| 摘要 |
<p>A gas turbine engine (10) comprising a bypass duct (22) defined radially outwardly by a nacelle (21) and radially inwardly by a core engine casing (56). The nacelle (21) comprises a thrust reverser unit (50) having at least one blocker door (76) rotatably attached to a static part (52) and slideably connected to a translating part (54). The translating part (54) is arranged to move between a stowed position and a deployed position and in the deployed position the blocker door (22) spans the bypass duct (22). In the stowed position the blocker door (76) is stowed inside the translating part (54) and does not form part of an airwash surface (29) of the bypass duct (22).</p> |
