Preliminary Calibration of a Generic Scramjet Combustor
INSTITUTE FOR COMPUTER APPLICATIONS IN SCIENCE AND ENGINEERING HAMPTON VA
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The results of a preliminary investigation of the combustion of hydrogen fuel at hypersonic flow conditions are provided. The tests were performed in a generic, constant-area combustor model with test gas supplied by a free-piston-driven reflected-shock tunnel. Static pressure measurements along the combustor wall indicated that burning did occur for combustor inlet conditions of Psub static approx. 19kPa, Tsub static approx. 1080K and velocity approx. 3630 ms with a fuel equivalence ratio approx. 0.9. These inlet conditions were obtained by operating the tunnel with stagnation enthalpy H sub s 8.1 M Jkg , stagnation pressure P sub s approx. 52MPa and a contoured nozzle with a nominal exit Mach number of 5.5.
- Air Breathing Engines (Unconventional)
- Combustion and Ignition
- Jet and Gas Turbine Engines