TURBINE ENGINE WITH A FLOW SPLITTER HAVING A PROFILE WITH INCLINED SERRATIONS

An aircraft turbine engine comprises an annular wall (160) for splitting a flow of air, downstream of an upstream fan (14), first stationary blades (24) for guiding a primary flow and the second stationary guidance blades (26) attached to the annular splitting wall (160), the wall being provided with at least one profiled structure for air flow having a profiled leading edge exhibiting a profile (28) with serrations exhibiting a succession of teeth (30) and troughs, such that, along the leading edge from a first location (21) to a second location (23), the teeth are individually inclined towards the second location, either towards an oblique orientation of the air flow, or in the direction of the line (240) of camber of the first blades. Alternatively, the troughs (32) are angularly interposed between two first circumferentially consecutive blades. 一种飞行器涡轮发动机，包括在上游风扇(14)的下游用于分隔气流的环形壁(160)，用于引导主流的第一固定叶片(24)以及被附接到环形分隔壁(160)上的第二固定导叶(26)，所述壁具有至少一种气流的异形结构，该异形结构具有带有轮廓的前缘，其呈现一带有锯齿的轮廓(28)，所述锯齿显示连续的齿(30)和槽，使得沿该前缘从第一位置