| 摘要 |
An anti-icing system for a nacelle (50) of an aircraft engine (10). The nacelle (50) has an inlet lip (56) that defines a leading edge of the nacelle (50), and further has an annular-shaped cavity (58) adjacent and delimited in part by an interior surface (64) of the inlet lip (56). An anti-icing system is located within the cavity (58) and includes a manifold (62,72) with a cross-sectional shape that conforms to the interior surface (64) of the inlet lip (56). A wall (65,75) of the manifold (62,72) faces the interior surface (64) of the inlet lip (56), and air is conducted to the manifold (62,72) to cause heating of the inlet lip (56) via the manifold wall (65,75). |
