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Simulation performance comparison between high temperature rise triple-swirler combustor with double-swirler combustor

Published online by Cambridge University Press:  11 December 2025

D. Wang Open the ORCID record for D. Wang [Opens in a new window] ,
F. Li Open the ORCID record for F. Li [Opens in a new window] ,
H. Lin  and
Y. Tan
D. Wang
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 102206, China
F. Li*
Affiliation:
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 102206, China
H. Lin
Affiliation:
Shenyang Engine Research Institute, Aero Engine Corporation of China, Shenyang 110015, China
Y. Tan
Affiliation:
Gas Turbine Establishment, Aero Engine Corporation of China, Chengdu 610500, China
*
Corresponding author: F. Li; Email: lifeng01@buaa.edu.cn
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Abstract

To investigate the advantages and disadvantages of two multi-swirl fuel-rich dome configurations, namely the triple-swirler and double-swirler, for a novel high-temperature rise centre-staged combustor, this study employed ANSYS Fluent software. Utilising the Reynolds-averaged Navier-Stokes (RANS) equation as the governing equation, three-dimensional numerical simulations were conducted using the Realisable k-ε turbulence model and non-premixed probability density function (PDF) combustion model to analyse the flow and combustion characteristics of both configurations. A comparative study was then performed to evaluate the performance differences between the two dome configurations under take-off and idle conditions. The results demonstrate that, under both conditions, the fuel-air mixing in the triple-swirler combustor occurs faster and more uniformly. Specifically, during takeoff, the primary zone temperature distribution in the triple-swirler combustor is more uniform, while during idle, the fuel-rich combustion region is more symmetrical. Furthermore, across both conditions, the outlet temperature distribution of the triple-swirler combustor is of superior quality, albeit with equivalent combustion efficiency. Notably, the formation of NOx and soot in the triple-swirler combustor, during takeoff conditions, exceeds that of the double-stage combustor along the flow path, whereas the generation of CO and UHC, during idle conditions, is lower in the former.

Keywords

triple-swirler combustorcentral-staged combustordouble-swirler combustorhigh temperature rise combustormulti-swirl fuel-rich dome

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 130 , Issue 1344 , February 2026 , pp. 371 - 417
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Copyright
© Beijing University of Aeronautics and Astronautics and the Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Kress, E.J., Taylor, J.R. and Dodds, W.J. Multiple Swirler Dome Combustor for High Temperature Rise Applications, In AIAA Meeting Paper 26th Joint Propulsion Conference, Orlando, US, 1990. https://doi.org/10.2514/6.1990-2159 CrossRefGoogle Scholar
Donald, W. and Clifford, C. Technology for the reduction of aircraft turbine engine pollutant emissions. ICAS Paper No. 74-31, 1974.Google Scholar
Bahr, D.W. Technology for the design of high temperature rise combustors, AIAA, 1987, 3, (02), pp 179–186. https://doi.org/10.2514/3.22971 Google Scholar
Jin, R. High temperature rise combustor technology, Propul. Technol. Prod., 1989, 4, (01), pp 34–36.Google Scholar
Hou, X. Aviation Gas Turbine Combustion Technology. National Defense Industry Press, Beijing, 2002.Google Scholar
Lin, Y., Xu, Q. and Liu, G. Gas Turbine Combustor. National Defense Industry Press, Beijing, 2008.Google Scholar
Mongia, H.C. Engineering aspects of complex gas turbine combustion mixers. Part I: High ΔT. AIAA-2011-107, 2011. https://doi.org/10.2514/6.2011-107 CrossRefGoogle Scholar
Mongia, H.C. Engineering aspects of complex gas turbine combustion mixers. Part II: High ΔT3. AIAA-2011-106, 2011.CrossRefGoogle Scholar
Mongia, H.C. Engineering aspects of complex gas turbine combustion mixers. Part III: 30 OPR. AIAA-2011-5525, 2011.CrossRefGoogle Scholar
Mongia, H.C. Engineering aspects of complex gas turbine combustion mixers. Part IV: Swirl Cup. AIAA-2011-5526, 2011.CrossRefGoogle Scholar
Mongia, H.C. Engineering aspects of complex gas turbine combustion mixers. Part V: 40 OPR. AIAA-2011-5527, 2011.CrossRefGoogle Scholar
Mongia, H.C. Recent Advances in the Development of Combustor Design Tool. Part I: High ΔT. AIAA-2003-4495, 2003.CrossRefGoogle Scholar
Wang, D. Annular curved-wall expanding-angle flow-facing design method: China, 202310419914.0. 2023-07-21, 2023.Google Scholar
Wang, D. Primary hole structure of air intake scoop bucket type for high temperature rise main combustors: China, 202310733703.4. 2023-09-15, 2023.Google Scholar
Wang, D. Convex arc flow-facing design method of flame tube convergence section: China, 202310851327.9. 2023-09-22, 2023.Google Scholar
Gao, W., Li, F., Gao, X., et al. Effect of swirler characteristic parameters on combustion performance of HTR combustor. Aeroengine, 2015, 41, (04), pp 29–34. https://link.cnki.net/doi/10.13477/j.cnki.aeroengine.2015.04.006 Google Scholar
Dang, X., Zhao, J., Xu, R., et al. Experimental investigation on effects of swirl number on aerodynamic characteristics of combustor, J. Aerosp. Power, 2011, 26, (01), pp 21–27. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2011.01.005 Google Scholar
Reddy, K.S., Reddy, D.N. and Varaprasad, C.M. Experimental and numerical investigations of swirling flows in a reverse flow gas turbine combustor. AIAA 2007-4219, 2007. https://arc.aiaa.org/doi/pdf/10.2514/6.2007-4219 Google Scholar
Khandelwal, B., Lili, D. and Sethi, V. Design and study on performance of axial swirler for annular combustor by changing different design parameters, J. Energy Inst., 2014, 87, (04), pp 372–382. https://doi.org/10.1016/j.joei.2014.03.022 CrossRefGoogle Scholar
Wang, H. Fluid Mechanics as I Understand It. National Defense Industry Press, Beijing, 2014.Google Scholar
Huang, Y., Lin, Y., Fan, W., et al. Combustion and Combustion Chambers. Beihang University Press, Beijing, 2009.Google Scholar
Hinze, J.O.. Turbulence, 2nd ed. McGraw-Hill Publishing Co., New York, 1975.Google Scholar
Wang, D., Li, F., Lin, H., et al. Design and simulation of high temperature rise triple-swirler combustor, Aeronaut. J., 2024, 129, (1335), pp. 1320–1360. https://doi.org/10.1017/aer.2024.127 CrossRefGoogle Scholar
O’Rourke, P.J. Collective Drop Effects on Vaporizing Liquid Sprays. Princeton University, Princeton, NJ, 1981.Google Scholar
Beale, J.C. and Reitz, R.D. Modeling spray atomization with the Kelvin-Helmholtz/Rayleigh-Taylor hybrid model, Atom. Spray., 1999, 9, (6), pp 623–650. https://doi.org/10.1615/AtomizSpr.v9.i6.40 Google Scholar
Patterson, M.A. and Reitz, R.D. Modeling the Effects of Fuel Spray Characteristics on Diesel Engine Combustion and Emission, SAE Trans., 1998, pp. 27–43. https://doi.org/10.4271/980131 Google Scholar
Zhou, T. A Study on Flame Structure and Emission Characteristic in a Multi-swirler Concentric Staged Lean Direct Injection Combustor. Beihang University, Beijing, 2024.Google Scholar
Wang, D., Li, F., Lin, H., et al. Research on substitutability of single-dome versus triple-dome center staged combustor, Case Stud. Therm. Eng., 2024, 60, p 104633. https://doi.org/10.1016/j.csite.2024.104633 CrossRefGoogle Scholar
Wang, K. Research on the Control Mechanism of Boundary Temperature and Optimization of Key Design Parameters for Combustor in Gas Turbines, Beihang University, Beijing, 2024.Google Scholar
Khan, I.M. and Greeves, G. A Method for Calculating the Formation and Combustion of Soot in Diesel Engines. Architectural Institute of Japan, In Afgan, N.H. and Beer, J.M. (eds.), Heat Transfer in Flames. Chapter 25, Scripta, Washington, DC, 1974.Google Scholar
Tesner, P.A., Snegiriova, T.D. and Knorre, V.G. Kinetics of dispersed carbon formation, Combust. Flame, 1971, 17, (02), pp 253–260. https://doi.org/10.1016/S0010-2180(71)80168-2 CrossRefGoogle Scholar
Wang, D. High Temperature Rise Triple-swirler Combustor: China, 202211681365.6. 2023-05-10, 2023.Google Scholar
Ballal, D.R. and Lefebver, A.H. A proposed method for calculating film-cooled wall temperatures in gas turbine combustion chamber, Cranfield Rep. SME, 1973, (4). https://resolver.tudelft.nl/uuid:560dc72a-8ab5-4667-b17b-821e157ef069 Google Scholar
Colladay, R.S. Importance of combining convection with film cooling. AIAA paper 72-8, 1972. https://ntrs.nasa.gov/api/citations/19720005294/downloads/19720005294.pdf CrossRefGoogle Scholar
Lin, Y., Lin, Y., Zhang, C., et al. Discussion on combustion airflow distribution of advanced staged combustor, J. Aerosp. Power, 2010, 25, (09), pp 1923–1931. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2010.09.007 Google Scholar
Lefebvre, A.H. Gas Turbine Combustion, 2nd ed. Taylor & Francis, Philadelphia, PA, USA, 1999.Google Scholar
Zhang, C., Zhang, R., Xu, G., et al. Experimental investigation on atomization of an air-blast atomizer with Plainorifice nozzle and dual-swirl cup, J. Aerosp. Power, 2006, 21, (05), pp 805–809. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2006.05.004 Google Scholar
Liu, B., Lin, Y., Yuan, Y., et al. Research on the lean blow-out stabilities of the high temperature rise combustor, J. Propul. Technol., 2003, 24, (05), pp 456–459. https://link.cnki.net/doi/10.13675/j.cnki.tjjs.2003.05.018 Google Scholar
Celik, I.B., Ghia, U., Roache, P.J., et al. Procedure for estimation and reporting of uncertainty due to discretization in CFD applications, J. Fluids Eng., 2008, 130, (07), pp 078001–078004. https://doi.org/10.1115/1.2960953 Google Scholar
Wang, F. Computational Fluid Dynamics Analysis: Principles and Applications of CFD Software, Tsinghua University Press, Beijing, 2004.Google Scholar
Gao, X. Numerical Simulation and Performance Analysis of Complex Swirler Combustor, Beihang University, Beijing, 2014, pp 18–26.Google Scholar
Gao, X., Li, F. and Guo, D. Design and computational analysis of ultra-high temperature rise concentric staged combustor, Aeroengine, 2015, 41, (01), pp. 9–15. https://link.cnki.net/doi/10.13477/j.cnki.aeroengine.2015.01.002 Google Scholar
Luo, W., Li, F., Gao, X., et al. Numerical analysis of high temperature rise combustor with a multi-swirler, Aeroengine, 2015, 41, (02), pp 17–21. https://link.cnki.net/doi/10.13477/j.cnki.aeroengine.2015.02.004 Google Scholar
Luo, W., Li, F., Gao, X., et al. Numerical analysis for performance of high temperature rise swirl combustors, J. Propul. Technol., 2015, 36, (11), pp 1686–1693. https://link.cnki.net/doi/10.13675/j.cnki.tjjs.2015.11.012 Google Scholar
Shang, S., Gao, X., Guo, R., et al. Capability prediction of high temperature rise center-staged combustor, J. Aerosp. Power, 2014, 29, (05), pp 1001–1007. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2014.05.002 Google Scholar
Li, F., Shang, S., Cheng, M., et al. Research on the feasibility of displacing the single annular combustor with a dual annular combustor, J. Aerosp. Power, 2008, 23, (01), pp 145–149. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2008.01.023 Google Scholar
Li, F., Cheng, M., Shang, S., et al. Capability compare of twin annular premixing swirler with the single annular and dual annular combustor, J. Aerosp. Power, 2012, 27, (08), pp 1681–1687. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2012.08.006 Google Scholar
Liu, Q., Suo, J., Liang, H., et al. Numerical investigation of combination of direct mixing combustion and LPP combustor, J. Aerosp. Power, 2012, 27, (11), pp 2448–2454. https://link.cnki.net/doi/10.13224/j.cnki.jasp.2012.11.017 Google Scholar
Yang, X., Zhang, Z., Guo, Z., et al. Numerical simulation of high temperature rise combustor, Aeronaut. Sci. Technol., 2017, 28, (02), pp 13–19. https://link.cnki.net/doi/10.19452/j.issn1007-5453.2017.02.013 Google Scholar