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以对转压气机为研究对象,在数值方法校验的基础上,应用全通道定常流场分析手段计算了对转压气机不同周向畸变条件下的三维流场,获取了周向总压进气畸变对该压气机性能以及流场结构的影响效应,确定了对转压气机的临界畸变角,分析了不同畸变强度对压气机性能的影响规律,探讨了周向总压畸变在对转压气机中的发展演化过程。结果表明:(a)所研究的对转压气机临界畸变角约为72°,略高于传统动-静叶排交替的压气机临界畸变角;(b)相比均匀进气工况,当畸变指数为0.24时,对转压气机失速点压比和失速裕度分别下降3%和9.6%,当畸变指数为0.5时二者分别下降8.3%和19.8%;(c)未畸变区与畸变区流体之间存在的压力梯度影响转子叶片相对来流速度。进入畸变区叶片来流相对速度减小,负荷降低,退出畸变区叶片来流相对速度增大,负荷增大;(d)上游转子使得畸变水平提高,下游转子反向旋转效应抑制了来流相对速度变化趋势,增强了气流在其叶片通道中的掺混,使得畸变水平有所下降。
Based on the numerical method verification, the three-dimensional flow field under different circumferentially distorted conditions of the compressor is calculated by means of steady-state flow field analysis of all channels. The total circumferential pressure Gas distortion on the performance of the compressor and the effect of the flow field structure to determine the critical angle of compression compressor, analyzed the different distortion strength of the impact of the performance of the compressor, discusses the total circumferential pressure distortion in the conversion of gas Machine in the evolution of the evolution process. The results show that: (a) The critical angle of deflection for the compressor is about 72 °, which is slightly higher than that of the traditional compressor-stator row. (B) Compared with the uniform inlet air condition, When the distortion index was 0.24, the pressure drop and stall margin of the compressor were decreased by 3% and 9.6%, respectively, and the values were decreased by 8.3% and 19.8% respectively when the distortion index was 0.5. (C) The undistorted region and distortion The pressure gradient existing between zone fluids affects the relative blade flow velocity. (D) upstream rotor makes the level of distortion increased, and the effect of downstream rotor reverse rotation restrains the relative flow rate from being relatively The trend of velocity variation enhances the airflow mixing in the vane channels, resulting in a decrease of the distortion level.