航空发动机叶片外物损伤与模拟试验研究
发布时间：2018-10-20 12:51
【摘要】：发动机的叶片可能被外来物撞击而受到损伤,这种外物冲击损伤简称FOD。FOD带来的危害非常严重,许多案例都证明,机场道面上的外来物可以很容易被吸入到发动机,导致发动机失效,碎片也会堆积在机械装侕中,影响起落架、机翼等设备的正常运行,不仅会损坏飞机和夺去宝贵的生命,而且还伴随着巨大的经济损失。目前,国内大多数机场跑道监察工作主要靠道面巡查人员进行人工完成,在道面巡查时将关闭跑道,这使得航班通行能力不仅效率低、可靠性差,而且占用了宝贵的跑道使用时间。航空发动机在近地状态运行时,会吸入随高速气流运动的小石块、砂砾、铆钉等硬物,对风扇/压气机叶片造成外物损伤在高周疲劳载荷作用下,FOD极易诱使疲劳裂纹萌生并快速扩展,引起叶片的疲劳断裂失效,从而严重威胁飞行安全。因此,开展叶片FOD课题研究,对于尽可能减少并防止FOD引发飞行事故,保障发动机安全使用和飞机飞行安全,具有重要的工程实践意义。论文围绕叶片FOD的特征分析及模拟试验研究,重点开展了以下三个方面的研究工作:(1)针对两起某型发动机故障的损伤叶片,开展了叶片FOD的宏观、微观损伤特征进行了统计分析。研究表明,损伤叶片的损伤位置主要分布在叶片的进气边和排气边中部,分布密度从叶片边缘中部向叶根和叶尖逐步递增。通过对损伤叶片的宏观、微观检测,以及理化分析可以看出,损伤叶片外来物含Fe元素较多的钢类硬质物体,并且凹坑和缺口是主要的FOD损伤形式。(2)通过以上分析方法,针对故障发动机Ⅰ、Ⅱ中损伤叶片较多的部位进行抽取叶片,对损伤叶片进行了测量、分析,统计分析结果。由L、H的单值图可知,L主要在0~4mm之内,而H主要在0~3mm之内。(3)采用空气炮试验系统,在TC4平板试样上进行了FOD的有效模拟,并试验研究了损伤试样的HCF疲劳强度。试验结果表明,FOD致使试样的疲劳强度明显下降。对损伤试样的疲劳断口分析表明,FOD为疲劳裂纹的萌生及扩展提供了有利条件。
[Abstract]:The blade of the engine may be damaged by a foreign object, and the damage caused by the external object impact is very serious. Many cases have proved that the foreign matter on the plane of the airport can easily be inhaled into the engine. As a result of engine failure, debris will also accumulate in the mechanical installation, affecting the normal operation of landing gear, wings and other equipment, not only will damage the aircraft and take away valuable lives, but also accompanied by huge economic losses. At present, most of the airport runway monitoring work in China mainly depends on the manual completion of the pavement inspection personnel, which will close the runway during the pavement inspection. This makes the flight passage capacity not only low efficiency, but also poor reliability. And it takes up valuable runway time. When an aeroengine is running near the ground, it will inhale hard objects such as small stones, gravel, rivets and so on that move with high speed airflow. Under high cycle fatigue load, FOD easily induces fatigue crack initiation and rapid expansion, which causes fatigue fracture failure of the blade, which seriously threatens flight safety. Therefore, it is of great significance in engineering practice to carry out the research on blade FOD to minimize and prevent the flight accidents caused by FOD and to ensure the safe use of engines and flight safety of aircraft. This paper focuses on the characteristic analysis and simulation test of blade FOD, focusing on the following three aspects: (1) for two damaged blades of a certain engine, the macroscopic FOD of blade is carried out. The microscopic damage characteristics were analyzed statistically. The results showed that the damage location of the damaged leaf was mainly located at the inlet and exhaust edge of the leaf, and the distribution density increased gradually from the middle of the blade edge to the root and tip of the leaf. According to the macroscopic, microscopic and physical and chemical analysis of damaged leaves, it can be seen that the foreign materials of damaged leaves contain more Fe elements, and the pits and notches are the main forms of FOD damage. (2) through the above analysis methods, The damaged blades are measured, analyzed, and the results of statistical analysis are obtained from the more damaged parts of the damaged blades in the fault engine 鈪，
本文编号：2283246
[Abstract]:The blade of the engine may be damaged by a foreign object, and the damage caused by the external object impact is very serious. Many cases have proved that the foreign matter on the plane of the airport can easily be inhaled into the engine. As a result of engine failure, debris will also accumulate in the mechanical installation, affecting the normal operation of landing gear, wings and other equipment, not only will damage the aircraft and take away valuable lives, but also accompanied by huge economic losses. At present, most of the airport runway monitoring work in China mainly depends on the manual completion of the pavement inspection personnel, which will close the runway during the pavement inspection. This makes the flight passage capacity not only low efficiency, but also poor reliability. And it takes up valuable runway time. When an aeroengine is running near the ground, it will inhale hard objects such as small stones, gravel, rivets and so on that move with high speed airflow. Under high cycle fatigue load, FOD easily induces fatigue crack initiation and rapid expansion, which causes fatigue fracture failure of the blade, which seriously threatens flight safety. Therefore, it is of great significance in engineering practice to carry out the research on blade FOD to minimize and prevent the flight accidents caused by FOD and to ensure the safe use of engines and flight safety of aircraft. This paper focuses on the characteristic analysis and simulation test of blade FOD, focusing on the following three aspects: (1) for two damaged blades of a certain engine, the macroscopic FOD of blade is carried out. The microscopic damage characteristics were analyzed statistically. The results showed that the damage location of the damaged leaf was mainly located at the inlet and exhaust edge of the leaf, and the distribution density increased gradually from the middle of the blade edge to the root and tip of the leaf. According to the macroscopic, microscopic and physical and chemical analysis of damaged leaves, it can be seen that the foreign materials of damaged leaves contain more Fe elements, and the pits and notches are the main forms of FOD damage. (2) through the above analysis methods, The damaged blades are measured, analyzed, and the results of statistical analysis are obtained from the more damaged parts of the damaged blades in the fault engine 鈪，
本文编号：2283246
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