Power System Analysis of an Aero-Engine

Abstract

The aim of this study is analyzed in detail for better understanding of energy and power of an aero-engine. In this regard, this study presents energy equations were applied to the turbofan engine components. The engine has a thrust range of 82 to 109 kN. It consists of fan, axial low pressure compressor (LPC), axial high pressure compressor (HPC), an annular combustion chamber, high-pressure turbine (HPT) and low pressure turbine (LPT). The results show that power of the engine flow approaches a maximum value to be 82.85 MW in the combustor outlet, while minimum power is observed at LPC inlet with the value of 1.37 MW. Furthermore, important parameters of the engine are also analyzed from reverse-engineering method. It is expected that results of this study will be beneficial of power, cogeneration and aero-propulsive generation systems in similar environment.

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Turan, O. and Aydin, H. (2015) Power System Analysis of an Aero-Engine. Journal of Power and Energy Engineering, 3, 443-448. doi: 10.4236/jpee.2015.34060.

Conflicts of Interest

The authors declare no conflicts of interest.

References

[1] Gohardani, A., Georgios, S. and Doulgeris, R.S. (2010) Challenges of Future Aircraft Propulsion: A Review of Distributed Propulsion Technology and Its Potential Application for the All-Electric Commercial Aircraft. Progress in Aer-ospace Sciences, 47, 369-391. http://dx.doi.org/10.1016/j.paerosci.2010.09.001
[2] IPCC (1999) IPCC Special Report on Aviation and the Global Atmosphere. Intergovernmental Panel on Climate Change.
[3] Aylesworth, J.H. (1996) Global Atmospheric Effects of Aviation: A Policy Perspective. Aerospace Industries Association of Ameri-ca.
[4] Greene, D.L. (1995) Commercial Air Transport Energy Use and Emissions: Is Technology Enough? Conference on Sustainable Transportation—Energy Strategies.
[5] Enviro (2011) http:// www.enviro.aero/Content/Upload/File/BeginnersGuide_Biofuels_Web
[6] Peeters, P.M., Middel, J. and Hoolhorst, A. (2005) Fuel Efficiency of Commercial Aircraft: An Overview of Historical and Future Trends. NLR-CR-2005-669.
[7] MIT (2011) http://web.mit.edu/airlines/analysis/analysis_airline_industry.html
[8] http://www.pw.utc.com/Home
[9] Balkan, F., Colak, N. and Hepbasli, A. (2005) Performance Evaluation of a Triple Effect Evaporator with Forward Feed Using Exergy Analysis. International Journal of Energy Research, 29, 455-470. http://dx.doi.org/10.1002/er.1074
[10] Dincer, I., Hussain, M. and Al-Zaharnah, I. (2004) Energy and Exergy Use in Public and Private Sector of Saudi Arabia. Energy Policy, 32, 1615-1624. http://dx.doi.org/10.1016/S0301-4215(03)00132-0
[11] http://www.gknaerospaceenginesystems.com/aero/global/en-gb/products/Engine%20components/commercial_engines/Pages/pw6000.aspx
[12] Edwards, C.F. (2004) Development of Low-Irreversibility Engines. Energy Research at Stanford Report, 36.
[13] Koroneos, C., Dompros, A., Roumbas, G. and Moussiopoulos, N. (2005) Advantages of Use of Hydrogen Fuel as Compared to Kerosene. Resources, Conservation and Recycling, 44, 99-113. http://dx.doi.org/10.1016/j.resconrec.2004.09.004
[14] Wall, G. (2003) Exergy Tools. Proceedings Institution of Me-chanical Engineering, 125-136.
[15] El-Sayed, A.F. (2008) Aircraft Propulsion and Gas Turbine Engines. CRC Press, UK.
[16] Ayd?n, H., Turan, O., Hikmet Karakoc, T. and Midilli, A. (2014) Sustainability Assessment of PW6000 Turbofan Engine: An Exergetic Approach. International Journal of Exergy, 14, 388-412. http://dx.doi.org/10.1504/IJEX.2014.061025

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