航空发动机流体动压密封优化设计与验证  

Parameter Optimization and Experimental Verification of Hydrodynamic Pressure Mechanical Seal in Aero Engine

作　　者：熊伟 王建磊[2] 嵇佳佳 李神龙 

机构地区：[1]中国航发南方工业有限公司(331厂),湖南 株洲 [2]西安理工大学机械与精密仪器工程学院,陕西 西安 [3]中国航发长江动力有限公司,研发中心,湖南 岳阳

出　　处：《机械工程与技术》2022年第3期249-256,共8页Mechanical Engineering and Technology

摘　　要：针对航空发动机用接触式机械密封存在泄漏量大、寿命较短等问题,首先采用无限长平面平行槽的惠普尔理论构建上游泵机械密封计算模型,然后仿真计算密封结构参数对液膜刚度及泄漏量等密封性能的影响,最后以泄漏量最小、最大液膜刚度为优化目标,对上游泵送密封结构参数进行优化设计,并通过模拟运转试验验证了优化结构的正确性。Aiming at the shortcomings of traditional mechanical seal in the Aero engine, such as large leakage and short seal life, the model of Upstream pumping mechanical seal was established on the basis of infinitely long plane parallel groove theory named as Whipple theory, the effects of the seal structure parameters on sealing performance including fluid film stiffness and leakage were simulated, and the structural parameters of Upstream pumping mechanical seal were optimized to obtain the film stiffness. The correctness of optimal results were proved by the simulation test.

关 键 词：航空发动机 上游泵送机械密封 螺旋槽 参数优化 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]