Numerical analysis of combustion instabilities of homogeneous propellants in axisymmetric rocket motors

Tae Seong Roh, Vigor Yang

Research output: Contribution to conferencePaperpeer-review


A numerical analysis of unsteady motions in solid rocket motors has been conducted. The formulation considers a 2-D axisymmetric combustion chamber and treats the complete conservation equations accounting for turbulence closure and finite-rate chemical kinetics in the gas phase and subsurface reactions. The governing equations has been modified and solved in two dimensional Cartesian coordinates. A fully coupled implicit scheme based on a dual time-stepping integration algorithm has been adopted to solve the governing equations and associated boundary conditions. Results of the steady-state calculations indicate that the onset of turbulence occurs in the middle of the combustion chamber and substantially modifies the combustion wave structure in the downstream region. Interactions between acoustic waves and propellant combustion are studied by imposing periodic pressure oscillations at the chamber exit. The oscillatory flow characteristics are significantly altered by the presence of turbulence, due to enhanced momentum and energy transport in the gas phase near the propellant surface. This enhancement also affects the unsteady combustion response of the condensed phase. The turbulent reactive acoustic boundary layer on a solid propellant surface, could be one of the primary mechanisms in velocity-coupled erosive burning.

Original languageEnglish
Publication statusPublished - 1996
Event32nd Joint Propulsion Conference and Exhibit, 1996 - Lake Buena Vista, United States
Duration: 1996 Jul 11996 Jul 3


Other32nd Joint Propulsion Conference and Exhibit, 1996
CountryUnited States
CityLake Buena Vista

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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