Flowfield in a Model Scramjet Combustor in Case of Injecting Fuel Perpendicularly behind the Backward-Step.

Takahashi, Shuhei; Yamano, Goro; Wakai, Kazunori; Tsue, Mitsuhiro; Kono, Michikata

doi:10.2322/jjsass.47.333

Cited by 2 publications

(1 citation statement)

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“…This mechanism does not consider the effects of downstream configuration in the combustor on the transition. Takahashi et al [5] demonstrated that the mode transition occurred due to the changing geometry of the downstream section in the combustor at the same equivalence ratio. The intensive mode was attainted in the constant-area combustor, and the weak mode was attained in the diverging combustors.…”

Section: S I)mentioning

confidence: 99%

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

Kouchi¹,

Masuya²,

Mitani³

et al. 2012

Journal of Propulsion and Power

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A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weak-and intensive-combustion modes. The weak mode occurred below the overall fuel equivalence ratio (Φ) of around 0.4. Transition from the weak mode to the intensive mode occurred at Φ ~ 0.4, accompanied by a sudden increase in thrust. Mechanisms of the transition were numerically investigated in this study. Our simulations captured the sudden increase in thrust at the mode transition. In the weak mode, combustion occurred in only a region near the topwall where an igniter was installed. The combustion region expanded toward the cowl with boundary-layer separation at the mode transition. Our simulations demonstrated that low ignition capability resulted in the weak mode. We demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire Φ range. Nomenclature G H2•O2 = flame index (=

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Section: S I)mentioning

confidence: 99%

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

Kouchi¹,

Masuya²,

Mitani³

et al. 2012

Journal of Propulsion and Power

View full text Add to dashboard Cite

show abstract

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

Kouchi

Masuya

Mitani

et al. 2012

Journal of Propulsion and Power

View full text Add to dashboard Cite

A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weakand intensive-combustion modes. The weak mode occurred below the overall fuel equivalence ratio () of around 0.4. Transition from the weak mode to the intensive mode occurred at 0:4, accompanied by a sudden increase in thrust. Mechanisms of the transition were numerically investigated in this study. Simulations captured the sudden increase in thrust at the mode transition. In the weak mode, combustion occurred in only a region near the topwall where an igniter was installed. The combustion region expanded toward the cowl with boundary-layer separation at the mode transition. Simulations demonstrated that low ignition capability resulted in the weak mode. This study demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire range.

show abstract

Flowfield in a Model Scramjet Combustor in Case of Injecting Fuel Perpendicularly behind the Backward-Step.

Cited by 2 publications

References 0 publications

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine

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