Interactions of homogeneous propellant combustion and acoustic wavesin a solid rocket motor

Tseng, I.; Yang, Vigor

doi:10.2514/6.1992-101

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…Hence, for sufficiently large values of e, the transient vorticity can be more intense than that of the steady Culick velocity components. Calculated axial velocity variation with radius is qualitatively similar to the spatial oscillations observed experimentally by Brown et al 1 ' 2 Tseng and Yang 19 and Tseng et al 7 provide a computational model for a premixed laminar flame adjacent to a cylindrical porous surface through which a combustible mixture is injected. The flame is a surrogate for solid propellant combustion in a rocket chamber.…”

Section: Introductionsupporting

confidence: 77%

“…Instantaneous values of the flow variables are presented to describe the time evolution of unsteady vorticity creation and propagation. This provides an alternative to the studies by Tseng and Yang, 19 Flandro and Roach, 15 Smith et al, 16 and Tseng et al,17 where an acoustic-based time-averaging approach is used to study mean spatial distributions.…”

Section: Discussionmentioning

confidence: 99%

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Unsteady vorticity generation and evolution in a model of a solid rocket motor

Kirkkopru

Kassoy

Zhao

1996

Journal of Propulsion and Power

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The cylindrical, axisymmetric Navier-Stokes equations are solved numerically to study the generation and evolution of vorticity in an injection-induced transient shear flow. An initially steady internal flowfield driven by constant sidewall injection is disturbed by positive transient sidewall injection, which simulates the unsteady mass input from propellant burning variations. The disturbance amplitude is as large as that of the steady sidewall injection to ensure that nonlinear effects influence the vorticity field evolution. Initial value solutions show that relatively intense vorticity is generated at the sidewall and eventually fills the cylinder with a rotational flow. Although the pressure response is essentially that found in acoustic stability theory, the axial and radial velocity components contain large local radial velocity gradients that cannot be predicted from acoustic theory alone.

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Section: Introductionsupporting

confidence: 77%

Section: Discussionmentioning

confidence: 99%