The effect of full-annular swirling-flow on a flow-zone combustor design is investigated. Swirl flow angles of 25, 35, and 45 degrees were investigated in a combustor design envelope typical of those used in modern engines. The two-zone combustor had 24 pilot-zone fuel injectors and 24 main-fuel injectors located in the centerbody between the pilot and swirl passage. Combustor performance was determined at idle, and two parametric 589 K inlet temperature conditions. Combustor performance was highest with the 45 degree swirl vane design; at the idle condition, combustion efficiency was 99.5 percent. The 45 degree swirl vane also produced the lowest pattern factor of the three angles and showed a combustor lean blowout limit below a 0.001 fuel-air ratio. Combustor total pressure drop varied from a low of 4.6 percent for the 25 degree swirl to a high of 4.9 percent for the 45 degree swirl.


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    Titel :

    Preliminary Investigation of a Two-Zone Swirl Flow Combustor


    Beteiligte:
    J. A. Biaglow (Autor:in) / S. M. Johnson (Autor:in) / J. M. Smith (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    20 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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    Preliminary investigation of a two-zone swirl flow combustor

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