Mixing and Combustion Studies Using Cavity-Based Flameholders in a Supersonic Flow

Gruber, Mark; Donbar, Jeffrey M.; Carter, C. D.; Hsu, Kuang–Yu

doi:10.2514/1.5360

Cited by 310 publications

(148 citation statements)

References 14 publications

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“…Previous research has shown that in the case of a cavity with the fuel injector inside the cavity, the open cavity with the aft ramp has a higher performance as a flame holder [22], although the performance depends on injection position [22,30]. However, in the case of a cavity with upstream fuel injection, a small L/D has better performance for flame stabilization compared to the cavity with the aft ramp.…”

Section: Introductionmentioning

confidence: 80%

“…A cavity model also enhances the characteristics of air mixing [20], and it has been investigated as a flame holding mechanism for the scramjet engine [21][22][23][24][25][26][27][28][29][30][31][32]. Additionally, the cavity model possesses the feature of comparatively low profile drag compared to a step injector model [33,34] or strut injector model [35,36], although this feature depends strongly on the cavity geometry.…”

Section: Introductionmentioning

confidence: 99%

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Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Ukai

Zare‐Behtash

Erdem

et al. 2014

Experimental Thermal and Fluid Science

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Section: Introductionmentioning

confidence: 80%

Section: Introductionmentioning

confidence: 99%

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Ukai

Zare‐Behtash

Erdem

et al. 2014

Experimental Thermal and Fluid Science

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“…The main parameters to evaluate efficiency of the combustion chamber are the mixture degree, ignition condition, combustion efficiency and pressure losses. Results of experimental researches at different Mach numbers [9][10], however, have shown essential discrepancy between real characteristics of combustion chamber and anticipated values, in particular, in realization of self-ignition and achievement of high level of combustion efficiency.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hydrogen Jet Injection and Ignition in Supersonic Flow

Zakharova¹,

Федорова²,

Valger³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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“…Although laser-based techniques like coherent anti-Stokes Raman scattering (CARS) (Eckbreth et al 1988, Vereschagin et al 2001, Cutler et al 2003, O'Byrne et al 2007) and planar laser-induced fluorescence (PLIF) (Allen et al 1993, McMillin 1993, McIntyre et al 1997, Gruber et al 2004) have proved to be very useful in laboratory scramjet tests because of their nonintrusive, species-specific measurement capabilities, these techniques require large, expensive pulsed laser systems that cannot realistically be put onto a flight experiment.…”

Section: Introductionmentioning

confidence: 99%

Diode Laser Sensor for Scramjet Inlets

O’Byrne¹,

Wittig²,

Kurtz³

et al. 2011

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Report Documentation PageForm Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. REPORT DATE JUN 20112. REPORT TYPE This work presents test results of a diode-laser sensor for an axially symmetric inlet in a Mach 6 hypersonic flow facility. The conical inlet design presented here is more realistic than the flat plate design presented in the previous report, and is similar to the design that will be chosen as part of the Australian Space Research Program SCRAMSPACE flight test scheduled for 2012. The optical system was changed for this study to make the pitch and catch optics less sensitive to vibration, and to fit into a smaller volume than for the previous test. In addition, wavelength modulation detection was attempted with the system. Initial tests of the conical inlet design showed that it was not starting, as indicated using flow visualization images. The second version of the sensor has similar velocity sensitivity to the system used for the flat plate inlet test. The conical system was, however, still too susceptible to amplitude noise, which hinders the ability of the system to measure the free stream temperature or the angle of attack. Electrical problems with the log-ratio amplifier prevented temperature measurements for the vehicle. Preliminary vibration tests have shown that the problem is caused by independent motion between the laser and collimator when the tunnel fires. A preliminary design of a low-power lock-in amplifier for use in field experiments was completed, and tests with current inputs in place of photodiodes proved successful. SUBJECT TERMS

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Mixing and Combustion Studies Using Cavity-Based Flameholders in a Supersonic Flow

Cited by 310 publications

References 14 publications

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

Numerical Simulation of Hydrogen Jet Injection and Ignition in Supersonic Flow

Diode Laser Sensor for Scramjet Inlets

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