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mahmoodi, M., Jahromi, M., Pirkandi, J., Hashemzadeh, G. (2026). Multi-objective optimization of heat transfer and weight of CFM56 engine combustion chamber. Electronic and Cyber Defense, 21(3), 101-113. doi: 10.47176/MAJ.2025.1513
mostafa mahmoodi; Mehdi Jahromi; Jamasb Pirkandi; Gholamreza Hashemzadeh. "Multi-objective optimization of heat transfer and weight of CFM56 engine combustion chamber". Electronic and Cyber Defense, 21, 3, 2026, 101-113. doi: 10.47176/MAJ.2025.1513
mahmoodi, M., Jahromi, M., Pirkandi, J., Hashemzadeh, G. (2026). 'Multi-objective optimization of heat transfer and weight of CFM56 engine combustion chamber', Electronic and Cyber Defense, 21(3), pp. 101-113. doi: 10.47176/MAJ.2025.1513
mahmoodi, M., Jahromi, M., Pirkandi, J., Hashemzadeh, G. Multi-objective optimization of heat transfer and weight of CFM56 engine combustion chamber. Electronic and Cyber Defense, 2026; 21(3): 101-113. doi: 10.47176/MAJ.2025.1513

Multi-objective optimization of heat transfer and weight of CFM56 engine combustion chamber

مکانیک هوافضا
Article 8, Volume 21, Issue 3 - Serial Number 81, October 2025, Pages 101-113    PDF (1.19 M)
Document Type: Propulsion and Heat Transfer
DOI: 10.47176/MAJ.2025.1513
Authors
mostafa mahmoodi* 1; Mehdi Jahromi2; Jamasb Pirkandi3; Gholamreza Hashemzadeh4
1Associate Professor, , Malek Ashtar University of Technology, Tehran, Iran.
2Assistant Professor, Malek Ashtar Universityof Technology, Tehran, Iran
3Associate Professor, Malek Ashtar University of Technology, Tehran, Iran
4Assistant Professor,Malek Ashtar University of Technology, Tehran, Iran
Abstract
In this study, the conceptual design and optimization of an air gas turbine combustor were investigated to reduce the liner temperature and simultaneously decrease the overall weight, including the casing and liner. The combustor under study belongs to the CFM56 engine, with initial data obtained from GasTurb software and similar studies. The NSGA-II multi-objective optimization algorithm and MATLAB software were used for optimization. At the beginning of the study, design equations and fundamental principles were examined. Heat transfer within the combustor was considered one-dimensional and without additional cooling to optimize the worst-case scenario. The optimization results show a 16% reduction in thermal stresses on the liner and a 10% decrease in combustor weight. This study also highlights the importance of selecting proper performance constraints, as an inappropriate constraint range can lead to a non-physical or limited Pareto front. The proposed optimization process can accelerate the design of gas turbine combustors, reducing excessive iterations needed to resolve design conflicts that are often difficult to assess during conventional design phases.
Keywords
Multi-objective optimization; Conceptual design; Combustion chamber; FM56 Engine
References

[1] Laveneziana L, Rosafio N, Salvadori S, Misul DA, Baratta M, Forno L, et al. Conjugate Heat Transfer Analysis of the Aero-Thermal Impact of Different Feeding Geometries for Internal Cooling in Lifetime Extension Processes for Heavy-Duty Gas Turbines. Energies. 2022;15(9):3022.  DOI  https://doi.org/10.3390/en15093022

[2] da Graca Carvalho M, Coelho PJ. Heat transfer in gas turbine combustors. Journal of Thermophysics and Heat Transfer. 1989;3(2):123–31. DOI  https://doi.org/10.2514/3.138

[3] Kim KM, Yun N, Jeon YH, Lee DH, Cho HH, Kang S-H. Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation. Journal of Mechanical Science and Technology. 2010;24(9):1939–46. DOI  https://doi.org/10.1007/s12206-010-0625-8

[4] Lefebvre AH, Ballal DR, Taylor, Francis, Lefebvre AH, Ballal DR. Gas turbine combustion : alternative fuels and emissions. Third edition. ed. Boca Raton: Taylor & Francis; 2010. DOI https://doi.org/10.1201/9781420086058

[5] Ahmet Topal  SU, Altug Piskin. One-Dimensional Heat Transfer Analysis and Experimental Investigation of a Gas Turbine Combustor.  International Symposium on Convective Heat and Mass Transfer; Turkey2014. DOI http://dx.doi.org/10.1615/ICHMT.2014.IntSympConvHeatMassTransf.230

[6] Mattingly JD, Heiser WH, Boyer KM, Haven BA, Pratt DT. Aircraft engine design. Third edition ed. Reston, Virginia: American Institute of Aeronautics and Astronautics. DOI https://doi.org/10.2514/5.9781624105173.0000.0000

[7] Sawyer JW, Japikse D. Sawyer's Gas turbine engineering handbook. 3rd ed. Norwalk, Conn., USA: Turbomachinery International Publications; 1985. 3 v : ill p. DOI https://doi.org/10.1016/B978-0-7506-7846-9.X5000-7

[8] Shao C, Liu Y, Zhang Z, Lei F, Fu J. Fast Prediction Method of Combustion Chamber Parameters Based on Artificial Neural Network. Electronics. 2023;12(23):4774. DOI https://doi.org/10.3390/electronics12234774

[9] Khosravian E. Numerical Investigation and Machine Learning Predictions for Enhanced Thermal Management in Pulsating Heat Pipes: Modeling Turbulent Flow and Heat Transfer Characteristics in Nuclear Applications. International Journal for Numerical Methods in Fluids. 2025;97(4):446–61. DOI http://dx.doi.org/10.1002/fld.5358

[10] Deb K, Pratap A, Agarwal S, Meyarivan T. A fast and elitist multiobjective genetic algorithm: NSGA-II. IEEE Transactions on Evolutionary Computation. 2002;6(2):182–97. DOI http://dx.doi.org/10.1109/4235.996017

[11] Conrado AC, Lacava PT, Carlos AL, Filho P, Física Dd, Sanches MdS, editors. BASIC DESIGN PRINCIPLES FOR GAS TURBINE COMBUSTOR, 2004.

[12] Mark CP, Selwyn A. Design and analysis of annular combustion chamber of a low bypass turbofan engine in a jet trainer aircraft. Propulsion and Power Research. 2016;5(2):97–107. DOI https://doi.org/10.1016/j.jppr.2016.04.001

[13] Sitharam TG, Govindaraju L, SpringerLink. Theory of Elasticity. 1st 2021. ed. Singapore: Springer Singapore : Imprint: Springer; 2021. DOI https://doi.org/10.1007/978-981-33-4650-5

[14] Glass DE, Dilley AD, Kelly HN, Langley Research C. Numerical analysis of convection/transpiration cooling. Hampton, Virginia: National Aeronautics and Space Administration, Langley Research Center; 1999. DOI https://doi.org/10.2514/2.3666

[15] Pera RJ, Onat EA, Klees GW, Tjønneland EN, editors. A method to estimate weight and dimensions of aircraft gas turbine engines. Volume 1: Method of analysis1977.

[16] https://www.grc.nasa.gov/www/k-12/airplane/turbwt.html  [

[17] Martins DAR. Off-Design Performance Prediction of the CFM56-3 Aircraft Engine: universidade de lisboa; 2015.

[18] Serbezov V. TURBOFAN ENGINE MODEL FOR ESTIMATION OF THE FUEL CONSUMPTION FOR COMPENSATION OF AUXILIARY ENERGY SUPPLY. 2011.

[19] https://www.gasturb.com/ 

[20] Habermehl S. Coefficient of thermal expansion and biaxial Young's modulus in Si-rich silicon nitride thin films. Journal of Vacuum Science & Technology A. 2018;36(2). DOI https://doi.org/10.1116/1.5020432

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