Browse > Article
http://dx.doi.org/10.7734/COSEIK.2017.30.2.119

Conjugate Simulation of Heat Transfer and Ablation in a Small Rocket Nozzle  

Bae, Ji-Yeul (Department of Mechanical Engineering, Yonsei Univ.)
Kim, Taehwan (Department of Mechanical Engineering, Yonsei Univ.)
Kim, Ji Hyuk (Department of Mechanical Engineering, Yonsei Univ.)
Ham, Heecheol (Agency for Defense Development)
Cho, Hyung Hee (Department of Mechanical Engineering, Yonsei Univ.)
Publication Information
Journal of the Computational Structural Engineering Institute of Korea / v.30, no.2, 2017 , pp. 119-125 More about this Journal
Abstract
Ablative material in a rocket nozzle is exposed to high temperature combustion gas, thus undergoes complicated thermal/chemical change in terms of chemical destruction of surface and thermal decomposition of inner material. Therefore, method for conjugate analysis of thermal response inside carbon/phenolic material including rocket nozzle flow, surface chemical reaction and thermal decomposition is developed in this research. CFD is used to simulate flow field inside nozzle and conduction in the ablative material. A change in material density and a heat absorption caused by the thermal decomposition is considered in solid energy equation. And algebraic equation under boundary layer assumption is used to deduce reaction rate on the surface and resulting destruction of the surface. In order to test the developed method, small rocket nozzle is solved numerically. Although the ablation of nozzle throat is deduced to be higher than the experiment, shape change and temperature distribution inside material is well predicted. Error in temperature with experimental results in rapid heating region is found to be within 100 K.
Keywords
ablative material; ablation; thermal decomposition; ATJ graphite;
Citations & Related Records
연도 인용수 순위
  • Reference
1 Boyarintsev, V.I., Zvyagin, Y. (1972) The Ablation of Graphite in the Turbulent Flow of a Reacting Gas, (No.FTD-MT-24-1754-71) WRIGHT-PATTER SON AFB OHIO.
2 Gordon, S., McBride, B.J. (1996) Computer Program for Calculation of Ccomplex Chemical Equilibrium Compositions and Applications, National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program.
3 Koo, J., Ho, W., Ezekoye, O. (2006) A Review of Ablation Modeling for Thermal Protection Systems, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 0 vols., American Institute of Aeronautics and Astronautics.
4 Menter, F.R. (2009) Review of the Shear-Stress Transport Turbulence Model Experience from an Industrial Perspective, Int. J. Comput. Fluid Dyn., 23(4), pp.305-316.   DOI
5 Thakre, P., Yang, V. (2008) Chemical Erosion of Carbon-Carbon/Graphite Nozzles in Solid-Propellant Rocket Motors, J. Propuls. & Power, 24(4), pp.822-833.   DOI
6 Rindal, R., Flood, D., Kendall R. (1966) Analytical and Experimental Study of Ablation Material for Rocket Eengine Application, NASA CR-54757, 15.