Variable Combustor Geometry for Improving the Altitude Relight Capability of a Double Annular Combustor |
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25 percent open 3.6 newtons 7.0 newtons added to snout airflow distortion plates altitude relight capability area punched plate axial flow air axial flow swirlers bypass air centimeter for model combustion combustor average temperature combustor configuration Combustor inlet combustor snout inlet cone spray fuel diameter exit transition diameter inlet airflow diffuser inlet distortion punched plate double annular combustor Double-Annular Ram-Induction ence velocity exit transition liner flapper valves flat spray fuel flat spray nozzles fuel flow Headplate hollow cone spray ignition improving the altitude inflow air swirlers Inlet air velocity inlet airflow distortion inlet total pressure inlet velocity Inner diameter inlet Jet engine Lewis Research Center models 6-2BO N/cm² NASA newtons per square number of 0.05 open area punched outer annulus outer diameter exit outer exit transition percent open area primary zone punched plate added radial inflow air reference Mach number relights were obtained snout airflow spray fuel nozzles variable combustor geometry