Numerical researches of gaseous fuel pre-injection in hypersonic 3-D inlet

Gouskov, O.; Waltrup, P. J.; Kopchenov, V. I.; Lomkov, K.; Vinogradov, V. A.

doi:10.2514/6.2000-3599

Cited by 5 publications

(8 citation statements)

References 1 publication

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“…At x/d = 16, the Wide and Medium pylons exhibit a self normalized penetration height of greater than 1.5 (the average value observed in previous studies). [2][3][4] This plot again shows the slight advantage the wide pylon has compared to the Medium pylon, which makes it a better choice given they produce similar losses. Tall pylon provides the thinnest spread, which corresponds to the jet being spread more so along the vertical (y) axis.…”

Section: No-plif End View Resultsmentioning

confidence: 99%

“…Further numerical studies have begun to propose optimal geometries for these pylons. 4 The current research aims to investigate the use of these optimal pylon geometries and introduce imaging techniques that have not been applied to this configuration as of yet.…”

Section: Fuel Injection and Mixingmentioning

confidence: 99%

“…The hardware was installed with injection immediately behind the pylon and at a distance of 0.9L (cavity lengths) upstream of the cavity employed by Gruber et al 1 Each pylon is a thin triangular wedge with a 30 o inclination angle. Optimal pylon heights, widths, and pylon distances from injection were determined from previous computational research 4 and correlate with sizes used in prior experimentation. [2][3] The investigation included measuring the effects of penetration height and width, shock effects, mixing effectiveness and pressure profiles.…”

Section: Mixing Effects Of Pylon-aided Fuel Injection Located Upstreamentioning

confidence: 99%

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Mixing Effects of Pylon-Aided Fuel Injection Located Upstream of a Flameholding Cavity in Supersonic Flow

Montes¹

2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: No-plif End View Resultsmentioning

confidence: 99%

Section: Fuel Injection and Mixingmentioning

confidence: 99%

Section: Mixing Effects Of Pylon-aided Fuel Injection Located Upstreamentioning

confidence: 99%

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Mixing Effects of Pylon-Aided Fuel Injection Located Upstream of a Flameholding Cavity in Supersonic Flow

Montes¹

2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Each pylon was a triangular wedge with a 30°inclination. Pylon designs were based on the two best geometries determined from a computational study, 6 and correlated with sizes used in separate experimental work. 7,8 The research showed that pylons improved penetration and mixing potential over a baseline transverse injection case without a pylon.…”

Section: Introductionmentioning

confidence: 99%

Performance of Pylons Upstream of a Cavity-Based Flameholder in Non-Reacting Supersonic Flow (Postprint)

Haubelt¹,

King²,

Gruber³

et al. 2006

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, 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 Department of Defense, Washington Headquarters Services, Directorate for Information SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORING AGENCY ACRONYM(S) AFRL-PR-WP ABSTRACTCavity-based fuel injection and flame holding, typically found in hydrocarbon-fueled scramjet applications, are of current interest for use in supersonic combustors. Both the Air Force Research Lab (AFRL) and the Air Force Institute of Technology (AFIT) at WrightPatterson Air Force Base in Ohio are investigating the enhancement of fuel-air mixing with small pylons that project into the supersonic flow upstream of a flame holder cavity. The pylons were of three sizes (medium, tall, and wide) and shaped as a thin triangular wedge with a 300 inclination angle. A total of four configurations (pylons plus baseline) were tested at two different fuel injection pressures in a Mach continuous flow wind tunnel housed at AFRL. The goal was to measure the mixing efficiency and shock loss of each pylon setup for comparison to the baseline condition of transverse injection without pylons. Non-reacting flow was measured using intrusive and non intrusive techniques to obtain pitot pressure, total temperature, cone-static pressure and laser induced Raman spectroscopy to determine species concentration over the cavity. SUBJECT TERMS D.American Institute of Aeronautics and Astronautics 2 P t = total pressure q = jet-to-freestream momentum flux ratio u = freestream velocity W = pylon width X i = mole fraction X p = spanwise centerline of injection port x flam = flammable mixture distance x fm = fully mixed distance = power law coefficient = equivalence ratio max = maximum equivalence ratio = pylon wedge angle = density = total pressure loss coefficient

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“…The methods for ignition and flame-holding in subsonic combustors are not generally applied to supersonic combustors because of their lower aerodynamic efficiency. Several concepts have been proposed to promote air/fuel mixing, combustion ignition and flame-holding in supersonic flows, such as swirling jets, the thin plate for fuel injection, cavities embedded in combustor walls, ramp injectors and stream-wise vortex generators [1][2][3][4][5][6][7]. Each concept has its own merits and limitations when used in the propulsion system of supersonic air-breathing vehicles; however better understanding on these topics was gained from these kinds of studies and the hypersonic research benefits.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation on the flowfield of “swallowtail” cavity for supersonic mixing enhancement

Wang

Jiang

et al. 2008

Acta Mech Sin

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A "swallowtail" cavity for the supersonic combustor was proposed to serve as an efficient flame holder for scramjets by enhancing the mass exchange between the cavity and the main flow. A numerical study on the "swallowtail" cavity was conducted by solving the three-dimensional Reynolds-averaged Navier-Stokes equations implemented with a k-ε turbulence model in a multi-block mesh. Turbulence model and numerical algorithms were validated first, and then test cases were calculated to investigate into the mechanism of cavity flows. Numerical results demonstrated that the certain mass in the supersonic main flow was sucked into the cavity and moved spirally toward the combustor walls. After that, the flow went out of the cavity at its lateral end, and finally was efficiently mixed with the main flow. The comparison between the "swallowtail" cavity and the conventional one showed that the mass exchanged between the cavity and the main flow was enhanced by the lateral flow that was induced due to the pressure gradient inside the cavity and was driven by the three-dimensional vortex ring generated from the "swallowtail" cavity structure.

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Numerical researches of gaseous fuel pre-injection in hypersonic 3-D inlet

Cited by 5 publications

References 1 publication

Mixing Effects of Pylon-Aided Fuel Injection Located Upstream of a Flameholding Cavity in Supersonic Flow

Mixing Effects of Pylon-Aided Fuel Injection Located Upstream of a Flameholding Cavity in Supersonic Flow

Performance of Pylons Upstream of a Cavity-Based Flameholder in Non-Reacting Supersonic Flow (Postprint)

Numerical investigation on the flowfield of “swallowtail” cavity for supersonic mixing enhancement

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