基于实测数据的涡轮导向器喉道面积不确定性分析及特性修正方法研究

谭家宁; 周志鸿; 刘火星

doi:10.13224/j.cnki.jasp.20240535

基于实测数据的涡轮导向器喉道面积不确定性分析及特性修正方法研究

doi: 10.13224/j.cnki.jasp.20240535

谭家宁^{1, 2,},
周志鸿^{1, 2,*, ,},
刘火星^{1, 2}

1.
北京航空航天大学航空发动机研究院，北京 102206
2.
北京航空航天大学航空发动机气动热力国家级重点实验室，北京 102206

基金项目: 中国航发科技创新稳定支持项目（HFZL2021WCXY001）

详细信息

作者简介:
谭家宁（1999-），男，硕士生，研究方向为航空发动机涡轮气动性能不确定性。E-mail：tanjianing1999@163.com

通讯作者:
周志鸿（1991-），男，助理研究员，博士，研究方向为先进涡轮气动设计与测试技术。E-mail：zhouzhihong@buaa.edu.cn

中图分类号: V232.4
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- 被引次数: 0
出版历程
- 收稿日期: 2024-08-01
- 网络出版日期: 2025-02-27

Uncertainty analysis of turbine nozzle area and turbine characteristic correction based on measured data

TAN Jianing^{1, 2
,},
ZHOU Zhihong^{1, 2,*
, ,},
LIU Huoxing^{1, 2}

1.
Research Institute of Aero-Engine，Beihang University，Beijing 102206，China
2.
National Key Laboratory of Science and Technology on Aero-Engine Thermodynamics，Beihang University，Beijing 102206，China

摘要

摘要:
基于高压导向器喉道面积和叶片型面几何实测数据，采用主成分分析法和代理模型方法，在对型面几何偏差的量化建模的基础上，利用数值仿真方法分析喉道面积的不确定性分布，并以此作为特性的修正变量，利用多项式拟合，发展涡轮特性修正方法，建立了考虑喉道面积偏差的涡轮特性修正模型。研究表明，对象高压涡轮喉道面积分散性在−1.08%～1.4%，质量流量均值增大约1.813%；3个截面计算喉道等效宽度时，测量面积误差最大可达到3%，增加测量截面能够有效减小测量误差；通过分步拟合以及训练检验的涡轮特性修正模型的质量流量和效率预测误差可以控制在2%以下。
- 涡轮导向器 /
- 喉道面积 /
- 几何不确定性 /
- 代理模型 /
- 多项式拟合 /
- 特性修正
Abstract:
Based on the measured data of throat area and blade surface geometry, the uncertainty distribution of throat area was analyzed by numerical simulation method on the basis of quantitative modeling of surface geometry deviation. Using this as a characteristic correction variable, polynomial fitting was used to establish a turbine characteristic correction method considering the deviation of throat area. The results showed that the dispersion of the high-pressure turbine throat area was between −1.08% and 1.4%, and the average mass flow increased by about 1.813%; when measuring three cross-sections, the maximum measurement area error can reach 3%. Increasing the number of measurement cross-sections can effectively reduce the measurement error; the mass flow rate and efficiency prediction error of the turbine characteristic correction model can be controlled below 2% through stepwise fitting and training verification.
- turbine guide vane /
- throat area /
- geometric uncertainty /
- agent model /
- polynomial fitting /
- characteristic correction

HTML

图 1 喉道面积测量截面示意图

Figure 1. Schematic diagram of throat area measurement cross-section

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图 2 n-n截面喉道宽度以及喉道面积分布

Figure 2. n-n cross-sectional throat width and throat area distribution

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图 3 喉道面积测量值样本分布

Figure 3. Distribution of throat area measurement values

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图 4 叶片型面法向偏差分布

Figure 4. Normal deviation distribution of blade profile

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图 5 网格无关性验证

Figure 5. Grid independence verification

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图 6 不确定性分析流程

Figure 6. Process of uncertainty analysis

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图 7 喉道面积变化率和流量分布

Figure 7. Distribution of throat area change rate and mass flow rate

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图 8 效率分布

Figure 8. Distribution of efficiency

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图 9 喉道型线偏差位置示意图

Figure 9. Schematic diagram of deviation position of throat profile

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图 10 4凸包（hump 4）几何示意图

Figure 10. Geometric diagram of “hump 4”

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图 11 真实喉道面积与计算喉道面积的偏差量计算结果

Figure 11. Calculation results of deviation between actual throat area and calculated throat area

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图 12 涡轮级流量特性

Figure 12. Mass flow characteristic of turbine stage

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图 13 涡轮级效率特性

Figure 13. Efficiency characteristic of turbine stage

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图 14 转速-效率特性图

Figure 14. Relationship between rotational speed and efficiency

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图 15 面积变化率-折合流量拟合结果

Figure 15. Fitting results of area change rate and mass flow

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图 16 流量截止前的流量特性拟合曲线

Figure 16. Fitting curve of mass flow characteristics before blockage status

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图 17 流量截止前效率特性拟合曲线

Figure 17. Fitting curve of efficiency characteristics before blockage status

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图 18 流量截止前的流量特性修正拟合曲线

Figure 18. Correction fitting curve of mass flow characteristics before blockage status

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图 19 流量截止前的效率特性修正拟合曲线

Figure 19. Correction fitting curve of efficiency characteristics before blockage status

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图 20 流量截止后的效率特性拟合曲线

Figure 20. Fitting curve of efficiency characteristics after blockage status

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表 1 喉道测量结果的统计特征

Table 1. Statistical characteristics of throat measurement results

参数	设计值	均值μ	差值Δ	标准差σ
宽度W_m/mm	10.944	10.7402	−0.2038	0.1417
宽度W_p/mm	11.134	10.9513	−0.1827	0.1154
宽度W_n/mm	11.297	11.1108	−0.1862	0.1442
高度H/mm	41.8	41.7933	−0.0067	0.1237
面积S/cm²	9.252	9.0641	−0.1879	0.0536

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表 2 气动边界条件

Table 2. Aerodynamic boundary condition

参数	数值
进口总压/kPa	3140.2
进口总温/K	1753
出口静压/kPa	650
转速/（r/min）	14675
无冷气流量/（kg/s）	1.3565

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表 3 各工况效率仿真结果

Table 3. Efficiency simulation results of each working condition

工况	膨胀比	效率
工况	膨胀比	网格2	网格3	网格4
小膨胀比、转速为 1.1倍设计转速	1.27102	0.865852	0.865881	0.865912
	1.22581	0.855425	0.855514	0.855484
	1.19716	0.840515	0.840541	0.840560
设计点、转速为 1.0倍设计转速	4.12041	0.914462	0.914468	0.914466
	4.07305	0.914213	0.914216	0.914214
	4.01145	0.914145	0.914148	0.914150
大膨胀比、转速为 0.7倍设计转速	4.86410	0.915216	0.915251	0.915230
	4.75201	0.916513	0.916544	0.916525
	4.67843	0.917363	0.917378	0.917350

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表 4 涡轮特性误差区间样本数

Table 4. Number of samples in error interval of turbine characteristics

误差区间	样本数
误差区间	流量修正模型	效率修正模型
0%～0.5%	46	48
0.5%～1.0%	24	24
1.0%～2.0%	17	15
>2.0%	0	0
最大误差/%	1.91	1.89

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表 5 不同训练集容量的效率特性误差区间样本数

Table 5. Number of samples in error interval of efficiency characteristics under different training set capacities

误差区间	样本数
误差区间	m=100	m=200	m=300
0%～0.5%	49	51	53
0.5%～1.0%	32	32	32
1.0%～2.0%	17	17	15
>2.0%	2	0	0
最大误差/%	2.32	1.89	1.54

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