Numerical Study on Supersonic Combustion Using k -ω SST Turbulence Model with Compressibility Modifications
Supersonic combustion of hydrocarbon fuel is simulated using the in-house two-dimensional compressible, turbulent and reacting flow code. Three kind of compressibility modifications, namely the dilatational compressibility, structural compressibility and shock-unsteadiness corrections are incorporated into the k - to Shear Stress Transport (SST) model respectively. In addition, the case that employing all the three corrections simultaneously is also performed to evaluate the coupling effects of these individual corrections. Effects of different compressibility modifications on supersonic combustion are compared and investigated. The predicted static pressure distributions along the combustor walls are compared with experimental data. Results show that SST model with compressibility modifications can obtain a more accurate prediction compared to the standard SST model. The growth of turbulent kinetic energy is depressed to a more reasonable level by compressibility corrections. The suppression effect yielded by shock unsteadiness correction is more remarkable than the other two corrections. Moreover, the best agreement between computation and experiments is obtained by the coupling case, indicating that the overlying effects may improve the prediction accuracy.
supersonic combustion k-ω SST model compressibility modification numerical simulation
NIU Dong-sheng HOU Ling-yun
School of Aerospace, Tsinghua University, Beijing, China
国际会议
4th International Symposium on Jet Propulsion and Power Engineering(第四届喷气推进与动力工程国际会议 ISJPPE2012)
西安
英文
387-394
2012-09-10（万方平台首次上网日期，不代表论文的发表时间）