Assessment of stability margin loss of aeroengine under inlet combined distortion measured in flight test
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摘要:
为确定航空发动机在飞行试验实测压力温度组合畸变下的稳定裕度损失，开展了基于图谱等效转换和平行压气机模型的稳定裕度损失评估方法研究。通过对试飞实测组合畸变图谱进行等效协调转换，结合平行压气机模型仿真计算，得到畸变下压缩系统的稳定边界，再通过畸变时刻发动机参数确定压缩系统工作点，从而得到畸变时的稳定裕度损失。对涡轮风扇发动机装机试飞下的实测进气畸变进行计算，得到温度不均匀度为2.2%、周向总压畸变强度为3.3%、高温区和低压区相位一致条件下的风扇稳定裕度损失为9.2%，表明形成的方法可用于试飞实测压力温度组合畸变下发动机稳定裕度损失确定。
Abstract:To determine the stability margin loss of aeroengine under measured pressure and temperature combined distortion in flight test, the stability margin loss evaluation method was studied based on equivalent conversion of distortion contour and parallel compressor model. The stability boundary of the compression system under distortion was obtained by equivalent coordinated conversion of the combined distortion contour and parallel compressor model calculation. Then the operating point of compression system was determined through the flight test data at the moment of distortion, and the stability margin loss can be calculated. For a stalled turbofan engine during flight test, the stability margin loss of the fan was 9.2% when the temperature non-uniformity was 2.2%, the circumferential total pressure distortion intensity was 3.3%, and the high-temperature and low-pressure regions were in phase. The results showed that the method can be used to determine the stability margin loss of aeroengine under pressure and temperature combined distortion measured in flight test.
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图 1 组合畸变下稳定裕度损失评估流程
Figure 1. Assessment of stability margin loss under inlet combined distortion
图 4 协调后的温度云图（7→8子压气机）
Figure 4. Temperature contour after coordination（7→8 sub-compressor）
图 6 均匀进气与畸变条件下的稳定边界
Figure 6. Stability boundary of inlet clean and combined distortion condition
表 1 畸变指数对比
Table 1. Comparison of distortion index
对比指标 等效前 等效后 相对误差/% δT2,FAV/% 3.77 3.77 0 $ \Delta {\bar T_2} $/% 2.15 2.17 0.9 $ \theta _T^ + $/（°） 154 154 0 
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表 2 畸变指数对比
Table 2. Comparison of distortion index
对比指标 等效前 等效后 相对误差/% $p^*_{\mathrm{av}} $/kPa 92 92 0 $ \Delta {\bar \sigma _0} $/% 3.31 3.36 1.42 $ \theta _p^ - $/（°） 182 180 1.1
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表 3 等效方案（温度→压力）
Table 3. Equivalent solution （temperature→pressure）
方案编号 Nh $ \theta _T^ + $/（°） $ \Delta \theta _T^ + $/（°） 1 4 180 26 2 3 135 −19
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表 4 与压力畸变协调的温度畸变图谱等效前后相关畸变参数对比
Table 4. Comparison of temperature distortion index before and after coordination
协调方案 δT2,FAV/% $ \Delta {\bar T_2} $/% $ \theta _T^ + $/（°） 协调前
（子压气机个数为7）3.77 2.17 154 协调后
（子压气机个数为8）3.77 2.20 135
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表 5 压力畸变图谱等效的子压气机周向范围及子压气机平均总压
Table 5. Sub-compressor circumferential range and average total pressure after coordination
参数 子压气机编号 1 2 3 4 5 6 7 8 $ \theta $/（°） （7, 52） （52, 97） （97, 142） （142, 187） （187, 232） （232, 277） （277, 322） （322, 7） $p^*_{\mathrm{av}} $/kPa 93.6 96.4 96.6 93.7 90.1 87.7 87.9 89.9
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表 6 与压力畸变协调的温度畸变图谱等效的子压气机周向范围及子压气机平均温度
Table 6. Sub-compressor circumferential range and average temperature of the temperature distortion map coordinated with pressure distortion
参数 子压气机编号 1 2 3 4 5 6 7 8 $ \theta $/（°） （357, 42） （42, 87） （87, 132） （132, 177） （177, 222） （222, 267） （267, 312） （312, 357） T/K 310.3 308.1 307.2 306.9 308.5 312.7 315.5 314.1
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表 7 相位保持一致后的子压气机周向范围及其进口参数
Table 7. Sub-compressor circumferential range and inlet parameters after phase consistency
参数 子压气机编号 1 2 3 4 5 6 7 8 $ \theta $/（°） （7, 52） （52, 97） （97, 142） （142, 187） （187, 232） （232, 277） （277, 322） （322, 7） $p^*_{\mathrm{av}} $/kPa 93.6 96.4 96.6 93.7 90.1 87.7 87.9 89.9 T/K 310.3 308.1 307.2 306.9 308.5 312.7 315.5 314.1
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表 8 pe=33.0 kPa时子压气机的工作点和稳定压比
Table 8. Sub-compressor operating point and stability pressure ratio when pe is 33.0 kPa
参数 子压气机编号 1 2 3 4 5 6 7 8 Wa,c 0.978 0.981 0.979 0.977 0.974 0.969 0.964 0.972 $ \pi _{\text{c}}^* $ 1.041 1.018 1.017 1.042 1.076 1.085 1.099 1.080 $ \pi _{\text{b}}^* $ 1.232 1.238 1.234 1.229 1.224 1.187 1.174 1.217
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表 9 pe=39.5 kPa时子压气机的工作点和稳定压比
Table 9. Sub-compressor operating point and stability pressure ratio when pe is 39.5 kPa
参数 子压气机编号 1 2 3 4 5 6 7 8 Wa,c 0.964 0.967 0.965 0.963 0.960 0.953 0.95 0.958 $ \pi _{\text{c}}^* $ 1.124 1.126 1.124 1.123 1.120 1.015 1.002 1.023 $ \pi _{\text{b}}^* $ 1.133 1.141 1.135 1.130 1.126 1.017 1.002 1.027
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表 10 不同换算转速下的稳定边界点
Table 10. Stability boundary points parameters of different corrected speeds
参数 N1cr =0.7 N1cr =0.8 N1cr =0.9 N1cr =0.95 N1cr =1.0 N1cr =1.1 Wa,c 0.584 0.682 0.818 0.894 0.960 1.004 $ \pi _{}^* $ 0.585 0.716 0.880 1.000 1.082 1.147
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