Cold flow investigation of the flow acoustic coupling in solid propellant boosters

Anthoine, J.; Planquart, Philippe; Olivari, D.

doi:10.2514/6.1998-475

Cited by 7 publications

(6 citation statements)

References 7 publications

(3 reference statements)

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“…The recirculation bubble behind the inhibitor develops over an axial distance of x= h D 6:2, where h is the inhibitorheight. Anthoine et al 37 have carried out an experimental investigation with an inhibitornozzle distance, such as l= h D 27, and have shown that the length of the recirculation bubble behind the inhibitor is approximately equal to 12h. For the shorter inhibitor-nozzle distance used in this numerical simulation (l= h D 8), the recirculation bubble is, of course, limited to 8h.…”

Section: Mean Flowmentioning

confidence: 98%

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Effect of Nozzle Cavity on Resonance in Large SRM: Numerical Simulations

Anthoine

Buchlin

Guery

2003

Journal of Propulsion and Power

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The nozzle design effect on sound production is investigated to improve the understanding of the aeroacoustic coupling that occurs in solid rocket motors with a submerged nozzle. Earlier analytical and experimental work demonstrated that ow-acoustic coupling is observed only for submerged nozzles for which the sound pressure level increases linearly with the nozzle cavity volume. Numerical simulations of the ow-acoustic coupling phenomena and in particular of the effect of the nozzle cavity volume on the pressure pulsations are performed using the code CPS. The numerical and experimental pressure spectra are compared. The frequencies are well simulated by the numerical code even if the pressure levels are overestimated. The nozzle design effect on sound production is also observed with a reduction of pressure level of 55% when the nozzle cavity is removed. Furthermore, the nozzle cavity modi es the ow eld around the nozzle head. With the cavity, the recirculation bubble is shorter, and the ow close to the nozzle head presents high amplitudes of radial mean velocity and uctuation. That explains why the vortices break up when interacting with the nozzle head. With the cavity, the vortices shed by the inhibitor move along the border of the recirculation bubble and then pass in front of the cavity entrance, where they generate sound by interacting with the velocity uctuations induced by the cavity volume. This results in a strong interaction between the vortices and the nozzle, which leads to large pressure oscillations. Nomenclature a = sound speed D = internal diameter of the model d = internal diameter of the inhibitor f = frequency of the oscillation H e = Helmholtz number j = excited acoustic mode number L = total length l = inhibitor-nozzle distance M 0 = mean Mach number P = average acoustic power p s = mean static pressure p 0 = oscillatory pressure r = radial coordinate u 0 = oscillatory velocity vector V c = nozzle cavity volume v = vortex transport velocity vector x = axial coordinate°= ratio of speci c heats ½ 0 = mean density ! = vorticity vector

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Section: Mean Flowmentioning

confidence: 98%

“…For the nozzle without a cavity, the recirculation bubble behind the inhibitor extends over the whole space between the obstacle and the nozzle because x=h D 8 is smaller than 12 and reattaches on the nozzle head. 37 Velocity pro les are plotted in Fig. 18 for both velocity components and for the two nozzles with and without a cavity.…”

Section: Mean Flowmentioning

confidence: 99%

Effect of Nozzle Cavity on Resonance in Large SRM: Numerical Simulations

Anthoine

Buchlin

Guery

2003

Journal of Propulsion and Power

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“…For example, in the SRM problem, if one is interested in the nature of the flow one second after ignition, one must interrogate the solution at t ¼ 1=b seconds of simulation time, since the slow time has been accelerated by a factor of b. And, if one is interested in vortex-shedding dynamics (from an inhibitor, say, see Sutton and Biblarz [18] and Anthoine et al [1]) one second after ignition, this will correspond to the simulated evolution (at the simulating time scale) evaluated again at t ¼ 1=b seconds, but the variation of these dynamics (e.g., changes in shedding frequency) will occur b times faster.…”

Section: Discussion and Generalizationsmentioning

confidence: 99%

Slow-time acceleration for modeling multiple-time-scale problems

Haselbacher

Najjar

Massa

et al. 2010

Journal of Computational Physics

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“…The purpose of the second test case is to re-visit the experimental work of Anthoine et al [10] on the zero-flow acoutic characterization of a typical solid propellant booster. This axisymmetric test facility consists of a contoured nozzle with a throat diameter of 30 mm, a section diameter of 76 mm and a booster length (L = 405 mm).…”

Section: Test-case 1: 1-dof Mechanical Systemmentioning

confidence: 99%

“…Due to the difficulties of predicting acoustic resonance using analytical or numerical methods, much of the work has been conducted experimentally, similar to the shaker excitations used for modal extraction in structural engineering. A classical approach to establish possible links between observed instabilities and acoustic resonances is based on white-noise excitation of the component under study and the filtering of acoustic resonance frequencies by using loudspeakers [10][11][12][13][14]. In many cases, such experimental simple acoustic characterization may well provide crucial information about flow-induced resonant sound generation during operating conditions [15,16].…”

Section: Introductionmentioning

confidence: 99%

A combined time and frequency domain approach for acoustic resonance prediction

Chassaing

Sayma

Imregun

2008

Journal of Sound and Vibration

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This is the accepted version of the paper.This version of the publication may differ from the final published version.Permanent repository link: http://openaccess.city.ac.uk/7905/ Link to published version: http://dx. AbstractA general time and frequency methodology has been developed to identify acoustic resonance conditions of internal flow configurations. The resonant frequencies and the corresponding acoustic modes are determined by imposing onto the flow a time-dependent excitation at several locations on the boundary. The resulting time-domain responses of the pressure signals, which are computed via an unsteady Favre-Reynolds averaged Navier-Stokes solver, are used to determine the frequency response function matrix of the fluid which can be considered to be a multipleinput multiple-output system. The main test case was selected to be a closed-end cylindrical duct for which the effect of different excitation techniques on the predicted resonant acoustic field is discussed in detail. The last test case deals with the acoustic characterization of a 2-D channel with symmetric bumps and an inlet flow velocity of 17 ms −1 . It is shown that the methodology was suitable for identifying both axial and transverse acoustic modes in a 10 Hz -3 kHz frequency range.

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Cold flow investigation of the flow acoustic coupling in solid propellant boosters

Abstract: This paper deals with an analysis of the flow instabilities in the Ariane 5 solid propellant booster.

Cited by 7 publications

References 7 publications

Effect of Nozzle Cavity on Resonance in Large SRM: Numerical Simulations

Effect of Nozzle Cavity on Resonance in Large SRM: Numerical Simulations

Slow-time acceleration for modeling multiple-time-scale problems

A combined time and frequency domain approach for acoustic resonance prediction

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