| 摘要 |
<p>An aircraft engine, preferably of the turbofan gas turbine engine type, comprises a nacelle 24, and a stator structure having a surface, within a relatively high pressure region, from which the boundary layer is bled via at least one duct 46, 82 to at least one aperture 84, 86 in the nacelle 24 at a region of relatively low pressure, so as the pressure differential instigates the bleeding. The at least one aperture preferably is a nozzle directing the bled fluid, preferably for the purpose of providing additional thrust. The stator structure preferably comprises a first wall 32 around a set of rotor blades 28, possibly fan blades, and at least one set of stator vanes 48, possibly fan outlet vanes, 48 or core inlet vanes 62. The means to bleed fluid from the stator structure may comprise a porous member, which may be a metal or a composite.</p> |
