海军航空大学学报2026，Vol.41Issue(3)：441-452,462,13.DOI:10.7682/j.issn.2097-1427.2026.03.003
边界层吸入下非轴对称节距布局静子抗畸变研究
Anti-Distortion Investigation for Non-Axisymmetric Pitch Layout Stator with Boundary Layer Ingestion
摘要
Abstract
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%.关键词
边界层吸入/进气畸变/进气道风扇一体化/非轴对称节距布局/气动性能Key words
boundary layer ingestion/inlet distortion/intake-fan integrated/non-axisymmetric pitch layout/aerody-namic performance分类
航空航天引用本文复制引用
傅文广,左瑞,孙鹏,余军杨..边界层吸入下非轴对称节距布局静子抗畸变研究[J].海军航空大学学报,2026,41(3):441-452,462,13.基金项目
国家自然科学基金(U2233207) （U2233207）
大连大学优秀人才科研启动项目(2025-XRCZK-09) （2025-XRCZK-09）
