47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011
JUL 31-AUG 03, 2011
San Diego, CA, United states
Combustion and flame stability of supercritical kerosene were studied experimentally in a supersonic model combustor at various air and fuel conditions. The lean and rich blowout limits of supercritical kerosene injected from the bottom of a cavity flameholder were examined in Mach 2.5 airflow. It was found that the rich blowout limit was very sensitive to the stagnation temperature of the airflow while the lean limit was only slightly affected. Damkohler number was used to correlate the two limits. On the other hand, the lean blowout limits of supercritical kerosene injected upstream the cavity were investigated and compared at three different Mach numbers of 2.0, 2.5 and 3.0. ? 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
American Institute for Aeronautics and Astronautics (AIAA)
Wang J,Fan XJ,Zhang TC,et al. Measurements of the blowout limits of supercritical aviation kerosene in a supersonic combustor[C]47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011,2011.