Ariane 5-MPS - Chamber pressure oscillations full scale firing results: Analysis and further studies

Scippa, Sergio; Philippe, Pascal; Zanier, Francesca

doi:10.2514/6.1994-3068

Cited by 35 publications

(9 citation statements)

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“…Solid rocket motors having large length (L) to diameter (D) ratio (i.e. L/D > 9 − 10, as US Space Shuttle SRM [47], Ariane 5 P230 SRM [93], Titan SRM [16,34] and the five-segment Even if each motor shows different timing and duration of the oscillating phase, the pressure oscillations are described by some common features. The pressure fluctuations are generally not threatening for motor life but, in spite of this, the oscillations represent a point of interest.…”

Section: Solid Rocket Motor Pressure Oscillationsmentioning

confidence: 99%

“…Several experimental tests have been performed in order to characterize the different phenomena involved into the acoustic resonance. As shown by the static firing tests analysis developed by Scippa, the Ariane 5 P320 SRM is characterized by the presence of pressure oscillations (1994, [93]). Couton (1999, [25]) experimental analysis 1 showed that the wall injection of mass flow rate modifies the acoustic amplification level.…”

Section: State Of the Art Of The Aeroacoustic Modelingmentioning

confidence: 99%

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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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Section: Solid Rocket Motor Pressure Oscillationsmentioning

confidence: 99%

Section: State Of the Art Of The Aeroacoustic Modelingmentioning

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

View full text Add to dashboard Cite

show abstract

“…These pressure oscillations have been reported for the Space Shuttle RSRM, the Titan-34D SRM, the Titan-IV SRMU and the Ariane 5 MPS. [4][5][6][7][8] All these boosters have a length over diameter ratio (L/D) in the range 9 − 12 and demonstrated similar pressure oscillations, whatever the number of segments. Zero-peak relative amplitudes are typically less than 0.5% for pressure oscillations and less than 5% for thrust oscillations.…”

Section: Previous Studiesmentioning

confidence: 99%

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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“…The results demonstrated that pressure oscillations could be excited when the vortices shed by the thermal inhibitor passing in front of the submerged cavity, and the oscillation amplitude increased linearly with the submerged cavity volume. In addition, Brown et al, 19 Flatau and Moorhem, 20 and Scippa et al 10 conducted cold gas experiments on the subscale motors of Titan 34D, Space Shuttle, and Ariane 5 SRM, respectively. Similar conclusions, such as pressure oscillations were due to vortex shedding caused by the thermal inhibitor, were obtained.…”

Section: Introductionmentioning

confidence: 99%

Influence of thermal inhibitor position and temperature on vortex-shedding-driven pressure oscillations

Zhang

et al. 2013

Chinese Journal of Aeronautics

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Vortex-acoustic coupling is one of the most important potential sources of combustion instability in solid rocket motors (SRMs). Based on the Von Karman Institute for Fluid Dynamics (VKI) experimental motor, the influence of the thermal inhibitor position and temperature on vortex-shedding-driven pressure oscillations is numerically studied via the large eddy simulation (LES) method. The simulation results demonstrate that vortex shedding is a periodic process and its accurate frequency can be numerically obtained. Acoustic modes could be easily excited by vortex shedding. The vortex shedding frequency and second acoustic frequency dominate the pressure oscillation characteristics in the chamber. Thermal inhibitor position and gas temperature have little effect on vortex shedding frequency, but have great impact on pressure oscillation amplitude. Pressure amplitude is much higher when the thermal inhibitor locates at the acoustic velocity anti-nodes. The farther the thermal inhibitor is to the nozzle head, the more vortex energy would be dissipated by the turbulence. Therefore, the vortex shedding amplitude at the second acoustic velocity antinode near 3/4L (L is chamber length) is larger than those of others. Besides, the natural acoustic frequencies increase with the gas temperature. As the vortex shedding frequency departs from the natural acoustic frequency, the vortex-acoustic feedback loop is decoupled. Consequently, both the vortex shedding and acoustic amplitudes decrease rapidly.

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Ariane 5-MPS - Chamber pressure oscillations full scale firing results: Analysis and further studies

Cited by 35 publications

References 0 publications

Numerical simulations of acoustic resonance of Solid Rocket Motor

Numerical simulations of acoustic resonance of Solid Rocket Motor

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

Influence of thermal inhibitor position and temperature on vortex-shedding-driven pressure oscillations

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