Abstract
For ideal nozzles, basically two different types of shock structures in the plume may appear for overexpanded flow conditions, a regular shock reflection or a Mach reflection at the nozzle centreline. Especially for rocket propulsion, other nozzle types besides the ideal nozzles are often used, including simple conical, thrust-optimized or parabolic contoured nozzles. Depending on the contour type, another shock structure may appear: the so-called cap-shock pattern. The exact knowledge of the plume pattern is of importance for mastering the engine operation featuring uncontrolled flow separation inside the nozzle, appearing during engine start-up and shut-down operation. As consequence of uncontrolled flow separation, lateral loads may be induced. The side-load character strongly depends on the nozzle design, and is a key feature for the nozzle’s mechanical structure layout. It is shown especially for the VULCAIN and VULCAIN 2 nozzle, how specific shock patterns evolve during transients, and how - by the nozzle design - undesired flow phenomena can be avoided.
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References
Hoffman, J.D.: Design of compressed truncated perfect nozzles. AIAA-85–1172 (1985)
Rao, G.V.R.: Exhaust Nozzle Contours for Optimum Thrust. Jet Propuls. 28(6), 377–383 (1958)
Rao, G.V.R.: Approximation of optimum thrust nozzle contours. ARS J. 30(6), 561 (1960)
Moelder, S., Gulamhussein. A., Timofeev, E., Voinovich, P.: Focusing of conical shocks at the centreline of symmetry. In: Proceedings of the 21st International Symposium on Shock Waves (1997)
Frey, M.: Behandlung von Strömungsproblemen in Raketendüsen bei Überexpansion. Ph.D. Dissertation, Institute of Aerodynamics and Gasdynamics, University of Stuttgart (2001)
Shapiro, A.H.: Compressile Fluid Flow. Wiley, New York (1953)
Moelder, S., Gulamhussein, A., Timofeev, E., Voinovich, P.: Focusing of conical shocks at the centreline of symmetry. In: Proceedings of the 21st International Symposium on Shock Waves (1997)
Hagemann, G., Immich, H., Nguyen, T., Dumnov, G.: Rocket engine nozzle concepts. Liquid rocket thrust chambers: aspects of modeling, analysis, and design. Progr. Astronaut. Aeronaut. vol. 200, 437–467 (2004)
Terhardt, M., Hagemann, G., Frey, M.: Flow Separation and side-load behaviour of the VULCAIN engine. AIAA 99–2762 (1999)
Hagemann, G., Frey, M., Koschel, W.: On the appearance of restricted shock separation in rocket nozzles. J. Power Propuls. 18(3), 577–584 (2002)
Hagemann, G., Preuss, A., Grauer, F., Frey, M., Kretschmer, J., Ryden, R., Jensen, K., Stark, R., Zerjeski, D.: Flow separation and heat transfer in high area ratio rocket nozzles. AIAA-2004-3684 (2004)
Watanabe, Y., Sakazume, N., Yonezawa, K., Tsujimoto, Y.: LE-7A engine nozzle separation phenomenon and the possibility of RSS suppression by the step inside the nozzle. AIAA-2004–4014 (2004)
Goetz, O., Monk, J.: Combustion device failures during space shuttle main engine development. In: Proceedings of the 5th International Symposium on Long Life Combustion Device Technologies, Chattanooga. 27–30 October 2003
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Communicated by K. Hannemann.
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Hagemann, G., Frey, M. Shock pattern in the plume of rocket nozzles: needs for design consideration. Shock Waves 17, 387–395 (2008). https://doi.org/10.1007/s00193-008-0129-y
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DOI: https://doi.org/10.1007/s00193-008-0129-y