A catalytic combustor was designed, an existing one modified, and both were tested on a small turbojet engine. The existing catalytic combustor, combustor A, used straight through flow and was modified by adding a flame arrestor to the combustor inlet. Combustor B was designed to use reverse flow with a preburner and air dilution zones. Combustors A and B were designed for an air capacity up to 0.75 lbm/sec and outlet temperatures of 1800 F. Combustor B did prove successful. Cold flow total pressure loss in combustor B was two percent, while the total pressure loss during heat addition was a maximum of seven percent. The flame arrestors tested on combustor A did not prove to be successful. Hydrogen was used as fuel for both combustors. Temperatures across the catalyst face varied by 290 F at a turbine inlet temperature of 1070 F, 370 F at 1450 F. Turbine inlet temperatures varied by 55 F at an average 1045 F, 190 F at an average 1475 F. The maximum temperature rise across the combustor during testing was 1565 F and the maximum turbine inlet temperature tested was 1855 F. (Posamentier)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    An experimental study of a catalytic combustor for an expendable turbojet engine


    Additional title:

    Experimentelle Untersuchung einer katalytischen Brennkammer fuer ein Einweg-Turboluftstrahltriebwerk


    Contributors:

    Published in:

    Publication date :

    1978


    Size :

    43 Seiten


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English