Patent ID: 8221080

Claim:
A method for improving flow conditions on a propeller or fan of an aircraft engine, comprising: providing the propeller or fan with a hub cone and supplying same with an air inflow (A); at an air stagnation point at an upstream tip of the hub cone, conducting a part (B) of the inflowing air into an interior of the hub cone through at least one connecting line; in an area with minimum static pressure at a downstream end of the hub cone, on a circumference of the hub cone and at a velocity essentially corresponding to a velocity of the air inflow, injecting the part (B) of the air into a thick boundary layer on the hub cone in the direction of flow, thereby accelerating the boundary layer to the velocity of the air inflow and reducing its thickness; and providing the at least one connecting line with a portion of decreasing area to accelerate the air flowing through and exiting the connecting line.