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Design and simulation of high temperature rise triple-swirler combustor

Published online by Cambridge University Press:  11 December 2024

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

To meet the development needs of aeroengines for high thrust-to-weight ratios and fuel-air ratios, a high temperature rise triple-swirler main combustor was designed with a total fuel-air ratio of 0.037, utilising advanced technologies including staged combustion, multi-point injection and multi-inclined hole cooling. Fluent software was used to conduct numerical simulations under both takeoff and idle conditions, thereby obtaining the distribution characteristics of the velocity and temperature fields within the combustor, as well as the generation of pollutants. The simulation results indicate that under takeoff conditions, the high temperature rise triple-swirler combustor achieves a total pressure loss coefficient of less than 6% and a combustion efficiency exceeding 99%. Under takeoff conditions, the OTDF and RTDF values are 0.144 and 0.0738, respectively. The mole fraction of NOx emissions is 3,700ppm, while the mole fraction of soot emissions is 2.55×10−5ppm. Under idle conditions, the triple-swirler combustor maintains a total pressure loss coefficient of less than 6% and a combustion efficiency greater than 99.9%. The OTDF and RTDF values are 0.131 and 0.0624, respectively. The mole fractions of CO and UHC emissions are both 0×10−32ppm at the calculation limit of Fluent software.

Keywords

high temperature rise combustortriple-swirler combustormain combustor designcentral staged combustornumerical simulation
Type
Research Article
Information
The Aeronautical Journal , Volume 129 , Issue 1335 , May 2025 , pp. 1320 - 1360
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Copyright
© The Author(s), 2024. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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References

Jiang, M. and Hu, Y. Battle requirement research of the fourth generation fighter, Aeronaut. Sci. Technol., 2003, 01, 29–30, 40. https://doi.org/10.3969/j.issn.1007-5453.2003.01.008 Google Scholar
Jin, R. and Suo, J. Advanced Gas Turbine Combustor, Aviation Industry Press, 2016, Beijing. Google Scholar
Jiao, J. and Li, M. The key to the development of aero engine combustor (Part 2), China Aviation News, 2017, (008).Google Scholar
Kress, E.J., Taylor, J.R. and Dodds, W.J. Multiple swirler dome combustor for high temperature rise applications [Report], AIAA Paper 90–2159, 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 [Report]. ICAS Paper No. 74–31, 1974.Google Scholar
Bahr, D.W. Technology for the design of high temperature rise combustors, AIAA J., 1987, 3, (2), pp 179–186. https://doi.org/10.2514/3.22971 Google Scholar
Dodds, W. Engine Technology Development to Address Local Air Quality Concerns [Report], International Coordinating Council of Aerospace Industries Associations, 2008, Belgium. Google Scholar
Jin, R. High temperature rise combustor technology, Propul. Technol. Products, 1989, 4, (1), pp 34–36.Google Scholar
Hou, X. Aviation gas Turbine Combustion Technology, National Defense Industry Press, 2002, Beijing. Google Scholar
Lin, Y., Xu, Q. and Liu, G. Gas Turbine Combustor, National Defense Industry Press, 2008, Beijing. Google Scholar
Wang, D., Li, F., Lin, H. and Zhang, S. Annular curved-wall expanding-angle flow-facing design method (P.R.C. Patent No. 202310419914.0), China National Intellectual Property Administration, 2023. Google Scholar
Wang, D., Li, F., Lin, H. and Zhang, S. Primary hole structure of air intake scoop bucket type for high-temperature rise main combustors (P.R.C. Patent No. 202310733703.4), China National Intellectual Property Administration, 2023. Google Scholar
Wang, D., Li, F., Lin, H., Zhang, S. and Wang, D. Convex arc flow-facing design method of flame tube convergence section (P.R.C. Patent No. 202310851327.9), China National Intellectual Property Administration, 2023. Google Scholar
Hinze, J.O. Turbulence, 2nd ed, McGraw-Hill Publishing Co, 1975, New York. Google Scholar
Mongia, H.C. and Dodds, W.G.A.E. Low emissions propulsion engine combustor technology evolution past, present and future, Proceedings of the 24th Congress of the International Council of the Aeronautical Sciences, Yokohama, Japan, 2004. https://www.icas.org/ICAS_ARCHIVE/ICAS2004/PAPERS/609.PDF Google Scholar
Sarkar, S. and Balakrishnan, L. Application of a Reynolds stress turbulence model to the compressible shear layer, AIAA J., 1990, 29, (5), pp 743–749. https://doi.org/10.2514/3.10649 CrossRefGoogle Scholar
O’Rourke, P.J. Collective drop effects on vaporizing liquid sprays [Doctoral dissertation, Princeton University], 1981. Google Scholar
Beale, J.C. and Reitz, R.D. Modeling spray atomization with the Kelvin-Helmholtz/Rayleigh-Taylor hybrid model, Atomization Sprays, 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
Bazdidi-Tehrani, F. and Zeinivand, H. Presumed PDF modeling of reactive two-phase flow in a three dimensional jet-stabilized model combustor, Energy Convers. Manag., 2010, 51, (1), pp 225–234. https://doi.org/10.1016/j.enconman.2009.09.020 Google Scholar
Masri, A.R., Kalt, P.A.M. and Barlow, R.S. The compositional structure of swirl-stabilised turbulent nonpremixed flames, Combustion Flame, 2004, 137, (1–2), pp 1–37. https://doi.org/10.1016/j.combustflame.2003.12.004 Google Scholar
Jones, W.P. and Whitelaw, J.H. Calculation methods for reacting turbulent flows: A review. Combust. Flame, 1982, 48, pp 1–26. https://doi.org/10.1016/0010-2180(82)90112-2 CrossRefGoogle Scholar
Hanson, R.K. and Salimian, S. Survey of rate constants in the N/H/O system, Combustion Chem., 1984, pp 361–421. https://doi.org/10.1007/978-1-4684-0186-8_6 CrossRefGoogle Scholar
Khan, I.M. and Greeves, G. A method for calculating the formation and combustion of soot in diesel engines, Architectural Institute of Japan, 1974. Google Scholar
Magnussen, B.F. and Hjertager, B.H. On mathematical modeling of turbulent combustion with special emphasis on soot formation and combustion, Symp. Combustion, 1977, 16, (1), pp 719–729. https://doi.org/10.1016/S0082-0784(77)80366-4 CrossRefGoogle Scholar
Tesner, P.A., Snegiriova, T.D. and Knorre, V.G. Kinetics of dispersed carbon formation, Combustion Flame, 1971, 17, (2), pp 253–260. https://doi.org/10.1016/S0010-2180(71)80168-2 CrossRefGoogle Scholar
Lin, Y., Lin, Y., Zhang, C. and Xu, Q. Discussion on combustion air flow distribution of advanced staged combustor, J. Aerospace Power, 2010, 25, (9), pp 1923–1931.Google Scholar
Lefebvre, A.H. Gas Turbine Combustion, 2nd ed, Taylor & Francis, 1999, Philadelphia, PA. Google Scholar
Zhang, C., Zhang, R., Xu, G. and Lin, Y. Experimental investigation on atomization of an air-blast atomizer with plain-orifice nozzle and dual-swirl cup, J. Aerospace Power, 2006, 21, (5), pp 805–809. https://doi.org/10.3969/j.issn.1000-8055.2006.05.004 Google Scholar
Liu, B., Lin, Y., Yuan, Y., Liu, G., Hu, Z. and Xu, H. Research on the lean blow-out stabilities of the high temperature rise combustor, J. Propul. Technol., 2003, 24, (5), pp 456–459. https://doi.org/10.3321/j.issn:1001-4055.2003.05.018 Google Scholar
Gao, X. Numerical simulation and performance analysis of complex swirler combustor [Master’s thesis, Beihang University], 2014. Google Scholar
Li, F., Shang, S., Cheng, M., Peng, L., Yang, H. and Song, B. Research on the feasibility of displacing the single annular combustor with a dual annular combustor, J. Aerospace Power, 2008, 23, (1), pp 145–149.Google Scholar
Li, F., Cheng, M., Shang, S., Liu, D., Zhang, S. and Song, B. Capability compare of twin annular premixing swirler with the single annular and dual annular combustor, J. Aerospace Power, 2012, 27, (8), pp 1681–1687.Google Scholar
Liu, Q., Suo, J., Liang, H., Li, M. and Li, H. Numerical investigation of combination of direct mixing combustion and LPP combustor, J. Aerospace Power, 2012, 27, (11), pp 2448–2454.Google Scholar
Yang, X., Zhang, Z., Guo, Z. and Suo, J. Numerical simulation of high temperature rise combustor. Aeronaut. Sci. Technol., 2017, 28, (2), pp 13–19.Google Scholar