摘要
对发动机中封严篦齿进行了相关齿形的变化 ,建立了 8种封严结构模型 ,运用 RNG k～ ε湍流模型、非结构化网格和 SIMPLE算法来模拟封严篦齿流动问题。探讨了篦齿前后压比与泄漏系数的变化关系 ,系统分析了齿形结构的微小变化对封严效果的影响。筛选出一种齿形进行实验研究 ,计算与实验变化规律一致 ,误差为1 0 .87%。通过对篦齿模型不同倾角的数值模拟 ,发现当篦齿朝气流倾斜一定角度时 ,有利于封严 ,考虑工艺性以及封严效果的综合因素 ,倾角选择在 60°左右较为合理。研究结果表明 :齿腔大小和齿腔形状是决定篦齿封严效果的重要因素。
In order to improve the performance of the seal labyrinth in aeroengine, many characteristic structures are applied to the seal. Eight models are numerically analyzed and one model is chosen to be tested. RNG k～ε of turbulence model, SIMPLE and the non-structure grid are applied in the numerical investigation of the flow in the seal labyrinth. The relation between the total pressure ratio and discharge coefficient is studied. The effect of micro changes on the labyrinth structure is systematically analyzed. Numerical results are in agreement with experimental data and the error between them is 10 87%. Considering the effect obliquity angles of labyrinth in the seal the angle of 60° is reasonable. Results show that the shape and the size of the labyrinth are important factors in the seal.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2004年第6期732-735,共4页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
篦齿
封严
泄漏
形状
湍流
labyrinth
seal
discharge
shape
turbulence
