Experimental research of variable solidity tandem cascade performance
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摘要: 对具有大小2种稠度后排叶片的高亚声速串列叶栅进行了试验研究，其中，大稠度叶栅后排叶片稠度为小稠度叶栅的2倍，其物理位置分为前排叶片尾迹区和主流区2种，小稠度叶栅只具有尾迹区的后排叶片。研究表明：对于大稠度叶栅而言，位于尾迹区附近的后排叶片较位于主流区的负荷更高、做功能力更强；本研究的小稠度叶栅性能优于大稠度叶栅，但大稠度的叶栅出口流场相对更为均匀。此类叶栅的设计应对后排叶片的物理位置和型面进行优化，并权衡其使用环境和目的。Abstract: Experimental research is carried out on a high subsonic tandem cascade, the rear blades of which have two different solidities. For test cascade A, the number of the rear blades is double the amount of B, and there are two locations of rear blades in cascade A, which is following the wake or the mainstream of the front, while the test cascade B only have the rear blades located at the wake of the front. It can be seen from the results that for test cascade A, the load and work capacity of the blades are higher when the rear blades are located near the wake than the mainstream. The larger solidity of rear blades would lead to a blockage in the channel. But cascade B have more uniform outlet flow. Optimizations design should be done about the locations of rear blades and profiles according to the use environment and purpose.
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Key words:
- tandem cascaded /
- variable solidity /
- loss /
- blockage /
- uniform
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图 3 叶型简图(左侧为叶栅A，右侧为叶栅B)
Figure 3. Tandem cascade profile(the left is A and the right is B)
图 4 Ma1=0.80总压恢复系数周向分布
Figure 4. Circumferential distribution of total pressure recovery coefficient at Ma1=0.80
图 5 Ma1=0.95总压恢复系数周向分布
Figure 5. Circumferential distribution of total pressure recovery coefficient at Ma1=0.95
图 7 设计角不同位置叶片表面马赫数对比(Ma1=0.80, β1=28.8°)
Figure 7. Isentropic Mach number distribution comparison at Ma1=0.80, β1=28.8°
图 8 正攻角不同位置叶片表面马赫数对比(Ma1=0.95, β1=25.0°)
Figure 8. Isentropic Mach number distribution comparison at Ma1=0.95, β1=25.0°
图 9 负攻角不同位置叶片表面马赫数对比(Ma1=0.75, β1=30.0°)
Figure 9. Isentropic Mach number distribution comparison at Ma1=0.75, β1=30.0°
图 11 Ma1=0.80叶栅B总压恢复系数分布
Figure 11. Distribution of total pressure recovery coefficient at Ma1=0.80(cascade B)
图 12 Ma1=0.95叶栅B总压恢复系数分布
Figure 12. Distribution of total pressure recovery coefficient at Ma1=0.95(cascade B)
图 13 Ma1=0.80叶栅B叶片表面等熵马赫数分布
Figure 13. Isentropic Mach number distribution variation with inlet angle at Ma1=0.80(cascade B)
图 14 设计角下表面马赫数对比(Ma1=0.80, β1=28.8°)
Figure 14. Isentropic Mach number distribution comparison at Ma1=0.80, β1=28.8°
图 15 负攻角下表面马赫数对比(Ma1=0.75, β1=30.0°)
Figure 15. Isentropic Mach number distribution comparison at Ma1=0.75, β1=30.0°
图 16 正攻角下表面马赫数对比(Ma1=0.95, β1=26.0°)
Figure 16. Isentropic Mach number distribution comparison at Ma1=0.95, β1=26.0°
图 17 总压损失系数随进口气流角变化
Figure 17. Total pressure loss coefficient variation with inlet angle
图 18 总压损失系数随进口马赫数变化
Figure 18. Total pressure loss coefficient variation with inlet Mach number
图 19 总压恢复系数随进口气流角变化
Figure 19. Total pressure recovery coefficient variation with inlet angle
图 20 总压恢复系数随进口马赫数变化
Figure 20. Total pressure recovery coefficient variation with inlet Mach number
图 23 出口马赫数与其平均值之差的平方分布
Figure 23. The difference square distribution of outlet Mach number and its average value in a pitch
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