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采用数值模拟的方法,对某大涵道比小型涡扇发动机的风扇部分进行建模,并分别设置等效低压区为扇形角度60°、90°、120°及150°这4种不同程度的总压畸变进口条件,研究进气道径向总压畸变进口条件下,风扇前后流场的变换规律。研究发现,风扇后流场的总压畸变指数比风扇前大,说明风扇后流场受到风扇转动作用,其不稳定度程度比风扇前大;相对于切向速度和轴向速度,径向速度畸变指数受总压畸变的影响更大;总压畸变指数在风扇前呈增长趋势,且不同径向总压畸变进口条件的变化规律十分相似,总压畸变指数在风扇后存在最大值区域。
The fan part of a large bypass ratio small turbofan engine is modeled by numerical simulation and the equivalent low pressure zone is set at four different degrees of fan angle of 60 °, 90 °, 120 ° and 150 ° Total pressure distortion inlet conditions, the inlet radial total pressure distortion inlet conditions, the fan before and after the flow field transformation. The results show that the total pressure distortion index of the flow field is larger than that of the fan, which shows that the flow field of the fan is affected by the rotation of the fan and the degree of instability is larger than that of the fan. Relative to the tangential and axial velocities, The distortion index is more affected by the total pressure distortion. The total pressure distortion index shows an increasing trend before the fan, and the variation rules of the different radial total pressure distortion inlet conditions are very similar. The total pressure distortion index exists in the maximum area after the fan.