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中文摘要：
为了在压缩机的流动地上探索机翼探查试管和它的款项位置的效果，串联，并且发现机制怎么机翼探查影响压缩机串联的空气动力学的特征，这份报纸在一样的压缩机串联上执行了数字、试验性的工作。实验主要集中了于低马赫数字的案例(妈 = 0.1 ) ，并且有不同马赫数字的案例(0.1， 0.3， 0.7 ) 并且不同发生角度(-5, 0， 5 ) 被数字方法调查。没有机翼探查试管的案例作为基线，和另外的三个案例被引用，机翼探查试管在不同 chordwise 位置安装了(30% ， 50% ， 70% 弦长度) 被学习。机翼探查试管的直径是 3mm，它根据几何类似原则作为某特别机翼探查的 300% 扩大被设置。结果证明机翼探查试管根本在串联的流动能力上有否定影响调查点。分离和在压力方面上由机翼探查试管导致了的大规模 streamwise 旋涡在高马赫数字引起大多数损失。在压力方面表面的附近的流动领域上的机翼探查试管的影响是在低马赫数字的本地分离。机翼探查试管也有一清楚地在漏流动上完成。它减少漏流动的集体流动并且削弱漏旋涡的紧张，但是扩大影响区域。试管在 chordwise 位置通常是的一半被安装的盒子的全部的压力损失特别在高马赫数字比另外的盒子降低，它能甚至减少损失与基本盒子相比。
英文摘要：
To explore the effects of airfoil-probe tubes and its installment position on the flow field of the compressor cas- cade, and find out the mechanism that how the airfoil-probes affect the aerodynamic characteristics of the com- pressor cascade, this paper performed both numerical and experimcntal works on the same compressor cascade. The experiment mainly focused on the cases of low Mach number （Ma = 0.1）, and cases with different Mach numbers （0.1, 0.3, 0.7） and different incidence angles （-5, 0, 5） are investigated by the numerical method. The case without the airfoil-probe tube was referenced as the baseline, and other three cases with the airfoil-probe tubes installed in different chordwise positions O0%, 50%, 70% of the chord length） were studied. The diameter of the airfoil-probe tube is 3ram, which is configured as 300% amplification of some particular airfoil-probe ac- cording to the geometrical similarity principle. The results show that the airfoil-probe tubes have a negative in- fluenc~ on the flow capacity of the cascade at all investigation points. The separations and the large scale stream- wise vortices that induced by the airfoil-probe tube on the pressure side cause most the losses at the high Mach number. The influence of the airfoil-probe tube on the flow field in the vicinity of the pressure side surface is lo- cal separation at the low Mach number. The airfoil-probe tubes also have a clearly effect on the leakage flow. It decreases the mass flow of the leakage flow and weakens the intensity of the leakage vortex, but enlarges the in- fluence area. The total pressure loss of the case that the tube is installed at the half chordwise position is generally lower than other cases especially at the high Mach number, it can even decrease the losses compared with the ba- sic case.
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Experimental study of effects of Grooved Tip Clearances on the Flow Field in a Compressor Cascade Pa
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