Circumferential non-uniform flow characteristics and stall criterion of eccentric compressors
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摘要:
在压气机实际运行条件下，转轴偏心、机匣变形或加工装配误差等因素会导致叶尖间隙具有周向非均匀特征，对其性能尤其是稳定性产生重要影响。以NASA Rotor 67为研究对象，针对转轴偏心造成的周向非均匀条件开展数值研究。通过机匣-转子分域建模手段，构建叶顶间隙周向非均匀分布条件，对3种偏心度条件下的压气机三维流场进行全环仿真，获得了流场周向非均匀分布规律，并基于“等效间隙原则”建立了周向非均匀间隙压气机失稳准则。结果表明：偏心转子中大间隙区域叶尖泄漏流动增强导致阻塞效应加剧，使叶顶局部流量系数降低，更接近失稳边界，而小间隙区域则相反；流量系数极值位置相比间隙极值位置不重合，具有一定的相位延迟；偏心转子的失速流量系数接近以大间隙扇区平均间隙为间隙值的同心转子失速流量系数，因此“大间隙扇区平均间隙”等效原则可作为预估周向非均匀间隙压气机失速点的判定准则。
Abstract:Under actual operating conditions of compressor, factors such as shaft eccentricity, casing deformation or machining and assembly errors may lead to circumferential non-uniform characteristics of blade tip clearance, yielding an important impact on its performance, especially its stability. Taking NASA Rotor 67 as the research object, the circumferential non-uniform conditions caused by shaft eccentricity were studied numerically. The circumferential non-uniform distribution conditions of tip clearance were established by means of casing-rotor separated-domain modeling, and the three-dimensional compressor flow field under three eccentricity conditions was simulated to obtain the circumferential non-uniform distribution rules of flow field, and the stall criteria of compressor with circumferential non-uniform clearance were established based on the ‘equivalent clearance principle’. The results showed that the increase of tip leakage flow in the large clearance area of the eccentric rotor led to the intensified blocking effect, and the local tip flow coefficient decreased and got closer to the stall boundary, while the small clearance area was opposite. The extremum position of flow coefficient did not coincide with that of gap and had a certain phase delay. The stalling flow coefficient of the eccentric rotor was close to that of the concentric rotor with the average clearance of large gap sectors. Therefore, the equivalent principle of ‘average clearance of large gap sectors’ can be used as the criterion for estimating the stalling point of the circumferential non-uniform gap compressor.
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图 7 不同偏心率压气机转子性能曲线对比
Figure 7. Comparison of performance curves of compressor rotor with different eccentricities
图 8 转子进口流量系数分布（线图为95%叶高流量系数沿周向分布）
Figure 8. Flow coefficient distribution of rotor inlet （curve: circumferential distribution of flow coefficient at 95% span）
图 9 近失速工况流道平均流量系数沿周向分布
Figure 9. Circumferential distribution of passage-averaged flow coefficient at near-stall condition
图 10 叶顶区域静熵和马赫数分布
Figure 10. Distribution of static entropy and Mach number in tip region
图 11 最大间隙等效同心转子性能曲线对比
Figure 11. Comparison of performance curves of maximum clearance equivalent concentric rotor
图 12 近失速工况99%叶高熵分布
Figure 12. Entropy distribution of 99% span at near-stall condition
图 13 叶尖流量系数与当地局部失速流量系数的比较
Figure 13. Comparison of tip flow coefficient with local stall flow coefficient
表 1 NASA Rotor 67主要设计参数
Table 1. Main design parameters of the NASA Rotor 67
参数 数值 转速/（r/min） 16043 叶片数 22 流量/（kg/s） 33.25 设计压比 1.63 叶尖速度/（m/s） 429 设计叶顶间隙/cm 0.1061 叶尖相对马赫数 1.38 展弦比 1.5 
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