Thermoacoustic Coupling Mechanism of Combustion Instability in a Continuously Variable Resonance Combustor

Koizumi, Hiroshi; Tsutsumi, Seiji; Omata, Noriyasu; Shimizu, Taro

doi:10.2514/6.2020-1071

Cited by 2 publications

(2 citation statements)

References 26 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Dynamic mode decomposition (DMD (Tu et al, 2014)) is a purely data-driven matrix decomposition technique that does not rely on any prior physical law and aims to characterize data modes using extracted low-dimensional structures. The temporal and spatial modes of the data sets can be decomposed individually by DMD, which makes the method particularly suitable for analyzing the thermoacoustic instability at specific frequencies (Koizumi et al, 2020). Over the past 10 years, several forms of DMD have been developed, and the version used in this study, named exact DMD, was summarized by Tu et al (Tu et al, 2014).…”

Section: Dynamic Mode Decomposition Analysismentioning

confidence: 99%

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Guo

Ren

et al. 2022

Front. Energy Res.

View full text Add to dashboard Cite

This study numerically investigated the thermoacoustic combustion instability characteristics of a scaled rocket combustor based on a hybrid of the Reynolds-averaged Navier–Stokes and large–eddy simulation method. The turbulence–combustion interactions were treated using flamelet generated manifold approach. An unstable case was simulated with detailed reaction mechanisms (GRI-Mech 3.0). The obtained results agree well with experiment data from Purdue University, in terms of pressure oscillations frequency and power spectral density spectrum. The combustion instability mode was identified to be coupled with the first longitudinal acoustic mode of the combustion chamber by dynamic model decomposition method. According to Rayleigh index analysis, the unstable driving source was found to be located near the combustor step, which was further confirmed by time-averaged flow fields. Detailed three-dimensional vortex ring shedding evolutions at the combustor step were tracked with fine time resolution. Results indicate that the combustion instability arises from periodic vortex ring shedding at the combustor step and interacting with the chamber wall. The unburnt reactants were rolled up by the shedding vortex ring, which would not break up until impact with the chamber wall. Therefore, the mixing performance was significantly enhanced, leading to sudden heat release. Consequently, the thermal energy is added to the acoustic field, and the first longitudinal mode is thus reinforced, giving rise to large amplitude axial velocity oscillations which prompt the generation of the new vortex ring. The results of the present investigation will support the design and development of high-performance rocket engines.

show abstract

Section: Dynamic Mode Decomposition Analysismentioning

confidence: 99%

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Guo

Ren

et al. 2022

Front. Energy Res.

View full text Add to dashboard Cite

show abstract

“…Aoki et al (2020) experimentally examined the randomness of pressure fluctuations during intermittent high-frequency combustion instability in a cylindrical combustor by estimating the information entropy in an ordinal partition transition network. Koizumi et al (2020) examined the directional coupling between the pressure and heat release rate fluctuations during high-frequency combustion instability in a continuously variable resonance combustor using the transfer entropy. Kasthuri et al (2022) have experimentally studied the spatio-temporal dynamics during a transition from the intermittent state to high-frequency combustion instability in a model rocket combustor with multiple elements using a weighted spatial network.…”

Section: Introductionmentioning

confidence: 99%

Complex-network analysis of high-frequency combustion instability in a model single-element rocket engine combustor

et al. 2023

View full text Add to dashboard Cite

We study the spatio-temporal dynamics of high-frequency combustion instability in a model single-element rocket combustor using an acoustic energy flux-based spatial network. The acoustic energy source collapses by the formation of small communities with weak connection when the flame edge is attached to the injector rim. In contrast, large communities with strong connection are formed in the shear layer between the oxygen and hydrogen jets when the flame edge is detached from the injector rim, which has a significant impact on driving combustion instability. The switching between the attachment and detachment of the flame edge during combustion instability can be explained by the spectral-clustering-based transition network constructed from the pressure and flow velocity of the hydrogen jet at the injector exit, and the temperature near the injector rim.

show abstract

Thermoacoustic Coupling Mechanism of Combustion Instability in a Continuously Variable Resonance Combustor

Cited by 2 publications

References 26 publications

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Complex-network analysis of high-frequency combustion instability in a model single-element rocket engine combustor

Contact Info

Product

Resources

About