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借助于某高速轴流压气机试验台,研究了45°周向总压畸变对轴流压气机转子绝对流动角的影响,初步探索了周向压力畸变引起的转子进口/出口绝对流动角变化的规律。结果表明,在45°周向总压畸变情况下,压气机转子的进口绝对流动角在周向受到影响的范围大约为90°(即畸变扰动区),转子出口的气流绝对流动角的畸变扰动区沿着周向大约为75°。气流绝对流动角在沿转动方向进入畸变扰动区时开始增加,在畸变网边缘达到正向最大值(与转动方向同为正);然后逐渐减小,在跨出畸变网的边缘得到负的最大值;随后又慢慢增加,跨出畸变扰动区。并且,随着换算质量流量的减少,转子进口绝对流动角变化不明显,而转子出口的绝对流动角则明显增加。
With a high-speed axial compressor test bench, the effect of 45 ° circumferential total pressure distortion on the absolute flow angle of the axial flow compressor rotor was studied. The change of the absolute inlet flow angle of the rotor caused by the circumferential pressure distortion law. The results show that in the circumstance of 45 ° circumferential total pressure distortion, the inlet absolute flow angle of the compressor rotor is affected in the circumferential direction by about 90 ° (ie, distorted disturbance zone) and distorted perturbation of the absolute flow angle at the rotor outlet The zone is approximately 75 ° along the circumference. The absolute flow angle of gas flow begins to increase when it enters the distorted disturbance zone along the rotation direction and reaches the positive maximum (same as the rotation direction) at the edge of the distortion network; then decreases gradually and reaches the maximum at the edge across the distortion network Value; then slowly increase, across the distortion disturbance zone. And with the reduction of mass flow rate, the absolute inlet angle of rotor inlet does not change obviously, but the absolute outlet angle of rotor outlet increases obviously.