design and optimisation of a reference multipurpose Twin-Engine-Light civil rotorcraft; modelled after the Bo105 helicopter; which employs two Rolls-Royce Allison 250-C20B turboshaft engines. Through the implementation of a single-objective optimisation strategy; notionally based optimum engine design configurations are acquired in terms of engine weight; mission fuel burn and mission gaseous emissions inventory at constant technology level. The acquired optimum regenerative engine configurations are subsequently deployed for the design of conceptual rotorcraft regenerative engine configurations; targeting improved mission fuel economy; enhanced payload-range capability as well as overall environmental impact; while maintaining the respective rotorcraft airworthiness requirements. The proposed methodology essentially constitutes as an enabler for designing rotorcraft powerplants within realistic; three-dimensional operations and towards realising their associated design trade-offs at mission level. © 2015; Royal Aeronautical Society. All rights reserved;

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