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.
出处
《火箭推进》
CAS
2013年第4期56-61,共6页
Journal of Rocket Propulsion
基金
国家863项目(2007AA705302)
关键词
非接触式端面密封
气膜刚度
参数优化
重复使用
non-contacting end-face seal
air film stiffness
parameter optimization
reusability
作者简介
陈杰（1971-），男，高级工程师，研究领域为机械密封设计
