Method for improving the flow conditions of a propeller or fan of an airplane engine and nose cone constructed according to the method

摘要

A portion (B) of air inflow to air stagnation point at the tip (8a) of hub cone (8) of a propeller or a fan is conducted into interior of hub cone through air inlet openings (9) and air outlet openings (10). The portion of airflow is injected to thick boundary layer on the hub cone in specific flow direction on the circumference of the hub cone at velocity corresponding to velocity of the air inflow in an area with minimum static pressure at the downstream end of the hub cone so as to accelerate the boundary layer. An independent claim is included for hub cone for propeller or fan of aircraft engine.