The present paper focuses on the methods to consistently compare conventional aircraft gas turbine engines with novel hybrid energy propulsion systems and electric energy propulsion systems. In advance, the limitation of thermal-based figures of merit for the evaluation of hybrid energy conversion processes was identified. Subsequently, existing exergy analysis methods served as the basis for the development of unified propulsion system metrics in order to allow for both the consideration of different energy sources for the conversion process as well as the integration into existing aircraft propulsion performance metrics. Therefore, the inner efficiency definition (a.k.a. thermal efficiency) was adjusted to a loss-based representation accounting for the unavailability of the supplied energy, the loss due to transfer of energy into the system, system-internal energy transfer losses, as well as exhaust residual losses. Based on this, two efficiency definitions were introduced: the energy availability efficiency and the energy conversion efficiency. The requirement for a clear distinction between both properties in order to consistently analyze a combustion-based and hybrid energy-based system is an important outcome of the present work. Finally, the unified applicability and comparability of the introduced performance metrics has been successfully demonstrated for a conventional turbofan, a parallel-hybrid turbofan, a novel integrated hybrid turbofan concept, and an entirely electrical fan concept.
Unified applicable propulsion system performance metrics
Transactions of the ASME, Journal of Engineering for Gas Turbines and Power ; 135 , 11 ; 111201/1-111201/9
2013
9 Seiten, 6 Bilder, 3 Tabellen, 22 Quellen
Aufsatz (Zeitschrift)
Englisch
Unified Applicable Propulsion System Performance Metrics
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