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The aim of this study is to investigate the overall performance (exergetic, exergoeconomic and exergoenvironmental) of CT7-7A turboprop engine manufactured by General Electric Aviation (GE Aviation) and currently used to power CN-235, a medium range transport aircraft. The investigation has been carried out using the thermoeconomic, sustainability and environmental damage cost analysis methods. The adopted turboprop engine has been investigated to observe the behaviour of various performance parameters, sustainability, emission parameters as well as cost parameters of engine. Due to ever increasing demand in air transport systems, focus has been on developing efficient and sustainable systems with lowest possible cost. In order to reduce cost & environmental effects of engine and at same time to acquire higher performance, it is necessary to understand the mechanism that can offer improvements in the engine operating and design parameters so that higher performance can be obtained.

In comparison to other thermal power cycles, gas turbine based energy conversion cycles exhibit superior thermodynamic performance as well as reduced emission. Gas turbine manufacturers and research & development (R&D) organizations are working on modification in basic gas turbine (BGT) cycle, which are intended to improve the basic gas turbine cycle thermodynamic performance and reduce emissions. The present work reports a comparison of thermodynamic performance, NOx and CO emission for basic and intercooled gas turbine (IcGT) cycles. Various cycle operating parameters such as compressor-pressure-ratio (rp,c), combustor-primary-zone-temperature, equivalence-ratio, and residence time of gas turbine based cycles has been examined. IcGT cycle exhibits higher gas turbine specific work and gas turbine efficiency in comparison to BGT cycle for the same rp,c and turbine rotor inlet temperature.