基于整机试验数据辨识的雷诺数对涡扇发动机的性能影响

王冠夫; 齐晓雪; 李长晖; 任文成; 蒋琇琇; 李斌

doi:10.13224/j.cnki.jasp.20210352

基于整机试验数据辨识的雷诺数对涡扇发动机的性能影响

doi: 10.13224/j.cnki.jasp.20210352

中国航发沈阳发动机研究所，沈阳 110015

基金项目: 航空动力基金（6141B09050360）

详细信息

作者简介:
王冠夫（1985-），男，高级工程师，硕士，主要研究方向为航空发动机总体性能仿真和气路故障诊断

中图分类号: V231.1
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出版历程
- 收稿日期: 2021-07-07
- 网络出版日期: 2022-09-05

Reynolds number effects on performance of turbofan based on whole engine test data identification

Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
为了研究雷诺数对涡扇发动机性能的影响并提升稳态性能模型在工作包线内的计算精度，提出了一种基于整机试验数据辨识的计算分析方法。选取用于气路分析的测量参数，提升辨识算法的收敛性和计算结果的有效性；结合非线性气路分析算法辨识计算出各试验点的部件性能修正因子，统计分析雷诺数和各部件性能修正因子的变化关系，定量得到雷诺数对发动机各部件性能的影响程度；修正基线稳态性能模型，并对计算精度进行验证对比。结果表明：对比试验结果，修正后的稳态性能模型各参数计算偏差不大于2.5%。对比基线稳态性能模型各参数计算结果，计算精度平均提升2.3%，最大提升9.2%。
- 雷诺数 /
- 稳态性能 /
- 部件性能 /
- 高空试验 /
- 修正因子 /
- 辨识计算
Abstract:
In order to investigate Reynolds number effects on the performance of turbofan and improve state performance model calculation accuracy in flight envelope, a computational analysis method based on whole engine test data identification was presented. Identification algorithm convergence and result validity were improved through measurement parameters selection for gas path analysis. Component performance scale factor for each test point was identified by non-linear gas path analysis method. Statistical analysis of the relationship between Reynolds Number and component performance scale factor was performed, and the performance change of each component affected by Reynolds Number was quantitatively obtained. Baseline steady state performance model was modified and calculation accuracy was compared and verified. Compared with test data, modified steady state performance model calculation error was not more than 2.5%. Compared with baseline steady state performance model calculation result for each parameter, the average calculation accuracy was improved 2.3%, and the maximal calculation accuracy was improved 9.2%.
- Reynolds number /
- steady performance /
- component performance /
- altitude test /
- scale factor /
- identification algorithm

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图 1 雷诺数对涡扇发动机性能影响的研究思路

Figure 1. Scheme of Reynolds number effects on turbofan engine performance

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图 2 基于整机试验数据的辨识计算流程图

Figure 2. Identification calculation flow chart based on whole engine test data

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图 3 迭代计算过程示意图

Figure 3. Schematic diagram of iterative calculation process

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图 4 试验结果与部件特性的相对关系

Figure 4. Relation between test results and component characteristics

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图 5 大涵道比分排涡扇发动机

Figure 5. Unmixed high bypass turbofan engine

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图 6 某大涵道比涡扇发动机高空性能试验点

Figure 6. Altitude performance test point of a high bypass turbofan engine

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图 7 雷诺数对各部件性能的影响（N_1r=95%）

Figure 7. Reynolds number effects on the performance of each component （N_1r=95%）

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图 8 修正前后的稳态性能模型计算结果相对偏差对比 (N_1r=95%)

Figure 8. Comparison of pre- and post- modified steady state performance model relative deviation of calculation results (N_1r=95%)

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图 9 雷诺数对整机性能参数的影响（Ma=0.6、N_1r=95%）

Figure 9. Reynolds number effects on the performance parameters of whole engine （Ma=0.6, N_1r=95%）

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表 1 不同测量参数组合的条件数对比

Table 1. Condition number of measured parameters combination contrast

测量参数组合	条件数
W_fm, p₄₄, p₁₃, T₄₄, T₅, N₂, p₃, T₃, p₂₅, T₂₅	30.1
W_fm, p₄₄, p₁₃, T₄₄, T₅, N₂, p₃, T₃, p₂₅, P₅	121.5
W_fm, p₄₄, p₁₃, T₄₄, T₅, N₂, p₃, T₃, p₂₅, W₂	149.7
W_fm, p₄₄, p₁₃, T₄₄, T₅, N₂, p₃, p₅, p₂₅, T₂₅	615.7

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表 2 测量参数标准差和权重

Table 2. Measured parameters standard deviation and weights

测量参数	标准差/%	权重
N₂	0.1	1
W_fm	0.3	0.11
p₁₃	0.2	0.25
p₂₅	0.2	0.25
T₂₅	0.3	0.11
p₃	0.3	0.11
T₃	0.2	0.25
p₄₄	0.3	0.11
T₄₄	0.5	0.04
T₅	0.4	0.06

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表 3 修正前后的稳态性能模型计算结果相对偏差 (N_1r=95%)

Table 3. Pre- and post- modified steady state performance model relative deviation of calculation results (N_1r=95%)

参数	模型计算相对偏差/%
参数	修正前	修正后
N₂	0.02～1.06	0.08～1.72
W_fm	1.85～9.46	0.08～2.06
p₁₃	0.27～2.93	0.08～1.73
T₂₅	0.01～1.93	0.04～1.52
p₂₅	1.24～4.95	0.30～1.94
T₃	0.02～2.88	0.06～1.18
p₃	2.61～5.08	0.01～1.40
T₄₄	1.35～7.47	0.38～2.24
p₄₄	2.28～4.45	1.29～2.21
T₅	2.31～8.22	0.05～2.47
p₅	1.37～4.27	1.53～2.50

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