Ethylene flame-holding in double ramp flows

Chang, Eric Won Keun; Yang, Seung Min; Park, Gisu; Choi, Hong‐Keun

doi:10.1016/j.ast.2018.07.012

Cited by 19 publications

(3 citation statements)

References 37 publications

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“…The stagnation temperature of the incoming flow had a significant impact on flame stabilization. This was tested by Chang EWKC et al (2018). The stagnation temperature ranged from 1270 K to 1810 K. The results showed that a stable flame was maintained inside the cavity at 1540 K, whereas no flame was established at 1270 K although ignition was achieved.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Wen

Tian

Zhang

et al. 2020

J. Zhejiang Univ. Sci. A

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Flame stabilization in a kerosene-fueled scramjet combustor was investigated experimentally through Schlieren, flame luminosity, and wall pressure measurement, aiming to obtain better insight into combustion characteristics. Experiments were conducted in a direct-connected supersonic combustion facility with inflow conditions of Mach number 2.0, stagnation pressure 0.82 MPa, and temperature 950 K, simulating the flight condition of Mach number 4.0. Results revealed that kerosene was able to be ignited when the equivalence ratio of pilot hydrogen reached 0.080, but was unsuccessful when the equivalence ratio was 0.040. Once ignited, the intense combustion induced high back pressure forcing the flame to spread into the isolator. The pilot flame invariably appeared in the cavity shear layer and attached to the cavity ramp under different equivalence ratios of pilot hydrogen. With the mass flux of pilot hydrogen increased, the kerosene flame located near the cavity ramp was asymmetrical and unstable since it propagated upstream repeatedly. Therefore, the kerosene could be ignited by a suitable equivalence ratio of continuous pilot hydrogen, potentially accompanied with unstable combustion.

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Section: Introductionmentioning

confidence: 99%

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Wen

Tian

Zhang

et al. 2020

J. Zhejiang Univ. Sci. A

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“…Shock impingement and large associated changes in local flow-field properties are prevalent for hypersonic flight vehicles (Heiser & Pratt 1994;Ward & Smart 2021). While an uncontrolled flow separation results in an engine unstart (Im & Do 2018) and energy losses, shock impingement in internal flow configurations also initiates combustion (Laurence et al 2013;Landsberg et al 2018;Curran, Wheatley & Smart 2019) and flame-holding (Chang et al 2016(Chang et al , 2018Landsberg et al 2020a,b;Vanyai et al 2021). Although beneficial, the extreme local thermal loads may also result in structural failure (Stillwell 1965).…”

Section: Introductionmentioning

confidence: 99%

“…2018; Curran, Wheatley & Smart 2019) and flame-holding (Chang et al. 2016, 2018; Landsberg et al. 2020 a , b ; Vanyai et al.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers

et al. 2022

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Interactions between shock waves and boundary layers produce flow separations and augmented pressure/thermal loads in hypersonic flight. This study provides details of Mach 7 impinging-shock-flat-plate experiments conducted in the T4 Stalker Tube. Measurements were taken at flow conditions of Mach 7.0 (2.44 MJ kg $^{-1}$ ) and Mach 7.7 (2.88 MJ kg $^{-1}$ ) flight enthalpies with a range of freestream unit Reynolds numbers from $1.43 \times 10^{6}$ m $^{-1}$ to $5.01 \times 10^{6}$ m $^{-1}$ . A shock generator at $12^{\circ }$ or $16^{\circ }$ to the freestream created an oblique shock which impinged on a boundary layer over a flat plate to induce flow separation. The flow field was examined using simultaneous measurements of wall static pressure, heat transfer and schlieren visualisation. Measured heat transfer along the flat plate without the shock impingement indicated that the boundary layer remained laminar for all flow conditions. The shock impingement flow field was successfully established within the facility test duration. The onset of separation was observed by a rise in wall pressure and a decrease in heat transfer at the location corresponding to the stem of the separation shock. Downstream of this initial rise, an increased pressure and higher heating loads were observed. The heat-transfer levels also indicated an immediate boundary layer transition due to the shock impingement. The separation data of the present work showed good agreement with our previous work on shock impingement on heated walls (Chang et al., J. Fluid Mech., vol. 908, 2021, pp. 1–13). A comparison with the previous scaling indicated that the separation also relates to the pressure ratio and the wall temperature parameter.

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Nozzle Flow Influence on Forebody Aerodynamics

Park

2020

Int. J. Aeronaut. Space Sci.

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Ethylene flame-holding in double ramp flows

Cited by 19 publications

References 37 publications

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Experimental investigation on flame stabilization of a kerosene-fueled scramjet combustor with pilot hydrogen

Hypersonic shock impingement studies on a flat plate: flow separation of laminar boundary layers

Nozzle Flow Influence on Forebody Aerodynamics

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