Slag Prediction in Submerged Rocket Nozzle Through Two-Phase CFD Simulations

Chaturvedi, Amit K.; Kumar, Sudarshan; Chakraborty, Debasis

doi:10.14429/dsj.65.7147

Cited by 6 publications

(1 citation statement)

References 19 publications

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“…Since, the hostile character of the environment inside a solid rocket motor permits only pressure measurements, numerical simulations were the best way to acquire knowledge of details of the internal flowfield. Geometric evolution of grain boundaries and performance parameters 11 are predicted, erosive burning correlations for axisymmetric geometries are extended to complex grain shapes 12,13 and accumulated slag were estimated for a large segmented rockets with submerged nozzle 14 . Nozzle damping coefficients were estimated numerically 15 16 emphasised that the motor instability is linked to the hydro-dynamic instability of the mean flow sheared regions.…”

Section: Introductionmentioning

confidence: 99%

Computational Fluid Dynamics Simulation of Combustion Instability in Solid Rocket Motor : Implementation of Pressure Coupled Response Function

Saha

Chakraborty

2016

Def. Sc. Jl.

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Combustion instability in solid propellant rocket motor is numerically simulated by implementing propellant response function with quasi steady homogeneous one dimensional formulation. The convolution integral of propellant response with pressure history is implemented through a user defined function in commercial computational fluid dynamics software. The methodology is validated against literature reported motor test and other simulation results. Computed amplitude of pressure fluctuations compare closely with the literarture data. The growth rate of pressure oscillations of a cylindrical grain solid rocket motor is determined for different response functions at the fundamental longitudinal frequency. It is observed that for response function more than a critical value, the motor exhibits exponential growth rate of pressure oscillations.

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