边界层吸入下非轴对称节距布局静子抗畸变研究OA

The intake distortion problem widely exists in blended-wing-body aircraft,which will seriously jeopardize the aircraft's operational safety.In order to improve the anti-distortion ability and aerodynamic performance of bound-ary layer ingestion fan,a non-axisymmetric pitch layout stator(NAS)is designed,taking the intake and single-stage fan as the research object.The 3D unsteady numerical simulation study reveals that the non-axisymmetric pitch stator can reduce the diffusion factor and loss of the stator vane root region in the distortion-influenced region.The total pressure loss coefficient in the stator domain is relatively reduced by 7.5%,and the fan efficiency increased by 0.46%without re-ducing the total pressure ratio.However,NAS increases the contact area between the airflow and the stator vanes,which causes additional friction loss and leads to the increase of the loss under the blocked condition.Under the near-stall con-dition,NAS inhibits the radial development of low-energy flow on the suction surface of the stator and reduces the flow separation range,the total pressure loss coefficient of the stator is relatively reduced by 1.1%,the fan efficiency and the total pressure ratio are increased by 0.17%and 0.05%,respectively.The NAS fan is able to work at a lower flow rate,the fan stability margin is relatively increased by 19.4%.