Advertisement

Acta Mechanica Sinica

, Volume 32, Issue 1, pp 75–82 | Cite as

Engine performance analysis and optimization of a dual-mode scramjet with varied inlet conditions

  • Lu Tian
  • Li-Hong ChenEmail author
  • Qiang Chen
  • Feng-Quan Zhong
  • Xin-Yu Chang
Research Paper

Abstract

A dual-mode scramjet can operate in a wide range of flight conditions. Higher thrust can be generated by adopting suitable combustion modes. Based on the net thrust, an analysis and preliminary optimal design of a kerosene-fueled parameterized dual-mode scramjet at a crucial flight Mach number of 6 were investigated by using a modified quasi-one-dimensional method and simulated annealing strategy. Engine structure and heat release distributions, affecting the engine thrust, were chosen as analytical parameters for varied inlet conditions (isolator entrance Mach number: 1.5–3.5). Results show that different optimal heat release distributions and structural conditions can be obtained at five different inlet conditions. The highest net thrust of the parameterized dual-mode engine can be achieved by a subsonic combustion mode at an isolator entrance Mach number of 2.5. Additionally, the effects of heat release and scramjet structure on net thrust have been discussed. The present results and the developed analytical method can provide guidance for the design and optimization of high-performance dual-mode scramjets.

Graphical Abstract

A dual-mode scramjet can achieve high thrust in a wide range of flight conditions. The present work uses modified quasi-1-D analysis model and simulated annealing strategy to investigate the engine performance of kerosene-fueled parameterized dual-mode scramjet at a crucial flight Mach number of 6. Engine structure and heat release distributions were optimized to obtain optimal engine net thrust for varied inlet conditions. The highest net thrust can be achieved by subsonic combustion mode at an isolator entrance Mach number of 2.5. The present results and analytical method can provide guidance for the design and optimization of high-performance dual-mode scramjets.

Keywords

Dual-mode scramjet Engine performance Thrust Optimization Heat release distribution Simulated annealing algorithm 

Notes

Acknowledgments

This work was supported by the National Natural Science Foundation of China (Grant 11002148)..

References

  1. 1.
    Curran, E.T.: Scramjet engines: the first 40 years. J. Propuls. Power 17, 1138–1148 (2001)CrossRefGoogle Scholar
  2. 2.
    Heiser, W.H., Pratt, D.T., Deley, D.H.: Hypersonic Airbreathing Propulsion. American Institute of Aeronautics and Astronautics Inc, Washington, D.C. (1994)CrossRefGoogle Scholar
  3. 3.
    Dessornes, O., Scherrer, D.: Tests of the JAPHAR dual mode ramjet engine. Aerosp. Sci. Technol. 9, 211–221 (2005)CrossRefGoogle Scholar
  4. 4.
    Canell, K., Hass, N., Storch, A., Gruber, M.: HIFiRE direct-connect rig (HDCR) phase I scramjet test results from the NASA langley arc-heated scramjet test facility. In: 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, AIAA-2011-2248 (2011)Google Scholar
  5. 5.
    Waltrup, P.J., Billig, F.S., Stockbridge, R.D.: A procedure for optimizing the design of scramjet engines. J. Spacecr. Rockets 16, 163–172 (1979)CrossRefGoogle Scholar
  6. 6.
    Pinckney, S.Z.: Integral Performance Predictions for Langley Scramjet Engine Module. NASA TM-X-74038 (1978)Google Scholar
  7. 7.
    Henry, J.R., Anderson, G.Y.: Design considerations for the airframe integrated scramjet. In: 1st International Symposium on Air Breathing Engine, Marseille, June 1972; also NASA TMX-2895 (1973)Google Scholar
  8. 8.
    Billig, F.S., Dugger, G.L.: The interaction of shock waves and heat addition in the design of supersonic combustors. In: Twelfth Symposium (International) on Combustion, The Combustion Institute, Pittsburgh, pp. 1125–1134 (1969)Google Scholar
  9. 9.
    O\(^{\prime }\)Brien, T., Starkey, R., Lewis, M.: Quasi-one-dimensional high-speed engine model with finite-rate chemistry. J. Propuls. Power 17, 1366–1374 (2001)Google Scholar
  10. 10.
    Ferguson, F., Dhanasar, M.: A model for the design and analysis of thrust optimized ccramjets. In: 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, AIAA 2009–7337 (2009)Google Scholar
  11. 11.
    Bussing, T.R.A., Murman, E.M.: A One-Dimensional Unsteady Model of Dual Mode Scramjet Operation. AIAA Paper 83–0422 (1983)Google Scholar
  12. 12.
    Tian, L., Chen, L.H., Chen, Q., et al.: Quasi-one-dimensional multimodes analysis for dual-mode scramjet. J. Propuls. Power 30, 1559–1567 (2014)Google Scholar
  13. 13.
    Li, F., Yu, X.L., Gu, H.G., et al.: Measurement of flow parameters in a scramjet combustor based on near-infrared absorption. Chin. J. Theor. Appl. Mech. 43, 1061–1067 (2011). (in Chinese)Google Scholar
  14. 14.
    Daines, R., Segal, C.: Combined rocket and airbreathing propulsion systems for space-launch applications. J. Propuls. Power 14, 605–612 (1998)CrossRefGoogle Scholar
  15. 15.
    Castro, J., Brink, C., Mutzman, R., et al.: X51 session. In: Proceedings of 46th American Institute of Aeronautics and Astronautics Joint Propulsions Conf, American Institute of Aeronautics and Astronautics, Reston (2010)Google Scholar
  16. 16.
    Cao, R.F., Chang, J.T., Bao, W., et al.: Analysis of combustion mode and operating route for hydrogen fueled scramjet engine. Int. J. Hydrog. Energy 38, 5928–5935 (2013)CrossRefGoogle Scholar
  17. 17.
    Chen, Q., Chen, L.H., Gu, H.B., et al.: Investigation of the effect and optimization of heat release distributions in the combustor on scramjet performance. J. Propuls. Technol. 30, 135–138 (2009). (in Chinese)Google Scholar
  18. 18.
    Starkey, R.P., Lewis, M.J.: Sensitivity of hydrocarbon combustion modeling for hypersonic missile design. J. Propuls. Power 19, 89–97 (2003)CrossRefGoogle Scholar
  19. 19.
    Kirkpatrick, G., Gelatt Jr, C.D., Vecchi, M.P.: Optimization by simulated annealing. Science 220, 671–680 (1983)CrossRefMathSciNetzbMATHGoogle Scholar
  20. 20.
    Billig, F.S.: Research on Supersonic Combustion, 10th Aerospace Sciences Meeting and Exhibit, Reno, AIAA-92-0001 (1992)Google Scholar
  21. 21.
    Tian, L.: Investigation on Simplified Modeling and Its Application of Dual-Mode Scramjet Combustor [Master Thesis], University of Chinese Academy of Sciences, Beijing (2013)Google Scholar

Copyright information

© The Chinese Society of Theoretical and Applied Mechanics; Institute of Mechanics, Chinese Academy of Sciences and Springer-Verlag Berlin Heidelberg 2015

Authors and Affiliations

  • Lu Tian
    • 1
  • Li-Hong Chen
    • 1
    Email author
  • Qiang Chen
    • 1
  • Feng-Quan Zhong
    • 1
  • Xin-Yu Chang
    • 1
  1. 1.State Key Laboratory of High-Temperature Gas Dynamics, Institute of MechanicsChinese Academy of SciencesBeijingChina

Personalised recommendations