Experimental determination of the suitable rang of injectors used in the vortex combustion chamber in liquid rocket engine

Document Type : Research Paper

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Abstract

Vortex combustion chamber which is a new generation of liquid fuel engine with different arrangements of injectors generated a vortex flow into the combustion chamber. This vortex contributed to increased cooling and mixing the components of the propellant in the combustion chamber and can be generated a complete combustion in a small volume chamber. In this chamber several type of injector used in various locations including, centrifugal, flow and vortex injectors. In this study, the design of these injectors and then experimental test to investigate the effect of geometrical parameters on their hydrodynamic characteristics is done using water flow. Spry forming process, flow measurement, pressure drop and injector spray angle including hydrodynamic characteristics that have been studied. The results show acceptable agreement of the predicted design with performance of injectors. Accordingly, centrifugal and flow injectors that injected the fuel and oxidizer into the chamber were selected and shown that increasing the number of tangential vortex injectors to 6, generated more uniformity in the rising vortex flow in the chamber but the entry angle to 5 degrees no significant effect on rising flow.

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References

[1] Y.H Zahao, M.H Hou, J.S Chin, Drop Size Distribution from Swirl and Air-blast Atomizer, Atomization and Spray Technology, Vol. 17, pp. 3-15, 1986.
[2] D.H. Taylor, B.E. Walshm, Combustion Processes in a Medium Diesel Enggin, The Inst. Eng, Vol. 202, pp. 67-76, 1986.
[3] D. Sivakumar, B.N.R., Role of geometric parameteres on the drop size characterisitics of liquid-liquid coaxial swirl atomizers,  Atomization and Spray Technology, Vol. 14, pp. 547-563, 1998.
[4]. A. Karegar, Layout optimization model of injectors in injector page by using cold test results, Master's thesis, Department of Mechanical Engineering, Tarbiat Modares University, Tehran, 2006. (in Persianفارسی )
[5]. A.J. Yule, , R.A. Shen, , J.R. Jeong, G.G Nasr, D.D. James, The Performance Characteristics of Solid – Cone – Spray Pressure–Swirl Atomizersو Atomization and sprays, Vol. 10, pp. 627-646, 1990.
[6] R. D. Rietz, F. V Bracco, Mechanisms of breakup of Round liquid Jes, The Encyclopedia of Fluid Mechanics, Cheremisnof N., Gulf Publishing, Houston, Texas , Vol.3, chap. 10 , pp. 233-249, 1986.
[7] H.I, Makkarti, S.C. Molvi, Science and Engineering of Droplets: Fundamentals and Application, William Andrew Publishing, chap. 5, pp.121-137, 2000.
[8] R. W. Tate, Spray patternation, Ind. Eng. Chem, Vol. 52, No.10, pp. 49-52, 1960.
[9] V.M Kodryatcev, V.A. Kuznetsov, Fundamental of theory and calculation of liquid propulsion rockets, Moscow chap. 6, pp. 78-95, 1993.
[10]. F. Ommi, Engine and spacecraft propulsion, Tehran,Besat Publishers, chap 5, pp. 47-80, 2010. (in Persianفارسی )
[11] E. Valizadeh, M.J. Montazeri, M.R. Eshkevari and M. Dadkhah, Scenario of mass & energy parametrs optimization of specific liquid propellant engine and hot test, The Eighth Annual Conference of the Association of Aerospace, Malek Ashtar University, 2009. (in Persianفارسی )
[12] A. Saghari, Study of vortex combustion chamber performance in Missile and space propulsion systems, Master's thesis, Malek Ashtar University, 2010. (in Persianفارسی )
[13] M. J. verini, M.J. Malecki, J.A. Sauer, W. H. Knuth, Vortex Combustion Chamber Development for Future Liquid Rocket Engine Applications, AIAA Paper 2149, 2002.
[14] L. Gongnan, Design and simulation of gas oxygen/ methane vortex cooling thrust chamber, The 64th International Astronautical Congress, Beijing, China, 2013.
[15] J. Martin Chiaverini, J. Majdalani, Vortex Thrust Chamber Testing and Analysis for O2-H2 Propulsion Applications, The 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, July 2003.
[16] K. Ramamurthi, Journalof, Experimental study of liquid sheets formed in coaxial swirl injectors, Propulsion and Power, Vol. 14, pp. 1103-1109, 1995.
[17]. S.A. Esfehani, Proposing a Model to design of a bipropellant atomizer and its experimental testing, Master's thesis, Malek Ashtar University, 2012. (in Persianفارسی )
[18]. E. Valizadeh, S. M. Mousavi Naeenian, M. M. [18]. E. Valizadeh, S. M. Mousavi Naeenian, M. M. Heydari, H. Saadati, Numerical analysis of the flow in vortex combustion chamber simulator cylinder of liquid propellant engines and its experimental test, Modares Mechanical Engineering Journal, Vol. 15, No. 9, pp. 313-321, 2014. (in Persianفارسی )

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