Patent ID: 11913405
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B | IPC F

Claim 0:
1. 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 arranged downstream of the front fan and separating the air flow into a primary flow and a secondary flow;
inlet guide vanes for guiding the primary flow in the turbomachine, each inlet guide vane having an inlet guide vane leading edge;
outlet guide vanes for guiding the secondary flow in the turbomachine, each outlet guide vane having a leading edge, the inlet guide vanes for guiding the primary flow and the outlet guide vanes guiding the secondary flow being connected to the annular airflow dividing wall; and
wherein at least one of the annular airflow dividing wall, the inlet guide vanes and the outlet guide vanes comprise a profiled structure having a serrated leading edge including a succession of teeth and depressions, such that, along the serrated leading edge, from a first location to a second location, the teeth of the serrated leading edge 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 generally face the air flow, 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 inlet guide vanes at the serrated 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 inlet guide vanes, so that said at least some of the depressions are angularly interposed between two circumferentially successive inlet guide vanes, and wherein the teeth have apexes located upstream the inlet guide vane leading edge.