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http://dx.doi.org/10.5139/JKSAS.2015.43.7.593

Fuel-Rich Combustion Characteristic of a Combined Gas Generator  

Lee, Dongeun (Department of Aerospace Engineering, Konkuk University)
Lee, Changjin (Department of Aerospace Engineering, Konkuk University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.43, no.7, 2015 , pp. 593-600 More about this Journal
Abstract
In this study, a combined hybrid rocket system is newly introduced which has characteristics of both gas generators and afterburner type hybrid rockets. In particular, a combined gas generator utilizing solid fuel and liquid/gas oxidizer was designed as a primary combustor of the system. Combustion tests were carried out with various equivalence ratio affected by parameters such as fuel length, oxidizer flow rate, fuel port diameter and fuel type. In general, fuel-rich gas generator produces low combustion gas temperature to meet the temperature requirement and the target temperature was transiently set less than 1600 K. Since it was found that controlling parameters showed limited effects on the change of equivalence ratio, mixture of $O_2$ and $N_2$ as an oxidizer was additionally introduced. As a result, a combined gas generator successfully produced combustion gas temperature of less than 1600 K Future studies will carry out more combustion tests to attain fuel-rich combustion gas temperature less than 1200 K, which was a temperature requirement of a gas generator system in the previous studies.
Keywords
Fuel-Rich Combustion; Gas Generator; Combined Hybrid Rocket;
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  • Reference
1 Shackelford, B., "The Hybrid Propulsion Technology Program Phase 1," NAS8-37777, Vol. 3, 1989.
2 Shackelford, B., "The Hybrid Propulsion Technology Program Phase 1," NAS8-37777, Vol. 4, 1989.
3 Kuo, K. K., Lu, Y. C., Chiaverini, M. J., Johnson, D. K., Serin, N., Risha, G. A., Merkle, C. L., and Venkateswaran, S., "Fundamental Phenomena On Fuel Decomposition and Boundary-Layer Combustion Processes with Applications to Hybrid Rocket Motors," NAS8-39945, 1996.
4 Rajesh, K. K., "Thrust Modulation in a Nitrous-Oxide/Hydroxyl-Terminated Polybutadiene Hybrid Rocket Motor," 42nd AIAA Joint Propulsion Conference & Exhibit, AIAA 2006-4503, 2006.
5 Pastrone, D., "Approaches to Low Fuel Regression Rate in Hybrid Rocket Engines," Hindawi Publishing Corporation International Journal of Aerospace Engineering, Vol. 2012, Article ID 649753, 2012.
6 Pilon, B., and Louwers, J., "Development of Staged Combustion Aft-Injected Hybrid (SCAIH) Propulsion at Cesaroni Technology Inc," 46th AIAA Joint Propulsion Conference, AIAA 2010-6786, 2010.
7 Pilon, B., "Investigation of Injector System and Gas Generator Propellant For Aft-Injected Hybrid Propulsion," master's thesis, Carleton University, Canada, 2006.
8 Humble, R. W., Henry, G. N., and Larson, W. J., "Space Propulsion Analysis and Design," McGraw-Hill, lnc., New York, 1995
9 Korting, P. A. O. G., Schoyer, H. F. R., and van der Geld, C. W. M., "On the Use of an Ultrasonic Pulse-Echo Technique for Regression Rate Analysis," SFCC publication, No. 24, 1987.
10 Sutton, G. P., and Biblarz, O., "Rocket Propulsion Elements," 7th Ed., John Wiley & Sons Inc., New York, 2001, pp.579-606.