Gaseous emissions were measured in single-cup flametube tests of an advanced low-NOx combustor concept at simulated supersonic cruise conditions. The combustor concept is a low technology readiness level (TRL), lean front-end design developed under the NASA Fundamental Aeronautics/Supersonics project to minimize NOx emissions at supersonic cruise. The flametube conditions matched or approached combustor conditions at supersonic cruise, with combustor inlet temperatures up to 920 K, inlet pressures up to 19 bar, and combusted gas temperatures up to 2,120 K. Whether these conditions met or just approached supersonic cruise conditions depended on the type of engine the combustor would be installed in. Two types of engines were considered here: a “derivative” engine based on a current technology and an “advanced” engine with a higher operating pressure ratio and higher temperature limits. For the “derivative” engine, the combustor is expected to be at least close to meeting the NASA NOx emissions goal of 10 g-NOx/kg-fuel at supersonic cruise. However, with the higher combustor inlet and flame temperatures of the advanced engine, NOx emissions are expected to be well above the goal.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Flametube Evaluation of a Lean-Lean Combustor Concept Developed for Supersonic Cruise Aircraft


    Contributors:

    Conference:

    IGTI 2022 Turbomachinery Technical Conference & Exposition ; 2022 ; Rotterdam, NL


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Combustor Stability & Lean Blowout

    Ballal, Dilip | AIAA | 2004


    Multifuel Evaluation of Rich/Quench/Lean Combustor

    J. J. Notardonato / A. S. Novick / D. L. Troth | NTIS | 1982


    Multifuel Evaluation of Rich/Quench/Lean Combustor

    A. S. Novick / D. L. Troth / J. Notardonato | NTIS | 1982


    Multifuel evaluation of rich/quench/lean combustor

    Notardonato, J. J. / Novick, A. S. / Troth, D. L. | NTRS | 1982