| 摘要 |
A hub cone (20, 30, 40) is provided for an aircraft engine having a propeller (2, 32, 42) or a blower (fan) (3) enveloped by a casing (5). To reduce flow losses of the hub cone and increase efficiency of the engine, a contour of the hub cone is described by the following equation: S(x)=Rmax*{1−[(x−Lmax)/Lmax]2}1/M; where: S(x) is a shape of the cone defined along the machine axis x; Rmax is a maximum extension (26) of the cone in the radial direction; Lmax is a maximum extension (25) of the cone in the direction of the machine axis x and M is a quantity describing the shape S(x).
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