| 摘要 |
An aircraft engine ( 10 comprising a nacelle ( 24 ), a first wall ( 32 ) around a set of fan blades ( 28 ) and a set of fan outlet guide vanes ( 48 ). The set of fan outlet guide vanes ( 48 ) comprises a plurality of stator vanes extending between a second wall ( 34 ) and a third wall ( 32 ). The nacelle ( 24 ) defines an aerodynamic shape for a fluid and the nacelle ( 24 ) has apertures ( 84,86 ) at a region of relatively low pressure. A means to bleed fluid ( 40,44,54,58,54,53,60,72 ) from a region of relatively high pressure at one or more of the first wall ( 32 ) around the set of fan blades ( 28 ), the second wall ( 34 ), the third wall ( 32 ) or the set of stator vanes and at least one duct ( 46,82 ) to connect the means to bleed fluid ( 40,44,54,58,54,53,60,73 ) from the region of relatively high pressure to the at least one aperture ( 84,86 ) in the nacelle ( 24 ) at the region of relatively low pressure. In operation the static pressure at the region of high pressure is greater than the static pressure at the region of relatively low pressure such that at least some of the boundary layer of the fluid flows through the at least one duct ( 46,82 ) to the at least one aperture ( 84,86 ) in the nacelle ( 24 ).
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