针对高推重比、高隐身航空发动机的技术需求,提出了1种带气膜冷却的加力内锥、整流支板和火焰稳定器的加力燃烧室一体化设计方法,对一体化加力燃烧室的温升、壁温分布、总压恢复系数、CO排放和燃烧效率分别进行了计算。结果表明:该方法在保证加力燃烧室燃烧性能不变的前提下,能将现有的加力燃烧室长度缩短1/5,并使加力内锥壁温降低33.3%。为实现高推重比、高隐身动力技术提供了新的思路和研究方向。 In order to meet the technical requirements of high thrust-weight ratio and high stealth aero-engine, an integrated design method of afterburner with gas-cooled inner cone, rectification support and flame stabilizer is proposed. Room temperature, wall temperature distribution, total pressure recovery coefficient, CO emissions and combustion efficiency were calculated. The results show that this method can shorten the length of the existing afterburner by 1/5 and reduce the inner cone temperature by 33.3% under the premise of keeping the combustion performance of the afterburner. In order to achieve high thrust-to-weight ratio, high stealth power technology provides a new way of thinking and research direction.