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为了分析航空发动机涡轮级中的燃气入侵现象,提出一种研究封严间隙处流动规律的理论方法,并采用全环模型进行了数值模拟。在该理论方法中,动盘旋转、封严冷气、外环主流对流动的影响用三个特征速度来表征;它们的相互作用用速度比来描述。数值模拟结果表明:随着速度比的变化,封严间隙处呈现燃气沿静盘入侵、燃气基本不入侵以及燃气沿动盘入侵等三种流动形式。利用速度比的影响规律,可初步判断封严间隙处的燃气入侵情况以及最小封严冷气流量。
In order to analyze the phenomenon of gas invasion in the turbine stage of aeroengine, a theoretical method of studying the law of flow at the seal gap was proposed, and the numerical simulation was carried out by using the whole-loop model. In this theoretical approach, the influence of the moving disk rotation and the sealing of the cooling air, the influence of the outer ring on the flow, is characterized by three characteristic velocities; their interaction is described by the velocity ratio. The results of numerical simulation show that with the change of velocity ratio, there are three kinds of flow patterns at the seal gap: gas invasion along the static disk, basic non-invasion of gas and invasion of gas along the moving disk. By using the law of speed ratio, the gas invasion at the seal gap and the minimum seal air flow can be judged initially.