Startup Analysis Simulator for a Small Staged Combustion–Cycle Engine Powerpack
Publication: Journal of Aerospace Engineering
Volume 30, Issue 6
Abstract
In general, staged combustion-cycle engines have higher propulsion efficiency than that of open-cycle engines, prompting further research to develop the next generation of the former type of engines. Especially when it is on the development stage, a liquid rocket engine system may show unpredictable behavior affected by pressure and/or temperature variation. In addition, it is more dangerous when the engine is on the starting process. Therefore, prediction of the engine start up is very important both for the development of liquid rocket engines, and for preventing unfortunate accidents. In this study, a startup analysis simulator was developed for staged combustion-cycle engine powerpacks. This simulator can predict such various engine parameters as propellant flow rates, pressures temperature, and rotational speed of the turbopumps as functions of time. It is validated by comparison to real combustion test results. The tests were performed for an 8-tonf class engine. As a result, this simulator showed good agreement with the test results, not only qualitatively, but also quantitatively. This study confirms that the proposed simulator is suitable for starup analysis; furthermore, it can indicate appropriate startup operation.
Get full access to this article
View all available purchase options and get full access to this article.
References
Gordon, S., and McBride, B. J. (1996). “Computer program for calculation of complex chemical equilibrium compositions and applications. II: Users manual and program description.”, National Aeronautics and Space Administration, Cleveland.
Jung, T., and Han, S. (2015). “Pipe flow model for a liquid rocket engine startup analysis.” Proc., Society for Aerospace System Engineering Conf., Society for Aerospace System Engineering, Daejeon, Korea, 11–14.
Kanumuri, A., Wakamatsu, Y., Shimura, T., Toki, K., and Torii, Y. (1985). “Start transient analysis of turbopump-fed LOX/LH2 rocket engine (LE-5).”, National Aerospace Laboratory of Japan, Tokyo.
Karimi, H., and Mohammadi, R. (2007). “Modeling and simulation of a two combustion chambers liquid propellant engine.” Aircr. Eng. Aerosp. Technol., 79(4), 390–397.
Karimi, H., and Nassirharand, A. (2006). “Application of a simulation algorithm to a specific liquid propellant engine with experimental verification.” Aircr. Eng. Aerosp. Technol., 78(2), 132–137.
Kim, S. H., Ko, T. H., Jeong, Y. S., and Yoon, W. S. (2014). “Modeling of liquid rocket engine system transient during engine start up and thrust control.” Proc., 13th Space Launch Vehicle Technology Symp., Korean Society for Aeronautical & Space Sciences, Seoul, 54–59.
Lee, S., and Moon, I. (2014). “A study on the start transient analysis of the staged combustion cycle engine.” Proc., Korean Society Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 634–638.
Lee, S., and Moon, I. (2015). “Simulator development for startup analysis of staged combustion cycle engine powerpack.” J. Korean Soc. Propul. Eng., 19(5), 62–70.
Lee, S. Y., and Moon, I. (2012). “A study on the characteristics of staged combustion cycle engine.” Proc., Korean Society Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 457–460.
Moon, I., Ha, S., Lee, S., and Lee, S. Y. (2013). “A study on the temperature distribution at the exit of oxygen rich preburners.” J. ILASS-Korea, 18(1), 27–34.
Moon, I., Lee, S. Y., Moon, I. Y., and Lee, S. (2016). “Development of ultra lean burn preburners for small liquid engines.” J. Propul. Power, 32(4), 1040–1043.
Moon, Y., Kim, S. H., Kim, C. W., and Seol, W. S. (2009). “Prediction of startup characteristic for 30 tonf liquid rocket engine TP-GG-CC coupled test.” Proc., Korean Society Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 62–65.
Nam, C. H., and Park, S. Y. (2013). “A study on start-up of 75tonf thrust class liquid propellant rocket engine.” Korean Soc. Mech. Eng., 2013(5), 206–208.
Park, S., Chio, H., and Seol, W. (2004). “Transient analysis of liquid rocket engine around the nominal thrust level.” Proc., Korean Society Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 68–76.
Park, S., and Cho, W. K. (2008). “Program development for the mode calculation of gas-generator cycle liquid rocket engine.” Proc., Korean Soc. Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 366–370.
Park, S. Y., Nam, C. H., Moon, I. S., and Seol, W. S. (2005). “A study on the start transient analysis of the turbopump-fed liquid rocket engine.” J. Aerosp. Technol., 4(2), 142–152.
Park, S. Y., and Seol, W. S. (2007). “Numerical analysis on the startup of a rocket engine.” J. Korean Soc. Propuls. Eng., 11(5), 60–71.
Paulo, C. L. (1998). “Dynamic models for liquid rocket engines with health monitoring application.” M.Sc. thesis, Massachusetts Institute of Technology, Cambridge, MA.
Son, M., Kim, D., and Koo, J. (2010). “Analysis of transient characteristics for turbopump-fed liquid propellant rocket engine in start-up.” Proc., Korean Society Propulsion Engineers Conf., Korean Society of Propulsion Engineers, Daejeon, Korea, 34–37.
Tabrizi, M. N., Chime, S. A. R. J., and Karimi, H. (2013). “Modeling and simulation of open cycle liquid propellant engines.” J. Sci. Eng., 1(1), 17–37.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 30 • Issue 6 • November 2017
Copyright
©2017 American Society of Civil Engineers.
History
Received: Jul 27, 2016
Accepted: Feb 9, 2017
Published online: Jul 27, 2017
Published in print: Nov 1, 2017
Discussion open until: Dec 27, 2017
Authors
Metrics & Citations
Metrics
Citations
Download citation
If you have the appropriate software installed, you can download article citation data to the citation manager of your choice. Simply select your manager software from the list below and click Download.