To provide desired engine restart capability and limit ignition operating time to minimum, development of flameout sensor was considered; compressor discharge pressure (CDP) was used as most desirable sensing parameter to obtain positive indication of flameout; sensor is pressure sensitive switch actuated by 3-lb differential in air pressure between 2 chambers, separated by snap-action-diaphragm; sensor actuates ignition in less than 0.1 sec and "ON" time for ignition is controlled by duration of 1-lb pressure differential; schematic diagram; results of flight testing.


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    Title :

    Bendix flameout sensor for turbine engine aircraft


    Additional title:

    SAE -- Paper


    Contributors:
    Welch, H.C. (author)

    Conference:

    SAE Meeting ; 1964 Combustion



    Publication date :

    1964


    Size :

    3 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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