攻角条件下弹用整体式液体冲压发动机燃烧室性能建模与分析

Modeling and Analysis of Integrated Liquid Ramjet for Missile Combustor Performance Under the Condition of Angle of Attack

整体式液体冲压发动机性能与导弹外弹道参数耦合密切,其中攻角是液体冲压发动机燃烧室性能的重要影响因素,CFD方法分析此类问题计算量较大而进行试验成本较高。进一步发展了冲压发动机性能工程计算方法,建立了适用于分析冲压发动机与外弹道参数耦合问题的燃烧室性能计算模型。利用模型重点分析了攻角变化对冲压发动机燃烧室出口总温、加热比的影响。分析表明,燃烧室出口总温随攻角增加而上升,反之则下降;燃烧室加热比随攻角增加而下降,反之则上升;出口总温和加热比随攻角、速度的变化图像,受进气道起动特性影响,均存在起动边界。

Integrated liquid ramjet performance is closely coupled with missile external ballistic parameters,in which angle of attack is an important factor affecting the performance of combustor.The CFD analysis of such problems requires a large amount of calculation and a high test cost.The performance engineering calculation method of ramjet is further developed,and a combustor performance calculation model suitable for analyzing the coupling problem between ramjet and external ballistic parameters is established.The influence of angle of attack on the total temperature and heating ratio at the outlet of ramjet combustor is analyzed by using the model.The analysis shows that the total temperature at combustor outlet increases with the increase of angle of attack,and vice versa.The heating ratio of the combustor decreases with the increase of angle of attack,and vice versa.Start-up boundary is showed on the image of the total temperature and heating ratio at the outlet varied with angle of attack and velocity,which are affected by the start-up characteristics of the inlet.