一种一体化加力燃烧室的数值模拟

为适应新一代航空发动机高推质比的设计要求,设计出一种一体化加力燃烧室方案,利用截尾支板与带凹腔的分流环组合结构取代了传统火焰稳定器。对该方案进行了数值模拟研究及试验验证,结果表明:在该一体化加力燃烧室内涵中有3个低速回流区；截尾支板结构不仅起整流支板的作用,还能够起到火焰稳定器的作用；燃烧效率在90%～93%之间,流阻系数约为0.26；在所研究的工况下总压恢复系数均高于0.975,且主要的总压损失集中在截尾支板及分流环凹腔处。 

Numerical simulation on a type of the integrated afterburner

To meet with the design requirement of the new-generation aero-engine having high thrust-mass ratio, a type of integrated afterburner was designed to replace the traditional combination of flame holder with a composite structure containing truncated strut and splitter lip with cavity. Numerical simulation and test research were conducted. The results show that the integrated afterburner has three low-speed recirculation zone in the inner channel; the truncated strut is not only a guide vane, but also a flame holder; the combustion efficiency of the integrated afterburner is 90%-93%, the flow drag coefficient is about 0.26; all of the total pressure recovery coefficient in the research are higher than 0.975, the main total pressure loss is concentrated in truncated strut and cavity of splitter lip.