THERMAL SCIENCE

International Scientific Journal

NUMERICAL ANALYSIS OF THE FLOW DYNAMICS OF AN N2 CRYOGENIC JET

ABSTRACT
Injection and mixing of cryogenic propellants are very complex at near-critical and supercritical conditions. The concise description and the reliable measurements on such flows are still questionable. In this work, a RANS study is performed for a pure N2 fluid injection at transcritical conditions on a laboratory scale test rig. An in-depth thermodynamical analysis on the real-gas behavior has allowed N2 density prediction over the experimental range of the injection temperature and for several equations of state. A focus was thrown on the prediction of the density evolution on the chamber centerline and across the injector. The calculations were performed using both adiabatic and constant temperature conditions for the injector wall. The inner heat transfer in the injector had a significant effect on the jet density distribution and therefore, on the overall flow dynamics. Numerical results regarding axial profiles of density and dense core lengths agree fairly well with the experimental data provided by the literature.
PAPER SUBMITTED: 2019-08-05
PAPER REVISED: 2020-02-27
PAPER ACCEPTED: 2020-03-27
PUBLISHED ONLINE: 2020-05-02
DOI REFERENCE: https://doi.org/10.2298/TSCI190805162B
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2021, VOLUME 25, ISSUE Issue 2, PAGES [1573 - 1586]
REFERENCES
  1. Lu, F. K., Braun, E. M., Rotating Detonation Wave propulsion: Experimental Challenges Modelling, and Engine Concepts, Journal of Propulsion and Power, 30 (2014), 5, pp. 1125-1142
  2. Haidn, J., Habiballah, M., Research on High Pressure, Cryogenic Combustion, Aerospace Science and Technology, 7 (2003), 6, pp. 473-491
  3. Gomet, L., et al., Lagrangian Modelling of Turbulent Spray Combustion under Liquid Rocket Engine Conditions, Acta Astronautica, 91 (2014) 1, pp. 184-197
  4. Vigneshwaran, S., et al., Wall Heat Flux Mapping of Liquid Rocket Thrust Chamber with Multi-Attitude GH2/GO2 Jets, Proceedings, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, Atlanta, Geo., USA, 4766, 2017
  5. Candel, S., et al., Advances in Combustion and Propulsion Applications, European Journal of Mechanics B/Fluids, 40 (2003), July-Aug., pp. 87-106
  6. Oschwald, M., et al., Injection of Fluids into Supercritical Environments, Combustion Science and Technology, 178 (2006), 1-3, pp. 49-100
  7. Jarczyk, M., Pfitzner, M., Large Eddy Simulation of Supercritical Nitrogen Jets, Proceedings, 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Nashville, Tenn., USA, 2012, p. 1270
  8. Mayer W., Kruelle, G., Rocket Engine Coaxial Injector Liquid/Gas Interface Flow Phenomena, Journal of Propulsion and. Power, 11 (1995), 3, pp. 513-518
  9. Mayer, W., Tamura, H., Propellant Injection in a Liquid Oxygen/Gaseous Hydrogen Rocket Engine, Journal of Propulsion and Power, 12 (1996), 6, pp. 1137-1147
  10. Smith, J., et al., Supercritical LOX/Hydrogen Rocket Combustion Investigations Using Optical Diagnostics, Proceedings, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Indianopolis, Ind., USA, 2002, p. 4033
  11. Candel, S., et al., Experimental Investigation of Shear Coaxial Cryogenic Jet Flames, Journal of Propulsion and Power, 14 (1998), 5, pp. 826-834
  12. Mayer, W., Raman Measurements of Cryogenic Injection at Supercritical Pressure, Heat and Mass Transfer, 39 (2003), July, pp. 709-719
  13. Chehroudi, B., Raman Scattering Measurements in the Initial Region of Sub- and Supercritical Jets, Proceedings, 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Ala., USA, 2000, p. 3392
  14. Oschwald, M., Schik, A., Supercritical Nitrogen Free Jet Investigated by Spontaneous Raman Scattering, Experiments in Fluids, 27 (1999), Nov., pp. 497-506
  15. Branam, R., Mayer, W., Characterization of Cryogenic Injection at Supercritical Pressure, Journal of Propulsion and Power, 19 (2003), 3, pp. 342-355
  16. Oefelein, J. C., Mixing and Combustion of Cryogenic Oxygen-Hydrogen Shear-Coaxial Jet Flames at Supercritical Pressure, Combustion Science and Technology, 178 (2006), 1-3, pp. 229-252
  17. Hosangadi, A., et al., The 3-D Hybrid RANS/LES Simulations of a Supercritical Liquid Nitrogen Jet, Proceedings, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Hartford, Conn., USA, 2008, p. 5227
  18. Schmitt, T., et al., Large-Eddy Simulation of transcritical flows, C. R. Mecanique, 337 (2009), 6-7, pp. 528-538
  19. Cheng, G. C., Farmer, R., Real Fluid Modelling of Multi-Phase Flows in Liquid Rocket Engine Combustors, Journal of Propulsion and Power, 22 (2006), 6, pp. 1373-1381
  20. Poschner, M., Pfitzner, M., Real gas CFD simulation of supercritical H2-LOX combustion in the Mascotte Single-Injector Combustor Using a Commercial CFD Code, Proceedings, 46th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nev., USA, 2006, p. 952
  21. Kim, T., et al., Numerical Analysis of Gaseous Hydrogen/Liquid Oxygen Flamelet at Supercritical Pressures, International Journal of Hydrogen Energy, 36 (2011), 10, pp. 6303-6316
  22. Riahi, Z., et al., Numerical Study of Turbulent Normal Diffusion Flame CH4-AIR Stabilized by Coaxial Burner, Thermal Science, 17 (2013), 4, pp. 1207-1219
  23. Benmansour, A., et al., A 3-D Numerical Study of LO2/GH2 Supercritical Combustion in the ONERA Mascotte Test-Rig Configuration, Journal of Thermal Science, 25 (2016), 1, pp. 97-108
  24. Benarous, A., Liazid, A., H2-O2 Supercritical Combustion Modelling Using a CFD Code, Thermal Science, 13 (2009), 3, pp. 139-152
  25. Kim, T., et al., Real-Fluid Flamelet Modelling for Gaseous Hydrogen/Cryogenic Liquid Oxygen Jet Flames at Supercritical Pressure, Journal of Supercritical Fluids, 58 (2011), 2, pp. 254-262
  26. De Giorgi, M., et al., Application and Comparison of Different Combustion Models of High Pressure LOX/CH4 Jet Flames, Energies, 7 (2014), 1, pp. 477-497
  27. Kim, S. K., et al., Thermodynamic Modelling Based on a Generalized Cubic Equation of State for Kerosene/LOx Rocket Combustion, Combustion and Flame, 159 (2012), 3, pp. 1351-1365
  28. Müller, H., et al., Large-Eddy Simulation of Nitrogen Injection at Trans- and Supercritical Conditions, Physics of Fluids, 28 (2016), 015102
  29. Soave, G., Equilibrium Constants from a Modified Redlich-Kwong Equation of State, Chemical Engineering Science, 27 (1972), 6, pp. 1197-1203
  30. Peng, D. Y., Robinson, D. B., A New Two-Constant Equation of State, Industrial and Engineering Chemistry Fundamentals, 15 (1976), 1, pp. 59-64
  31. Aungier, R. H., A Fast, Accurate Real Gas Equation of State for Fluid Dynamic Analysis Applications, Journal of Fluids Engineering, 117 (1995), 2, pp. 277-281
  32. Launder, B. E., et al., Prediction of Free Shear Flows - A Comparison of Six Turbulence Model, NASA Langley Res. Center Free Turbulent Shear Flows, USA, 1973, Vol.1, pp. 361-426
  33. Cheng, G. C., Farmer, R., Development of Efficient Real-Fluid Model in Simulating Liquid Rocket Injector Flows, Proceedings, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Ala., USA, 2003, p. 4466
  34. Pope, S. B., An Explanation of the Turbulent Round-jet/plane-jet Anomaly, AIAA Journal, 16 (1978), 3, pp. 279-281
  35. Harsha, P. T., Free Turbulent Mixing: A Critical Evaluation of Theory and Experiment, Turbulent Shear Flows, CP-93, AGARD, 1971
  36. Chehroudi, B., et al., Initial Growth Rate and Visual Characteristics of a Round Jet into a Sub- to Supercritical Environment of Relevance to Rocket, Gas Turbine, and Diesel Engines, Proceedings, 37th Aerospace Sciences Meeting and Exhibit, Reno, Nev., USA, 1999. p. 206
  37. Bensalem, C., et al., Vers la caractérisation du mélange en sortie d'un injecteur coaxial cryotechnique: Influence de la loi de comportement (Towards the characterization of the mixture at the output of a cryogenic coaxial injector: Influence of the law of behavior - in French), Proceedings, 23th Congrès Français de Mécanique, Lille, France, 2017, S11, 130196
  38. Haidn, O. J., Atomization, Combustion, and Heat Transfer, Second International Workshop on Rocket Combustion Modelling, Lampoldshausen, Germany, 2001
  39. ***, ANSYS FLUENT v16.2, Inc., Canon-sburg, PA, USA, 2016
  40. Cheng, G. C., Farmer, R., The CFD Simulation of Liquid Engine Rocket Injectors Part 1, Simulations of the RCM-1 Experiments, Proceedings, 2nd International Workshop on Rocket Combustion Modelling, Lampoldshausen, Germany, 2001
  41. Banuti, D. T., Hannemann, K., The Absence of a Dense Potential Core in Supercritical Injection: A Thermal Break-up Mechanism, Physics of Fluids, 28 (2016), 035103

© 2024 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, National Institute of the Republic of Serbia, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence