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The Strategy of using porous material in liquid fuel space propulsion injectors

Document Type : Original Article

Authors

1 PhD student , tarbiat modares university

2 Professor, mechanical Engineering Department, Tarbiat Modares University (TMU), Tehran, Iran

3 Aerospace Science and Technology Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology

Abstract

In the course of all-round advancement of engineering science, space research can be considered as the drivers of this forward movement. In the field of space propulsion, this trend can be seen as a backward trend, not in the sense of regression, but in the sense of optimizing the original designs used for space systems, which not only lead to the re-invention of these systems based on the acquisition of specific modern manufacturing technologies, but also strengthened the link between sciences such as Materials science and Mechanics science. In this research, according to the space propulsion system roadmap and also the review of old and reference designs, an attempt has been made to study some of the optimizations made in recent years and to express the weaknesses and challenges ahead. One of the ideas that optimizes, minimizes and increases the reliability of the space propulsion system is the injection of fuel through the porous media. The study of a type of showerhead injector expresses the formation path of the idea of using porous materials in the injection system and then the efficiency of these two types of injections is compared in a design that connects the porous material with the coaxial injector design.

Keywords

Main Subjects

Article Title [Persian]

The Strategy of using porous material in liquid fuel space propulsion injectors

Authors [Persian]

  • alireza moradi 1
  • fathollah ommi 2
  • Zoheir Saboohi 3

1 PhD student , tarbiat modares university

2 Professor, mechanical Engineering Department, Tarbiat Modares University (TMU), Tehran, Iran

3 Aerospace Science and Technology Research Institute, Aerospace Research Institute, Ministry of Science, Research and Technology

Abstract [Persian]

In the course of all-round advancement of engineering science, space research can be considered as the drivers of this forward movement. In the field of space propulsion, this trend can be seen as a backward trend, not in the sense of regression, but in the sense of optimizing the original designs used for space systems, which not only lead to the re-invention of these systems based on the acquisition of specific modern manufacturing technologies, but also strengthened the link between sciences such as Materials science and Mechanics science. In this research, according to the space propulsion system roadmap and also the review of old and reference designs, an attempt has been made to study some of the optimizations made in recent years and to express the weaknesses and challenges ahead. One of the ideas that optimizes, minimizes and increases the reliability of the space propulsion system is the injection of fuel through the porous media. The study of a type of showerhead injector expresses the formation path of the idea of using porous materials in the injection system and then the efficiency of these two types of injections is compared in a design that connects the porous material with the coaxial injector design.

Keywords [Persian]

  • Injector
  • Injector face plate
  • Porous material
  • Space propulsions
References
[1] Ommi, Fathollah, “History and Introduction to Liquid Fuel Rocket Design”, Tehran, Majed publishing, fall 1993.
[1] Deeken, Jan & Suslov, D. & Haidn, Oskar & Schlechtriem, Stefan. (2010). Design and testing of a porous injector head for transpiration cooled combustion chambers. 10.2514/6.2010-1595.
[2] "NASA Technology Roadmaps, TA 2: In-Space Propulsion Technologies," National Aeronautics and space administration, (2015).
[3] Armbruster, W., Hardi, J. S., Suslov, D., and Oschwald, M.(2018). Experimentalinvestigation of self-excited combustion instabilities withinjection coupling in a cryogenic rocket combustor. Acta Astronautica.151, 655–667.
[4] Börner, M., Deeken, J. C., Manfletti, C., and Oschwald, M.(2019). Experimental study of a laser ignited thruster with a porous injector head. International Journal of Energetic Materials and Chemical Propulsion.
[5] Börner, M., Manfletti, C., Hardi, J. S., Suslov, D., Kroupa, G., and Oschwald, M.(2018). Laser ignition of a multi-injector lox/methane combustor. CEAS Space Journal 10, 273–286.
[6] Kim, B.-D., Heister, S. D., and Collicott, S. H.(2005).Three-Dimensional Flow Simulations in the Recessed Region of a Coaxial Injector. Journal of Propulsion and Power, Vol. 21, No. 4, pp. 728–742.
[7] Zhaleh D, Ommi F, Saboohi Z.(2020). Numerical Investigation of Pore-Structure in Design of Catalytic Beds for Mono-Propellant Thrusters. Modares Mechanical Engineering. 20,193-202.
[8] URL: http://mme.modares.ac.ir/article-15-27494-en.html
[9] Gotzig, Ulrich & Schulte, Georg & Ehmann, Dieter & Riehle, Martin. (2005). New Generation of EADS Bipropellant Engines with Micro Showerhead Injector System. 10.2514/6.2005-4526.
[10] D. Kim, K. Lee, and J. Koo, (2014). Combustion Characteristics of a Coaxial Porous Injector. Journal of Propulsion and Power, Vol. 30, No. 6, pp. 1620–1627.
[11] U. Gotzig, E. Dargies. (2003). Development Status of Astriums New 22N Bipropellant Thruster Family. AIAA-4777
[12] Wood ward, R.D., Pal, S., Farhangi, S., Jensen, G.E., and Santoro, R.J. (2007). LOX/GH2 Shear Coaxial Injector Atomization Studies: Effect of Recess and NonConcentricity. AIAA Aerospace Sciences Meeting and Exhibit, AIAA Paper 2007-0571.
[13] Gill, G.S., and Nurick, W.H. (1976). Liquid Rocket Engine Injectors. NASA TR-SP-8089.
[14] Nunome, Y., Tamura, H., Onodera, T., Sakamoto, H., Kumakawa, A., and Inamura, T. (2009). Effect of Liquid Disintegration on Flow Instability in a Recessed Region of a Shear Coaxial Injector. AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA Paper.
[15] Bazarov, V., and Yang, V. (2004). Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design, AIAA, Reston, VA, Chap. 2.
[16] Strakey, P. A., Talley, D. G., and Hutt, J. J. (2001). Mixing Characteristics of Coaxial Injectors at High Gas/Liquid Momentum Ratios. Journal of Propulsion and Power, Vol. 17, No. 2, pp. 402–410. doi:10.2514/2.5756.
[17] Salgues, D., Mouis, A., Lee, S., Kalitan, D., Pal, S., and Santoro, R. (2006). Shear and Swirl Coaxial Injector Studies of LOX/GCH4 Rocket Combustion Using NonIntrusive Laser Diagnostics. 44th AIAA Aerospace Sciences Meeting and Exhibit, AIAA Paper 2006-0757.
[18] Glogowski, M. J., Bar-Gill, M., Puissant, C., Kaltz, T., Milicic, M., and Micci, M. M. (1994). Shear Coaxial Injector Instability Mechanisms. 30th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 1994-2774.
[19] Ferraro, M., Kujala, R. J., Thomas, J. L., Glogowski, M. J., and Micci, M. M. (2002).Effects of GH2/LOX Velocity and Momentum Ratios on Shear Coaxial Injector Atomization. Journal of Propulsion, Vol. 18, No. 1, pp. 209–211. doi:10.2514/2.5920.
[20] Mayer, W., and Kriille, G. (1995). Rocket Engine Coaxial Injector Liquid/Gas Interface Flow Phenomena. Journal of Propulsion and Power, Vol. 11, No. 3, pp. 513–518. doi:10.2514/3.23872.
[21] Mayer, W., Schik, A., Vielle, B., Chauveau, C., Gokalp, I., Talley, D., and Wood ward, R. (1998). Atomization and Break up of Cryogenic Propellants Under HighPressure Subcritical and Supercritical Conditions. Journal of Propulsion and Power”, Vol. 14, No. 5, pp. 835–842. doi:10.2514/2.5348
[22] Taylor, G. (1956). Fluid Flow in Regions Bounded by Porous Surfaces. Proceedings of the Royal Society of London, Series A: Mathematical and Physical Sciences, Vol. 234, No. 1199, pp. 456–475. doi:10.1098/rspa.1956.0050.
[23] Bazarov, V. G. (1993). A New Class of Porous Injectors for Combustion Chambers and Gas Generator. AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 1993-1955.
[24] Sozer, E., Shyy, W., and Thakur, S. (2006). Multi-Scale Porous Media Modeling for Liquid Rocket Injector Applications. AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit, AIAA Paper 2006- 5044.
[25] Kim, Dohun & Lee, Keonwoong & Koo, Jaye. (2016). Effects of Wall-Injection Length on Spray and Combustion in a Coaxial Porous Injector. JOURNAL OF PROPULSION AND POWER. 32. 10.2514/1. B35575.
Journal of Aerospace Science and Technology
Volume 13, Issue 2
October 2020
Pages 73-84
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