Evaluation of parallel injector configurations for supersonic combustion

Northam, G. B.; Greenberg, I.; Byington, Carl S.

doi:10.2514/6.1989-2525

Cited by 74 publications

(24 citation statements)

References 2 publications

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“…Because of the high velocity, high temperature and low density of the combustor flow, the mixing of the fu :1 and air is relatively slow at the higher flight speeds. Consequently, mixing augmentation and enhancement by the controlled generation of turbulence and/or large-scale vortices in the mixing and flame-holding zones are being examined in both numerical studies [2] and experimental studies [3]. These techniques generally involve sorne type of recirculating flow in the wake of a body, step or transverse jet and hence require some finite time to reach steady state (or a quasi-periodic state).…”

Section: Introductionmentioning

confidence: 99%

Flow establishment in a generic scramjet combustor

Jacobs¹,

Rogers

Weidner

et al. 1992

Journal of Propulsion and Power

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Section: Introductionmentioning

confidence: 99%

Flow establishment in a generic scramjet combustor

Jacobs¹,

Rogers

Weidner

et al. 1992

Journal of Propulsion and Power

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“…--Mixing and combustion characteristics of wall-mounted ramps with base fuel injection were studied in the DCSCTF at conditions simulating Mach 5 to 7 flight. [14][15][16] The objective of the tests was to explore the enhancement of the fuel/air mixing and thus reduce the length of a scramjet combustor. Since fuel injection directed downstream is useful to extract energy from hydrogen fuel that has been used to cool the engine and airframe, techniques to enhance the relatively slow mixing of parallel fuel jets were investigated.…”

Section: Dcsctfmentioning

confidence: 99%

“…However, basic research studies of scramjet phenomena continued. These studies included transverse fuel injector operation, 12,13 injector concepts for fuel mixing enhancement, [14][15][16][17] application of nonintrusive measurement systems for supersonic combustion, [18][19][20] and nozzle performance effects. 21,22 Ground test capability at true flight stagnation enthalpy also was needed to simulate the hypervelocity conditions of transatmospheric flight.…”

Section: The Nasp Eramentioning

confidence: 99%

Experimental supersonic combustion research at NASA Langley

Rogers

Capriotti

Guy

1998

20th AIAA Advanced Measurement and Ground Testing Technology Conference

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Experimental supersonic combustion research related to hypersonic airbreathing propulsion has been actively underway at NASA Langley Research Center (LaRC) since the mid-1960's. This research involved experimental investigations of fuel injection, mixing, and combustion in supersonic flows and numerous tests of scramjet engine flowpaths in LaRC test facilities simulating flight from Mach 4 to 8. Out of this research effort has come scramjet combustor design methodologies, ground test techniques, and data analysis procedures. These technologies have progressed steadily in support of the National Aero-Space Plane (NASP) program and the current Hyper-X flight demonstration program. During NASP nearly 2500 tests of 15 scramjet engine models were conducted in LaRC facilities. In addition, research supporting the engine flowpath design investigated ways to enhance mixing, improve and apply nonintrusive diagnostics, and address facility operation. Tests of scramjet combustor operation at conditions simulating hypersonic flight at Mach numbers up to 17 also have been performed in an expansion tube pulse facility. This paper presents a review of the LaRC experimental supersonic combustion research efforts since the late 1980's, during the NASP program, and into the Hyper-X Program.

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“…This indicates that the use of streamwise vortices is effective for a supersonic mixing. Many researchers have developed fuel injector designs actively introducing streamwise vortices 5,6) . Sunami et al 6) proposed 'alternating-wedge (AW) strut injector'.…”

Section: Introductionmentioning

confidence: 99%

Large-Eddy Simulation of Fuel Mixing Using Streamwise Vortices in a Supersonic Flow

Watanabe

Takita

Sunami

2012

AEROSPACE TECHNOLOGY JAPAN

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Turbulent mixing field of hydrogen jets injected in supersonic streamwise vortices was numerically investigated using large-eddy simulation (LES). The jet and the streamwise vortices were introduced in a similar and simplified manner to those introduced by the alternating-wedge (AW) strut injector. The LES reproduced the large-scale wavy jet structure containing small-scale vortices as those observed in the past experiment of the AW strut. The streamwise vortices strongly promoted the jet spreading and the turbulent transition. Downstream of the turbulent transition, the fully developed turbulent state was achieved in the wavy jet structure. The instantaneous and time-averaged mixing efficiencies were quantitatively evaluated and compared each other to investigate the intermittency of mixing state. The mixing efficiency rapidly increased by the turbulent transition. The jet mixing in the streamwise vortices had lower intermittency compared to the transverse jet from the wall. The effects of the incident shock wave across the hydrogen jet were also investigated in detail. The turbulent properties such as the fluctuation intensity and the power spectrum hardly changed by the crossing of oblique shock wave. The mixing efficiency slightly increased after the oblique shock wave passed through the hydrogen jet.

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Evaluation of parallel injector configurations for supersonic combustion

Cited by 74 publications

References 2 publications

Flow establishment in a generic scramjet combustor

Flow establishment in a generic scramjet combustor

Experimental supersonic combustion research at NASA Langley

Large-Eddy Simulation of Fuel Mixing Using Streamwise Vortices in a Supersonic Flow

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