低温非接触式端面密封参数优化与试验验证  

Parameter optimization and experimental verification of non-contacting end-face seals in cryogenic condition

作　　者：陈杰[1] 李建克[1] 王少鹏[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第4期56-61,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2007AA705302)

摘　　要：针对液氧/煤油发动机使用的接触式端面密封存在端面温升大、重复使用性能不理想等问题,首先采用无限长平面平行槽的惠普尔理论构建非接触式端面密封计算模型,然后仿真计算密封结构参数对气膜刚度以及泄漏量等密封性能的影响,最后以最大气膜刚度为优化目标,对非接触端面密封结构参数进行优化设计。低温运转试验验证了优化结果的正确性和非接触式端面密封具有良好的重复使用性。Aiming at the shortcomings of the traditional end-face seal in the LOX/kerosene rocket engine, such as high temperature rise caused by large friction and lack of reusability, the model of non-contacting end-face seal was established on the basis of infinitely long plane parallel groove theo- ry named as Whipple theory, the effects of the seal structure parameters on sealing performance in- cluding air film stiffness and leakage were simulated, and the structural parameters of non-contacting end-face seal were optimized to obtain the best film stiffness. The correctness of optimal results and better reusability of non-contacting end-face seal were proved through test in cryogenic condition.

关 键 词：非接触式端面密封 气膜刚度 参数优化 重复使用 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]