Effect of fuel nozzle protrusion on transient and steady-state turbojet combustor performance
Description:
Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.
Date:
February 23, 1955
Creator:
McCafferty, Richard J. & Donlon, Richard H.
Item Type:
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Report
Partner:
UNT Libraries Government Documents Department