Design studies and an experimental test program have been conducted to provide basic technology and preliminary flightweight designs for a small (2 lb/sec total engine airflow) high temperature rise combustor with a 3000 F exit temperature, as a first step towards demonstration in a research engine. Tests were conducted to evaluate the combustor design parameters developed in the initial design study phase of the program pertaining to liner cooling techniques, fuel introduction, and primary zone performance. The preliminary designs optimize the technology developed in this program and comprise both annular and can end-mounted combustor configurations incorporating an annular vaporizer fuel introduction system and transpiration cooled liners.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Advanced High Temperature Combustor Research for Small Gas Turbine Engines


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Mid-Year Meeting ; 1968



    Publication date :

    1968-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English



    Design methodology for combustor in advanced gas turbine engines: a review

    Kim, Insong / Jin, Hakson / Ri, Kwangsong et al. | Emerald Group Publishing | 2024


    Vortex combustor concept for gas turbine engines

    Roquemore, W. / Shouse, Dale / Burrus, Dave et al. | AIAA | 2001


    Combustor Imaging Probe for Gas Turbine Engines

    Beitel, Gregg / Savage, Keith / Catalano, Daniel et al. | AIAA | 2007


    Trapped Vortex Combustor Concept for Gas Turbine Engines

    Roquemore, W. M. / Shouse, D. / Burrus, D. et al. | British Library Conference Proceedings | 2001


    Small gas turbine combustor study: Combustor liner evaluation

    Norgren, C. T. / Riddlebaugh, S. M. | NTRS | 1983