涡轮喷气发动机的过渡过程是个很复杂的物理过程。为了分析发动战的加速性,工作稳定性以及设计发动机燃油控制系统,需要建立一个精确的过渡过程数字模型。目前比较通用的过渡过程数学模型,大案是只考虑发动机转子惯性和发动机流道上的容腔影响。许多计算证明,对于一般过渡过程容腔影响极小,完全可以忽略不计。通过对一台单轴涡轮喷气 Turbojet engine transition process is a very complex physical process. In order to analyze the accelerations of the war, the stability of the work, and the design of the engine fuel control system, a precise numerical model of the transition process needs to be established. At present, the transitional mathematic model is more common. The major case only considers the inertia of the engine rotor and the influence of the cavity on the engine runner. Many calculations show that the impact on the general transitional process cavity is negligible and completely negligible. Passing on a single-shaft turbojet