Exergy analysis of an experimental turbomachine used in missiles

In this study, an exergy analysis of an experimental TRS18 turbojet engine was carried out in Anadolu University Aeronautics and Astronautics Faculty Test Laboratory. While unmeasured engine performance values are calculated together with the experimental data of the engine, then exergy analysis parameters and exergetic-sustainability values are calculated with thermodynamic relations. In the tests conducted, the thrust of the experimental turbojet engine was measured as 1320 N, the air and fuel flow measured as 2.27 kg / s and 0.042 kg / s, respectively. At the end of the study, the exergy efficiency for the compressor, combustion chamber and turbine were calculated as 91 %, 60.4 % and 77 %, respectively, which is 42 % for the TRS18 turbojet engine. The exergetic performance of the engine was also calculated according to the parameters of improvement exergy potential ratio, productivity lack ratio, fuel depletion ratio, relative exergy destruction, fuel / product exergy factors and relative irreversibility parameters for the combustion chamber, compressor and turbine. Furthermore exergetic-sustainability analysis of the engine was carried out using five parameters: waste exergy ratio, exergy recoverable rate, exergy destruction factor, environmental effect factor and exergetic sustainability index. By the results of this study, it was possible to calculate the location and magnitude of the irreversibilities of the TRS18 experimental missile engine under the actual operating conditions of the components. In the future, it is considered to decrease the energy losses and improve the performance in design works of the related missile engine class with the aid of this work.