翼身融合体旋流对单级轴流压气机性能影响的数值研究

Effects of Hybrid Wing Body Swirl on Single-Stage Axial Flow Compressor Performance Using Numerical Simulation

为探究翼身融合体(Hybrid wing body,HWB)飞机发动机进口旋流对压气机性能和稳定性的影响,利用数值模拟的方法探究了单级轴流压气机在HWB旋流作用下的气动响应,获得均匀进气条件和旋流进气条件下的压气机特性线和流场分布。结果表明,HWB旋流导致压气机增压能力和效率下降,失速点流量增加,在100%,90%和80%换算转速下,压比最大降低幅度分别为0.52%,0.42%,0.38%,峰值效率分别下降了4.93%,5.74%,6.14%,喘振流量分别增加了2.43%,5.4%,2.94%。研究发现,压气机稳定工作边界由最恶劣的进气旋流区域决定,压气机失稳是HWB旋流中的反向旋流导致转子叶尖进气攻角增大、气流在叶片前缘溢流造成的。

In order to estimate the effects of swirl at the engine inlet of hybrid wing body(HWB)aircraft on performance and stability of compressor,the aerodynamic response of a single-stage axial flow compressor under the effect of HWB swirl was investigated by numerical simulation.The compressor characteristic map and flow field with HWB swirl was calculated by this method and compared with characteristic map and flow field with clean inflows.The results show that HWB swirl decreases the pressurization capacity and efficiency of the compressor,and mass flow at stall boundary increases.There is a maximum decrease of total pressure ratio and peak efficiency by 0.52%,0.42%,0.38%and 4.93%,5.74%,6.14%respectively,and mass flow at stall boundary increases by 2.43%,5.4%,2.94%with 100%,90%and 80%corrected speed.It is found that stall boundary of the compressor is determined by the most severe intake conditions.The negative swirl in the HWB swirl results in the increase of the blade tip inlet attack angle.Leading edge spillage of tip leakage flow leads to instability.