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为了获得不同飞行状态下双模态超燃冲压发动机最大供油状态,在集总参数方程的双模态超燃冲压发动机性能计算模型基础上,通过分析双模态超燃冲压发动机堵塞边界条件及工作机理,发展了最大供油模态流量平衡的求解方法,并以此为基础建立了双模态超燃冲压发动机最大供油模态计算模型。给出某飞行条件下的最大供油模态迭代计算过程,并详细描述了其所表征的物理现象,其流量平衡计算精度达10~(-4),并在此基础上完成了不同飞行马赫数下的最大供油模态计算,获得相应的燃烧室最大供油量及隔离段/燃烧室沿程参数分布。结果表明,该计算方法可实现双模态超燃冲压发动机最大供油模态的流量平衡计算,并能精确地捕捉给定燃油分配形式下的燃烧室最大供油量。
In order to obtain the maximum fueling state of bimodal scramjet engine under different flight conditions, based on the calculation model of the bimodal scramjet engine performance model of the lumped parameter equation, by analyzing the clogging boundary conditions of the bimodal scramjet engine and Working principle and developed the solution method of the maximum fuel supply mode flow balance. Based on this, the maximum fuel supply model calculation model of the dual-mode scramjet engine was established. The iterative calculation process of the maximum fuel supply mode under a certain flight condition is given and the physical phenomena characterized by it are described in detail. The calculation precision of the flow balance is 10 ~ (-4). On this basis, Number of the maximum fuel mode calculation, access to the corresponding maximum combustion chamber fuel supply and isolation section / combustion chamber along the distribution parameters. The results show that the calculation method can achieve the flow balance calculation of the maximum fuel supply mode of the dual-mode scramjet and accurately capture the maximum fuel supply of the combustion chamber under a given fuel distribution.