Experimental validation of stability assessment methods for segmented solid propellant motors

Vincent, François; Traineau, J. C.; Prévost, Michel; Lupoglazoff, Nicolas

doi:10.2514/6.1993-1883

Cited by 13 publications

(9 citation statements)

References 5 publications

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“…That conclusion, and particularly the reasons behind it, more clarified with sub-scale tests with cold flow and with further numerical simulations (Vuillot et al 1993;Lupoglazoff and Vuillot 1996). Those works document the discovery of a new phenomenon, the second kind of vortex shedding referred to above, occurring without edges or obstacles, and called "parietal vortex shedding" Vuillot 1996 and.…”

mentioning

confidence: 86%

Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics

Culick

2000

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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mentioning

confidence: 86%

Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics

Culick

2000

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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“…Each corner or protruding object (i.e: inhibitor rings) can be a point for fluid-dynamics instabilities origin and a vorticity production can occur if the generated shear layer becomes unstable. Therefore, the presence of an obstacle or of propellant surface discontinuities can involve vorticity generation [107,106]. Culick underlines the presence of a shear flow region adjacent to a surface with radial mass injection [27]; in a solid rocket motor such addition is related to the grain regression.…”

Section: Fluid-dynamics Instabilities and Vortex Sheddingmentioning

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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“…As will be seen later, this grid size is suitable for resolving the boundary layer at the second diaphragm where the origin of instability is located. Vuillot et al, 8 have encountered a cell Reynolds number limitation at the second diaphragm (no-slip wall). Hence they de®ne a viscosity limit.…”

Section: Computational Domainmentioning

confidence: 99%

“…Also, in the range 50m lam 4 m`200m lam the solutions obtained with the ®ne mesh are approximately the same. Thus, in view of these results and in order to verify the limit observed by Vuillot et al 8 necessary to capture the boundary layer that develops along the second diaphragm (minimum of six grid points), we chose the viscosity of 80m lam to perform computations on the ®ne mesh.…”

Section: Computational Domainmentioning

confidence: 99%

See 1 more Smart Citation

Shear layer instability and acoustic interaction in solid propellant rocket motors

Kourta

1997

Int. J. Numer. Meth. Fluids

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Experimental validation of stability assessment methods for segmented solid propellant motors

Cited by 13 publications

References 5 publications

Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics

Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics

Numerical simulations of acoustic resonance of Solid Rocket Motor

Shear layer instability and acoustic interaction in solid propellant rocket motors

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