Low-frequency combustion instability mechanisms in a side-dump combustor

Samaniego, J. M.; Yip, Brandon; Poinsot, Thiérry; Candel, Sébastien

doi:10.1016/0010-2180(93)90120-r

Cited by 68 publications

(25 citation statements)

References 18 publications

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“…Such images yield valuable information on the location of the driving/damping zones (Ref. 14). Figures 7 and 8 are the results for the Aerodynamic and BluffBody nozzles, respectively (Identical operating conditions as in Figure 6).…”

Section: Identification Of Driving Damping Zonesmentioning

confidence: 99%

Lean Premixed Combustion/Active Control

Seery¹

2000

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Section: Identification Of Driving Damping Zonesmentioning

confidence: 99%

Lean Premixed Combustion/Active Control

Seery¹

2000

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“…LES of ramjet has however received less attention although in the early 90's, massive effort coming from the military allowed new designs for such devices. If these configurations are simple in their geometry when no flame holder is used, physical complex phenomephenomenan make them hard to simulate: flame stabilization is very complex and strongly influenced by flow structures, wall heat fluxes are high because the flame develops in the vicinity of shear layers near combustor's structure... Two main type of instabilities [5,6,7] can appear in such combustors and are essentially due to interactions between combustion, acoustic and turbulence that can lead to non desired operating conditions of the chamber or its destruction. The first type of instability appears at low frequency and is linked with pressure oscillations in the whole device which can deteriorate air breathing and imperfect combustion.…”

Section: Introductionmentioning

confidence: 99%

Comparison of numerical methods and combustion models for LES of a ramjet

Roux

Reichstadt

Bertier

et al. 2009

Comptes Rendus. Mécanique

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Ramjets are very sensitive to instabilities and their numerical predictions can only be addressed adequately by Large Eddy Simulation (LES). With this technique, solvers can be implicit or explicit and handle structured, unstructured or hybrid meshes... Turbulence and combustion models are other sources of differences. The impact of these options is here investigated for the ONERA ramjet burner. To do so, two LES codes developed by ONERA and CERFACS compute one stable operating condition. Preliminary LES results of the two codes underline the overall robustness of LES. Mean flow features at the various critical sections are reasonably well predicted by both codes. Disagreement mainly appear in the chamber where combustion positions differ pointing to the importance of the combustion and subgrid mixing models. The two LES produce different energy containing motions. With CEDRE, a low frequency dominates while AVBP produces different ranges of low frequencies that can be linked with acoustic modes of the configuration. To cite this article : A. Roux et al., C. R. Mecanique (2009). RésuméStratégie numérique pour la simulation aux grandeséchelles de statoréacteurs. L'impact des méthodes numériques ainsi que du modèle de combustion sur la simulation aux grandeséchelles d'un statofuséeétudié expérimentalement par l'ONERA est analys. Pour ce faire, deux codes développés respectivement par l'ONERA et le CERFACS sont utilisés pour calculer un point de fonctionnement stable. Les caractéristiques moyennes sont raisonnablement bien prédites par les deux codes. Les désaccords apparaissent dans la chambre de combustion où la position des zones réactives diffèrent soulignant l'importance des modèles utilisés. Les deux SGE produisent des contenusénergétiques fréquentiels différents. Avec CEDRE, une basse fréquence domine le spectre tandis qu'AVBP montre toute une gamme de basses fréquences qui peutêtre liée aux modes acoustiques de la configuration. Pour citer cet article : A. Roux et al., C. R. Mecanique (2009).

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“…To obtain important factors for control of combustion oscillations, quantitative measurements of the flame response to acoustic perturbations have been conducted by Poinsot et al (3) and Harper et al (4) . Flame-acoustic interactions in unstable combustors have been investigated by Samaniego et al (5) , Broda et al (6) and Balachandran et al (7) using phase-locked measurements. In general, these results show the significant influence of the combustor geometry or acoustic properties of the combustion system on the unstable phenomena.…”

Section: Introductionmentioning

confidence: 99%

Large-Scale Vortical Motion and Pressure Fluctuation in Noise-Controlled, Swirl-Stabilized Combustor

Shimura

Tanahashi

Choi

et al. 2009

JTST

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To clarify the mechanisms of combustion oscillation, combustion noise and their suppression by secondary fuel injection, simultaneous measurements of stereoscopic particle image velocimetry (SPIV) and pressure fluctuation in combustion chamber were conducted on several planes of a swirl-stabilized turbulent premixed flame for no control case and noise-controlled case by continuous secondary fuel injection. Velocities measured by SPIV were averaged in 8 phases of the pressure fluctuation and streamlines were obtained from the phase-averaged velocities. For no control case, large-scale vortical structures are generated in regions around the axial centerline of the combustor and outer edge of the swirl nozzle in the phase of low pressure. With increasing pressure, they move near the contour surface of mean progress variablec = 0.5 which have been obtained in the previous study. These large-scale vortical motions induce fluctuation of flame front and enhance entropy term in the acoustic sound source. The secondary fuel injection suppresses the velocity fluctuation in the inner recirculation zone, resulting in reduction of combustion noise. These results show that control of the large-scale vortical motion is important for reduction of combustion noise.

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Low-frequency combustion instability mechanisms in a side-dump combustor

Cited by 68 publications

References 18 publications

Lean Premixed Combustion/Active Control

Lean Premixed Combustion/Active Control

Comparison of numerical methods and combustion models for LES of a ramjet

Large-Scale Vortical Motion and Pressure Fluctuation in Noise-Controlled, Swirl-Stabilized Combustor

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