Analysis of Thrust Chamber of 35 KN Cryogenic Engine and Sensitivity Analysis of Film Cooling Mass Flow Rate
Document Type : Original Article
Author
School of Aerospace Engineering, College of Interdisciplinary Science and Technology, University of Tehran, Tehran, Iran
Abstract
In this paper, using a developed software, the combustion process inside the cryogenic engine is simulated one-dimensionally and using the equilibrium solution. The propellants are kerosene_LOx. In this regard, models for combustion and nozzle analysis have been used. By using this software, initially, the behavior of the cryogenic motor at the design point is simulated. Then the sensitivity analysis has been done on the film cooling flow percentage. The results of the analysis at the design point show the accuracy of the engine performance. The results of the sensitivity analysis show that the temperature of the combustion chamber has an increasing-decreasing behavior based on the percentage of flow rate, because the fuel-to-air ratio of the combustion chamber approaches the stoichiometric number for some flow rates and then falls away, but the molar mass of the gases has changed and as a result of the impact The specific and characteristic speed of the behavior has a decreasing behavior in terms of the increase in flow rate, so that increasing the cooling percentage up to 20% reduces the specific impact by 7 seconds.
Keywords
Subjects
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[2] J. Bradford, A. Charania and B. S. Germain, "REDTOP-2: Rocket Engine Design Tool Featuring Engine Performance, Weight, Cost, and Reliability," in 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit , Fort Lauderdale, Florida, AIAA-2004-3514, p.1-18, 2004.
[3] McBRIDE and GORDON, "Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and R efleaed Shocks, and Chapman-Jouguet Detonations," NASA SP-73, 1976.
[4] A. Ponomarenko, "RPA: Thermal Analysis of Thrust Chambers.," 2012.
[5] M. EidiAttarZade, M. Farshchi, A. Sarabadani, h. khosrobeygi, g. Davarnia and A. Ramezani, "Investigation of injector dimension on the performance of combustion chamber of a bi-propelant thruster," Fuel and Combustion, vol. 13, no. 4, pp. 63-78, 2020.
[6] "http://sierraengineering.com/ROCCID/roccid.html," [Online], [July 18, 2024].
[7] K. J. Davidian, "Comparison of Two Procedures for Predicting Rocket Engine Nozzle Performance," in 23rd Joint Propulsion Conference, San Diego, CA, U.S.A., AIAA-87-2071, 1987.
[8] C. Manfletti, "Start-Up Transient Simulation of a Pressure Fed LOx/LH2 Upper Stage Engine Using the Lumped Parameter-based MOLIERE Code," in 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Nashville, 2010.
[9] H. L. Gray, "Modelling of combustion processes in small liquid bipropellant thruster," in 28th Joint Propulsion Conference and Exhibit, Nashville, 1992.
[10] M. EidiAttarZade, A. SarAbadani, G. Davarnia, H. Khosrobeygi, M. Farshchi and A. Ramezani, "Investigation of a Bi-propellant Thruster by a Developed Space Engine’s Thrust Chamber Analysis Code," Journal of Space Science & Technology, p. In persian, 2020.
[11] J. Hayashi, H. Tani, N. Kanno, D. Sato, Y. Daimon, F. Akamatsu and J. Gabl, "Multilayer reaction zones of a counterflow flame of gaseous Nitrogen Tetroxide and a liquid Monomethylhydrazine pool," Combustion and Flame, vol. 201, p. 244–251, 2019.
[12] S. Nonnenmacher and M. Piesche, "Design of hollow cone pressure swirl nozzles to atomize Newtonian fluids," Chemical Engineering Science , vol. 55, no. 19, pp. 4339-4348, 2000.
[13] N. K. Rizk and A. H. Lefebvre, "Internal flow characteristics of simplex swirl atomizers," Journal of propulsion and power, vol. 1, no. 3, pp. 193-199, 1985.
[14] S. Kim, T. Khil, D. Kim and Y. Yoon, "Effect of geometric parameters on the liquid film thickness and air core formation in a swirl injector." 20, no. 1 (2008): 015403.," Measurement Science and Technology, vol. 20, no. 1, 2008.
[15] N. K. Rizk and A. H. Lefebvre, "Prediction of velocity coefficient and spray cone angle for simplex swirl atomizers," in Proceedings of the 3rd International Conference on Liquid Atomization and Spray Systems, London, 1985.
[16] P. Fu, L. Hou, Z. Ren, Z. Zhang, X. Mao and Y. Yu, "A droplet/wall impact model and simulation of a bipropellant rocket engine," Aerospace Science and Technology, vol. 88, pp. 32-39, 2019.
[17] H. Kang, H. Kim, S. Heo, S. Jung and S. Kwon, "Experimental analysis of hydrogen peroxide film-cooling method for nontoxic hypergolic thruster," Aerospace Science and Technology, vol. 71, p. 751–762, 2017.
[18] S. Tauchi, C. Inoue, Z. Wang, Y. Daimon and G. Fujii, “Optimal Liquid Engine Architecture by Performance-Cooling Tradeoff Analysis”, Journal of Propulsion and Power, Vol. 40, No. 4, p. 631-641, 2024, https://doi.org /10.2514/1.B39409.
[19] H. Tani, H. Terashima, Y. Daimon, M. Koshi and R. Kurose, "A Numerical Study on Hypergolic Combustion of Hydrazine Sprays in Nitrogen Tetroxide Streams," Combustion Science and Technology, Vols. 190,, p. 515–533, 2017.
[20] Y.H. Kang, H.J. Ahn, C.H. Bae, J.S. Kim, J.W. Lee and J.H. Kim, Performance Characteristics of the Film-cooling System Applied to 200 N-class GCH4-LOx Small Rocket Engine, AIAA 2023-0717, p. 1-9, 2023.
[21] G. Fujii, Y. Daimon, K. Furukawa, C. Inoue, D. Shiraiwa and N. Tanaka, “Visualization of Coolant Liquid Film Dynamics in Hypergolic Bipropellant Thruster”, Journal of Propulsion and Power, Vol. 38, No. 2, 2022, https://doi-org.access.semantak.com/10.2514/1.B38421.
[22] G. P. Sutton and O. Biblarz, Liquid, 7th ed., New York: John Wiley & Sons, 2001, p. 197–240.
[23] J. D. Anderson, Modern compressible flow : with historical perspective, Boston: McGraw-Hill, 2003.
Volume 4, Issue 2
March 2025Pages 14-23
- Receive Date 09 June 2024
- Revise Date 19 July 2024
- Accept Date 20 November 2024