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    Application of exergetic analysis to inverted Brayton cycle engine at different flight conditions
    (Pergamon-Elsevier Science Ltd, 2023) Karabacak, Mustafa; Kirmizi, Mehmet; Aygun, Hakan; Turan, Onder
    The aviation sector has continued to be modernized by overcoming technological challenges involving strict constraints for mission requirements. In this context, the great attention to newly proposed methods which the requirements satisfied has been drawn in the related aviation field. As a novelty, performance and exergy analyses of inverted Brayton cycle engine (IBCE) are investigated at supersonic speed (2.5 M) by comparing it with a conventional afterburning turbojet engine (CATE) in this study. Moreover, exergy analysis is performed solely for the IBCE at 5 M where only the IBCE could generate thrust. According to performance findings, specific fuel consumption (SFC) of the CATE changes from 57.97 g/kNs and 71.72 g/kNs whereas it raises from 51.76 g/kNs and 56.57 g/kNs for the IBCE due to variation of turbine inlet temperature (TIT) and afterburner exit temperature (AET) at 2.5 M. Also, thermal efficiency of the CATE varies approximately between 32.97% and 46.73% while that of IBCE changes between 50.72% and 58.43% for IBCE at 2.5 M. At hypersonic speed, SFC of the IBCE is measured to vary between 71.34 g/kN and 85.49 g/kN at 5 of Mach. Lastly, the exergy efficiency of IBCE changes between 23.73% and 27.70% at same conditions. Where the higher TIT leads to lowering it whereas the higher AET provides increment of exergy efficiency. This study shows that thanks to cycle change, gas turbine engines could provide more advantages for new generation aircraft compared with conventional ones.
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    Engine weight estimation of fifth generation fighter aircraft for high range and manoeuvrability
    (Inderscience Enterprises Ltd, 2020) Karabacak, Mustafa; Turan, Onder
    This study focuses on afterburner turbofan engine weight estimation for fifth generation fighter aircrafts. Model developed in this study by investigating 26 engine cases categorised by the criteria the requirement of selection amongst to engines expected to be used in fifth generation fighter depend on four parameters with approximate to +/- 25% error. Technology level effect engine weight strongly so parameter reflect technology level is determined based on new technology engines used in fifth generation fighter aircraft by statistical method. Model reflect technology level is expected to be used in conceptual design stages of fifth generation fighter engine.
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    Turbofan engine weight estimation for preliminary design
    (Inderscience Enterprises Ltd, 2019) Karabacak, Mustafa; Turan, Onder
    The aim of the study is to prepare weight estimation model of turbofan engines to help designer in the conceptual stages of modem turbofan design. To achieve this purpose, statistical data is used on yielding robust analytical expression and experiments are conducted to prepare model for turbofan engine weight estimation is not easy due to the high cost and insufficient technical facility. Turbofan engine classified into five categories (three shaft turbofan engine, light weight two shaft turbofan engine, medium weight two shaft turbofan engine, high weight two shaft turbofan engine and two shaft geared turbofan engine) and turbofan engine weight model is developed for each category separately to increase model sensitivity. Model sensitivity is investigated for each category by error analysis to give idea about model reflection of real world to conceptual designer.
  • Küçük Resim Yok
    Öğe
    Turbofan engine weight estimation for preliminary design
    (Inderscience Enterprises Ltd, 2019) Karabacak, Mustafa; Turan, Onder
    The aim of the study is to prepare weight estimation model of turbofan engines to help designer in the conceptual stages of modem turbofan design. To achieve this purpose, statistical data is used on yielding robust analytical expression and experiments are conducted to prepare model for turbofan engine weight estimation is not easy due to the high cost and insufficient technical facility. Turbofan engine classified into five categories (three shaft turbofan engine, light weight two shaft turbofan engine, medium weight two shaft turbofan engine, high weight two shaft turbofan engine and two shaft geared turbofan engine) and turbofan engine weight model is developed for each category separately to increase model sensitivity. Model sensitivity is investigated for each category by error analysis to give idea about model reflection of real world to conceptual designer.