高空台动静架连接新型篦齿密封结构封严特性研究

针对高空模拟试车台动静架连接处气体泄漏问题，开展基于中段进气的新型篦齿密封结构优化设计与封严特性的数值模拟与试验研究。设计了新型篦齿密封结构，选取篦齿齿尖厚、齿根厚及后倾角为参数变量，泄漏量为优化目标函数，根据Box-Behnken方法设计的样本点和数值计算结果建立二阶响应面模型，开展新型篦齿密封结构泄露特性数值模拟与优化研究，并通过实验进行验证。研究表明，实验结果与有限元计算结果误差不超过10％，验证了数值模型的准确性；通过优化设计与分析，新型篦齿连接结构泄漏量降低12.5％，使得该结构更容易实现最优的封严效果。新型篦齿密封结构封严特性较初始结构提高99.2％，消除了由连接处泄漏带来的附加阻力695.2N。本研究对改进现有高空台动静架连接篦齿密封结构，提升其试验台推力测量的准确性具有重要作用。

Sealing Characteristics Study on New Labyrinth Seal Structure of Dynamic and Static Frame Connection of Altitude Simulation Test Facility

Numerical simulation and experimental research on the optimized design and sealing characteristics of a new labyrinth seal structure based on a mid-inlet were carried out to address the gas leakage problem at the dynamic and static frame connection of the aero-engine high-altitude simulation test facility. The new labyrinth sealing structure is designed, the thickness of the tooth tip, the thickness of the tooth root, and the back inclination angle of the tooth are selected as the parameter variables, the leakage amount is the optimization objective function, the sample points are designed according to the Box-Behnken method and the second-order response surface model is established by numerical calculation results to realize the numerical simulation and optimization of the leakage characteristics of the new labyrinth sealing structure, and is verified by test. The study shows that the error between the test results and the finite element calculation results does not exceed 10%, which verifies the accuracy of the numerical model; the leakage of the new labyrinth joint structure is reduced by 12.5% through the optimized design and analysis, making it easier to achieve the optimal sealing effect. The new labyrinth seal structure has 99.2% better sealing characteristics than the initial structure and eliminates the additional resistance of 695.2N caused by leakage at the joint. This study is an important role for improving the existing labyrinth sealing structures of the dynamic and static frame connection and enhancing the accuracy of thrust measurement in its test facility.