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Estimation and Calculus of Turbojet Performances with Optimal Turbine Blades Cooling
Salim Bennoud
Pages - 100 - 110     |    Revised - 01-10-2013     |    Published - 01-11-2013
Volume - 7   Issue - 4    |    Publication Date - November 2013  Table of Contents
Engine Performances, Thermodynamic Turbojet Cycle, Turbine Blades Cooling.
The temperature augmentation of the turbine inlet gas will always produce an augmentation of thrust, thus the improving of overall performances of the turbojet. This augmentation will benefit the performance, but this effect has drawbacks because of the produced effects on the turbine blades such as the thermal fatigue, the corrosion and also the creep.

These problems act and influence on the thermal and mechanical characteristics of the material, so the factors of security and cost are affected accordingly. Under these conditions, the turbine blades must be cooled to maintain their integrity and achieve their maximum life period.

The principal objective of this work is to develop a data processing application able to calculate the turbojet performances, as well as the calculation of turbine blades cooling.

The developed application makes the calculation of the turbine blades cooling to different altitudes, and has certain advantages, such as: the possibility to have detailed results, the capacity to work out a report, the total absence of intermediate calculations appearance and a total elimination of the curves and graphs use to get the values of each simulation.
CITED BY (2)  
1 Bennoud, S. Modeling and Simulation of Defects Due to corrosion in Turbine Blades of Turbojet.
2 Bennoud, S., Hocine, S., & Slme, H. Calculus of Turbojet Performances for Ideal Case.
1 A. H Lefebvre, D. R Ballal, Gas turbines combustion, 3rd ed, Taylor & Francis, 2010.
2 F. Piltan, N. Sulaiman, P. Ferdosali and I. Assadi Talooki, “Design Model-free Fuzzy Sliding Mode Control: Applied to Internal Combustion Engine”, International Journal of Engineering (IJE), vol. 5(4), 302-312, 2011.
3 S. Bennoud and F.Larbi, “Simulation of the Premixed Turbulent Flame Caused by Swirled Injector”, Sixth International Conference on Thermal Engineering: Theory and Applications,Istanbul, Turkey, May 29-June 1 2012, ISBN: 978-192676908-0, 2012.
4 N. Peters, Turbulent combustion, Cambridge University Press, 2004.
5 L.Li, T.Liu, X.F.Peng, “Flow characteristics in an annular burner with fully cooling”, Applied Thermal Engineering, vol. 25, 3015-3024, 2005.
6 J. Cousin, W. M. Ren and S. Nally, “Recent developments in simulations of internal flows in high pressure swirl injectors”, Oil & Gas Science and Technology, vol. 54(2), 227-231, 1999.
7 C. H. Hwang, S. Lee, J. H. Kim and C. E. Lee, “An experimental study on flame stability and pollutant emission in a cyclone jet hybrid combustor”, Applied Energy, vol. 86, 1154-1161,2009.
8 S. Mendez, “Numerical simulation and modeling of the flow around the multi-perforated plate”, thesis, University Montpellier II, 2007, (in French).
9 R. Borghi and M.Destriau, Combustion and Flames: Chemical and Physical Principles,TECHNIP, 1998.
10 L. Debiane, B. Ivorra, B. Mohammadi, F. Nicoud, T. Poinsot, A. Ern and H. Pitsch, “A low complexity global optimization algorithm for temperature and pollution control in flames with complex chemistry”, International Journal of Computational Fluid Dynamics, vol. 10 (2), 93-98, 2006.
11 Je-Chin Han, “Recent studies in turbine blade cooling”, International Journal of Rotating Machinery, vol. 10(6): 443-457, 2004.
12 D. Thibault, “study of cooling by jets impact through a thin wall and with a flow shearing upstream: application to the turbine blades”, thesis, ENSMA, Poitiers, 2009 (in French).
13 J. D Mattingly, Elements of gas turbine propulsion, 2nd ed. AIAA, 2005.
14 M. G. Dunn, “Convection Heat Transfer and Aerodynamics in Axial Flow Turbines”, ASME Journal of Turbomachinery. vol. 123 (4):.637-686, 2001.
15 J.C. Han, S. Dutta, and S.V. Ekkad, Gas turbine heat transfer and cooling technology,Taylor & Francis, New York, 2000.
16 J. D Mattingly, W. H. Heiser, T. P. Pratt., Aircraft engine design, 2 nd ed, AIAA Educational Series, 2002.
17 V. B. Rutovsky, “thermodynamic cycles of aviation gas turbine engines”,www.eolss.net\eolss-sampleallchaptre.aspx
18 M. Badami, P. Nuccio, A. Signoretto, “Experimental and numerical analysis of a small-scale turbojet engine”, Energy Conversion and Management, vol. 76, 225-233, 2013.
19 U. K. Kayadelen, Y. Ust, “Prediction of equilibrium products and thermodynamic properties in H2O injected combustion for CaHßO?Nd type fuels”, Fuel, vol. 113, 389-401, 2013.
20 E. Benini, S. Giacometti, “Design, manufacturing and operation of a small turbojet-engine for research purposes”, Applied Energy, vol. 84(11), 1102-1116, 2007.
21 Kyo-Soo Song, Seon-Gab Kim, Daehan Jung, Young-Ha Hwang, “Analysis of the fracture of a turbine blade on a turbojet engine”, Engineering Failure Analysis, vol. 14(5), 877-883,2007.
22 “Aircraft accident report”, NTSB-AAR-77-1, National Transportation Safety Board,Washington, D.C,1976.
23 M. Ralf, B727-200 performance handbook, USA, 1st ed, 2011.
Associate Professor Salim Bennoud
Faculty of Technology/Laboratory of Aircrafts University of Saad Dahlab Blida,09000 - Algeria