Patent ID: 8152451
Filing Date: 2012-04-10
Classification: F01D,F05D

Abstract:
1. A fairing for a structural strut in a gas turbine engine, comprising: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece, wherein the vane is defined by a pair of spaced-apart sidewalls extending between a leading edge and a trailing edge each of the sidewalls being split into forward and aft portions by the generally transverse plane, and wherein each of the sidewall portions carries a radially-inwardly extending tab, the tabs positioned such that pairs of the tabs lie adjacent to each other when the nose piece and tail piece are in an assembled condition; (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other; and (f) a slotted buckle which surrounds and clamps together pairs of the tabs.