The invention belongs to the technical field of drag reduction surface structure design, and particularly relates to a micro-nano nested groove surface drag reduction structure based on vortex drive design. A two-stage unit group with the size smaller than that of each unit is added to the inner surface of the unit of a single-stage periodic groove structure, the two-stage unit groups are nested layers, and the nested layers are in a micro-nano scale. The micro-nano nested groove surface drag reduction structure is adopted to improve the drag reduction performance of a traditional groove surface, the structure can be applied to the design of aircraft wings or engine blades, and the friction resistance of the aircraft wings or the engine blades is reduced.

    本发明属于减阻表面结构设计技术领域,具体为一种基于涡驱动设计的微纳米尺度嵌套沟槽表面减阻结构。其在单级周期性沟槽结构的每个单元内部表面加入尺寸小于该单元的二级单元群,这种二级单元群即是嵌套层,嵌套层的尺度为微纳米尺度。本发明采用微纳米尺度嵌套沟槽表面减阻结构提升传统沟槽表面的减阻性能,该结构可以应用于飞机机翼或发动机叶片的设计之中,降低其摩擦阻力。


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    Title :

    Micro-nano nested groove surface drag reduction structure based on vortex drive design


    Additional title:

    一种基于涡驱动设计的微纳米尺度嵌套沟槽表面减阻结构


    Contributors:
    SUN GANG (author) / WANG LIYUE (author) / WANG CONG (author) / WANG SHUYUE (author) / YOU BO (author)

    Publication date :

    2021-03-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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