航空涡轴发动机油滤组件滑油流道压力损失研究  

Study on pressure loss of oil flow channel for aeroengine oil filter

作　　者：唐志清 雷寰兴 粟晖 贺剑 TANG Zhiqing;LEI Huanxing;SU Hui;HE Jian

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《现代机械》2024年第2期1-5,共5页Modern Machinery

摘　　要：为研究航空涡轴发动机油滤组件内部滑油流道压力损失情况,利用试验测试和数值仿真计算的方法,对油滤组件滑油流道在不同温度、流量和结构形式下的压力损失进行了试验测试,获得了滑油流道压力损失数据和变化规律;将试验数据和FLUENT数值仿真数据进行了对比分析,结果表明,滑油流量不超过18 L/min,温度不超过80℃时,压力损失试验数据和计算数据较吻合,数值仿真可较准确地指导工程设计;当滑油流量超过18 L/min,温度超过100℃时,应修正数值计算模型和系数以提高计算精度。In order to study the pressure loss in the internal oil flow channel of the aeroengine oil filter,tests and numerical simulation calculation were carried out to study the pressure loss of oil flow channel with different structures at different temperatures and flow rates.The pressure loss data and variation patterns of the oil flow channel were obtained.The test data and FLUENT numerical calculation results were compared and analyzed.The results showed that the test data were in good agreement with the calculation data when the flow rate was under 18 L/min and the temperature was under 80℃,and the numerical calculation could guide the engineering design.When the oil flow rate exceeded 18 L/min and the temperature exceeded 100℃,the calculation model and coefficients should be revised to improve the calculation accuracy.

关 键 词：航空发动机 油滤组件 滑油流道 压力损失 

分 类 号：V263.3[航空宇航科学与技术—航空宇航制造工程]