Evaluation of parallel injector configurations for Mach 2 combustion

Northam, G. B.; Greenberg, I.; Byington, Carl S.; Capriotti, D. P.

doi:10.2514/3.23503

Cited by 58 publications

(11 citation statements)

References 2 publications

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“…The majority of experiments are carried out with kerosene, which is heated up to 560580 K. The number of injectors is four. They are similar to those proposed in [37]. Injector con¦guration and its dimensions are described in [35].…”

Section: Combustor Model and Experimental Setupsupporting

confidence: 52%

Specific features of ignition and flameholding of hydrocarbon fuels in high-speed flow

Goldfeld

2016

Progress in Propulsion Physics

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The paper describes the results of experimental investigations of a supersonic combustion chamber with solid and discrete cavities at the entrance Mach numbers of 3 and 3.5. Kerosene and propane were used as fuel. The conditions required for self-ignition and intense combustion of the fuels were determined. The possibility of e©cient combustion in a supersonic §ow was demonstrated. Analysis of applicability of existing criteria predicting the conditions of self-ignition and extinction of combustion has been performed based on the experimental results obtained.

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Section: Combustor Model and Experimental Setupsupporting

confidence: 52%

Specific features of ignition and flameholding of hydrocarbon fuels in high-speed flow

Goldfeld

2016

Progress in Propulsion Physics

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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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“…In this speed regime, significant experimental attention has been paid toward the evaluation of perpendicular wall injection, 2 near-parallel injection concepts (e.g. swept ramp injectors), 3,4 transpiration/effusive injection cooling for transverse injection, 5 and the effect of fuel injector nozzle geometry on mixing characteristics [6][7][8] . The use of cavities for injection and flameholding has also been a subject of past research.…”

Section: Previous Workmentioning

confidence: 99%

Study of Forebody Injection and Mixing with Application to Hypervelocity Airbreathing Propulsion

Axdahl

Kumar²,

Wilhite

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The use of premixed, shock-induced combustion in the context of a hypervelocity, airbreathing vehicle requires effective injection and mixing of hydrogen fuel and air on the vehicle forebody. Three dimensional computational simulations of fuel injection and mixing from flush-wall and modified ramp and strut injectors are reported in this study. A well-established code, VULCAN, is used to conduct nonreacting, viscous, turbulent simulations on a flat plate at conditions relevant to a Mach 12 flight vehicle forebody. In comparing results of various fuel injection strategies, it is found that strut injection provides the greatest balance of performance between mixing efficiency and stream thrust potential.

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Evaluation of parallel injector configurations for Mach 2 combustion

Cited by 58 publications

References 2 publications

Specific features of ignition and flameholding of hydrocarbon fuels in high-speed flow

Specific features of ignition and flameholding of hydrocarbon fuels in high-speed flow

Experimental supersonic combustion research at NASA Langley

Study of Forebody Injection and Mixing with Application to Hypervelocity Airbreathing Propulsion

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