摘要
在内部流场气-热耦合数值模拟的基础上,研究了某涡轮导向器叶片烧蚀故障的原因。研究结果表明,叶片前缘和后缘易出现高温区,尾缘上下端壁处有较大的温度梯度,是叶片容易烧蚀的位置;喷嘴积碳、燃油品质不良以及气流结构变化等均易使燃烧室出现温度分布不均,导致导向器叶片出现局部烧蚀;使用中应加强导向器叶片前缘和尾缘的检查,并严格控制暖机和冷机时间,防止发动机超温。
The cause of turbine stator blades was analyzed on the base of numerical simulation by means of air-thermal coupling for heat transfer and temperature distribution. High temperature regions appear at the leading edge and the trailing edge of the blades, and major temperature gradient at both upper and lower of the ending edge of the blades make the leading, trailing and ending edge ablate easily. Non-uniform temperature distribution of blaster chamber by carbon deposition of the jet nozzle , bad quality of the fuel oil and change of the gas flow structure induce turbine stator blades to occur local ablation failure. To prevent over-temperature for aero-engine, it should be checked the leading, trailing and ending edge of the blades during service and controled the time of warming up and cooling of the engine strictly.
出处
《失效分析与预防》
2006年第4期27-29,共3页
Failure Analysis and Prevention
关键词
航空发动机
涡轮叶片
数值模拟
烧蚀
aero-engine
turbine blade
numerical simulation
ablation
