Experimental and numerical investigations of nozzle geometry effect on the instabilities in solid propellant boosters

Anthoine, J.; Buchlin, Jean‐Marie; Guery, Jean-Francois

doi:10.2514/6.2000-3560

Cited by 15 publications

(12 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…If the linearized equations of motion are considered, the method provides a solution in terms of reference acoustic mode perturbation 3 . This condition establishes a strong dependence on the acoustic field.…”

Section: Acoustic Balance Methodsmentioning

confidence: 99%

“…The stretching of the vortical structure with the motion toward the impingement point was also pointed out. Full numerical simulations were proposed by Anthoine (2000, [3]) and Hulshoff (2001, [60]) for the analysis of vortex-nozzle interaction; Anthoine et al (2000, [3]) demonstrated the effect of the submergence region as a sound amplifier. Numerical simulations have been also used by Dotson (1997, [34]) for studies on the Titan IV SRMU.…”

Section: State Of the Art Of The Aeroacoustic Modelingmentioning

confidence: 99%

“…The effect of different nozzle geometries is also analyzed by Anthoine [3]. In the same Mach number range, for each analyzed nozzle configuration the same acoustic mode is excited, and the only difference is the obtained pressure oscillation level.…”

Section: Anthoine's Model For Submergence Interactionmentioning

confidence: 99%

“…Such cases are related to highly rotational velocity fields 3. The reference acoustic modes are obtained from the solutions of the homogeneous equations, obtained in absence of forcing function, two-phase flow and combustion effects.…”

mentioning

confidence: 99%

See 3 more Smart Citations

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

View full text Add to dashboard Cite

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.

show abstract

Section: Acoustic Balance Methodsmentioning

confidence: 99%

Section: State Of the Art Of The Aeroacoustic Modelingmentioning

confidence: 99%

Section: Anthoine's Model For Submergence Interactionmentioning

confidence: 99%

mentioning

confidence: 99%

See 2 more Smart Citations

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

View full text Add to dashboard Cite

show abstract

“…However, the extension of the computational field substantially increases the cost of calculations. For problems, when the internal flow in the combustion chamber is of primary interest we follow references [13] and [14] and limit the computational field at the nozzle exit and apply a simple prescription of pressure. Although, from the numerical point of view the prescription of the exit pressure is formally not well posed if the exit is supersonic outlet, the physics of nozzles dictates that the supersonic outlet can only be achieved if the flow reaches a critical condition at the throat.…”

Section: Boundary Conditionsmentioning

confidence: 99%

Burning surfaces evolution in solid propellants: A numerical model

Szmelter

Ortiz

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Abstract:A methodology for the solution of the internal physics of solid propellant rocket motors is described. The problem involves the simulation of a burning surface -a dynamically changing interface between the solid propellant and combustion gas phases. Burning surfaces can have complex shapes that change in time according to the solid chemistry and deformation, and according to gas parameters. The key element of the proposed model is the development of a new technique to conform the computational mesh to the interface. The paper documents mesh handling and solution procedures suitable for axisymmetric applications. The approach is to treat the problem in a uniform manner for solid and gas phases as a flow with moving sources. Unstructured, dynamically adjusting meshes are employed in the same way for both phases. This paper presents two specific test cases, with non-deforming solids, for which a comparison with theoretical results is possible.

show abstract