Flameholding characteristics of ethylene-fueled model scramjet in shock tunnel

Kim, Keunyeong; Park, Gisu; Jin, Seongmin

doi:10.1016/j.actaastro.2019.02.022

Cited by 14 publications

(2 citation statements)

References 24 publications

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“…The smaller diameter the injector had, the greater performance the combustor acquired. In addition, Kim et al (2019) studied the flameholding characteristics of an ethylene-fueled scramjet through shadowgraph and flame luminescence image. The injection location affected flame stabilization mode and combustion stability.…”

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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“…For the Mach number measurement, the uncertainty was mainly caused by the imaging process. Because the Mach number dominates the structure of the supersonic flow field and it is difficult to measure the pre and post-shock wave flow conditions simultaneously, it is general to determine the Mach number by using the flow visualization techniques to capture the angle of the oblique shock wave [34] or the shock wave standoff distance at the blunt body [31]. In the present work, the flow visualization technique, the Z-type shadowgraph technique, was also used to determine the Mach number.…”

Section: Plos Onementioning

confidence: 99%

Assessment of drag measurement techniques in a shock tunnel

et al. 2022

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Three force measurement techniques in a shock tunnel, the free-flight, movable-support force balance, and stress-wave force balance techniques were employed, and each technique’s characteristics were assessed. For each force measurement technique, the system setup, data processing method, measurement uncertainties, and applied range of the test model size-flow establishment time were described in detail and compared. For a comparison and discussion, the drag coefficients of a circular pointed cone model with a semi-angle of 18.4° at a nominal freestream Mach number of 6 were measured. As a result, three force measurement techniques yield similar drag coefficients. However, the measurement uncertainties were increased in the order of the free-flight, the stress-wave force balance, and the movable-support force balance techniques. The main causes of the measurement uncertainties were the corner detection uncertainties for the free-flight techniques, and the propagation of the internal or external vibrations for the movable-support and stress-wave force balance techniques. To estimate the appropriate range of the test model size and flow establishment time for each technique’s application, the force measurement systems of the present work and the available literature were compared. As a result of comparative discussion, force measurement environments that can be advantageous for each technique are suggested.

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