Exergo-economic analysis of off-design a target drone engine for reconnaissance mission flight

Abstract

Nowadays, small-size turbojet engines play a significant role on various military and civil missions. In this study, exergoeconomic analysis of TRS-18 turbojet engine was conducted for nine flight phases. First aim is to find out differences between exergoeconomic behaviour of the components originated from their both irreversibility and purchase costs. The second objective is to reveal effects of flight phases on exergoeconomic performance of TRS-18 and its components by employing several exergoeconomic indicators regarding the TRS18. These indicators are exergy destruction cost, relative cost difference, exergoeconomic factor and specific thrust cost. To estimate cost-ineffective components of TRS-18 engine, component-based exergoeconomic assessment was carried out for each mission. Based on results of exergoeconomic analysis for the whole TRS-18 engine, specific thrust cost of the TRS-18 was found at relatively high values ranging 398.2 and 422.04 $/h.kN at loiter III and IV phases where the engine operates at partial power whereas taxi-out, take-off and landing (TTL) phases have the relatively low specific thrust cost values ranging 159.53 and 166 $/h.kN. Moreover, exergoeconomic factor of the whole TRS-18 was found as relatively low values with approximately 21% at TTL phases. Considering component-based results, the lowest exergoeconomic factor, ranging from 25% to 40%, belongs to combustor, whereas gas turbine has relatively high exergoeconomic factor, varying from 89% to 92%. Finally, for the combustor, exergy destruction cost was determined at the relatively highest rates for whole flight phases. It changes between 35.74 $/h at loiter-II phase and 69.79 $/h at take-off. It is thought this study can help in finding cost-effective flight phases by means of comprehending the nature of the relationship between flight phases and the corresponding exergoeconomic parameters. Also, off-design exergo-economy obtained with this paper may be applied to the other gas turbine engines.