Experiment of the effect of steady distortion on the stability of an eccentric compressor
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摘要:
为了探究偏心压气机中的流动不稳定现象以及进气畸变和偏心之间的流动干扰对压气机气动稳定性的影响，针对一台单级偏心压气机开展了均匀进气、4种相位的稳态周向总压畸变进气和6种相位的对涡旋流畸变进气下压气机气动稳定性测量实验。在均匀进气下，当压气机节流至近失速状态时，大间隙位置附近出现旋转不稳定现象，而小间隙位置处于有序的稳定流动状态，进一步分析发现偏心压气机不稳定流动最强的区域在最大间隙之后约45°，与流量系数最小的区域非常接近。进气畸变下的实验结果表明：进气畸变和偏心之间的相位关系是影响压气机稳定性的潜在因素，当周向总压畸变诱导的大攻角区域、旋流畸变诱导的负预旋区域与偏心压气机均匀进气下流动不稳定性最强的区域同相位时，压气机稳定性下降最严重。
Abstract:In order to investigate the flow instability phenomenon in eccentric compressor and the effect of flow disturbance between inlet distortion and eccentricity on the aerodynamic instability of the compressor, experiments were carried out to measure the aerodynamic stability of a single-stage eccentric compressor under uniform inlet, four phases of steady-state circumferential total pressure distortion inlet and six phases of paired vortex flow distortion inlet. When the compressor was throttled to near-stall condition under uniform inlet, rotational instability occurred near the large clearance location, while the small clearance location was in an orderly steady flow. Further analysis revealed that the strongest region of unsteady flow in the eccentric compressor was about 45° after the largest clearance, which was very close to the region with the smallest flow coefficient. Experimental results under intake distortion showed that the phase relationship between intake distortion and eccentricity was a potential factor affecting the stability of the compressor. When the large incidence region induced by the circumferential total pressure distortion and the negative precession region induced by the vortex distortion were in the same phase as the region with the strongest flow instability under the uniform inlet of the eccentric compressor, the stability of the compressor decreased most seriously.
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图 2 单级偏心压气机偏心示意图
Figure 2. Schematic diagram of the eccentricity of the single-stage eccentric compressor
图 4 总压畸变发生装置结构图
Figure 4. Structure of the total pressure distortion generating device
图 6 单级偏心压气机测点布置
Figure 6. Arrangement of measurement points of the single-stage eccentric compressor
图 7 稳态总压畸变影响下压气机进口流场
Figure 7. Flow field at the inlet of the compressor under the influence of steady state total pressure distortion
图 8 旋流畸变影响下压气机进口气流角分布
Figure 8. Flow angle distribution of compressor inlet under the influence of vortex
图 9 均匀进气条件下单级偏心压气机总静压升特性
Figure 9. Total static pressure rise characteristics of single-stage eccentric compressor under uniform inlet condition
图 11 转子叶顶静压信号的FFT变换
Figure 11. FFT transform of static pressure signal at the top of rotor blade
图 12 近失速工况下转子叶顶静压云图
Figure 12. Static pressure contour at the rotor blade top under near-stall condition
图 13 近失速点叶尖不稳定强度、流量系数与叶尖间隙的关系
Figure 13. Relationship between the intensity of tip instability, flow coefficient and tip clearance at near stall point
图 14 进口总压畸变与叶尖间隙分布的4种相对位置关系
Figure 14. Four relative positions of inlet total pressure distortion relative to tip clearance distribution
图 15 4种相对位置下压气机总静压升特性
Figure 15. Total static pressure rise characteristics of the compressor at four relative positions
图 16 相对位置为RP1时压气机失速前15圈至5圈周向8个位置的动态静压信号
Figure 16. Dynamic static pressure signals at eight positions in the circumferential direction from 15 to 5 revolutions before stalling of the compressor at the relative position of RP1
图 17 相对位置为RP3时压气机失速前15圈至5圈周向8个位置的动态静压信号
Figure 17. Dynamic static pressure signals at eight positions in the circumferential direction from 15 to 5 revolutions before stalling of the compressor at the relative position of RP3
图 18 旋流畸变与叶尖间隙分布的相对位置关系
Figure 18. Relative position of the vortex distortion with respect to the distribution of the tip clearance
图 19 偏心压气机在20°弯角旋流叶片3种相位影响下的总静压升特性
Figure 19. Total static pressure rise characteristics of the eccentric compressor under the influence of three phases of the 20° bend rotor blades
图 20 偏心压气机在40°弯角旋流叶片3种相位影响下的总静压升特性
Figure 20. Total static pressure rise characteristics of eccentric compressor under the influence of three phases of40° bend rotor blades
图 21 相对位置$ {\theta _{\mathrm{r}}} = 112.5{\text{°}} $时压气机失速前20圈至10圈周向8个位置的动态静压信号
Figure 21. Dynamic static pressure signals at eight positions in the circumferential direction from 20 to 10 revolutions before stalling of the compressor at the relative position $ {\theta _{\mathrm{r}}} = 112.5{\text{°}} $
图 22 相对位置$ {\theta _{\mathrm{r}}} = 202.5{\text{°}} $时压气机失速前20圈至10圈周向8个位置的动态静压信号
Figure 22. Dynamic static pressure signals at eight positions in the circumferential direction from 20 to 10 revolutions before stalling of the compressor at the relative position $ {\theta _{\mathrm{r}}} = 202.5{\text{°}}$
表 1 偏心压气机关键参数
Table 1. Key parameters of eccentric compressor
参数 数值 外径/mm 900 轮毂比 0.6 设计转速/（r/min） 1500 转子叶片数 19 静子叶片数 22 转子稠度 1 静子稠度 1 平均间隙/mm 2 最大间隙/mm 3 最小间隙/mm 1 （叶尖间隙/叶高）/% 1.1 
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