Design, Numerical and Experimental Investigation of High Swirling Flow in an Annular Combustion Chamber

Subject Areas : Mechanical Engineering

Zahra Ghahramani ¹ , Masoud Zareh ² , Hossein Pourfarzaneh ³ , Farshad Pazooki ⁴

1 - Department of Mechanical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
2 - Department of Mechanical Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran
3 - Designer head, Farzanegan Propulsion Systems Design Bureau, Iran Rasht
4 - Department of Aerospace Engineering, Science and Research Branch, Islamic Azad University, Tehran, Iran

Received: 2021-01-06 Accepted : 2021-04-25 Published : 2021-06-01

Keywords: Swirler Number (SN), Atmospheric Test (AT), 3D Numerical Simulation, Annular Combustion Chamber,

Abstract :

In this study, an annular combustion chamber of a turbojet engine with a net trust of 1650N is designed. Kerosene is considered as fuel in this study. The design consists of evaluation of the reference quantities, calculation of the required dimensions, estimation of air distribution and pressure drop, estimation of the number and diameter of air admission holes, as well as aerodynamic considerations. The design process is accompanied by Computational Fluid Dynamics (CFD) based on RANS simulation. Three-dimensional simulation of the reacting process within the combustion chamber is carried out based on the finite volume method. The RNG turbulent model and the finite rate/eddy dissipation combustion model are considered in the present study. Finally, the (atmospheric test) AT rig of the combustion chamber is explained. The Turbine Inlet Temperature (TIT) of combustion chamber is measured at different operating conditions. The TIT values in the numerical simulation and experimental measurement are 1191.1K and 1227 K, respectively, in the design point. The SN and the angle of the RZ are equal to 0.9955 and 35.26 degree, respectively. The temperature, velocity and pressure fields of RZ, air-fuel mixture, combustion turbulence are then presented in image outputs and graphs. The results indicate that the temperature distribution at the outlet of combustion chamber is relatively uniform.

References:

[1]     Lefebvre, A. H., Ballal, D. R., Gas Turbine Combustion: Alternative Fuels and Emissions, 3rd ed, CRC press, 2010, Chap. 4.

[2]     Mattingly, J. D., Heiser, W. H., and Pratt, D. T., Aircraft Engine Design, American Institute of Aeronautics and Astronautics, 3rd ed, American Institute of Aeronautics and Astronautics, Inc., Reston 2002, Chap. 9.

[3]     Mellor, Design of Modern Turbine Combustors, Academic Press, 1990, Chaps. 1, 4.

[4]     Mohammed, R. S. E., Design and Analysis of Annular Combustion Chamber for a Micro Turbojet Engine, International Journal of Aerospace and Mechanical Engineering, Vol. 13, No. 4, 2019, pp. 282-287.

[5]     Mark, C. P., Selwyn, A., Design and Analysis of Annular Combustion Chamber of a Low by Pass Turbofan Engine in a Jet Trainer Aircraft, Propulsion and Power Research, Vol. 5, No. 2, 2016, pp:97-107.

[6]     Zeng, Q., Yuan, Y., Flow Dynamics of Dual-Stage Counter-Swirl Combustor in Different Confinement Spaces, International Communications in Heat and Mass Transfer, Vol. 116, 2020, pp. 104633.

[7]     Jiang, Y., Yue, G., Dong, P., Gao, J., and Zheng, Q., Investigation on Film Cooling with Swirling Coolant Flow by Optimizing the Inflow Chamber, International Communications in Heat and Mass Transfer, Vol. 88, 2017, pp. 99-107.

[8]     Saboohi, Z., Ommi, F., and Akbari, M. J., Multi-Objective, Optimization Approach Toward Conceptual Design of Gas Turbine Combustor, Applied Thermal Engineering, Vol. 148, 2019, pp. 1210.

[9]     Amani, E., Rahdan, P., and Pourvosoughi, S., Multi-Objective Optimizations of Air partitioning in a Gas Turbine Combustor, Applied Thermal Engineering, Vol. 148, 2019, pp. 1292-1302.

[10]  Treedet, W., Suntivarakorn, R., Effect of Various Inlet Geometries on Swirling Flow in Can Combustor, Journal of Mechanical Engineering and Sciences, Vol. 12, 2018, pp. 3712-3723.

[11]  Eldrainy, Y. A., Saqr, K. M., Aly, H. S., Lazim, T. M., and Jaafar, M. N. M., Large Eddy Simulation and Preliminary Modeling of the Flow Downstream a Variable Geometry Swirler for Gas Turbine Combustors, International Communications in Heat and Mass Transfer, Vol. 38, No. 8, 2011, pp. 1104-1109.

[12]  Eldrainy, Y. A., Saqr, K. M., Aly, H. S., Lazim, T. M., Jaafar, M. N. M., CFD Insight of the Flow Dynamics in a Novel Swirler for Gas Turbine Combustors, International Communications in Heat and Mass Transfer, Vol. 36, No. 9, 2009, pp. 936-941.

[13]  Chen, R. H., Driscoll, J. F., The Role of the Recirculation Vortex in Improvement Fuel- Air Mixing within Swirling Flames, Processing in Symposium (International) on Combustion, Vol. 22, No. 1, 1989, pp. 531-540.

[14]  Liu, Y., Zhang, L., Chen, Z., and Zhou, L., Numerical Investigation on Mixture Particle Dispersion Characteristics in Swirling Particle-laden Combustion Chamber, International Communications in Heat and Mass Transfer, Vol. 117, 2020, pp.104720.

[15]  Çakmak, G., Yıldız, C., The Influence of the Injectors with Swirling Flow Generating on the Heat Transfer in the Concentric Heat Exchanger, International Communications in Heat and Mass transfer, Vol. 34, No. 6, 2007, pp. 728-739.

[16]  Torkzadeh, M., Bolourchifard, F., Amani, E., An Investigation of Air-Swirl Design Criteria for Gas Turbine Combustors through a Multi-Objective CFD Optimization, Fuel, Vol. 186, 2016, pp. 734-749.

[17]  Pourfarzaneh, H., Modelling of Turbojet Propulsion Performance and Experimental Validation, Ph.D. dissertation, Dept. Mech. Eng., Sharif Univ., Tehran, Iran, 2010.

[18]  Conrado, A. C., Locava, P. T., Filho, P., and Sanchez, M. S., Basic Design Principles for Gas Turbine Combustor, Processing of the 10th Brazilian Congress of Thermal Science and Engineering, Riodejaneiro, 2004.

[19]  Khandelwal, B., Lili, D., and Sethi, V., Design and Study on Performance of Axial Swirler for Annular Combustor by Changing Different Design Parameters, Journal of the Energy Institute, Vol. 87, No. 4, 2014, pp. 372-382.

[20]  Saboohi. Z., Ommi. F., and Fakhrtabatabaei, A., Development of an Augmented Conceptual Design Tool for Air Craft Gas Turbine Combustors, International Journal of Multiphysics, Vol. 10, 2016, pp. 53-73.

[21]  Ajmi, M., Hnaien, N., Marzouk, S., Kolsi, L., Ghachem, K., Aissia, H. B., and Almeshaal, M. A., Numerical Investigation of Heat Transfer Enhancement of an Inclined Heated Offset Jet, International Communications in Heat and Mass Transfer, Vol. 116, 2020, pp. 104682.

[22]  Luan, Y. T., Chuou, Y. P., and Wang, T., Numerical Analysis of Gasification Performance via Finite-Rate Model in a Cross-Type Two-Stage Gasifier, International Communication in Heat and Mass Transfer, Vol. 52, 2013, pp. 558-566.

[23]  Zeng, W., Liang, S., Li, H. X., and Ma, H. A, Chemical Kinetic Simulation of Kerosene Combustion in an Individual Flame Tube, Journal of Advanced Research, Vol. 5, 2014, pp. 357-366.

[24]  ANSYS Fluent Tutorials, Release 16, Ansys inc, 2015.

[25]  Montero Sistiagoa, M. L., Pourbabak, S., Humbeeck, J. V., Schryvers, D., and Vanmeensel, K., Micro Structure and Mechanical Properties of Hastelloy X Produced by HB-SLM (High Power Selective Laser Melting), Materials & Design, Vol. 165, 2019, pp. 107598.