航空发动机齿间凹槽对篦齿封严特性的影响

Analysis of Leakage Effect of Rub-groove On Aero-engine Labyrinth Seal

运用RNG k-ε两方程湍流模型,对篦齿腔对应壁面进行开槽的篦齿内部流场进行数值分析,获得了凹槽篦齿的封严规律,研究了凹槽尺寸、压比对其泄漏的影响。计算结果表明:适当的凹槽结构可以提高篦齿的封严效率,当凹槽深度和宽度分别为6mm和2mm时,相对于光滑篦齿可提高封严效率11%。凹槽篦齿泄漏系数随着压比增大而增大,达到一定压比后,趋于平缓。不同深度和宽度凹槽对压比敏感度不一致。

With RNG k-εtwo-equation turbulence model,numerical analysis on the flow in labyrinth seals with a rectangular groove on the wall correspond to the labyrinth seal cavity were carried out.The seal law for the grooved labyrinth seal was obtained.The influences on the amount of leakage of groove sizes,pressure ratio were investigated.The results showed that the appropriate groove structure could improve the Seal efficiency of the grooved labyrinth seal.When the depth and width of the rub-groove was 6mm and 2mm respectively,the seal efficiency of labyrinth seal with the rectangle rub-grooves could be increased up to 11%.The leakage coefficient of grooved labyrinth seal increased with increases of the pressure ratio,when pressure ratio achieved the critical value,the leakage coefficient became flat.The sensitivity of rub-groove with different depth and width to pressure ratio was inconsistent.