This paper presents an integrated approach targeting the multidisciplinary design of optimum powerplant configurations for rotorcraft at mission level. A single-objective and multiobjective particle swarm optimizer is coupled with a comprehensive rotorcraft mission analysis code. The combined approach is applied for the design and optimization of a reference twin-engine light civil rotorcraft modeled after the Bo105 configuration, manufactured by Airbus Helicopters. Through the implementation of a single-objective optimization strategy, optimum engine design configurations are acquired in terms of mission fuel consumption, engine weight, and gaseous emissions at constant technology level. Multiobjective optimization analyses are carried out to quantify the optimum interrelationship between mission fuel consumption and gaseous emissions. The acquired optimum thermodynamic cycles are subsequently deployed for the design of conceptual regenerative engines for rotorcraft, targeting improved mission fuel economy, enhanced payload-range capability, as well as reduced environmental impact.
Nomenclature
EWengine weight, kg FF mean mean fuel flow, kg/s T Comp compressor delivery temperature, K T Exhaust exhaust air temperature, K T out heat exchanger outlet temperature, K W engine design point mass flow, kg/s AUM i delta initial all-up-mass, % NO x delta nitrogen oxides, % SAR delta specific air range, %