论文部分内容阅读
对航空发动机压气机级间台阶篦齿封严进行了实验与计算研究。在不同压比(1.05~1.3)下,研究了转速(1.5~7.2kr/min)对篦齿的工作间隙变化、泄漏特性、温升特性和旋流特性的影响,并选取典型实验工况进行了数值模拟。研究表明实验结果与数值计算结果符合良好。随转速的增大,工作间隙减小,泄漏流量降低,两者最大降幅在40%左右;较小压比时流量系数微弱降低,较大压比时流量系数微弱增大。系统风阻温升随转速的增大而增大,且转速越大温升越快,最大温升为36K。另外,出口旋转盘腔同一径向位置的旋转比随转速的增大而增大,最大可达0.398;同一转速下,随出口旋转盘腔径向位置的增大,旋转比降低。
Aeroengine compressor stage stepped labyrinth seal strict experimental and computational studies. At different pressure ratios (1.05 ~ 1.3), the effects of rotating speed (1.5 ~ 7.2kr / min) on the working gap variation, leakage characteristic, temperature rise characteristic and swirling characteristic of the labyrinth teeth were studied, and the typical experimental conditions were selected Numerical simulation. The research shows that the experimental results are in good agreement with the numerical results. With the increase of rotational speed, the working clearance decreases and the leakage flow decreases, the maximum decrease of both is about 40%. When the pressure ratio is small, the flow coefficient weakly decreases and the flow coefficient increases slightly when the pressure ratio is higher. The temperature rise of the wind resistance increases with the increase of the speed, and the bigger the speed is, the faster the temperature rise is, the maximum temperature rise is 36K. In addition, the rotating ratio of the outlet rotating disk at the same radial position increases with the increase of the rotating speed, up to 0.398. At the same rotating speed, the rotating ratio decreases with the radial position of the outlet rotating disk.