Hostname: page-component-586b7cd67f-tf8b9 Total loading time: 0 Render date: 2024-11-22T17:29:34.604Z Has data issue: false hasContentIssue false
  • English
  • Français

3D numerical simulation of the supersonic combustion of H2

Published online by Cambridge University Press:  03 February 2016

Prashant Dinde ,
A. Rajasekaran  and
V. Babu
Prashant Dinde
Affiliation:
Department of Mechanical Engineering, Indian Institute of Technology, Madras, India
A. Rajasekaran
Affiliation:
Department of Mechanical Engineering, Indian Institute of Technology, Madras, India
V. Babu
Affiliation:
Department of Mechanical Engineering, Indian Institute of Technology, Madras, India
Get access Rights & Permissions [Opens in a new window]

Abstract

Results from numerical simulations of supersonic combustion of H2 are presented. The combustor has a single stage fuel injection parallel to the main flow from the base of a wedge. The simulations have been performed using FLUENT. Realisable k-ε model has been used for modelling turbulence and single step finite rate chemistry has been used for modelling the H2-Air kinetics. All the numerical solutions have been obtained on grids with average value for wall y+ less than 40. Numerically predicted profiles of static pressure, axial velocity, turbulent kinetic energy and static temperature for both non-reacting as well as reacting flows are compared with the experimental data. The RANS calculations are able to predict the mean and fluctuating quantities reasonably well in most regions of the flow field. However, the single step kinetics predicts heat release much more rapid than what was seen in the experiments. Nonetheless, the overall pressure rise in the combustor due to combustion is predicted well. Also, the k-ε model is not able to predict the fluctuating quantities in the base region of the wedge where there is strong anisotropy in the presence of combustion.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1114 , December 2006 , pp. 773 - 782
Copyright
Copyright © Royal Aeronautical Society 2006 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Goyne, C.P., Rodriguez, C.G., Krauss, R.H., Mcdaniel, J.C. and Mcclinton, C.R., Experimental and numerical study of dual mode scramjet combustor, 2002, AIAA paper 2002–5216.Google Scholar
2. Kim, J.H., Yoon, Y., Jeung, I.S., Huh, H. and Choi, J.Y., Numerical study of mixing enhancement by shock waves in a model scramjet engine, AIAA J, 2003, 41, (6).Google Scholar
3. Kim, K.M., Baek, S.W. and Han, C.Y., Numerical study on supersonic combustion with cavity based fuel injection, Int J Heat and Mass transfer, 2004, 47, pp 271–286.Google Scholar
4. Rodriguez, C.G., White, J.A. and Riggins, D.W., Three-dimensional effects in modelling of dual mode scramjets, 2000, AIAA paper 2000–3704.Google Scholar
5. Rodriguez, C.G. and Cutler, A.D., Numerical analysis of the SCHOLAR supersonic combustor, NASA-CR-2003-212689, 2003.Google Scholar
6. Baurle, R.A., Modelling of high speed reacting flows: Established Practices and Future Challenges, 2004, AIAA paper 2004–0267.Google Scholar
7. Rajasekaran, A. and Babu, V., Numerical simulation of threedimensional reacting flow in a model supersonic combustor, J Propulsion and Power, 2006, 22, (4), pp 820–827.Google Scholar
8. Oevermann, M., Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling, Aerospace Science and Technology, 2000, 4, pp 463–480.Google Scholar
9. Baurle, R.A. and Eklund, D.R., Analysis of dual-mode hydrocarbon scramjet operation at Mach 4-6.5, J Propulsion and Power, 2002, 18, (5), pp 990–1002.Google Scholar
10. Hsu, K. and Jemcov, A., numerical investigation of detonation in pre-mixed H2-Air mixture-Assessment of simplified chemical mechanism, 2000, AIAA paper 2000–2478.Google Scholar
11. Baurle, R.A., Mathur, T., Gruber, M.R. and Jackson, K.R., A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications, 1998, AIAA paper 98–3121.Google Scholar
12. Xiao, X., Hassan, H.A. and Baurle, R.A., Modelling scramjet flows with variable turbulent Prandtl and Schmidt Numbers, 2006, AIAA paper 2006–128.Google Scholar