THERMAL SCIENCE

International Scientific Journal

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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 Reynolds Averaged Navier-Stokes (RANS) study is performed for a pure N2 fluid injection at transcritical conditions on a laboratory scale test rig. An indepth 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 (EoS). 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
REFERENCES
  1. Lu, F.K., Braun, E.M., Rotating Detonation Wave propulsion: Experimental Challenges Modeling, 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), 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, 4766, 2017
  5. Candel, S., et al., Advances in combustion and propulsion applications, European Journal of Mechanics B/Fluids 40 (2003), pp. 87-106
  6. Oschwald, M., et al., Injection of Fluids into Supercritical Environments, Combustion Science and Technology 178 (2006), 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, 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, 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), 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, 2000, p. 3392
  14. Oschwald, M., Schik, A., Supercritical nitrogen free jet investigated by spontaneous Raman scattering, Experiments in Fluids 27 (1999), 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., Three-Dimensional Hybrid RANS/LES Simulations of a Supercritical Liquid Nitrogen Jet, Proceedings, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2008, p. 5227
  18. Schmitt, T., et al., Large-Eddy Simulation of transcritical flows, C.R. Mécanique 337 (2009), pp. 528-538
  19. Cheng, G. C., Farmer, R., Real Fluid Modeling of Multiphase 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, 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), 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 3D 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 modeling using a CFD code, Thermal Science 13 (2009), 3, pp. 139-152
  25. Kim, T., et al., Real-Fluid Flamelet Modeling 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 modeling based on a generalized cubic equation of state for kerosene/LOx rocket combustion, Combustion and Flame 159 (2012), 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), pp. 1197-1203
  30. Peng, D.Y., Robinson, D.B., A new two-constant equation of state, Industrial and Engineering Chemistry Fundamentals 15 (1976), 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), 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. 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., 1999. 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. 1999. p. 206
  37. Bensalem, C., et al., 2017. 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), Proceedings, 23ème Congrès Français de Mécanique, Lille, French, 2017, S11, 130196
  38. Haidn, O. J., Second (2nd) International Workshop on Rocket Combustion Modeling. March 25-27. Lampoldshausen, Germany, 2001
  39. ***, Ansys Fluent v16.2, Inc., Canonsburg, PA, USA, 2016.
  40. Cheng, G. C., Farmer, R., CFD Simulation of Liquid Engine Rocket Injectors Part 1. Simulations of the RCM-1 Experiments, Proceedings, Second (2nd) International Workshop on Rocket Combustion Modeling, 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