Olson, Walter T., Schroeter, Thomas T.
The performance of a 25 1/2-inch-diameter annular-type turbojet combustor was investigated with 11 combustor-basket designs at conditions simulating static (zero ram) operation of the turbojet engine over a range of altitudes and engine speeds. The investigation was conducted to determine the effect of the distribution of basket-hole area on the altitude operational limits of the engine as imposed by the combustor. Totla-pressure drop was recorded for each combustor configuration. In one of the basket configurations, the effect of fuel-nozzle spray angle and the effect of fuel-nozzle flow capacity on altitude operational limits was determined. Illustrative information was obtained with a few combustors on combustion efficiency, combustor-outlet temperature distribution, and fuel-manifold vapor-lock characteristics.
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