Effect of circumferential groove casing treatment on performance of counter-rotating compressor under influence of speed matching effect
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摘要:
采用数值模拟方法，通过分别在对转压气机（counter-rotating compressor, CRC）前后两排转子上进行周向槽机匣处理，研究了其在不同转速匹配方案下的扩稳效果以及对转压气机最先失速级的变化规律。结果表明：当前排转子R1转速高于后排转子R2时，其最先失速级为R1，当R2转速等于或高于R1时，其最先失速级为R2。在对转压气机的最先失速级进行机匣处理可以有效改善所处理转子的叶尖附近流场，包括来流相对气流角的减小、叶尖泄漏流反向轴向动量的减小、叶尖泄漏流与主流交界面位置的后移及叶尖堵塞程度的减弱等，进而提升了其失速裕度。机匣处理一般仅能对所处理转子的流场产生较大影响，但在特殊情况下也会使非处理转子的流场发生明显改变。
Abstract:Numerical simulation method was used to study the stability enhancement effect under different rotational speed matching schemes and the change of first stall stage of counter-rotating compressor (CRC) by performing circumferential groove casing treatment on front and rear rotors of the counter-rotating compressor respectively. The results showed that when the rotational speed of front rotor R1 was higher than that of rear rotor R2, its first stall stage was R1, and when the rotational speed of R2 was equal to or higher than R1, its first stall stage was R2. Casing treatment on first stall stage of the counter-rotating compressor can effectively improve the flow field near blade tip of the treated rotor, including reduction of relative flow angle of inflow, decrease of reverse axial momentum of tip leakage flow, backward movement of interface between tip leakage flow and main flow, and reduction of blade tip blockage, etc., and then improve its stall margin. Generally, the casing treatment can only have a great influence on the flow field of treated rotor, but in special cases, the flow field of non-treated rotor can also be significantly changed.
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图 3 对转压气机与周向槽机匣处理结构图
Figure 3. Structure diagram of CRC and circumferential groove casing treatment
图 4 叶片通道及周向槽网格划分
Figure 4. Grid distribution of blade passage and circumferential groove
图 5 不同转速匹配方案中对转压气机的等熵效率特性线
Figure 5. Isentropic efficiency characteristic lines of CRC in different speed matching schemes
图 6 不同转速匹配方案中对转压气机的总压比特性线
Figure 6. Total pressure ratio characteristic lines of CRC in different speed matching schemes
图 7 不同转速匹配时对转压气机进行机匣处理后的失速裕度改进量
Figure 7. Stall margin improvement of CRC after casing treatment in different speed matching schemes
图 8 不同转速匹配时对转压气机的速度三角形示意图
Figure 8. Schematic diagrams of velocity triangle of CRC in different speed matching schemes
图 9 R1和R2的周向质量平均出口相对气流角沿展向分布
Figure 9. Spanwise distributions of mass pitch-averaged relative flow angle at the outlet of R1 and R2
图 10 99%叶展处R1和R2叶尖静压系数沿相对轴向弦长分布
Figure 10. Distributions along normalized axial chord of tip static pressure coefficient of R1 and R2 at 99% blade span
图 12 R1和R2叶尖泄漏流轴向动量沿相对轴向弦长分布
Figure 12. Distributions along normalized axial chord of tip leakage flow axial momentum of R1 and R2
图 13 R1和R2进口周向质量平均来流相对气流角沿展向分布
Figure 13. Spanwise distributions of mass pitch-averaged relative flow angle at the inlet of R1 and R2
图 14 R1和R2在99%叶展截面的相对马赫数云图
Figure 14. Relative Mach number contours of R1 and R2 at 99% blade span
图 15 R1和R2叶尖泄漏流气流角沿相对轴向弦长分布
Figure 15. Distributions along normalized axial chord of tip leakage flow angle of R1 and R2
图 16 R1和R2的叶尖泄漏流三维流线图
Figure 16. Three-dimensional streamlines of tip leakage flow of R1 and R2
表 1 对转压气机两排转子的主要设计参数
Table 1. Main design parameters of two rotors of the CRC
设计参数 前排转子R1 后排转子R2 叶片数 19 20 进口轮毂比 0.485 0.641 转速/（r/min） 8000 −8000 叶尖弦长/m 0.0832 0.0769 叶尖线速度/（m/s） 167.6 167.6 叶尖间隙/mm 0.5 0.5 
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表 2 前后排转子的转速匹配方案
Table 2. Speed matching schemes of front and rear rotor
参数 方案1 方案2 方案3 方案4 方案5 方案6 方案7 n1/% 100 100 90 90 100 80 80 n2/% 100 90 100 90 80 100 80
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表 3 不同转速匹配时R1和R2的U和ΔWu
Table 3. U and ΔWu of R1 and R2 in different speed matching schemes
转速匹配
方案R1 R2 U ΔWu U ΔWu n1=n2 
n1<n2 n1>n2
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表 4 R1和R2在不同转速匹配方案下近失速点的叶尖相对负荷
Table 4. Relative blade tip loading of R1 and R2 at near stall point in different speed matching schemes
转速匹配方案 叶尖相对负荷 R1 R2 100%-100% 1 1 100%-80% 0.981 0.814 80%-100% 0.938 1.279
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