Numerical simulation of cold flow in a gas combustion chamber sample with a new design

Mazidi Sharfabadi, Mohammad; Hosseini Moghadam Emami, Ali; Mousavi Shad, Seyed Mohammad Sadegh

doi:10.22034/jast.2025.496857.1217

Numerical simulation of cold flow in a gas combustion chamber sample with a new design

Document Type : Original Article

Authors

Mohammad Mazidi Sharfabadi ¹

Ali Hosseini Moghadam Emami ²

Seyed mohammad sadegh Mousavi shad ³

¹ Mechanical Engineering, Development and Optimization of Energy Technologies Division, Research Institute of Petroleum Industry (RIPI)

² Iranian Research Organization for Science and Technology (IROST), Tehran, Iran

³ Islamic Azad University, Science and Research Unit, Tehran, Iran.

10.22034/jast.2025.496857.1217

Abstract

To enhance engine efficiency, extend the lifespan of components, and achieve more complete combustion, controlling the exhaust gases from the combustion chamber plays a crucial role in gas turbine design. This control can also be applied to cooling systems, which optimize the utilization of cooling air and improve the flow pattern within the combustion chamber. Notable progress has been made in utilizing these systems. One of the latest models of combustion chambers is the T56 series 3.5. While the general features of this chamber are identical to those of Series 3 and Series 2, the difference lies in the number and location of wall holes. Unfortunately, none of the manufacturer's technical specifications have been published. This paper aims to compare and assess these chambers' geometric and technical specifications through numerical modeling, using the base model (T56 series 3) as a reference. This localization of design knowledge for these chambers has been achieved. Simulation results indicate that flow rotation is almost eliminated in the secondary and dilution regions of the new chamber, and the thickness of the wall cooling layer remains nearly constant throughout the combustion chamber.

Keywords

3.5 series T56 motor

combustion chamber

Gas turbine

cold flow simulation

cooling

Subjects

Aerospace Science and Technology

[1] R. J. Lawson, “Computational Modeling of an Aircraft Engine Combustor to Achieve Target Exit Temperature Profiles”, ASME, No. 93, pp.164, 1993, https://doi.org/10.1115/93-GT-164

[2] N. C. Eccles, C. H. Priddin, Accelerated Combustion Design using CFD, ISABE pp No. 99-7094, 1999.

[3] H. A. Knight and R. B. Walker, “The Component Pressure Losses in Combustion Chambers”, Aeronautical Research Council R and M 2987, England, Report, 1953, https://reports.aerade.cranfield.ac.uk/handle/1826.2/3553.

[4] C. C. Graves and J. S. Gronman, “Theoretical Analysis for Tubular Turbojet Combustors with Constant Annulus and Liner Cross-Sectional Areas”, NACA Report 1373, 1957.

[5] A. H. Lefebvre, Gas Turbine Combustion, 2nd Edition, Taylor & Francis, 1998.

[6] D. S. Crocker and C. E. Smith “Numerical Investigation of Enhanced Dilution Zone Mixing in a Reverse Flow Gas Turbine Combustor”, Journal of Engineering for Gas Turbine and Power, Vol. 177, pp 272-281, 1995, https://doi.org/10.1115/1.2814091.

[7] V. E. Tangirala, A. K. Tolpadi, AL. M. Danis, and H. Mongia, “Parametric Modeling Approach to Gas Turbine Combustor Design”, ASME, No. 2000-GT-129, 2000, 10.1115/2000-GT-0129

[8] J. J. McGuirk, and A. Spencer, “Coupled and Uncoupled CFD Predictions of the Characteristics of Jets from Combustor Air Admission Ports”, Journal of Engineering for Gas Turbine and Power, Vol. 123, pp 327-332, 2001, https://doi.org/10.1115/1.1362319.

[9] D. S. Crocker, D. Nickolaus, and C. E. Smith, “CFD Modeling of a Gas Turbine Combustor from Compressor Exit to Turbine Inlet”, Journal of Engineering for Gas Turbine and Power, Vol. 121, pp. 89-95, 1999, https://doi.org/10.1115/1.2816318.

[10] J. J. McGuirk and J. M. L. M. Palma, “The Flow Inside a Model Gas Turbine Combustor: Calculations”, Journal of Engineering for Gas Turbines and Power, Vol. 115, pp. 594-602, 1993, https://doi.org/10.1115/1.2906748.

[11] T. S. Snyder, J. F. Stewart, M. D. Stoner, and R. G. McKinney, “Application of an Advanced CFD-Based Analysis System to the PW6000 Combustor to Optimize Exit Temperature Distribution – Part II: Comparison of Predictions to Full Annular Rig Test Data”, ASME pp 2001-GT-0064, 2001, https://doi.org/10.1115/2001-GT-0064.

[12] J. J., McGuirk and A.Spencer, “Coupled and Uncoupled CFD Prediction of the Characteristics of Jets from Combustor Air Admission Ports”, ASME pp 2000-GT-0125, 2000,https://doi.org/10.1115/2000-GT-0125.

[13] J. J. Gouws, “Combining A One-Dimensional Empirical and Network Solver with Computational Fluid Dynamics to Investigate Possible Modifications to A Commercial Gas Turbine Combustor”, Thesis for The Degree Master of Engineering, University of Pretoria, 2007.

[14] L. Zhan, et al. “LES Optimization of Annular Combustor Hole Distribution,” J. Propulsion Sci. Technol., vol. 12, pp. 45–57, 2020.

[15] R. Kumar and H. Lee, “Adjoint-Based Optimization of Reverse-Flow Combustors,” Int. J. Heat Fluid Flow, vol. 88, 108700, 2021.

[16] X. Zhao, et al. “Adaptive Cooling Holes for Transient Operations,” Energy, vol. 237, 122123, 2022.

[17] S. Ahmed, et al. “Machine Learning Surrogates for Combustor Design,” Comput. Methods Appl. Mech. Eng., vol. 379, 114742, 2023.

[18] M. H. Shojaeefard, M. Tahani, An Introduction to Turbulent Flows and Its Modeling, First Edition, Tehran: Iran University of Science and Technology Press, 2012. (In Persian).

[19] M. Mazidi Sharafabadi, S.M. Vaezi, and E. Norouzi, “Performance and Emission Analysis of Combustion Chamber of a Turboprop Engine at Different Operation Regimes” Sci. J. Fluid Mech. Aerodyn. Vol. 4, No. 1, pp.65-75, 2015, (In Persian).

[20] F. W. Skidmore and W. H. Schofield, “The Variation in Airflow Cofficinet for Allison T56 Combustion Liners”, Defence Science and Technology Organisation, Aeronautical Research Laboratories, Melbourne, Victoria, 1987.