| 摘要 |
<p>The present invention relates to a secondary-air nozzle of a two-flow jet engine having separated flows including an annular cowl element (27, 127, 227) translatably mobile in an axial direction between an upstream retracted position allowing the engine to operate under direct thrust and a downstream extended position, and a grid thrust reverser (28, 128, 228) in the form of cylindrical ring sectors coaxial with said cowl element, made up of blades with a radial setting, and axially separated such as to provide radial guide passages therebetween, the cowl element opening said radial guide passages in the downstream extended position through the thrust reverser grids. The nozzle is characterised in that the radius of the ring sectors forming the grids (28, 128, 228) is not constant around the circumference of the cowl element (27, 127, 227), and in that said annular cowl element (27, 127, 227) includes an inner wall (27int, 127int, 227int) delimiting the periphery of the secondary-air stream and an outer wall (27ext, 127ext 227ext) housing the nacelle, the radius of the transverse cuts of at least one of the walls not being constant, when moving around the circumference of the cowl element, the cuts being made between the upstream edge of the cowl element and the downstream edge thereof.</p> |
