摘要
叶顶间隙显著地影响着现代航空发动机的经济性和可靠性,叶顶间隙主动控制技术可以降低燃油消耗率的同时,保证安全性的要求。基于某型航空发动机的结构尺寸,分别建立了机匣、叶片、轮盘的数学模型。利用自行开发的叶顶间隙仿真程序,改进了叶片和涡轮盘数学模型,并与某型发动机整机的模拟程序相结合,计算了某型航空发动机高压涡轮叶顶间隙的时间历程变化。结果表明:叶顶间隙分别在慢车突然加速和反推力状态下出现最小值。叶顶间隙的计算结果基本上符合试验数据,说明该仿真程序不仅计算速度快,而且还具有足够的精度。
The tip clearance is one of the most concerned aspects of aero - engine＇s reliability and performance. Recent technological advance in the field of active clearance control promises to minimize the tip clearance loss, and guarantee the safety. Based on the structure of one type aero - engine, every part of high pressure turbine is modeled respectively. This paper developed numerical software and modified the numerical model of the blade and the turbine disk. Associated with one aero - engine simulation program, this software completed the calculation of the transient response of tip clearance. With the combination of one aero - engine simulation program, this software has achieved reasonable results： there two minimum tip clearances in the process of the first acceleration and re - burst, respectively. For all the results basically accord with the experiment data, this simulation is not only rapid, but also enough accurate.
出处
《计算机仿真》
CSCD
2008年第6期42-45,53,共5页
Computer Simulation
基金
军工项目
关键词
叶顶间隙
航空发动机
高压涡轮
数值分析
Tip clearance
Aero - engine
High pressure turbine
Numerical analysis
