Applying a finite difference scheme to the flow field analysis of rotating detonation engines using multiple fuels

• Published in: International journal of hydrogen energy 2023-06, Vol.48 (47), p.18083-18099
• Main Author: Al-Thehabey, Omar Yousef
• Format: Article
• Language: English
• Subjects: CFD; Chapman-Jouguet; Combustion; Oblique shock; Rotating detonation; Slip line
• ISSN: 0360-3199; 1879-3487
• DOI: 10.1016/j.ijhydene.2023.01.309

The objective of this study is to apply the finite difference method (FDM) scheme to generate profiles of velocity, vorticity, pressure, temperature, and density of the flow field inside the chamber of a rotating detonation engine. In addition, this study discusses the Kuo's algorithm used in the computation of Chapman-Jouguet (CJ) variables. A new computational algorithm is introduced to compute the CJ variables, the shock, and the post-shock conditions. Five different fuels are tested, H2–O2, H2-air, CH4-air, C2H6-air, and C2H2-air. The results show good performance for the FDM scheme, and the new algorithm is adopted in this study to perform all CJ calculations. The new algorithm's results are compared with the experimental data available for the tested fuels and show close results. Another important result is that the highest vorticity forms along the slip line of the combustion chamber, then it gradually shrinks along the path of the slip line. •Presenting a new algorithm to compute the Chapman-Jouguet variables.•Each detonation wave can achieve a different Chapman-Jouguet pressure.•CFD test cases fuels used: H2–O2, H2-air, CH4-air, C2H6-air, and C2H2-air.•The RDE detonation reactants mixture height varies with fuel type.•Vorticity is highest at the slip line and shrinks downstream the slip line.