| 摘要 |
<p>A gas turbine engine strut fairing (10, 110) includes: inner and outer bands; a hollow, airfoil-shaped vane (12, 112) extending between the bands; wherein the fairing (10, 110) is split along a transverse plane passing through the bands and vane (12, 112), defining a nose piece (24, 124) and a tail piece (26, 126); wherein the vane (12, 112) is defined by a spaced-apart sidewalls (18) extending between a leading edge and a trailing edge, each the sidewalls (18) being split into forward and aft portions by the transverse plane; wherein each of the sidewall portions carries a radially-inwardly extending post (32, 34, 132, 134), having a mating face (40, 46, 140, 146), the posts (32, 34, 132, 134) positioned with pairs of the posts (32, 34, 132, 134) lie adjacent to each other, with their respective mating faces (40, 46, 140, 146) contacting each other; and a pair of slotted buckles (38, 138), each buckle (38, 138) surrounding and clamping together a pair of the posts (32, 34, 132, 134); wherein a mechanical element (76, 143) engages the mating faces (40, 46, 140, 146) of the paired posts (32, 34, 132, 134), so as to block relative radial movement of the paired posts (32, 34, 132, 134).</p> |
