Aviation turbine guide vane preform and preparation method thereof

• Main Authors: DONG FANG, QIAN KUN, QIU HAIPENG, ZHANG DIANTANG, XIE WEIJIE, ZONG SHENG
• Format: Patent
• Language: Chinese; English
• Published: 21.12.2021
• Subjects: BLASTING; ENGINE PLANTS IN GENERAL; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR; FLEXIBLE SHEET MATERIAL NOT OTHERWISE PROVIDED FOR; HEATING; LAUNDERING; LIGHTING; LOOMS; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; METHODS OF WEAVING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; TEXTILES; TREATMENT OF TEXTILES OR THE LIKE; TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS,FABRICS, FEATHERS, OR FIBROUS GOODS MADE FROM SUCH MATERIALS; WALL, FLOOR OR LIKE COVERING MATERIALS, e.g. LINOLEUM,OILCLOTH, ARTIFICIAL LEATHER, ROOFING FELT, CONSISTING OF AFIBROUS WEB COATED WITH A LAYER OF MACROMOLECULARMATERIAL; WEAPONS; WEAVING; WOVEN FABRICS

The invention discloses an aviation turbine guide vane preform and a preparation method thereof, and belongs to the field of functional materials. According to the aviation turbine guide vane preform and the preparation method thereof, a blade body prefabricated body of the turbine blade is prepared by adopting an integral weaving method, yarns are reserved on the upper edge and the lower edge of the blade body, and then the upper edge reserved yarns and the lower edge reserved yarns are introduced into an upper edge plate and a lower edge plate to form the turbine blade prefabricated body of an integral structure, so that yarn arrangement and fine structure regulation and control are realized, the problems of weak interlayer performance, damage after machining and poor positioning precision are solved, and the structure/function integration requirement is met. Weaving of the turbine guide vane prefabricated body small in size and complex in shape is achieved; the problems of poor interlayer strength and many