Combustion Characteristics of a Cavity Flameholder with a Burned-Gas Injector at the Cavity Bottom Wall in a Scramjet Model Combustor

Yamaguchi, Tatsuya; Hizawa, Tomohiro; Yugami, Yasuto; Hasegawa, Mariko; Kudo, Taku; Hayakawa, Akihiro; Kobayashi, Haruo

doi:10.2322/tjsass.63.160

Cited by 6 publications

(1 citation statement)

References 6 publications

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“…The combustion gas for the micro-rocket torch sufficiently promotes ignition in the scramjet combustor by vertically injecting the combustion gas in the combustor. In previous studies, we clarified the effectiveness of a micro-rocket torch, which injects combustion gas, in promoting ignition within the scramjet combustor (Kobayashi et al, 2004;Yamaguchi et al, 2020;Ogawa et al, 2023). For example, in a previous study, we clarified the forced ignition process within the cavity using modal analysis (Ogawa 2023).…”

Section: Introductionmentioning

confidence: 99%

Development of combustion gas measurement systems for micro-rocket torch using a diode laser sensor

HIRAYAMA,

OGAWA

2023

Mechanical Engineering Letters

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Much noise from the combustion oscillations and more are included in the measurement data for combustion experiments of micro-rocket torch. To develop the combustion gas measurement system for the micro-rocket torch using tunable diode laser absorption spectroscopy (TDLAS) method, we develop the denoising algorithms using the Savitzky-Golay filter and K-fold cross validation for improved noise-rejection capabilities. First, a validation study has been conducted on the gas measurement system using denoising algorithms in the case of atmospheric measurements. The atmospheric measurement results using denoising algorithms are in exceptionally good agreement with atmospheric conditions. Therefore, this result indicated that this algorithm gave satisfactory accuracies in the case of atmospheric measurements. Next, we investigated the combustion gas measurements for micro-rocket torch using the TDLAS method and demonstrated the usefulness of the denoising algorithms. From the results of this study, it is obvious that a significant accuracy improvement was obtained in the majority of absorbance spectrum cases with use of the denoising algorithms. Furthermore, the tendency of time-series torch gas temperature using TDLAS method is similar to the time-series estimated values.

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Section: Introductionmentioning

confidence: 99%

Development of combustion gas measurement systems for micro-rocket torch using a diode laser sensor

HIRAYAMA,

OGAWA

2023

Mechanical Engineering Letters

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An Experimental Investigation on Forced Ignition Characteristics of Hydrocarbon Mixture Fuel in Scramjet Combustor

Ogawa

Kobayashi

Tomioka

2022

Lecture Notes in Electrical Engineering

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Mechanisms of ignition and combustion instability in a scramjet combustor with micro-rocket torch using dynamic mode decomposition

Ogawa

2024

Physics of Fluids

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Achieving ignition and stable combustion in scramjet combustors, which have residence times of milliseconds, requires effective flame stabilization. Previous studies have explored stable forced ignition and flame holding using various igniters, such as micro-rocket and plasma jet torches. This study investigated the forced ignition and combustion instability of a scramjet combustor with a micro-rocket torch. Although the micro-rocket torch successfully ignited the combustor in previous experiments, combustion instabilities were observed in the cavity flame holder through OH* chemiluminescence images. To understand the mechanisms behind forced ignition and combustion instability, dynamic mode decomposition (DMD) was employed. DMD is effective for analyzing combustion dynamics because it extracts spatiotemporally coherent structures from high-dimensional data. The OH* chemiluminescence images from prior experiments were analyzed using DMD to identify the dominant modes associated with the combustion instability. Power spectrum density analysis revealed that low-frequency instabilities (100–400 Hz) were caused by fuel injector flame feedback, very low frequencies (15–50 Hz) were due to torch gas injector flame feedback, and high frequencies (over 1000 Hz) resulted from interference between the cavity flame holder and the flow field. These findings provide insights into the complex flow dynamics within the cavity flame holder and shear layer, thereby enhancing the understanding of combustion instability mechanisms in scramjet engines equipped with micro-rocket torches.

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Combustion Characteristics of a Cavity Flameholder with a Burned-Gas Injector at the Cavity Bottom Wall in a Scramjet Model Combustor

Cited by 6 publications

References 6 publications

Development of combustion gas measurement systems for micro-rocket torch using a diode laser sensor

Development of combustion gas measurement systems for micro-rocket torch using a diode laser sensor

An Experimental Investigation on Forced Ignition Characteristics of Hydrocarbon Mixture Fuel in Scramjet Combustor

Mechanisms of ignition and combustion instability in a scramjet combustor with micro-rocket torch using dynamic mode decomposition

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