Classification of key influence factors for failure of turbo supercharged piston aeroengine
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摘要:
航空活塞发动机涡轮增压技术的应用大幅增加了动力系统的复杂性，与增压器相关的安全问题日趋严峻。以某型航空活塞发动机及其两级增压器为对象，聚焦失效诱因的判断方法研究，在建立的整机系统模型基础上，提出一种改进的对应分析法实现对增压器失效模式关键影响因素的分级。结果显示：通过列轮廓坐标随关键影响因素的数值偏离程度表明影响大小的分级方法，可以有效辨识出失效的关键影响因素，废气阀直径是影响各工作边界安全裕度的首要因素，需首先加以控制。
Abstract:Using turbocharging technology dramatically increases the complexity of piston engine systems and the safety issues associated with turbocharger are becoming urgent. A typical two-stage turbo supercharged piston engine is considered and the judgment method for failure of incentives is focused in this study. Based on the built whole engine system model, a modified correspondence analysis method is proposed, which implements the classification of factors on the failure modes. The results show that the key influence factors and potential causes of coupling failure for turbo supercharged piston engine in actual motion can be judged through changed column contour coordinates in proposed classification method. The test presents that the diameter of exhaust valve is the dominant factors for safety margin boundary and needs to be controlled primarily.
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图 2 航空两级涡轮增压活塞发动机系统模型示意图
Figure 2. Schematic diagram of system model for two-stage turbo supercharged piston aeroengine
图 4 输出功率的仿真与实验数据对比
Figure 4. Comparison of output power between simulation and experimental data
图 5 扭矩的仿真与实验数据对比
Figure 5. Comparison of torque between simulation and experimental data
图 7 列轮廓坐标F随关键影响因素数值改变而产生的相对位置偏离
Figure 7. Changed relative position of column contour coordinates F according to variation of key influence factors
图 8 增压系统工作边界代理模型数据与仿真模型数据的相对误差
Figure 8. Data relative error between surrogate model and simulation model for work boundary of supercharging system
图 9 增压系统资料矩阵的大样本点数下分析结果
Figure 9. Analysis results of data matrices with large sample point number for supercharging system
图 10 设计可控参数增大不同比例后工作边界安全裕度随关键影响因素产生的相对位置偏离
Figure 10. Relative position deviation of working boundary safety margin with key influencing factors is obtained by increasing proportion of design controllable parameters
图 11 关键影响因素改变产生的工作边界安全裕度相对距离偏离
Figure 11. Changed relative distance deviation of working boundary safety margin according to variation of key influence factors
表 1 某型无人机的飞行包线要求
Table 1. Flight envelope requirement of a certain type of UAV
节气门开度/% 发动机转速范围/(r·min-1) 飞机飞行状态 115 5200~5800 起飞状态 100 5000~5500 爬升状态 90 4800~5500 续航状态(高空或高速) 80 4500~5500 续航状态(高空或高速) 70 4200~5500 续航状态(高空或高速) 60 4000~5500 续航状态 50 3500~5300 续航状态 40 3500~5000 续航状态 30 3000~4500 续航状态 25 2500~4000 下降状态 12.5 1500~3500 下降状态 0~5 1200~2500 怠速状态(一般为地面) 
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表 2 样本点选取对应的工况点范围
Table 2. Range of operating point corresponding to selected sample points
海拔高度/km 节气门开度/% 发动机转速范围/(r·min-1) 7 70~100 4200~5500 10 70~100 4200~5500
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表 3 一组设计可控参数的初始仿真条件
Table 3. Initial simulation conditions for a set of design controllable parameters
设计可控参数 下限 上限 节气门开度e1/% 70 100 废气阀直径e2/mm 1.5 10.5 海拔高度e3/km 7 10 发动机转速e4/(r·min-1) 4 200 5 500 排气管直径e5/mm 40 60
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