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为了获得固体燃料超燃冲压发动机燃烧室初始型面和研究不同台阶高度下的初始型面的变化规律,将固体燃料燃面退移速率模型耦合到准一维流动方程中,发展了一种计算固体燃料超燃冲压发动机燃烧室性能的准一维数值计算方法。利用该方法,将燃空比和流场马赫数作为燃烧室性能的优化参数,得出了不同台阶高度下满足优化目标的燃烧室型面。根据所得的优化型面,归纳了型面参数随着台阶高度的变化规律。结果表明,随着台阶高度的增大,燃烧室的整体长度增大,等直段的长度增大,扩张段的扩张比减小,扩张段的长度减小。
In order to obtain the initial profile of the combustion chamber of a solid fuel scramjet and to study the variation of the initial profile under different step heights, a model of solid-fuel surface migration rate was coupled to the quasi-one-dimensional flow equation Quasi - one dimensional numerical method for calculating the performance of combustion chamber of solid fuel scramjet. By using this method, the fuel ratio and the Mach number of the flow field are taken as the optimization parameters of the combustion chamber performance, and the combustion chamber profile that satisfies the optimization goal under different step heights is obtained. Based on the optimized profile, the variation of the profile parameters with the height of the step is summarized. The results show that as the height of the step increases, the length of the combustion chamber increases, the length of the straight section increases, the expansion ratio of the expansion section decreases, and the length of the expansion section decreases.