The effect of oxygen addition on the low pressure altitude blowout limits of an experimental combustor segment was investigated. Data were obtained for two inlet-air temperatures, two inlet-airflow rates, and a constant fuel-air ratio of 0.020 with Jet A fuel. It was shown that the pressure at blowout could be reduced to correspond to an increase in altitude of 4.6 kilometers with oxygen flow rates of 8 to 16 percent by weight of the total fuel flow.


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    Title :

    Effect of Oxygen addition on altitude blowout and relight of an experimental combustor segment


    Contributors:

    Publication date :

    1974-12-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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