Experimental method of varying static pressure ratio for a transonic compressor rotor cascade
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摘要:
针对跨声速压气机平面叶栅变静压比实验问题，采用改变实验叶栅模型叶片数和调节背压的方式开展跨声速压气机转子叶栅实验方法研究，并基于计算流体力学（CFD）预测的叶片表面等熵马赫数分布发展了一种来流流场马赫数标定方法，并指导L030-4压气机转子叶栅近设计点的高静压比实验。研究结果表明减小叶片数和调节背压相结合的方法成功实现压气机叶栅变静压比的实验目的，模型7个叶片时可获得较好的实验效果；基于CFD的来流流场马赫数标定方法实现了L030-4压气机叶栅近设计点高静压比实验，获得的叶栅总压损失、静压比、出口气流角和轴向密流比参数同国外风洞实验数据相比，相对偏差均小于4%，验证了标定方法的合理性。
Abstract:The study focused on addressing the experimental challenge of increasing the static pressure ratio for transonic compressor rotor cascades. To this end, various experimental methods were investigated, including altering the blade numbers of the cascade model and adjusting the back pressure in a variable density plane cascade wind tunnel. A calibration method was developed to estimate the Mach number of the flow field, by utilizing the predicted isentropic Mach number distributions of blade surfaces obtained from computational fluid dynamics (CFD). This method effectively guided the high static pressure ratio experiments conducted near the design point of the rotor cascade of the L030-4 compressor. The results demonstrated the success of the combined approach, involving the reduction of blade numbers and adjustment of back pressure in achieving the desired high static pressure ratio conditions with seven blades. Furthermore, the Mach number calibration method based on CFD facilitated the realization of high static pressure ratio experiments near the design point of the L030-4 compressor cascade. The obtained parameters, including total pressure loss, static pressure ratio, exit flow angle, and axial density velocity ratio of the cascade, were compared with the experimental data from foreign wind tunnel experiments. The relative deviations were all below 4%, validating the rationality of the calibration method.
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Key words:
- compressor /
- transonic /
- supersonic /
- rotor cascade /
- static pressure ratio
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图 1 L030-4跨声速压气机转子叶型及主要流场特征
Figure 1. L030-4 transonic compressor rotor profile and flow filed characteristics
图 4 MAP程序预测ARL-SL19超声速叶栅流场（Ma1=1.58, π=2.41）
Figure 4. Supersonic flow field of ARL-SL19 cascade predicted by MAP （Ma1=1.58, π=2.41）
图 5 叶片表面等熵马赫数分布图（Ma1=0.82）
Figure 5. Blade surface isentropic Mach number distributions （Ma1=0.82）
图 6 CARDC风洞双栅距尾迹参数分布图（Ma1=0.82）
Figure 6. Wake parameter distributions of CARDC wind tunnel among two pitches （Ma1=0.82）
图 7 不同叶片数时叶片表面等熵马赫数分布
Figure 7. Blade surface isentropic Mach number distributions with different blade numbers
图 8 不同叶片数时实验与CFD预测马赫数云图分布
Figure 8. Experimental schlieren pictures and CFD predicted Mach number contours with different blade numbers
图 9 近设计点双栅距叶栅尾迹参数分布（Ma1=1.1, π=1.48）
Figure 9. Cascade wake parameter distributions among two pitches on near design condition （Ma1=1.1, π=1.48）
图 10 近设计点叶片表面等熵马赫数（Ma1=1.1）
Figure 10. Blade surface isentropic Mach number distributions on near design condition （Ma1=1.1）
图 11 近设计点实验纹影图与MAP预测马赫数云图
Figure 11. Experimental schlieren picture and MAP predicted Mach number contour on near design condition
表 1 叶栅气动参数分布表（Ma1=0.82）
Table 1. Aerodynamic parameters of experimental cascade （Ma1=0.82）
数据
来源总压损失
ωt静压比
π出口
气流角β2/（°）出口
马赫数Ma2CARDC 0.0354 1.21 45.76 0.586 DLR 0.0342 1.25 45.15 MAP 0.0324 1.22 45.05 0.583 
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表 2 实验与CFD参数对比表
Table 2. Parameter comparisons between experiments and CFD
参数 9片叶片 7片叶片 5片叶片 实验控制马赫数Ma 1.1 1.1 1.1 实验总压损失ωt 0.143 0.111 0.198 实验静压比π 1.40 1.38 1.34 实验轴向密流比Av 1.04 1.1 1.0 CFD计算马赫数Ma 1.05 1.20 1.29 CFD总压损失ωt 0.12 0.112 0.189 CFD静压比π 1.34 1.65 1.72 CFD轴向密流比Av 1.05 1.1 1.0 实验静压比修正值π 1.32 1.58 1.69
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表 3 近设计工况参数对比表
Table 3. Parameter comparisons on near design condition
参数 CARDC DLR MAP 进口马赫数Ma1 1.1 1.1 1.1 总压损失ωt 0.088 0.085 0.068 静压比π 1.48 1.52 1.54 出口气流角β2/（°） 46.2 45.5 43.6 轴向密流比Av 1.16 1.15 1.15
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