篦齿封严结构对高空台动静架连接密封特性 影响的数值仿真

Numerical Simulation of the Influence of Labyrinth Seal Structure on Sealing Characteristics of The SlipJoint Between the Moving and Fixed Element of Altitude Test Facility

中文关键词:  高空模拟试车台  篦齿封严  结构参数  泄漏量  封严特性  航空发动机

英文关键词:simulation altitude test facility  labyrinth seal  structural parameters  leakage rate  sealing characteristics  aeroengine

中文摘要:

      航空发动机高空模拟试车台动静架连接采用传统的篦齿密封结构，在试验中存在气体泄漏量大及流量管结冰现象。为 了提高高空模拟试验的准确性与安全性，针对新型篦齿密封结构，基于理论分析与数值仿真方法开展了动静架连接处篦齿封严机 理研究，获得了密封间隙、齿腔深宽比以及篦齿齿数等结构参数对新型篦齿密封结构封严特性的影响规律。结果表明：随着篦齿 密封间隙减小，改变控制口压比，泄漏量变化趋势较缓慢；齿腔深宽比基本不影响主流入口泄漏量的变化趋势；随着篦齿齿数的增 加，泄漏量减小。为高空台动静架篦齿密封结构设计和泄漏量分析提供了理论依据。

英文摘要:

      A traditional labyrinth seal structure was adopted for the slip Joint between the moving and fixed element of an aeroengine altitude test facility, where significant gas leakage and flow metering device icing were found during tests. To improve the accuracy and safety of the altitude simulation tests, theoretical analyses and numerical simulations were carried out to study the sealing mechanism of the new labyrinth seal structure of the slip Joint, the influential laws of the structural parameters such as seal clearance, chamber depth-width ratio, and the number of fins on the sealing characteristics of the new labyrinth seal structure were obtained. The results show that with the decrease of labyrinth seal clearance, changing of the control port pressure ratio results in a slower change of the leakage rate; the chamber depth-width ratio barely affects the change trend of the leakage rate at the mainstream inlet; with the increase of the number fins, the leak? age rate decreases. It provides a theoretical basis for the structural design and leakage rate analysis for the labyrinth seal structure of the slip Joint of altitude test facilities.