【摘要】：發(fā)動(dòng)機(jī)的葉片可能被外來(lái)物撞擊而受到損傷,這種外物沖擊損傷簡(jiǎn)稱FOD。FOD帶來(lái)的危害非常嚴(yán)重,許多案例都證明,機(jī)場(chǎng)道面上的外來(lái)物可以很容易被吸入到發(fā)動(dòng)機(jī),導(dǎo)致發(fā)動(dòng)機(jī)失效,碎片也會(huì)堆積在機(jī)械裝侕中,影響起落架、機(jī)翼等設(shè)備的正常運(yùn)行,不僅會(huì)損壞飛機(jī)和奪去寶貴的生命,而且還伴隨著巨大的經(jīng)濟(jì)損失。目前,國(guó)內(nèi)大多數(shù)機(jī)場(chǎng)跑道監(jiān)察工作主要靠道面巡查人員進(jìn)行人工完成,在道面巡查時(shí)將關(guān)閉跑道,這使得航班通行能力不僅效率低、可靠性差,而且占用了寶貴的跑道使用時(shí)間。航空發(fā)動(dòng)機(jī)在近地狀態(tài)運(yùn)行時(shí),會(huì)吸入隨高速氣流運(yùn)動(dòng)的小石塊、砂礫、鉚釘?shù)扔参?對(duì)風(fēng)扇/壓氣機(jī)葉片造成外物損傷在高周疲勞載荷作用下,FOD極易誘使疲勞裂紋萌生并快速擴(kuò)展,引起葉片的疲勞斷裂失效,從而嚴(yán)重威脅飛行安全。因此,開(kāi)展葉片F(xiàn)OD課題研究,對(duì)于盡可能減少并防止FOD引發(fā)飛行事故,保障發(fā)動(dòng)機(jī)安全使用和飛機(jī)飛行安全,具有重要的工程實(shí)踐意義。論文圍繞葉片F(xiàn)OD的特征分析及模擬試驗(yàn)研究,重點(diǎn)開(kāi)展了以下三個(gè)方面的研究工作:(1)針對(duì)兩起某型發(fā)動(dòng)機(jī)故障的損傷葉片,開(kāi)展了葉片F(xiàn)OD的宏觀、微觀損傷特征進(jìn)行了統(tǒng)計(jì)分析。研究表明,損傷葉片的損傷位置主要分布在葉片的進(jìn)氣邊和排氣邊中部,分布密度從葉片邊緣中部向葉根和葉尖逐步遞增。通過(guò)對(duì)損傷葉片的宏觀、微觀檢測(cè),以及理化分析可以看出,損傷葉片外來(lái)物含F(xiàn)e元素較多的鋼類硬質(zhì)物體,并且凹坑和缺口是主要的FOD損傷形式。(2)通過(guò)以上分析方法,針對(duì)故障發(fā)動(dòng)機(jī)Ⅰ、Ⅱ中損傷葉片較多的部位進(jìn)行抽取葉片,對(duì)損傷葉片進(jìn)行了測(cè)量、分析,統(tǒng)計(jì)分析結(jié)果。由L、H的單值圖可知,L主要在0~4mm之內(nèi),而H主要在0~3mm之內(nèi)。(3)采用空氣炮試驗(yàn)系統(tǒng),在TC4平板試樣上進(jìn)行了FOD的有效模擬,并試驗(yàn)研究了損傷試樣的HCF疲勞強(qiáng)度。試驗(yàn)結(jié)果表明,FOD致使試樣的疲勞強(qiáng)度明顯下降。對(duì)損傷試樣的疲勞斷口分析表明,FOD為疲勞裂紋的萌生及擴(kuò)展提供了有利條件。
[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，

本文編號(hào)：2283246