Review of Experiments on Ignition and Flameholding in Supersonic Flow

Cain, T. M.

doi:10.2514/6.2002-3877

Cited by 17 publications

(12 citation statements)

References 21 publications

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“…It is also well known that the stability of a combustion system has sensitivities due to the chemical content of the test medium. 15,16 Brabbs et. al., 17 showed that under ideal circumstances, vitiated contaminants can cause a change in ignition delay, leading to erroneous conclusions for the flight performance and operability in air.…”

Section: Rbcc Combustor Research Objectivesmentioning

confidence: 99%

Design and Fabrication of the ISTAR Direct-Connect Combuster Experiment at the Hypersonic Tunnel Facility

Lee

Krivanek

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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The Integrated Systems Test of an Airbreathing Rocket (ISTAR) project was a flight demonstration project initiated to advance the state of the art in Rocket Based Combined Cycle (RBCC) propulsion development. The primary objective of the ISTAR project was to develop a reusable air breathing vehicle and enabling technologies. This concept incorporated a RBCC propulsion system to enable the vehicle to be air dropped at Mach 0.7 and accelerated up to Mach 7 flight culminating in a demonstration of hydrocarbon scramjet operation. A series of component experiments was planned to reduce the level of risk and to advance the technology base. This paper summarizes the status of a full scale direct connect combustor experiment with heated endothermic hydrocarbon fuels. This is the first use of the NASA GRC Hypersonic Tunnel facility to support a direct-connect test. The technical and mechanical challenges involved with adapting this facility, previously used only in the free-jet configuration, for use in direct connect mode will be also described. REPORT DOCUMENTATION PAGE REPORT DATE SECURITY CLASSIFICATION OF ABSTRACT SECURITY CLASSIFICATION OF THIS PAGEPublic 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, 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, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503.

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Section: Rbcc Combustor Research Objectivesmentioning

confidence: 99%

Design and Fabrication of the ISTAR Direct-Connect Combuster Experiment at the Hypersonic Tunnel Facility

Lee

Krivanek

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…To ignite the room temperature kerosene in the early flight stage, various kinds of methods, including the torch ignition, pilot hydrogen ignition [8,9], choking ignition, etc., have been suggested [10]. Nevertheless, all of these methods need complex operation systems, which will be an extra burden for the scramjet vehicle.…”

Section: Introductionmentioning

confidence: 98%

Spark Ignition of Liquid Kerosene in Scramjet Combustor Equipped with Partly-Covered Cavity

Bao

Zhang

Pan

et al. 2015

Journal of Propulsion and Power

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The ignition of room temperature kerosene via a spark plug was investigated by direct-connect facility experiments with a flight condition of M 4.5. A partly covered cavity is installed in the scramjet combustor model to assist spark ignition of the liquid kerosene injection. The main factors affecting the ignition and flame expansion process, including the direct-injection pressure inside the partly covered cavity, the upstream-injection pressure, and the length of the baffle, were investigated with plenty of experiment results. The flame propagation process was analyzed via wall pressure distribution and thrust. The experiment results indicated that the pressure of the direct injection and the length of the baffle were key factors for the emergence of the weak combustion inside the partly covered cavity. The upstream injection could assist spark ignition inside the partly covered cavity and broaden the direct-injection pressure range that is suitable for ignition. Moreover, upstream injection can stimulate the propagation of the weak combustion to ignite the whole combustor. Fuel distribution near the shear layer of the partly covered cavity was indicated to be the key factor in this propagation process.Nomenclature H = depth of upstream cavity M = Mach number P 0 = stagnation pressure T 0 = stagnation temperature

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“…Even if the axisymmetric coflow configuration seems to be very simple, an accurate simulation of this lifted flame is quite demanding. The disadvantage of this and many other scramjet experiments is that the air inflow temperature is relatively high [40]. Hence, with respect to the reaction mechanism the inflow conditions are not the most critical ones that can appear in a scramjet combustor.…”

Section: Turbulent Supersonic Combustion Test Casementioning

confidence: 99%

Influence of reaction mechanisms, grid spacing, and inflow conditions on the numerical simulation of lifted supersonic flames

Gerlinger

Nold²,

Aigner³

2009

Numerical Methods in Fluids

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SUMMARYThe simulation of supersonic combustion requires finite-rate chemistry because chemical and fluid mechanical time scales may be of the same order of magnitude. The size of the chosen reaction mechanism (number of species and reactions involved) has a strong influence on the computational time and thus should be chosen carefully. This paper investigates several hydrogen/air reaction mechanisms frequently used in supersonic combustion. It is shown that at low flight Mach numbers of a supersonic combustion ramjet (scramjet), some kinetic schemes can cause highly erroneous results. Moreover, extremely fine computational grids are required in the lift-off region of supersonic flames to obtain grid-independent solutions. The fully turbulent Mach 2 combustion experiment of Cheng et al. (Comb. Flame 1994; 99: 157-173) is chosen to investigate the influences of different reaction mechanisms, grid spacing, and inflow conditions (contaminations caused by precombustion). A detailed analysis of the experiment will be given and errors of previous simulations are identified. Thus, the paper provides important information for an accurate simulation of the Cheng et al. experiment. The importance of this experiment results from the fact that it is the only supersonic combustion test case where temperature and species fluctuations have been measured simultaneously. Such data are needed for the validation of probability density function methods.

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Review of Experiments on Ignition and Flameholding in Supersonic Flow

Cited by 17 publications

References 21 publications

Design and Fabrication of the ISTAR Direct-Connect Combuster Experiment at the Hypersonic Tunnel Facility

Design and Fabrication of the ISTAR Direct-Connect Combuster Experiment at the Hypersonic Tunnel Facility

Spark Ignition of Liquid Kerosene in Scramjet Combustor Equipped with Partly-Covered Cavity

Influence of reaction mechanisms, grid spacing, and inflow conditions on the numerical simulation of lifted supersonic flames

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