| 摘要 |
<p num="1"><br/><br/> The present inventions include a boundary layer ejector fluidically <br/>connecting boundary layer bleed slots from an external surface of an aircraft <br/>to <br/>reduce aircraft/nacelle/pylon drag, reduce jet noise and decrease thrust <br/>specific <br/>fuel consumption. In one embodiment a boundary layer withdrawn through the <br/>boundary layer bleed slots is entrained with an exhaust flow of a gas turbine <br/>engine. In another embodiment a boundary layer withdrawn through the <br/>boundary layer bleed slots is entrained with a flow stream internal to the gas <br/><br/>turbine engine, such as a fan stream of a turbofan. Members can be provided <br/>near an outlet of a passageway conveying the withdrawn boundary layer air to <br/>locally reduce the pressure of the fluid in which the withdrawn boundary layer <br/>air <br/>is to be entrained. A lobed mixer can be used in some embodiments to effect <br/>mixing between the boundary layer and a primary fluid of the ejector.<br/></p> |
