Advanced Methods for Propulsion System Integration in Aircraft Conceptual Design

Abstract

Significant potentials for the further fuel burn reduction of future transport aircraft are expected from the application of novel propulsion system concepts. Central challenges in utilising these potentials are associated with the engine-airframe integration. In the present thesis, a new methodological approach to a concurrent conceptual design optimisation of advanced propulsion system concepts, the airframe and important mission requirements is presented. The implications of propulsion system design and integration on the conceptual design and performance characteristics of the aircraft are discussed, and, classic aircraft conceptual design methodology is extended through new, detailed design and simulation models. In an aircraft-level design study, the efficiency potentials of advanced propulsion systems featuring ducted and unducted propulsive devices, i.e. turbofan and open rotor engines, are comparatively analysed and evaluated.