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某航空发动机试验过程中发生振动大故障。分解后,发现高压涡轮转子叶片等多处零组件有磨损、变形甚至断裂的情况。将全台共计72片高压涡轮转子叶片委托中国航空工业集团公司失效分析中心进行分析,确认原因为高压涡轮转子叶片超温。分析高压涡轮转子叶片超温的多种可能原因,采用排除法,推断此次高压涡轮转子叶片超稳为局部超温,原因为高压涡轮导向器堵块脱落打伤高压涡轮转子叶片导致高压涡轮转子叶片冷却失效。根据推断寻找事实依据,推导故障模式。提出解决高压涡轮导向器堵块存在脱落可能性的方案,为后续高压涡轮转子叶片超温问题的判断提供分析思维导向。
Aeroengine test occurred during the vibration major fault. Decomposition, found that many parts such as high-pressure turbine rotor blades wear, deformation or even rupture. A total of 72 Taiwan high-pressure turbine rotor blades commissioned by China Aviation Industry Corporation Failure Analysis Center for analysis to confirm the reason for the high-pressure turbine rotor blades over-temperature. Analysis of high pressure turbine rotor blade over-temperature of a variety of possible reasons, the use of exclusion method, concluded that the high-pressure turbine rotor blade ultra-stable local over-temperature due to high-pressure turbine guide block plug off high-pressure turbine rotor blades lead to high-pressure turbine rotor Blade cooling failure. According to the inference to find the factual basis, derive the failure mode. Proposed to solve the possibility of high-pressure turbine guide block block off the possibility of program for the follow-up high-pressure turbine rotor blade over-temperature judgment to provide analytical thinking.