期刊文献+

Numerical simulations of turbulent flows in aeroramp injector/gas-pilot flame scramjet 被引量:2

Numerical simulations of turbulent flows in aeroramp injector/gas-pilot flame scramjet
原文传递
导出
摘要 To uncover the internal flow characteristics in an ethylene-fueled aeroramp injector/gaspilot(ARI/G-P)flame scramjet,a Reynolds-averaged Navier-Stokes(RANS)solver is constructed under a hybrid polyhedral cell finite volume frame.The shear stress transport(SST)k-x model is used to predict the turbulence,while the Overmann’s compressibility corrected laminar flamelet model is adopted to simulate the turbulent combustion.Nonreactive computations for Case 1(G-P jet on),Case 2(ARI jets on),and Case 3(both ARI and G-P jets on)were conducted to analyze the mixing mechanism,while reactive Cases 4–7 at equivalent ratios of 0.380,0.278,0.199 and0.167 respectively were calculated to investigate the flame structure and combustion modes.The numerical results are compared well to those of the experiments.It is shown that the G-P jet plays significant role in both the fuel/air mixing and flame holding processes;the combustion for the four reactive cases takes place intensively in the regions downstream of the ARI/G-P unit;Cases 4 and 5are under subsonic combustion mode,whereas Cases 6 and 7 are mode transition critical and supersonic combustion cases,respectively;the mode transition equivalent ratio is approximately 0.20. To uncover the internal flow characteristics in an ethylene-fueled aeroramp injector/gaspilot(ARI/G-P)flame scramjet,a Reynolds-averaged Navier-Stokes(RANS)solver is constructed under a hybrid polyhedral cell finite volume frame.The shear stress transport(SST)k-x model is used to predict the turbulence,while the Overmann’s compressibility corrected laminar flamelet model is adopted to simulate the turbulent combustion.Nonreactive computations for Case 1(G-P jet on),Case 2(ARI jets on),and Case 3(both ARI and G-P jets on)were conducted to analyze the mixing mechanism,while reactive Cases 4–7 at equivalent ratios of 0.380,0.278,0.199 and0.167 respectively were calculated to investigate the flame structure and combustion modes.The numerical results are compared well to those of the experiments.It is shown that the G-P jet plays significant role in both the fuel/air mixing and flame holding processes;the combustion for the four reactive cases takes place intensively in the regions downstream of the ARI/G-P unit;Cases 4 and 5are under subsonic combustion mode,whereas Cases 6 and 7 are mode transition critical and supersonic combustion cases,respectively;the mode transition equivalent ratio is approximately 0.20.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2017年第4期1373-1390,共18页 中国航空学报(英文版)
基金 co-supported by the National Natural Science Foundation of China (Nos. 51176003 and 51276007) the Fundamental Research Funds for the Central Universities of China (No. YWF-15-GFY)
关键词 Combustion mode Laminar flamelet model Menter's SST k-ω model Scramjet Turbulent combustion Combustion mode Laminar flamelet model Menter's SST k-ω model Scramjet Turbulent combustion
  • 相关文献

参考文献3

二级参考文献40

  • 1LEE ChunHian.A flamelet model for turbulent diffusion combustion in supersonic flow[J].Science China(Technological Sciences),2010,53(12):3379-3388. 被引量:10
  • 2LEE ChunHian.A numerical study of turbulent combustion characteristics in a combustion chamber of a scramjet engine[J].Science China(Technological Sciences),2010,53(8):2111-2121. 被引量:14
  • 3Linan A.The asymptotic structure of counterflow diffusion flames for large activation energies. Acta Astronautica . 1974
  • 4Libby P A,Williams F A.Turbulent combustion: fundamental as- pects and a review. Turbulent Re- acting Flows . 1994
  • 5Swaminathan N,Bilger R W.Assessment of combustion submodels for turbulent nonpremixed hydrocarbon flames. Combustion and Flame . 1999
  • 6Balakrishnan G,Williams F A.Turbulemt combustion regimes for hypersonic propulsion employing hydrogen/air diffusion flames. Journal of Propulsion and Power . 1993
  • 7Bray K N C,Libby P A,Williams F A.High speed turbulent com- bustion. Turbulent Reacting Flows . 1994
  • 8Waidmann W,Alff F,Bohm M, et al.Supersonic combustion of hy- drogen/air in a SCRAMJET combustion chamber. Space Technology . 1995
  • 9James L B.Turbulence model validation for hypersonic flows. AIAA 2002 -3308 . 2002
  • 10Kee R J,Rupley F M,Miller J A.The Chemkin Thermodynamic Data Base. Sandia Report SAND87-8215B . 1994

共引文献21

同被引文献5

引证文献2

二级引证文献3

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部