摘要
过渡态条件下热端部件热状态计算在评估发动机性能、强度寿命及内部间隙等方面占有十分重要的地位。参考了俄罗斯关于过渡态涂层叶片的1种计算方法,但对其中的数学处理作了更广泛的集成和推广,使得该方法能更充分地考虑过渡态变化过程的复杂性以及换热边界条件的适时变化等问题;以该方法编制了带涂层热端部件的工程计算程序,将计算结果与国外数据进行了对比,吻合较好。
The transient thermal behavior calculation of the hot section components was a very important role in the estimating aeroengine performance, intensity, life, and internal clearance. The mathematization for Russian transient thermal behavior calculation method of coated turbine blade were integrated and extended to consider the transient complexity and change of heat transfer boundary condition. The new engineering program of thermal behavior calculation for coated hot section component was compiled based on the method. The calculation results conform to foreign data well.
出处
《航空发动机》
2010年第1期20-23,共4页
Aeroengine
