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首页> 外文会议>ICCCI 2010;International conference on computer and computational intelligence >Stability limits of cavity-stabilized flames for liquid kerosene supersonic combustion
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Stability limits of cavity-stabilized flames for liquid kerosene supersonic combustion

机译：液态煤油超音速燃烧腔稳定火焰的稳定性极限

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摘要

Studies were performed to examine the stability limits of liquid kerosene-fueled flames in cavity flame-holders in a supersonic combustor. The numerical analysis of the kerosene spray supersonic combustion was carried out in the case of the air Mach number was 2.38, stagnation temperature was 1200K and the stagnation pressure was 1.68MPa, and the seven fuel-air equivalence ratios and three fuel injection locations, with the turbulence and chemistry interaction model, turbulence flow model and the discrete droplet model. For injected liquid kerosene from leading edge, the cavity has a wide range of stable operations and a large fuel-rich limit. For injection from floor wall and from aft wall, the cavity shows to suppress the fuel-rich blowout limit, to enhance the fuel-lean limit, and the floor wall injection is more than the aft wall injection. As fuel-air equivalence ratio is 3.0, the open cavity flow occurs for L/D=5 cavity. Transitional cavity flow occurs in the other case and is different from that in non-reacting flow. The simulation results demonstrate the conventional definition of cavity flow characteristics based on non-reacting flows needs to be made corrections.
机译：进行了研究，以检查超音速燃烧器中腔体火焰保持器中液体煤油燃料火焰的稳定性极限。在空气马赫数为2.38，停滞温度为1200K，停滞压力为1.68MPa的情况下进行了煤油喷雾超音速燃烧的数值分析，七个燃料-空气当量比和三个燃料喷射位置，湍流和化学相互作用模型，湍流模型和离散液滴模型。对于从前缘注入的液态煤油，型腔具有广泛的稳定运行范围和较大的富油极限。对于从地板壁和从后壁的喷射，腔显示出抑制了富燃料的喷出极限，提高了燃料稀薄极限，并且地板壁的喷射大于后壁的喷射。当燃料-空气当量比为3.0时，在L / D = 5腔时出现开腔流动。在另一种情况下会发生过渡腔流动，这与未反应的流动不同。仿真结果表明，需要对基于非反应流的腔体流动特性的常规定义进行校正。

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