压气机叶片加工误差离散性控制研究进展综述

何智伟; 李瑞宇; 李湉; 罗明

doi:10.13433/j.cnki.1003-8728.20240079

压气机叶片加工误差离散性控制研究进展综述

doi: 10.13433/j.cnki.1003-8728.20240079

何智伟^1,,
李瑞宇²,
李湉³,
罗明^1, ,

1.
西北工业大学机电学院航空发动机高性能制造工业和信息化部重点实验室, 西安 71007
2.
西安交通大学航天航空学院, 西安 710049
3.
中国航发航空科技股份有限公司, 成都 600503

基金项目:

国家自然科学基金项目 U2241249

详细信息

作者简介:
何智伟, 硕士研究生, hezhiwei0730@mail.nwpu.edu.cn

通讯作者:
罗明, 教授, 博士生导师, luoming@nwpu.edu.cn

中图分类号: V232.4
计量
- 文章访问数: 1150
- HTML全文浏览量: 12
- PDF下载量: 12
- 被引次数: 0
出版历程
- 收稿日期: 2023-04-24
- 刊出日期: 2024-07-25

A Review of Research Progress on Discreteness Control of Compressor Blade Machining Error

HE Zhiwei^1
,,
LI Ruiyu²,
LI Tian³,
LUO Ming^{1
, ,}

1.
Key Laboratory of High Performance Manufacturing for Aero Engine, Ministry of Industry and Information Technology, School of Mechatronics Engineering, Northwestern Polytechnical University, Xi'an 71007 China
2.
School of Aerospace Engineering, Xi'an Jiaotong University, Xi'an 710049, China
3.
AECC Aero Science and Technology Co., Ltd., Chengdu 600503, China

摘要

摘要: 航空发动机压气机整体叶盘通常设计为旋转周期对称结构。然而, 实际加工中同一级整体叶盘上不同叶片之间以及单个叶片自身存在的加工误差离散性会对流场参数产生不利影响。因此, 提高整体叶盘叶片加工误差一致性成为普遍关注的难题。综述了近年来针对同级叶盘不同叶片加工误差离散性对气动性能影响规律的相关研究, 以及加工过程强时变特性下误差离散度控制的相关成果。就误差离散性现象及产生原因、对性能影响规律及加工误差离散度控制方法这3个方面展开论述。最后展望了未来误差离散度加工控制方法发展趋势, 为未来相关研究工作提供参考。
- 整体叶盘 /
- 加工误差 /
- 气动性能 /
- 离散性 /
- 离散度控制
Abstract: The aero-engine compressor blisk is usually designed as a rotationally symmetric structure. However, in actual machining, the discreteness of machining errors between different blades on the same stage blisk and the individual blade itself will adversely affect the flow field parameters. Therefore, improving the consistency of machining errors of blisk's blades has become a common concern. This paper reviews the related researches on the influence of machining error dispersion on aerodynamic performance of different blades of the same stage in recent years, and the related results of error dispersion control under strong time-varying characteristics of machining process. The error dispersion phenomenon and its causes, the influence law on performance and the control method of machining error dispersion are discussed in three aspects. Finally, the development trend of error dispersion machining control method in the future is prospected, which provides a reference for future related research work.
- blisk /
- machining error /
- aerodynamic performance /
- discreteness /
- dispersion control

HTML全文

图 1 整体叶盘加工与设计意图的偏离^[10]

Figure 1. Manufacturing deviation from design intent^[10]

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图 2 整体叶盘叶片型线精度分析^[11]

Figure 2. Accuracy analysis of blade profile of integral blisk^[11]

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图 3 通过PDF对实测分布进行拟合^[23]

Figure 3. Fitting of measured distribution through a PDF^[23]

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图 4 前缘半径加工误差统计直方图^[26]

Figure 4. Statistical histogram of leading edge radius machining error^[26]

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图 5 叶型4个特征点的轮廓度误差统计分布^[27]

Figure 5. Statistical distribution of profile error of four feature points of blade profile^[27]

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图 6 4种叶片形状误差的概率密度统计结果^[28]

Figure 6. Statistical results of probability density of four kinds of bade shape errors^[28]

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图 7 GE E³叶尖叶型叶栅吸力面分离引起的叶片载荷扰动^[34]

Figure 7. Blade loading perturbation caused by suction-surface separation in GE E³ tip profile cascade^[34]

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图 8 GE E³叶尖叶型叶栅中由前缘流动分离引起的突尖波^[34]

Figure 8. Spike caused by leading edge separation in GE E³ tip profile cascade^[34]

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图 9 所有叶片的压力系数^[10]

Figure 9. Pressure coefficient for all blades^[10]

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图 10 实验环境下定子1和定子2下游的归一化总压力等值线^[36]

Figure 10. Normalized total pressure contours downstream of stator 1 and stator 2 from experiment^[36]

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图 11 八流道三维压力分布^[39]

Figure 11. 3D pressure distribution of one realization^[39]

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图 12 性能随流道增加的变化趋势^[39]

Figure 12. Variation trend of performance with increase of flow channel^[39]

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图 13 75%叶高处和0.986无量纲流量下的激波位置^[42]

Figure 13. Shock wave position at 75% span and non-dimensional flowrate of 0.986 ^[42]

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图 14 同一组随机生成安装角叶片的不同布置，平均变化0.437%^[42]

Figure 14. Different arrangements for same set of random generated blades with average change of stagger 0.437%^[42]

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图 15 切削刃的离散化和切削力的施加^[56]

Figure 15. Discretion and application of cutting force^[56]

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图 16 预测和测量的加工误差比较^[70]

Figure 16. Comparison between predicted and measured machining errors^[70]

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图 17 镜像补偿法^[74]

Figure 17. Mirror compensation method^[74]

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图 18 无应力夹具模型^[78]

Figure 18. Unstressed clamping model^[78]

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图 19 回转式辅助支撑机构^[79]

Figure 19. Rotary auxiliary support mechanism^[79]

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图 20 采用接触式测头进行在线测量

Figure 20. On-line measurement using a contact probe

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图 21 使用一种斜率方法预测残余应力引起的框架零件变形解析模型^[92]

Figure 21. A slope method is used to predict the deformation analytical model of frame parts caused by residual stress^[92]

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图 22 残余应力分层加载方法^[100]

Figure 22. Layered loading method of residual stress^[100]

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图 23 工序间主动控制方法示意图^[107]

Figure 23. Schematic of in-processes active control method^[107]

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图 24 薄壁零件误差在线补偿流程^[114]

Figure 24. Online error compensation process of thin-walled parts^[114]

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