Damping Coefficient Prediction of Solid Rocket Motor Nozzle Using Computational Fluid Dynamics

Javed, Afroz; Chakraborty, Debasis

doi:10.2514/1.b35010

Cited by 14 publications

(7 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…12. Multi-mode decay was predicted in simulations of Afroz and Chakraborty (20) due to use of cosine function for the mode shape in a non-cylindrical geometry. With the procedure outlined here to isolate a single mode, decay at a single frequency is predicted.…”

Section: Resultsmentioning

confidence: 99%

“…The only concern is regarding the flow-turning loss, which some studies (18) have claimed depends on radial distribution of vorticity. This, however, can now be refuted using the fact that both laminar and turbulent simulations predict almost equal damping rates (20) . It should, therefore, be possible to capture the flow-turning loss in quasi-1D simulations as long as the source terms to account for mass addition at grain boundaries correspond to a no-slip condition.…”

Section: Computational Toolsmentioning

confidence: 99%

“…Though some previous studies were apparently in agreement with this assertion, there is considerable evidence that cylindrical grains do have a flow-turning loss (17,18) . Recent multi-dimensional simulations (20) have also shown that total damping rate of axial modes is nearly the same whether the boundary layer at the grain surface is set to be laminar or fully turbulent. Since the vorticity distribution is very different in laminar and turbulent flows, this implies that the integrated effect depends on how much the flow turns overall and not on how the turning (i.e.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Damping of modal perturbations in solid rocket motors

et al. 2016

View full text Add to dashboard Cite

Quasi-one-dimensional (quasi-1D) tools developed for capturing flow and acoustic dynamics in non-segmented solid rocket motors are evaluated using multi-dimensional computational fluid dynamic simulations and used to characterise damping of modal perturbations. For motors with high length-to-diameter ratios (of the order of 10), remarkably accurate estimates of frequencies and damping rates of lower modes can be obtained using the the quasi-1D approximation. Various grain configurations are considered to study the effect of internal geometry on damping rates. Analysis shows that lower cross-sectional area at the nozzle entry plane is found to increase damping rates of all the modes. The flow-turning loss for a mode increases if the more mass addition due to combustion is added at pressure nodes. For the fundamental mode, this loss is, therefore, maximum if burning area is maximum at the centre. The insights from this study in addition to recommendations made by Blomshield(1)based on combustion considerations would be very helpful in realizing rocket motors free from combustion instability.

show abstract

Section: Resultsmentioning

confidence: 99%

Section: Computational Toolsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Damping of modal perturbations in solid rocket motors

et al. 2016

View full text Add to dashboard Cite

show abstract

“…Nevertheless, the effect of the turbulence transition inside the SRM chamber was not considered. Javed and Chakraborty [15] numerically evaluated nozzle damping in a solid rocket motor using ANSYS CFX. A sinusoidal pressure pulse was enforced at the closed end of a channel-fitted with nozzle, for a given period.…”

Section: Introductionmentioning

confidence: 99%

Turbulent Flow Characteristics in a Model of a Solid Rocket Motor Chamber with Sidewall Mass Injection and End-Wall Disturbance

Albatati

Hegab

Rady

et al. 2021

Mathematical Problems in Engineering

View full text Add to dashboard Cite

The present analytical, numerical, and experimental investigations are performed to study the flow field in acoustically simulated solid rocket motor (SRM) chamber geometry. The computational solution is carried out for a high Reynolds number and low Mach number internal flows driven by sidewall mass addition in a long chamber with end-wall disturbances. This kind of flow (transient, weakly viscous, and contains vorticity) have several features in common with a turbulent flow field. The numerical study is performed by solving the unsteady Reynolds-averaged Navier–Stokes equations along with the energy equation using the control volume approach based on a staggered grid system. The v2-f turbulence model has been implemented in the current study. A comparison of the SIMPLE and PISO algorithms showed that both algorithms provide identical results, and the computational time using the PISO algorithm is higher by about 6% than the corresponding value of the SIMPLE algorithm. A fair agreement has been obtained between the numerical, analytical, and experimental results. Moreover, the results showed that the complex turbulent internal flow patterns are induced inside the chamber due to the strong interaction of the sidewall injection with the traveling acoustic waves. Such a complex internal structure is shown to be dependent on the piston frequency and sidewall mass flux. The current study, for the first time, emphasizes the acoustic-fluid dynamics interaction mechanism and the accompanying unsteady rotational fields along with the effect of the generated turbulence on the unsteady vorticity and its impact on the real burning rate.

show abstract

“…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. To predict motor flow driven instabilities, we need to use a model that has the ability to describe, in the same framework, both acoustic and vortical waves.…”

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.

View full text Add to dashboard Cite

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.

show abstract

Damping Coefficient Prediction of Solid Rocket Motor Nozzle Using Computational Fluid Dynamics

Cited by 14 publications

References 6 publications

Damping of modal perturbations in solid rocket motors

Damping of modal perturbations in solid rocket motors

Turbulent Flow Characteristics in a Model of a Solid Rocket Motor Chamber with Sidewall Mass Injection and End-Wall Disturbance

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

Contact Info

Product

Resources

About