한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제14권6호
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  • Pages.38-44
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  • 2010
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
권호 표지

압력비 변화과정이 과팽창 노즐에서 발생하는 횡력 변동 특성에 미치는 영향

The Effect of the Variation of Pressure Ratio on the Characteristics of Lateral Forces in an Over-Expanded Nozzle

  • 이종성 (안동대학교 대학원 기계공학과) ;
  • 김희동 (안동대학교 기계공학과)
  • 투고 : 2010.10.01
  • 심사 : 2010.11.29
  • 발행 : 2010.12.30
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초록

과팽창 상태의 로켓 노즐에서 발생하는 충격파 경계층 간섭 형태는 엔진 시동 및 정지과정 중 예기치 않은 횡력을 수반한다. 본 연구에서는 비정상 노즐 구동 압력비 변화가 유동장의 천이형태 및 횡력 특성에 어떠한 영향을 미치는지 조사하기 위하여 수치해석적 연구를 수행하였다. 비정상, 축대칭, 압축성 N-S 방정식을 유한 체적법으로 이산화 하였으며, 난류모델은 SST k-${\omega}$을 적용하였다. 엔진 정지 및 시동과정을 모사하기 위하여, NPR은 2~10의 범위에서 계산 하였다. 본 연구의 결과로 박리 유동과 히스테리시스 현상은 구동 압력비에 크게 의존하며, 또한 압력비 변동 시간이 횡력 특성에 지대한 영향을 미칠 수 있음을 알았다.

The shock wave and boundary layer interaction patterns in an over-expanded rocket nozzle are associated with the production of undesirable side-forces during the start-up and shut-down processes of the engine. In the present work, a computational study is carried out to investigate the effect of the transient nozzle pressure ratio (NPR) on the flow fields inside the nozzle. The unsteady, compressible, axisymmetric, Navier-Stocks equations with SST k-${\omega}$ turbulence model are solved using a fully implicit finite volume scheme. NPR is varied from 2.0 to 10.0, in order to simulate the start-up and shut-down processes of the rocket engine. It is observed that the interaction patterns and the hysteresis phenomenon strongly depend on the time variation of NPR, leading to significantly different characteristics in the lateral forces.

키워드

참고문헌

  1. Rao, G.V.R., "Exhaust Nozzle Contours for Optimum Thrust," AIAA Journal of Jet Propulsion, Vol. 28, June, 1958, pp.377-383 https://doi.org/10.2514/8.7324
  2. Hoffman, J.D., "Design of Compressed Truncated Perfect Nozzles," AIAA Journal of Propulsion and Power, Vol. 3, No. 2, 1987, pp.150-156 https://doi.org/10.2514/3.22967
  3. Seddon, J., "The Flow Produced by Interaction of a Turbulent Boundary Layer with a Normal Shock Wave of Strength Sufficient to Cause Separation." Ph.D. Thesis, Ministry of Technology, 1967
  4. Lee, J.S., Kim, H.D., Setoguchi, T. and Matsuo, S., "Unsteady Shock-Flow Characteristics in an Over-Expanded Rocket Nozzle," Journal of Thermal Science, Vol. 19, No. 4, 2010, pp.332-336 https://doi.org/10.1007/s11630-010-0391-z
  5. Yonezawa, K., Yamashita, Y., Tsujimoto, Y., Watanabe, Y. and Yokota, K., "Effect of Contour on Flow Separation in Overexpanded Rocket Nozzles," Journal of Fluid Science and Technology, Vol. 2, No. 1, 2007, pp.97-108 https://doi.org/10.1299/jfst.2.97
  6. Nave, L.H. and Coffey, G.A., "Sea Levels Side Loads in High-Area-Ratio Rocket Engines," AIAA Paper 73-1284, 1973
  7. Chen, C. L., Chakravarthy, S. R., and Hung, C. M., "Numerical Investigation of Separated Nozzle Flows," AIAA Journal, Vol. 32, No. 9, 1994, pp.1836-1843 https://doi.org/10.2514/3.12181
  8. Frey, M., and Hagemann, G., "Restricted Shock Separation in Rocket Nozzle," Journal of Propulsion and Power, Vol. 16, No. 3, 2000, pp.478-484 https://doi.org/10.2514/2.5593
  9. Hagemann, G., Frey, M. and Koschel, W., "Appearance of Restricted Shock Separation in Rocket Nozzles," Journal of Propulsion and Power, Vol. 18, No. 3, 2002, pp.577-584 https://doi.org/10.2514/2.5971
  10. Hagemann, G., Frey, M., "Shock Pattern in the Plume of Rocket Nozzle: Needs for Design Consideration." Shock Waves Journal, Vol. 17, 2008, pp.387-395 https://doi.org/10.1007/s00193-008-0129-y
  11. 이종성, Vincent Lijo, 김희동, "과팽창 노즐에서 발생하는 충격파 박리 패턴의 천이에 관한 연구," 한국추진공학회지, 제14권, 제3호, 2010, pp.9-15
  12. Thi Nguyen, A. and Deniau, H., Girard, S. and Alziary de Roquefort, T., "Unsteadiness of Flow Separation and End-Effects Regime in a Thrust-Optimized Contour Rocket Nozzle," Flow, Turbulence and Combustion, Vol. 71, 2003, pp.161-181
  13. Menter, F. R., "Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications," AIAA Journal, Vol. 32, No. 8, 1994, pp.1598-1605 https://doi.org/10.2514/3.12149
  14. Lee, J.S., Kim, H.D., Setoguchi, T. and Matsuo, S., "Experimental Visualization of Separation Shock Waves in an Over-Expanded Nozzle." Proc. 14th International Symposium on Flow Visualization, Daegu, 2010
  15. Nebbache, A. and Pilinski, C., "Pulsatory Phenomenon in a Thrust Optimized Contour Nozzle," Aerospace Science and Technology, Vol. 10, 2006, pp.295-308. https://doi.org/10.1016/j.ast.2005.07.002
  16. Lee, J.S., Kim, Lijo, V. and Kim, H.D., "A Computational Study on the Transition of the Shock-Boundary Layer Interaction in an Over-Expanded Nozzle," Proc. the Korean Society of Mechanical Engineers Spring Conference, 2010, pp.157-162