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  • 1
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    Plasma torch igniter for scramjets (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A small, uncooled plasma torch was developed and used in combination with an injector designed to study ignition and flameholding in hydrogen-fueled supersonic flows. The plasma torch was operated on mixtures of hydrogen and argon with total flows of 10 to 70 scfh. The fuel injector design consisted of five small upstream pilot fuel injectors, a rearward facing step for recirculation, and three main fuel injectors downstream of the step. The plasma torch was located in the recirculation region, and all injection was perpendicular to the Mach 2 stream. Both semi-freejet and ducted tests were conducted. The experimental results indicate that a low power plasma torch operating on a 1:1 volumetric mixture of hygrogen and argon and located in the recirculation zone fueled by the upstream pilot fuel injectors is a good igniter for flow conditions simulating a flight Mach number of 3.7. The total temperature required to autoignite the hydrogen fuel for this injector geometry was 2640 R. The injector configuration was shown to be a good flameholder over a wide range of total temperature. Spectroscopic measurements were used to verify the presence of air total temperatures below 1610 R.
    Keywords: PROPELLANTS AND FUELS
    Type: Johns Hopkins Univ., The 23rd JANNAF Combustion Meeting, Volume 1; p 365-376
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Design and evaluation of a new injector configuration for supersonic combustion (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Ignition and flameholding behavior data are presented from experiments with a novel scramjet injector configuration consisting of five small upstream pilot fuel injectors, a rearward-facing step, and three primary fuel injectors downstream of the step; all injection is perpendicular to the Mach 2 airflow, and the ignition source is located in the recirculation region downstream of the step. The design attempts to minimize the amount of igniter energy required for ignition, but without introduction of the large losses associated with bluff bodies. Argon plasma, argon-hydrogen plasma, pyrophoric silane/hydrogen, and surface-discharge ignition sources are tested. The injector is found to be able to hold flames at 1400 R total temperatures without the use of large bluff bodies; the argon-hydrogen plasma was the most effective igniter.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Plasma torch igniter for scramjets (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A small, uncooled plasma torch was developed and used in combination with an injector designed to study ignition and flameholding in hydrogen-fueled supersonic flows. The plasma torch was operated on mixtures of hydrogen and argon with total flows of 10 to 70 scfh. The fuel injector design consisted of five small upstream pilot fuel injectors, a rearward facing step for recirculation, and three main fuel injectors downstream of the step. The plasma torch was located in the recirculation region, and all injection was perpendicular to the Mach 2 stream. Both semi-freejet and ducted tests were conducted. The experimental results indicate that a low power plasma torch operating on a 1:1 volumetric mixture of hydrogen and argon and located in the recirculation zone fueled by the upstream pilot fuel injectors is a good igniter for flow conditions simulating a flight Mach number of 3.7. The total temperature required to autoignite the hydrogen fuel for this injector geometry was 2640 R. The injector configuration was shown to be a good flameholder over a wide range of total temperature. Spectroscopic measurements were used to verify the presence of air total temperatures below 1610 R.
    Keywords: PROPELLANTS AND FUELS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 548-554
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Space and transatmospheric propulsion technology (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: This report focuses primarily on Japan's programs in liquid rocket propulsion and propulsion for spaceplane and related transatmospheric areas. It refers briefly to Japan's solid rocket programs and to new supersonic air-breathing propulsion efforts. The panel observed that the Japanese had a carefully thought-out plan, a broad-based program, and an ambitious but achievable schedule for propulsion activity. Japan's overall propulsion program is behind that of the United States at the time of this study, but the Japanese are gaining rapidly. The Japanese are at the forefront in such key areas as advanced materials, enjoying a high level of project continuity and funding. Japan's space program has been evolutionary in nature, while the U.S. program has emphasized revolutionary advances. Projects have typically been smaller in Japan than in the United States, focusing on incremental advances in technology, with an excellent record of applying proven technology to new projects. This evolutionary approach, coupled with an ability to take technology off the shelf from other countries, has resulted in relatively low development costs, rapid progress, and enhanced reliability. Clearly Japan is positioned to be a world leader in space and transatmospheric propulsion technology by the year 2000.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Loyola Coll., JTEC(WTEC Report and Program Summary; p 138-142
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A Detailed Investigation of Staged Normal Injection into a Mach 2 Flow (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A study of the staged injection of two jets of air behind a rearward facing step into a Mach 2 flow was performed using the SPARK 3-D Navier-Stokes code. Calculated mole fraction distributions were compared with an extensive set of planar mole fraction measurements made with a laser induced iodine fluorescence technique. A statistical measure, the standard deviation, was used to help assess agreement between calculation and experiment. Overall, good agreement was found between calculated and measured values. Generally, agreement was better in the far field of the injectors. The effect of grid resolution was investigated by calculating solutions on grids of 60,000, 200,000, and 450,000 points. Differences in the solutions on the two finer grids were small. However, the mole fraction distributions were distinguishable. The effect of turbulence modeling was investigated by employing three different algebraic models for the jet turbulence: the Baldwin-Lomax model, the Prandtl mixing length model, and the Eggers mixing length model. Overall, the Eggers mixing length model was found to be superior for this case. Finally, the effect of the jet exit conditions was examined. A recently proposed Mach number distribution at the jet exit was found to slightly improve agreement between measurement and calculation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: 27th JANNAF Combustion Subcommittee Meeting; Volume 3; 115-129
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Hypersonic propulsion research (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The development of technology for the modular airframe integrated scramjet has been the focus of hypersonic propulsion research for several years. An part of this research, a variety of inlet concepts have been explored and characterized. The emphasis of the inlet program has been the development of the short (light weight), fixed geometry, side wall compression inlets that operate efficiently over a wide Mach number range. As hypersonic combustion tunnels were developed, programs to study the parameters controlling fuel mixing and combustion with single and multiple strut models were conducted using direct connect test techniques. These various tests supported the design of subscale engine test hardware that integrated inlet and combustor technology and allowed the study of the effect of heat release on thrust and combustor/inlet interaction. A number of subscale engine tests have shown predicted performance levels at Mach 4 and 7 simulated flight conditions. A few of the highlights from this research program are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Aeropropulsion 1987; p 487-506
    Format: application/pdf
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  • 7
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    Application of CFD codes for the simulation of scramjet combustor flowfields (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An overview of CFD activities in the Hypersonic Propulsion Branch is given. Elliptic and PNS codes that are being used for the simulation of hydrogen-air combusting flowfields for scramjet applications are discussed. Results of the computer codes are shown in comparison with those of the experiments where applicable. Two classes of experiments will be presented: parallel injection of hydrogen into vitiated supersonic air flow; and normal injection of hydrogen into supersonic crossflow of vitiated air.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12; p 75-89
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Hypersonic propulsion research (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The NASA Langley Research Center has conducted hypersonic propulsion research since the 1960s. A variety of inlet concepts were explored and characterized. The emphasis of the inlet program was the development of the short (light weight), fixed geometry, side-wall-compression inlets that operate efficiently over a wide Mach number range. As hypersonic combustion tunnels were developed, programs to study the parameters controlling fuel mixing and combustion with single and multiple strut models were conducted using direct connect test techniques. These various tests supported the design of subscale engine test hardware that integrated inlet and combustor technology and allowed the study of the effect of heat release on thrust and combustor/inlet interaction. A number of subscale engine tests have demonstrated predicted performance levels at Mach 4 and 7 simulated flight conditions.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Aeropropulsion '87. Session 6: High-Speed Propulsion Technology; 20 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    IC Engine Applications of Carbon-Carbon (2000)
    In:  Other Sources
    Details
    Publication Date: 2011-08-23
    Description: Many of the properties of carbon-carbon make it an ideal material for reciprocating materials of intermittent combustion (IC) engines. Recent diesel engine tests, shown herein, indicate that the thermal and mechanical properties of carbon-carbon are adequate for piston applications, However, reducing the manufacturing costs and providing long term oxidation protection are still issues that need to be addressed.
    Keywords: Nonmetallic Materials
    Type: Advanced Engineering Materials (ISSN 1438-1656); Volume 2; No. 9; 583-586
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Combustion rate limits of hydrogen plus hydrocarbon fuel: Air diffusion flames from an opposed jet burner technique (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Combustion of H2/hydrocarbon (HC) fuel mixtures may be considered in certain volume-limited supersonic airbreathing propulsion applications. Effects of HC addition to H2 were evaluated, using a recent argon-bathed, coaxial, tubular opposed jet burner (OJB) technique to measure the extinction limits of counterflow diffusion flames. The OJB flames were formed by a laminar jet of (N2 and/or HC)-diluted H2 mixture opposed by a similar jet of air at ambient conditions. The OJB data, derived from respective binary mixtures of H2 and methane, ethylene, or propane HCs, were used to characterize BLOWOFF and RESTORE. BLOWOFF is a sudden breaking of the dish-shaped OJB flame to a stable torus or ring shape, and RESTORE marks sudden restoration of the central flame by radial inward flame propagation. BLOWOFF is a measure of kinetically-limited flame reactivity/speed under highly stretched, but relatively ideal impingement flow conditions. RESTORE measures inward radial flame propagation rate, which is sensitive to ignition processes in the cool central core. It is concluded that relatively small molar amounts of added HC greatly reduce the reactivity characteristics of counterflow hydrogen-air diffusion flames, for ambient initial conditions.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 139-153
    Format: text
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    NASA TECHNICAL REPORTS
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