한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제37권9호
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  • Pages.863-878
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  • 2009
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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DES를 이용한 초음속 유동내 수직 연료분사 유동의 비정상 3차원 해석 Part I : 비반응 유동장

Unsteady Three-Dimensional Analysis of Transverse Fuel Injection into a Supersonic Crossflow using Detached Eddy Simulation Part I : Non-Reacting Flowfield

  • 원수희 (서울대학교 기계항공공학부 대학원, 부산대학교 부품소재산학협력연구소) ;
  • 정인석 (서울대학교 기계항공공학부, 항공우주신기술연구소) ;
  • 최정열 (부산대학교 항공우주공학과)
  • 발행 : 2009.09.01
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초록

초음속 주 유동내 연료의 수직분사에 따른 비정상 3차원 유동장을 DES 난류 모델을 이용해 모사하였다. 해석 결과는 시간에 따른 에디 거동 및 생성 빈도에 대해 실험과 비교되었으며, 에디 생성 메커니즘을 이해하기 위해 분사기 주변 와도에 대한 분석을 수행하였다. DES 난류 모델은 에디의 대류 특성을 비교적 정확하게 모사하고 있으나, 에디 생성빈도는 다소 과대 예측하고 있다. 분사기 상류 재순환 영역에서 엇회전하는 와류가 번갈아 떨어져 나가면서 에디 구조가 생성된다.

Unsteady three-dimensional flowfield generated by transverse fuel injection into a supersonic mainstream is simulated with a DES turbulence model. Comparisons are made with experimental results in terms of the temporal eddy position and eddy formation frequency. The vorticity field around the jet exit is also analyzed to understand the formation mechanism of the large eddy structures. Results indicate that the DES model correctly predicts the convection characteristics of the large scale eddies. However, it is also observed that the numerical results slightly over-predict the eddy formation frequency. The large eddy structures are generated as the counter-rotating vortices are detached alternately in the upstream recirculation region.

키워드

참고문헌

  1. Fric, T. F. and Roshko, A., "Vortical Structurein the Wake of a Transverse Jet", Journal of FluidMechanics, Vol. 279, 1994, pp. 1-47. https://doi.org/10.1017/S0022112094003800
  2. Papamoschou, D. and Hubbard, D. G., "VisualObservations of Supersonic Transverse Jets",Experiments in Fluids, Vol. 14, No. 6, 1993, pp.468-471. https://doi.org/10.1007/BF00190201
  3. Gruber, M. R., Nejad, A. S., Chen, T. H., andDutton, J. C., "Bow Shock/Jet Interaction inCompressible Transverse Injection Flowfields",AIAA Journal, Vol. 34, No. 10, 1996, pp. 2191- 2193. https://doi.org/10.2514/3.13372
  4. Ben-Yakar, A., Mungal, M. G., and Hanson,R. K., "Time Evolution and Mixing Characteristicsof Hydrogen and Ethylene Transverse Jets inSupersonic Crossflows", Physics of Fluids, Vol. 18,2006. 026101. https://doi.org/10.1063/1.2139684
  5. Peterson, D. M., Subbareddy, P. K., andCandler, G. V., "DES Investigation of TransverseInjection into Supersonic Crossflow using a HybridUnstructured Solver", AIAA Paper 2006- 903, 2006.
  6. Kawai, S. and Lele, S. K., "Mechanisms of JetMixing in a Supersonic Crossflow: A Study usingLarge-Eddy Simulation", Annual Research Briefs 2007,Center for Turbulence Research, Stanford Universityand NASA-Ames, 2007, pp. 353-365.
  7. Boles, J. A., Edwards, J. R., and Baurle, R.A., "Hybrid LES/RANS Simulation of TransverseSonic Injection into a Mach 2 Flow", AIAA Paper2008-622, 2008.
  8. Sparlat, P. R., Jou, W.-H., Strelets, M., andAllmaras, S. R., "Comments on the Feasibility ofLES for Wings, and on a Hybrid RANS/LESApproach," Advances in DNS/LES : Direct NumericalSimulation and Large Eddy Simulation, 1997, pp.137-148.
  9. Strelets, M., "Detached Eddy Simulation ofMassively Separated Flows", AIAA Paper 2001-0879, 2001.
  10. Menter, F. R., “Two-Equation Eddy-ViscosityTurbulence Models for Engineering Applications",AIAA Journal, Vol. 32, No. 8, 1994, pp.1598-1605. https://doi.org/10.2514/3.12149
  11. Candler, G. V., Wright, M. J., and McDonald,J. D., "Data-Parallel Lower-Upper Relaxation Methodfor Reacting Flows", AIAA Journal, Vol. 32, No.12, 1994, pp. 2380-2386. https://doi.org/10.2514/3.12303
  12. Wright, M. J., Candler, G. V., andPrampolini, M., "Data-Parallel Lower-UpperRelaxation Method for the Navier-StokesEquations", AIAA Journal, Vol. 34, No. 7, 1996,pp. 1371-1377. https://doi.org/10.2514/3.13242
  13. Wissink, A. M., Lyrintzis, A. S., andStrawn, R. C., "Parallelization of a Three-Dimensional Flow Solver for Euler RotorcraftAerodynamics Predictions", AIAA Journal, Vol. 34,No. 11, 1996, pp. 2276-2283. https://doi.org/10.2514/3.13391
  14. Roache, P, J., "Verification of Code andCalculations", AIAA Journal, Vol. 36, No. 5, 1998,pp. 696-702. https://doi.org/10.2514/2.457
  15. 원수희, 정인석, 최정열, “GCI를 이용한 수직분사제트 수치모사의 검증 및 확인", 한국항공우주학회지, 제34권, 제4호, 2006, pp. 53-63.
  16. Gruber, M. R., Nejad, A. S., Chen, T. H.,and Dutton, J. C., "Mixing and PenetrationStudies of Sonic Jets in a Mach 2 Freestream",Journal of Propulsion and Power, Vol. 11, No. 2,1995, pp. 315-323. https://doi.org/10.2514/3.51427
  17. Rothstein, A. D. and Wantuck, P. J., "AStudy of the Normal Injection of Hydrogen Intoa Heated Supersonic Flow Using Planar Laser-Induced Fluorescence", AIAA Paper 92-3423, 1992.
  18. Kelso R. M., Lim, T. T., and Perry, A. E., "An Experimental Study of Round Jets in Corss-o rlow", Journal of Fluid Mechanics, Vol. 306, 1996, pp. 111-144. https://doi.org/10.1017/S0022112096001255
  19. Yuan, L. L., Street, R. L., and Ferziger, J.H., "Large-eddy Simulation of a Round Jet inCorssflow", Journal of Fluid Mechanics, Vol. 379,1999, pp. 71-104. https://doi.org/10.1017/S0022112098003346

피인용 문헌

  1. Characteristics of the Transverse Fuel Injection into a Supersonic Crossflow using Various Injector Geometries vol.22, pp.3, 2018, https://doi.org/10.6108/KSPE.2018.22.3.053