The invention relates to a blade (7) comprising: an aerodynamic profile structure (20) comprising two shell layers (22) facing each other; and-a spar (21) comprising a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the spar (21) comprising a blade root portion (24) extending outside the aerodynamic profile structure (20) and an airfoil portion (25) arranged inside the aerodynamic profile structure (20) between said two shell layers (22). Furthermore, within the blade root portion (24), the fibrous reinforcement (26) of the spar (21) comprises an interconnection region (27) and at least two non-interconnection regions (28) extending radially from the interconnection region (27) to form at least four different branches (29).
本发明涉及一种叶片(7),该叶片包括:空气动力学轮廓结构(20),该空气动力学轮廓结构包括彼此面对的两个壳层(22);以及‑翼梁(21),该翼梁包括通过三维编织获得并通过基体致密化的纤维增强件,该翼梁(21)包括延伸到空气动力学轮廓结构(20)外部的叶片根部部分(24)和被布置在空气动力学轮廓结构(20)内部、所述两个壳层(22)之间的翼型部分(25)。此外,在叶片根部部分(24)内,翼梁(21)的纤维增强件(26)包括互连区域(27)和至少两个非互连区域(28),至少两个非互连区域从互连区域(27)径向地延伸,以形成至少四个不同的分支(29)。
BLADE COMPRISING STRUCTURES MADE OF COMPOSITE MATERIAL AND
包括由复合材料制成的结构的叶片及相关的制造方法
2023-10-20
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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