Turbine engine with a flow splitter having a profile with inclined serrations

A turbomachine for an aircraft, the turbomachine comprising:

• a general axis about which rotating parts of the turbomachine rotate, the rotating parts including blades of a front fan;
• an annular airflow dividing wall for an air flow, the annular airflow dividing wall having a leading edge and arranged downstream of the front fan, the annular airflow dividing wall separating the air flow into a primary flow and a secondary flow;
• first guide vanes for guiding the primary flow in the turbomachine, each first guide vane having a leading edge;
• second guide vanes for guiding the secondary flow in the turbomachine, each second guide vane having a leading edge, the first guide vanes for guiding the primary flow and the second guide vanes guiding the secondary flow being connected to the annular airflow dividing wall;
• and
• a serrated leading edge profile including a succession of teeth and depressions, and such that, along the leading edge, from a first location to a second location, the teeth of the serrated leading edge profile are individually inclined towards the second location, wherein:
• a) the teeth are, circumferentially around said general axis and downstream of the front fan, individually inclined towards a generally oblique orientation of the air flow with respect to said general axis, to face it generally, or
• b) on the annular airflow dividing wall where they are present, the teeth are oriented in the direction of a camber line of the first guide vanes at the leading edge thereof, or
• c) about said general axis, at least some of said depressions of the serrated leading edge profile are angularly offset with respect to the angular position of the first guide vanes, so that said at least some of the depressions are angularly interposed between two circumferentially successive first guide vanes.