该模型的建立为预测航空发动机加力燃烧室振荡燃烧特性及控制规律提供了一种理论探索途径。
The model provides theoretical way for the research of the thermoacoustic oscillation in the aero-engine afterburner.
J-10采用了一个可调节机腹进气口为一台留里卡-土星设计局的AL-31FN加力燃烧涡轮风扇发动机提供空气。
The aircraft employs an adjustable, chin-mounted air intake that supplies air to the single Lyulka-Saturn AL-31FN afterburning turbofan jet engine.
在涡扇发动机基础上，以脉冲爆震燃烧室代替普通加力燃烧室构成涡扇-脉冲爆震组合发动机。
Based on a turbofan engine, the afterburner is replaced with pulse detonation combustor to form a turbofan-pulse detonation hybrid engine.
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