叶片单一与耦合误差对轴流压气机性能的影响

楚武利; 何旭东; 杨吉博; 刘凯烨

doi:10.13224/j.cnki.jasp.20220941

叶片单一与耦合误差对轴流压气机性能的影响

doi: 10.13224/j.cnki.jasp.20220941

1.
西北工业大学动力与能源学院，西安 710072
2.
中国航天科技集团有限公司西安航天动力研究所，西安 710100

基金项目: 国家科技重大专项（J2019-Ⅰ-0011）；国家自然科学基金（51576162）

详细信息

作者简介:
楚武利（1962−），男，教授、博士生导师，博士，主要从事高性能轴流及离心压气机先进流动控制研究

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2022-12-08
- 网络出版日期: 2024-01-15

Effects of blade single and coupling errors on axial flow compressor performance

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Xi’an Aerospace Propulsion Institute，China Aerospace Science and Technology Corporation，Xi’an 710100，China

摘要

摘要:
由于加工工艺等因素的限制，在实际的加工过程中，理论叶型与实际叶型之间总会存在微小误差。针对跨声速压气机转子Rotor 37，采用数值模拟和NIPC（非嵌入式多项式混沌方法）相结合的方法，研究轴向位置度误差与安装角误差对压气机气动性能的不确定性影响。结论表明：对于轴向位置度和安装角服从零均值标准正态分布的加工误差，两者单一变化或耦合变化时，转子气动性能对各误差敏感性基本一致，只有个别参数有区别。轴流压气机气动性能与各个误差的相关性有强弱之分，加工时应当关注强相关性的性能参数。叶片耦合误差对压气机的影响为叶片轴向位置度误差和安装角误差的影响的叠加。
- 跨声速轴流压气机 /
- 加工误差 /
- 不确定性 /
- 安装角误差 /
- 耦合误差
Abstract:
Due to the limitation of processing technology and other factors, there is always a small error between the theoretical blade profile and the actual blade profile in the actual processing. For transonic compressor Rotor 37, the influences of axial position and stagger angle errors on the uncertainty of compressor aerodynamic performance were studied by numerical simulation and NIPC (non-intrusive polynomial chaos method). The conclusion indicated that, for machining errors with zero mean standard normal distribution of axial position and stagger angle, the sensitivity of rotor aerodynamic performance was approximately the same when they changed singly or in coupling, only individual parameters were different. The correlation between the aerodynamic performance of axial flow compressor and each error was strong or weak, and attention shall be paid to the performance parameters with strong correlation during processing. The influence of blade coupling error on compressor lied in the superposition of the influences of blade axial position error and stagger angle error.
- transonic compressor /
- machining errors /
- uncertainty /
- stagger angle error /
- coupling error

HTML

图 1 NASA Rotor 37子午面及试验测量位置^[15]

Figure 1. Meridian and test measurement position of NASA Rotor 37^[15]

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图 2 轴向位置度误差示意图

Figure 2. Schematic of the axial position degree error

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图 3 叶片安装角误差示意图

Figure 3. Schematic of the stagger angle error

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图 4 耦合误差叶片示意图

Figure 4. Schematic of the coupling errors of blade

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图 5 Rotor 37网格示意图

Figure 5. Schematic of the grid of Rotor 37

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图 6 不同网格数量总性能曲线对比

Figure 6. Comparison of total performance curves with different grid numbers

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图 7 近失速工况等熵效率和出口气流角沿叶高分布图

Figure 7. Distribution of isentropic efficiency and outlet flow angle along the blade span under near stall condition

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图 8 近失速工况转子95%叶高截面相对马赫数分布图

Figure 8. Relative Mach number of 95% blade span of rotor under near stall condition

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图 9 不同阶数NIPC方法对试验函数的拟合效果

Figure 9. Fitting results of NIPC methods of different orders on test functions

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图 10 不同误差下转子各性能参数的变异系数

Figure 10. Coefficient of variation of rotor performance parameters with different errors

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图 11 峰值效率工况耦合误差作用时转子各性能参数对$ \delta $和Z误差的Spearman相关系数

Figure 11. Spearman correlation coefficient of rotor performance parameters to $ \delta $ error and Z error with the action of coupling error under peak efficiency condition

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图 12 近失速工况耦合误差作用时转子各性能参数对$ \delta $和$ Z $误差的Spearman相关系数

Figure 12. Spearman correlation coefficient of rotor performance parameters to $ \delta $ error and Z error with the action of coupling error under near stall condition

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图 13 单一误差下转子99%叶高处叶片表面静压系数的标准差

Figure 13. Standard deviation of blade surface static pressure coefficient at 99% blade span of rotor with single error

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图 14 耦合误差下转子99%叶高处叶片表面静压系数的标准差

Figure 14. Standard deviation of blade surface static pressure coefficient at 99% blade span of rotor with coupling error

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图 15 单一误差下峰值效率工况99%叶高相对马赫数变异系数

Figure 15. Coefficient of variation of 99% blade span relative Mach number under peak efficiency condition with single error

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图 16 单一误差时近失速工况99%叶高相对马赫数变异系数

Figure 16. Coefficient of variation of 99% blade span relative Mach number under near stall condition with single error

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图 17 耦合误差时99%叶高相对马赫数变异系数

Figure 17. Coefficient of variation of relative Mach number of 99% blade span with coupling error

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图 18 单一误差时近失速工况99%叶高部分参数均值云图

Figure 18. Mean value of partial parameters of 99% blade span under near stall condition with single error

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图 19 单一误差时近失速工况99%叶高标准螺旋度标准差云图

Figure 19. Standard deviation of helicity of 99% blade span section under near stall condition with single error

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图 20 耦合误差时近失速工况99%叶高截面部分参数均值云图

Figure 20. Mean value of partial parameters of 99% blade span under near stall condition with coupling error

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图 21 耦合误差时99%叶高标准螺旋度标准差云图

Figure 21. Standard deviation of helicity of 99% blade span under near stall condition with coupling error

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图 22 耦合误差时峰值效率工况性能参数概率分布

Figure 22. Probability distribution of performance parameters under peak efficiency condition with coupling error

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图 23 耦合误差时近失速工况压气机性能参数概率分布

Figure 23. Probability distribution of performance parameter under near stall condition with coupling error

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表 1 NASA Rotor 37部分参数

Table 1. Partial parameters of NASA Rotor 37

参数	数值
叶片数	36
设计转速/（r/min）	17188
设计流量/（kg/s）	20.19
设计总压比	2.106
等熵效率	0.889
叶顶间隙/mm	0.356
轮毂比	0.70
展弦比	1.19
堵塞流量/（kg/s）	20.93±0.14

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表 2 不同网格下部分参数数值模拟结果

Table 2. Numerical simulation results of partial parameters with different grids

网格数/10⁴	峰值效率	最大总压比	近失速点质量流量/（kg/s）
50	0.86144	2.120	19.24
60	0.86250	2.126	19.21
70	0.86300	2.127	19.22
80	0.86375	2.127	19.19
90	0.86370	2.127	19.19

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表 3 NIPC方法试验函数统计结果

Table 3. Statistical results of NIPC method test function

NIPC阶数	均值μ	标准差σ	e²
3	5.654020	14.845943	1.0×10⁻⁴
4	5.654025	14.845791	2.7×10⁻⁶
5	5.654025	14.845799	3.8×10⁻⁷
6	5.654025	14.845798	3.8×10⁻⁸

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