不同结构一体化加力燃烧室冷态流场与性能仿真

Investigation on Cold Flow Field and Performance of Afterburner with Different Structures

为研究不同结构一体化加力燃烧室冷态流场与性能,对整体物理模型进行数值仿真,分析了不同工况下燃烧室内部流场速度流线图、流阻系数与总压恢复系数。结果表明:加力燃烧室的总压恢复系数与流阻系数随入口马赫数增大而降低;当量扩张角越大,加力燃烧室性能越佳;带扭度截尾支板较无扭度截尾支板有更优良的整流效果:在Ma=0.28时,最大当量扩张角带扭度截尾支板设计方案流阻系数Φ=0.163;在Ma=0.13时,最大当量扩张角带扭度截尾支板设计方案总压恢复系数δ=0.9976;在采用带扭度截尾支板设计时,一体化加力燃烧室回流区结构完整,回流区面积与涡心位置对进口马赫数不敏感,能够有效保障加力燃烧室在不同实际飞行状态下稳定工作。

In order to study the cold flow field and performance of afterburner with different structures,the integral physical model was numerically simulated,and the velocity streamline diagram,flow resistance coefficient and total pressure recovery coefficient were analyzed under different conditions.The results show that the total pressure recovery coefficient and flow resistance coefficient of afterburner decrease with the increase of inlet Mach number;The larger the equivalent expansion angle,the better the afterburner performance;The results show that the torsional plate has better rectification effect than the without torsional plate.When Ma=0.28,the flow resistance coefficient of truncated support with torsionΦ=0.163;When Ma=0.13,the total pressure recovery coefficientδ=0.9976;When the design of the tail cutting plate with torsion is adopted,the reflux zone of the integrated afterburner is complete,the area of the return zone and the position of vortex center are not sensitive to the Mach number at the inlet,which can effectively guarantee the stable operation of the afterburner in different actual flight conditions.