The modeling design and analysis of centrifugal compressor
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摘要:
目的 作为叶轮机械领域的研究热点，离心式压气机对燃气轮机总体性能的影响很大。为了在相对较少的试验工况下实现性能优良的新型压气机设计，可采用效率高、成本低的模化设计方法。 方法 以某型高性能离心式压气机为母型，基于相似原理模化设计压比为4.42，绝热效率为79.19%的新型压气机，并采用NUMECA系列软件对离心压气机进行网格划分和三维流场数值模拟，对比分析模化压气机与母型压气机在80%，90%，100%，110%转速工况下的主要性能参数。 结果 结果表明：在100%转速工况下，模化压气机的喘振裕度比母型压气机提高了5.48%，但在其他转速工况下均下降了1%左右；模化压气机的压比与绝热效率在小流量工况下相对于母型压气机略有提升，但在大流量工况下均明显下降。 结论 基于相似原理进行模化设计的新型压气机基本达到了母型压气机的总体性能水平，研究成果可为离心压气机的模化设计提供参考。 Abstract:Objectives As a hot topic in the field of turbomachinery, centrifugal compressor has a huge impact on gas turbine general performance. In order to achieve the new compressor design with excellent performance under relatively few test conditions, the high efficiency and low cost modeling design method can be adopted. Methods In this paper, a new centrifugal compressor based on similarity principles with pressure ratio of 4.42 and efficiency of 79.19% was designed by modeling a prototype of a high-performance centrifugal compressor. NUMECA software was used to mesh and simulate the three-dimensional flow field of the centrifugal compressor, and the new compressor's main performance parameters and those of the prototype were compared at 80%, 90%, 100% and 110% rotation speeds. Results The results showed that at rotation speed settings of under 100%, the new compressor's surge margin is 5.48% higher than the prototype, but reduced by 1% at other speed settings. The new compressor's pressure ratio and efficiency are slightly improved at low flow conditions when compared to the prototype. However, at high flow conditions, the pressure ratio and efficiency of both compressors are significantly reduced. Conclusions The numerical simulation results show that the general performance of the new compressor has reached the performance level of the prototype compressor. The research results can be used as a reference for the modeling design of a centrifugal compressor. -
Key words:
- centrifugal compressor /
- modeling principle /
- similarity theory /
- tip leakage flow /
- endedge vortex
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图 1 母型压气机叶片的三维结构
Figure 1. Three dimensional structure of prototypical compressor blade
图 2 压气机的绝热效率−流量特性线
Figure 2. Adiabatic efficiency-flow characteristic line of compressor
图 4 80%转速下的绝热效率−相对流量特性线
Figure 4. Adiabatic efficiency-relative flow characteristic line at 80% rotating speed
图 5 80%转速下的压比−相对流量特性线
Figure 5. Pressure ratio-relative flow characteristic line at 80% rotating speed
图 6 90%转速下的绝热效率-相对流量特性线
Figure 6. Adiabatic efficiency-relative flow characteristic line at 90% rotating speed
图 7 90%转速下的压比−相对流量特性线
Figure 7. Pressure ratio-relative flow characteristic line at 90% rotating speed
图 8 100%转速下的绝热效率−相对流量特性线
Figure 8. Adiabatic efficiency-relative flow characteristic line at 100% rotating speed
图 9 100%转速下的压比−相对流量特性线
Figure 9. Pressure ratio-relative flow characteristic line at 100% rotating speed
图 10 110%转速下的绝热效率−相对流量特性线
Figure 10. Adiabatic efficiency-relative flow characteristic line at 110% rotating speed
图 11 110%转速下的压比−相对流量特性线
Figure 11. Pressure ratio-relative flow characteristic line at 110% rotating speed
图 13 90%叶高S1流面的相对马赫数分布
Figure 13. Relative Mach number distribution on 90% blade height of S1 section
图 15 通过分流叶片叶尖间隙的流线
Figure 15. Streamline through the tip clearance of the splitter blade
图 16 通过轮缘与机匣间隙的流线
Figure 16. Streamline through the clearance between the rim and the casing
图 17 50%叶高S1流面主叶片的尾缘涡流线
Figure 17. Streamline of vortex at main blade endedge on 50% blade height of S1 section
图 18 子午面无叶片空间的回流涡
Figure 18. Backflow vortex of the place without blade on the meridional section
图 19 扩压器50%叶高S1流面的绝对马赫数分布
Figure 19. Absolute Mach number distribution at 50% blade height of S1 section of diffuser
图 20 叶片前缘激波处的静压云图与流线
Figure 20. Static pressure contours and streamline of shock wave at leadedge of diffuser blade
图 21 扩压器50%叶高S1流面的绝对速度分布
Figure 21. Absolute velocity distribution at 50% blade height of S1 section of diffuser
图 22 子午面叶轮的相对马赫数分布
Figure 22. Relative Mach number distribution of impeller at meridional section
表 1 母型与模化压气机几何模型的主要结构参数
Table 1. Main structural parameters of geometry models of prototype and modeling compressors
结构参数 母型压气机 模化压气机 进口直径/mm 87.4 131.1 叶片出口直径/mm 128.4 192.6 进口轮毂直径/mm 35.8 53.7 叶片出口宽度/mm 5.9 8.85 叶片进口安装角/rad 0.387 0.387 叶片出口安装角/rad 1 1 
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表 2 母型与模化压气机的喘振裕度
Table 2. Surge margin of prototype and modeling compressor
相对转速/% 喘振裕度/% 母型压气机 模化压气机 变化量 80 9.60 8.83 －0.77 90 18.90 18.60 －0.30 100 13.60 19.08 ＋5.48 110 12.00 11.00 －1.00
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