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为了研究现代高性能战斗机更为曲折复杂的进气道所产生的旋流畸变对于压气机性能的影响,引入更为全面统一的旋流畸变评价指标,对旋流畸变进行量化和分类,并采用CFD技术对整体涡旋流畸变下轴流压气机的流场进行了数值计算,得到了相应的特性图。结果表明,正向整体涡旋流使压气机相应工作点的流量和压比减小,稳定裕度增大;反向整体涡旋流使相应工作点的流量和压比增大,稳定裕度减小,且旋流强度越大,变化程度越大。以旋流强度等于30°为例,遭遇正向整体涡时流量和压比的最大降幅分别为24.38%和0.28%,遭遇负向整体涡时流量和压比的最大增幅分别为15.90%和0.26%,在相同畸变强度下,正向整体涡对于压气机性能的影响程度更大。
In order to study the influence of the cyclone distortion caused by the more tortuous inlets of the modern high-performance fighter jet on the performance of the compressor, a more comprehensive and uniform evaluation index of the cyclone distortion is introduced to quantify and classify the cyclone distortion, The CFD technique is used to calculate the flow field of the axial flow compressor under the general eddy current distortion, and the corresponding characteristic diagram is obtained. The results show that the positive overall swirling flow decreases the flow rate and pressure ratio at the corresponding working point of the compressor and increases the stability margin. The reverse integral swirling flow increases the flow rate and pressure ratio at the corresponding working point. The stability margin Decrease, and the greater the swirling intensity, the greater the degree of change. Taking the swirling intensity equal to 30 ° as an example, the maximum decreases of flow and pressure ratio in the case of positive whole vortex are respectively 24.38% and 0.28%, and the largest increases of flow and pressure ratio in negative overall vortex flow are 15.90% and 0.26 %, The effect of forward integral eddy on compressor performance is greater under the same distortion strength.