| 李超东，朱家友.加工误差对2 维叶型损失系数影响的数值分析[J].航空发动机,2018,44(4):80-85 |
| 加工误差对2 维叶型损失系数影响的数值分析 |
| Numerical Simulation Analysis of the Influence of Machining Error On TwoDimensional Blade's Loss Coefficient |
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| DOI： |
| 中文关键词: 加工误差 误差函数 压气机叶片 气动性能 航空发动机 |
| 英文关键词:mismachining tolerance error function compressor blade aerodynamic performance aeroengine |
| 基金项目: |
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| 中文摘要: |
| 叶片加工时由于公差和误差等原因其形状和尺寸往往会偏离设计状态，由此对叶片的气动性能造成严重影响。为了找
到其中的规律，发展了1 套简便可行的误差函数，在此基础上得到考虑了加工误差后的实际叶型。通过数值模拟得到了实际叶型
的气动性能，并对其进行统计分析，验证了所采用的误差函数是可行的。计算了实际叶型的设计参数（如弦长、前尾缘半径、进出口金属
角、最大厚度及其位置等），发现最大厚度和前缘半径的变化是导致实际叶型气动性能发生变化的最重要原因。在不同公差下，计算得到
最小损失系数的概率密度函数，结合不同设计对叶型气动性能的不同要求，可用于评估设计和选取性价比最高的加工方式。 |
| 英文摘要: |
| The actual compressor blade may has deviation because of mismachining tolerance,which will influence strongly on
compressor aerodynamic performance. In order to find out the rule, a simple and feasible error function is developed. The actual compressor
blade considered machining error was then got. Through numerical simulation, the aerodynamic performance of the actual blade is obtained.
The adopted error function is verified feasible through statistical analysis. The design parameters of actual blade is also calculated (such as
chord,radius of leading edge and trailing edge,import metal angle and export metal angle,maximum thickness and its position). We find
that the change of maximum thickness and radius of leading edge are the most important factors which leading change of aerodynamic
performance of actual blade. Probability density function of the minimum loss coefficient is got under different tolerances. Different design
have different requirements to blade aerodynamic performance, which can be used to evaluate design and select the most economic
manufacture method . |
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