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用准一维分析方法,在相同的入流条件下,假设将当量比为1的燃料热量全部添加到气流中,研究了燃烧室工作过程与性能之间的关系。结果表明,随着特征马赫数的增加,在相同飞行马赫数下,亚声速燃烧室所需扩张比逐渐减小,而双模态燃烧室所需扩张比逐渐增大;亚声速燃烧室出现所需最小扩张比和最大比冲的特征马赫数分别是1和0,双模态燃烧室在最小特征马赫数时所需扩张比最小,获得的比冲最大,且与亚声速燃烧室能获得的最大比冲相差不大,在飞行马赫数4、5、6时,差值分别为5%、4%、3%;特征马赫数在亚声速范围内变化时发动机比冲的曲线比较平缓;壁面摩擦系数的变化对燃烧室所需扩张比的影响大于对比冲的影响。直连式实验获得的等截面燃烧室极限加热量数据证明了本方法的合理性。
Using the quasi-one-dimensional analysis method, under the same inflow conditions, it is assumed that all the fuel heat with the equivalent ratio of 1 is added to the gas flow, and the relationship between the working process and the performance of the combustion chamber is studied. The results show that with the increase of Mach number, the required expansion ratio of subsonic combustion chamber decreases with the same flight Mach number, while the required expansion ratio of dual-mode combustion chamber increases gradually. The subsonic combustion chamber The characteristic Mach numbers for the minimum expansion ratio and the maximum specific impulse are 1 and 0, respectively, and the required expansion ratio is the minimum for the dual-mode combustion chamber at the minimum characteristic Mach number, and the maximum specific impulse obtained is the same as that obtained with the subsonic combustion chamber The maximum specific impulse is not much difference, the difference is 5%, 4%, 3% respectively at Mach 4,5, Mach 4, and Mach 3. The curve of engine specific impulse when the characteristic Mach number changes in subsonic range is relatively flat. The influence of the change of friction coefficient on the required expansion ratio of the combustion chamber is greater than that of the contrasting impulse. The data of the ultimate heating of the equal-section combustor obtained by the direct-connected experiment proves the rationality of this method.