The authors developed a stinger-shaped injector (stinger injector) for supersonic combustors in cold-flow experiments. The stinger injector has a port geometry with a sharp leading edge in front of a streamwise slit. This injector produced higher jet penetration at a lower jet-to-crossflow momentum flux ratio J than a conventional circular injector. We applied the injector in a Mach 2.44 combustion test at a stagnation temperature of 2060 K. At a low fuel-equivalence ratio Φ regime (i.e., low J regime), the injector produced 10% higher pressure thrust than the circular injector because of high jet penetration as expected from the cold-flow experiments. Even at a moderate Φ regime, the stinger injector produced higher pressure thrust than the circular injector. At moderate Φ , the stinger injector held the flame around the injector and generated a precombustion shock wave in front of the injector. The presence of the precombustion shock wave decreased the momentum flux of the crossflow air and diminished the advantage of the injector for jet penetration. The injector, however, produced higher pressure thrust because better flame-holding produced higher pressure around the injector. At a higher Φ regime, the precombustion shock wave went upstream with both injectors. The far-upstream presence of a precombustion shock wave increased the turbulence in the crossflow and spread the fuel from both injectors. Thus, the difference in injector shape was insignificant for thrust performance.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Supersonic Combustion Using a Stinger-Shaped Fuel Injector


    Contributors:

    Published in:

    Publication date :

    2013-03-22


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

    Kouchi, Toshinori / Hirano, Kohshi / Kobayashi, Kan et al. | AIAA | 2008


    Supersonic Combustion Experiments with a Cavity-Based Fuel Injector

    Tarun Mathur / Mark Gruber / Kevin Jackson et al. | AIAA | 2001


    Supersonic combustion experiments with a cavity-based fuel injector

    Mathur, T. / Streby, G. / Gruber, M. et al. | AIAA | 1999


    Flowfield Studies of Diamond-Shaped Fuel Injector in a Supersonic Flow

    Kan Kobayashi / Rodney Bowersox / Ravichandra Srinivasan et al. | AIAA | 2007