| 摘要 |
<p>A gas turbine engine (1) comprising a fan nacelle (2) surrounding a core fairing (3) to define an annular bypass duct (4) there-between for discharging fan air and
one or more bifurcator members (5a, 5b, 5c, 5d, 5e, 5f, 5g, 5h, 11 a) positioned inside the bypass duct which cause the air flow through the bypass duct to bifurcate around the bifurcator members prior to exiting the bypass duct,wherein the, or each, bifurcator member spans locations in the duct and, when viewed along the axis of the duct, appears as an elongate 2-dimensional projected shape (6a, 6b, 6c, 6d) which extends in its long direction between said locations and varies in width along its length, wherein the projected shape (6b) has:
a first constant width section (7) extending from one of said locations to a transition position (8) proximate to the other of said locations, and
a second, shorter section (9) extending from said transition position to the other of said locations, the second section increasing in width to a maximum width at the other of said locations and forming smooth, outwardly concave profiles on both sides of the second section..</p> |
