浅槽动压整体式浮环密封静力与动力特性数值研究
Numerical study on static and dynamic characteristics of an integral floating ring seal with shallow groove dynamic pressure
赵欢 1姜金裕 1孙丹 1王双 1李延鹏1
作者信息
- 1. 沈阳航空航天大学航空发动机学院辽宁省航空推进系统先进测试技术重点实验室,沈阳110136
- 折叠
摘要
建立了浅槽动压整体式浮环密封静力与动力特性多频椭圆涡动求解模型,在验证数值计算方法准确性的基础上,分析了无槽、矩形槽、螺旋槽及T型槽4种结构整体式浮环密封的静力与动力特性,研究了不同结构与工况参数下的整体式浮环密封泄漏量、浮升力以及动力特性的变化规律,分析了槽型对整体式浮环密封转子稳定性的影响,揭示了动压槽型对整体式浮环密封动力特性的影响机理.研究结果表明:泄漏量与浮升力随着偏心率的增加而增大,相较于无槽浮环密封,矩形槽泄漏量最大,T型槽的浮升力最大,为无槽浮升力的434.7％;在同一涡动频率下,矩形槽的有效阻尼最大且为正值,切向气流力与转子涡动方向相反,从而抑制转子的涡动,提高转子稳定.
Abstract
A multi-frequency elliptic vortex solution model for static and dynamic characteristics of the monolithic floating ring seal with shallow groove dynamic pressure was established.On the basis of verifying the accuracy of the numerical calculation method,the static and dynamic characteristics of the integral floating ring seal with no groove,rectangular groove,spiral groove and T-groove were analyzed.The changes of leakage,buoyancy and dynamic characteristics of the integral floating ring seal under different structures and working condition parameters were studied.The influence of groove type on the stability of the integral floating ring seal rotor was analyzed,and the influence mechanism of dynamic pressure groove type on the dynamic characteristics of the integral floating ring seal was revealed.The results showed that the leakage and the lift force increased with the increase of eccentricity.Compared with the non-slotted floating ring seal,the rectangular groove had the largest leakage,and the T-shaped groove had the largest buoyancy,which was 434.7％of that without groove.Under the same vortex frequency,the effective damping of the rectangular groove was maximum and positive,and the tangential flow force was opposite to the rotor vortex direction,which can restrain the rotor vortex and improve the rotor stability.
关键词
整体式浮环密封/浅槽动压/静力特性/动力特性/气流力Key words
integral floating ring seal/shallow groove dynamic pressure/static characteristics/dynamic characteristics/airflow force引用本文复制引用
基金项目
国家自然科学基金(52075346)
先进航空动力创新工作站(依托中国航空发动机研究院设立)项目(HKC2020-02-030)
中国航空发动机集团产学研合作项目(HFZL2021CXY012)
出版年
2024
NETL
NSTL
万方数据