Aero-engine blade and blade cavity machining and filling method

According to the aero-engine blade, the weight reduction cavities are formed in the two ends of the aero-engine blade, the lightweight requirement is met, meanwhile, the strength and rigidity of the blade are not affected, and the quality of the blade is guaranteed. The blade comprises a blade body,...

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Bibliographische Detailangaben
Hauptverfasser:	ZHOU QIFAN, CUI HUIRAN, XU JIN, XU KUNHAO, LI XICHUAN, SHI KUI, HONG SUHANG
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	BLASTING COMBINED OPERATIONS ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	According to the aero-engine blade, the weight reduction cavities are formed in the two ends of the aero-engine blade, the lightweight requirement is met, meanwhile, the strength and rigidity of the blade are not affected, and the quality of the blade is guaranteed. The blade comprises a blade body, the two ends of the blade body are respectively a blade top part and a blade root part, and the blade top part and the blade root part are respectively provided with a weight reduction cavity extending towards the position of the blade body. 本发明提供了一种航空发动机叶片，其两端设有减重空腔，满足轻量化要求，同时不影响叶片的强度和刚度，保证叶片的质量。其包括叶身本体，所述叶身本体的两端分别是叶顶部位和叶根部位，所述叶顶部位、叶根部位处分别设有向所述叶身本体位置处延伸的减重空腔。