FIELD: non-displacement compressors and pumps.
SUBSTANCE: present invention relates to a fan, in particular for a small-size turbomachine, such as a turbojet, wherein the relative diameter of the hub of said fan is equal to ratio of the diameter of the inner limit of incoming air stream (26) at the radially inner ends of the leading edges of fan blades (10), divided by the diameter of the circle on which the outer ends of the fan blades are located, having value between 0.20 and 0.265.
EFFECT: reduced dimensions of the fan disk with reliable transmission of torque.
19 cl, 11 dwg
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