The invention discloses a gas turbine fan and gas compressor blade drag reduction structure based on shark gill jet flow, and relates to the technical field of gas turbine fan and gas compressor blades. The blade drag reduction structure comprises a blade and a plurality of exhaust stand columns, a concave cavity is formed in the surface of the blade root of the blade, and the exhaust stand columns are arranged in the concave cavity side by side. An airflow inlet channel is arranged between the multiple exhaust stand columns and the inner bottom wall of the concave cavity, one port of the concave cavity serves as the inlet end of the airflow inlet channel, and an airflow exhaust channel is formed between the two rows of adjacent exhaust stand columns. The blade drag reduction structure inthe invention can be used for gas turbine fan and gas compressor blades in the field of aviation, ships or power generation power devices, the wall surface speed gradient can be effectively controlled, boundary layer separation is inhibited, the blade surface friction resistance is reduced, the aerodynamic characteristics of the blade are optimized, and the working efficiency of the whole machineis improved. The airflow playing a role in drag reduction in the blade drag reduction structure is consistent with mainstream, substances such as drag reducers and additives do not need to be added, and the blade drag reduction structure is environmentally friendly and free of pollution.
本发明公开了基于鲨鱼鳃射流的燃气轮机风扇及压气机叶片减阻结构,涉及燃气轮机风扇及压气机叶片的技术领域,叶片减阻结构包括叶片和多根排气立柱,叶片的叶根部的表面设有凹腔,凹腔内并排设置有多根排气立柱,多根排气立柱与凹腔内底壁之间设有气流进气通道,凹腔的一端口为气流进气通道的入口端,相邻的两排气立柱之间形成气流排气通道。本发明的叶片减阻结构可用于航空、舰船或发电动力装置领域的燃气轮机风扇及压气机叶片,可有效控制壁面速度梯度,抑制附面层分离,减小叶表摩擦阻力,优化叶片气动特性,提高整机的工作效率,叶片减阻结构中起减阻作用的气流与主流一致,无需增加减阻剂、添加剂等物质,环境友好无污染。
Gas turbine fan and gas compressor blade drag reduction structure based on shark gill jet flow
基于鲨鱼鳃射流的燃气轮机风扇及压气机叶片减阻结构
2021-01-22
Patent
Electronic Resource
Chinese
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