涡扇发动机试车台进气导流装置优化初探  

The optimization analysis on turning vane of turbofan engine test stand

作　　者：王静[1] 孟进卓 卢强[1] 杨振军[1] 张能[1] 

机构地区：[1]中国航空规划建设发展有限公司,北京100120

出　　处：《燃气涡轮试验与研究》2015年第3期54-58,共5页Gas Turbine Experiment and Research

摘　　要：简要介绍了航空发动机试车台进气导流装置的结构形式,然后运用数值模拟手段对进气导流装置进行了分析,论证了进气导流装置方案的可行性和必要性。基于给定分析条件,对导流片安装角、叶片数量、进气角、圆弧半径、排气角5个变量进行组合分析,给出了5个变量与总压损失的关系;综合考虑规范要求、工程可实施性及经济成本,选出进气导流装置的5个优化参数组合(进气角0°、安装角47°、圆弧半径560 mm、叶片数量25、排气角-2°),使得试车间流场均匀度最好。The work was based on a 3D computational fluid dynamic method with FLUENT software. The construct of turning vane of turbofan engine test stand was simply introduced. The feasibility and necessity of the design was demonstrated. Based on the given conditions, five variables including installation angle, the number of vane, intake angle, radius and exhaust angle were analyzed, and the relationship between variables and the total pressure loss was presented. Considering general specifications, different calculating results, engineering implementation and cost, the most favorable combination （inlet angle 0°, installation an-gle 47°, radius 560 mm, 25 vanes, exhaust angle-2°） was offered. Under these conditions, the uniformity of flow field of test stand was the best. This analysis is helpful for test stand design in the future.

关 键 词：航空发动机试车台 进气导流装置 数值模拟 优化 导流片 流场均匀度 总压损失 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]