A subscale test program to assess the vortex shedding driven instabilities in segmented solid rocket motors

Traineau, J. C.; Prévost, Michel; Vincent, François; Breton, Prescott Le; Cuny, J.; Preioni, N.; Bec, Raymond

doi:10.2514/6.1997-3247

Cited by 15 publications

(5 citation statements)

References 1 publication

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“…Zero-peak relative amplitudes are typically less than 0.5% for pressure oscillations and less than 5% for thrust oscillations. Similar results were also observed on sub-scaled model rockets 9,10 and from numerical simulations. [11][12][13] The use of three-dimensional inhibitors to reduce the pressure oscillations was already tested and simulated by Telara et al 14 From cold flow experiments in a pipe with one or two inhibitors, Culick & Magiawala, 15 Dunlap & Brown, 16 Mettenleiter et al 17 and Anthoine 18 showed that the vortex shedding is produced at the inhibitors, and the confined space of the pipe acts as a resonator with its natural frequencies.…”

Section: Previous Studiessupporting

confidence: 86%

Comparison of Different Passive Control Solutions for Reducing SRM Pressure Oscillations Using Cold Flow Experiments

Anthoine

Lema²

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Cold gas experiments are used to study the pressure oscillations occurring in solid rocket motors (SRM) and the performance of different ways of passive control of these oscillations. Previous studies stated that flow-acoustic coupling is mainly observed for nozzles including cavity. The nozzle geometry has an effect on the pressure oscillations through a coupling between the acoustic fluctuations induced by the cavity volume and the vortices traveling in front of the cavity entrance. The most important reduction of pressure oscillations is obtained by removing the cavity located around the nozzle head. It has been firstly proved that removing the cavity located around the nozzle head is a very good solution both for the axial and radial flow injection configurations, with a reduction factor up to 10. However, the nozzle integration cannot be avoided and this solution can then not be implemented on real flight. A permeable membrane (with holes to allow the combustion gas to pass through) placed in front of the cavity allows a reduction by a factor 1.5. The Helmholtz resonator shows small attenuation of the pressure oscillations; however, its design can be optimized in order to maximize the acoustic damping. The 3D-shaped inhibitors show a good attenuation of the pressure fluctuations, especially when the opening cross-section is increased. This increase results in a shift of the Mach number associated to excitation. For a similar cross-section, the asymmetric inhibitor (crenel-shaped) provides a net reduction of 48% compared to an axisymmetric inhibitor. So, the asymmetry of the inhibitor provides a promising way of reducing the pressure oscillations.

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Section: Previous Studiessupporting

confidence: 86%

Comparison of Different Passive Control Solutions for Reducing SRM Pressure Oscillations Using Cold Flow Experiments

Anthoine

Lema²

2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Once attained a resonance configuration, the resonant frequency decreases with the grain burn back, because of the reduction of the mean flow velocity. When moved away from resonant conditions, a frequency jump occurs and the system brings back itself to a different resonant configuration, characterized by a different number of vortices [44,68,107,87,100]. As visible in fig.…”

Section: Flute Mode Behavior and Lock-inmentioning

confidence: 99%

Numerical simulations of acoustic resonance of Solid Rocket Motor

Ferretti¹,

Favini²,

Cavallini³

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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L'uomo attraversa il presente con gli occhi bendati. Può al massimo immaginare e tentare di indovinare ciò che sta vivendo. Solo più tardi gli viene tolto il fazzoletto dagli occhi e lui, gettato uno sguardo al passato, si accorge di che cosa ha realmente vissuto e ne capisce il senso. M. Kundera, Gli amori ridicoli II V The present Ph.D. dissertation is organized as follows. Chapter 1 An overview of pressure oscillation phenomenology in a solid rocket motor is highlighted. To understand the origin of pressure oscillations, a presentation of the basic phenomena characterizing the aeroacoustic coupling is provided. The aeroacoustic resonance characterization is completed with the description of Rossiter's feedback loop model and its possible interpretation. Some notes about flute mode behavior, lock-in phenomenon and combustion instabilities are given. The vortical structure definition and identification criteria are also presented. Chapter 2 The state of the art of the most important methods for aeroacoustic modeling are presented. After a general historical summary, the methods are described in terms of their fundamental features. Generalities are given about the full numerical simulations. Then Matveev's and Jou and Menon's reduced order models are introduced and analyzed. Chapter 3 An overview of SRM aeroacoustic mathematical model is provided, with special care in the derivation and analysis of the vorticity equation. A description of AGAR quasi-one dimensional model is presented. Chapter 4 The validation test case here presented is the simulation of cold flow in an axisymmetric combustor. A comparison with Jou and Menon's results is provided. The behavior and main characteristics of AGAR model are described, and an analysis of the interaction between vortex dynamics and acoustic waves is obtained. Chapter 5 The simulation of the aeroacoustic phenomena of P80 solid rocket motor, first stage of Vega launcher, by AGAR model is considered. The experimental data and the numerical results are described, analyzed and compared.

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“…Consider the combination of the ow turning and the rotational ow correction as represented by Eqs. (44) and (51). Their sum is…”

Section: Rotational Flow Correctionmentioning

confidence: 99%

Aeroacoustic instability in rockets

Flandro¹,

Majdalani

2001

37th Joint Propulsion Conference and Exhibit

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Current solid-propellant rocket instability calculations (e.g., Standard Stability Prediction Program) account only for the evolution of acoustic energy with time. However, the acoustic component represents only part of the total unsteady system energy; additional kinetic energy resides in the shear waves that naturally accompany the acoustic oscillations. Because most solid-rocket motor combustion chamber con gurations support gas oscillations parallel to the propellant grain, an acoustic representation of the ow does not satisfy physically correct boundary conditions. It is necessary to incorporate corrections to the acoustic wave structure arising from generation of vorticity at the chamber boundaries. Modi cations of the classical acoustic stability analysis have been proposed that partially correct this defect by incorporating energy source/sink terms arising from rotational ow effects. One of these is Culick's ow-turning stability integral; related terms that are not found in the acoustic stability algorithm appear. A more complete representation of the linearized motor aeroacoustics is utilized to determine the growth or decay of the system energy with rotational ow effects accounted for already. Signi cant changes in the motor energy gain/loss balance result; these help to explain experimental ndings that are not accounted for in the present acoustic stability assessment methodology.

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A subscale test program to assess the vortex shedding driven instabilities in segmented solid rocket motors

Cited by 15 publications

References 1 publication

Comparison of Different Passive Control Solutions for Reducing SRM Pressure Oscillations Using Cold Flow Experiments

Comparison of Different Passive Control Solutions for Reducing SRM Pressure Oscillations Using Cold Flow Experiments

Numerical simulations of acoustic resonance of Solid Rocket Motor

Aeroacoustic instability in rockets

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