Numerical study of the effect of air injection before fuel injection in supersonic air crossflow

Document Type : Research Paper

Authors

Tarbiat Modares University

Abstract

Transverse fuel injection in supersonic crossflow of scramjet combustors is one of the common methods for fuel-air mixing. Air jet injection before fuel jet can improve fuel penetration but with the excess stagnation pressure loss. In this paper, the position of air jet is changed to find the position that maximum fuel jet penetration height and minimum stagnation pressure loss is achieved. For numerical simulations, Two-dimensional Navier-Stokes equations and k-ω sst turbulence model and the perfect gas equation are solved. Then the results of the numerical solution are compared and validated with experimental data. Numerical results showed good agreement with the experimental values. In the experimental test, Helium is injected into supersonic crossflow and so numerical simulation is started with Helium injection. In scramjet usually, hydrogen was used as fuel. Therefore, hydrogen fuel injection is used for the parametric study. In the case of air injection near the fuel injection, maximum fuel penetration with minimum stagnation pressure loss is achieved.

Keywords

References

[1] Martin, Michael A., Huy H. Nguyen, William D. Greene, and David C. Seymout, Transient mathematical modeling for liquid rocket engine systems: Methods, capabilities, and experience, 5th International Symposium on Liquid Space Propulsion, Chattanooga, TN; United States, Oct 27-30. 2003.
[2] Sutton, George P., and Oscar Biblarz. Rocket propulsion elements. John Wiley & Sons, pp. 223-225, 2016.
[3] Binder, Michael, Thomas Tomsik, and Joseph P. Veres. RL10A-3-3A rocket engine modeling project, NASA Technical Report, 1997.
[4] Binder, Michael. A transient model of the RL10A-3-3A rocket engine. In 31st Joint Propulsion Conference and Exhibit, p. 2968. 1995.
[5] Binder, Michael. An RL10A-3-3A rocket engine model using the Rocket Engine Transient Simulator (ROCETS) software. 29th Joint Propulsion Conference and Exhibit. 1993.
[6] Di Matteo, Francesco. Modelling and simulation of liquid rocket engine ignition transients. PhD Thesis, Department of Aerospace Engineering, SAPIENZA University, Roma, 2010..
[7] Di Matteo, Francesco, Marco De Rosa, and Marcello Onofri. Start-up transient simulation of a liquid rocket engine. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. 2011.
[8] Di Matteo, Francesco, Marco De Rosa, and Marcello Onofri. Transient simulation of the RL-10A-3-3A rocket engine. Space Propulsion Conference. 2012.
[9] A. Santana Jr., F.I. Barbosa, M. Niwa, L.C.S. Goes, Modeling and Robust Analysis of a Liquid Rocket Engine, 36th Joint Propulsion Conference & ExhibitHuntsville, Alabama, July 2000.
[10] H. Karimi, A. Nassirharand, and M. Beheshti, Dynamic and Nonlinear Simulation of Liquid Propellant Engines, AIAA Journal of Propulsion and Power, pp. 938-944, vol. 19, no. 5, 2003
[11] A. Kanmuri, T. Kanda, Y. Wakamatsu, Y. Torri and E. Kagawa, K. Hasegawa, Transient Analysis of LOX/LH2 Rocket Engine (LE-7), 25th Joint Propulsion Conference & ExhibitHuntsville, Monterey, CA, July 10-12, 1989
[12] Liu Kun, Zhang Yulin, Study on Versatile Simulation of Liquid Propellant Rocket Engine Systems Transients, 36th Joint Propulsion Conference & Exhibit Huntsville, Huntsville, AL, July 17-19, 2000
[13] D. Ramesh, M. Aminpoor, Nonlinear, Dynamic Simulation of an Open Cycle Liquid Rocket Engine, 43th Joint Propulsion Conference & Exhibit Huntsville, Cincinnati, OH, July8 - 11 , 2007.
[14] i Bel, Núria Margarit, and Manuel Martínez Sánchez. Simulation of a Liquid Rocket Engine, 1st Meeting of EcosimPro Users, UNED, Madrid, 3-4 May 2001.
[15] Beliaev, E. Chevanov, V. , Chervakov, V., Mathematical Modeling of Operating Process of Liquid Propellant Rocket Engines, , MAI , 1999. (In Russian)
[16] Hybrid Systems Analysis Unit and System Dynamics Unit, Engine Balance and Dynamics Model, Rockwell International Corporation, Rocket dyne Division, report number RL00001, January 19, 1992.
[17] Avsianikov, B.V. , Theory and calculation of feed system’s elements of liquid propellant rocket engines, Mashinostroeinye Publications, Moscow, Russia, 1983. (In Russian)
[18] V.A.Shesterianikov, Hydraulic Modeling of Start Regime of Liquid Propellant Rocket Engines, 1981. (In Russian)
[19] T.P.C. Lozano, Dynamic models for liquid rocket engines with health monitoring application, Master of Science, Aeronautics and Astronautics, Massachusetts Institute of Technology, 1998.

Files

Share

How to cite

Statistics