摘要
管壳式燃滑油散热器换热特性直接影响航空发动机滑油系统的散热冷却能力,对滑油系统的热平衡建立至关重要。为了更准确地进行滑油系统热分析计算,优化滑油系统设计,必须掌握更为精确的燃滑油散热器换热特性的计算方法。在对散热器壳程的复杂流动进行分析的基础上,分别采用Kern法、Bell-Delaware法和分段模拟法计算换热特性,并通过试验结果验证计算准确度,经对比表明,将壳程换热按流动特性进行分段模拟计算的方法具有更高的准确度,满足滑油系统设计需要。
Heat transfer characteristics of tube and shell type fuel oil heat exchanger has a direct impact on the heat dissipation and cooling capability of aeroengine lubrication system, and it is especially important to thermal balance establishment. More accurate calculating method of fuel oil heat transfer characteristics must be mastered in order to carry on thermal analysis and design optimization of oil system. Based on the analysis of complex flow of the heat exchanger shell side, Kern method, Bell-Delaware method and dividable simulation method were conducted to calculate the heat transfer characteristics. The result demonstrates that the shell side calculating method is carried on by stages according to fluid characteristics,which has high accuracy and can meet the design requirements of oil system.
出处
《航空发动机》
2013年第1期65-69,共5页
Aeroengine
关键词
燃滑油散热器
换热特性
滑油系统
壳程
航空发动机
fuel and oil heat exchanger
heat transfer characteristics
oil system
shell side
aeroengine
