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A fairing for a structural strut in a gas turbine engine includes: (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 v

A fairing for a structural strut in a gas turbine engine includes: (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; and (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.

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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 an

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. 2. The fairing of claim 1 wherein a pin passes through the buckle and at least one of the tabs. 3. 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, wherein mating surfaces of the sidewalls have a non-planar shape; and(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. 4. The fairing of claim 1 wherein the nose piece and the tail piece carry mating flanges adapted to be coupled together by one or more fasteners. 5. The fairing of claim 1 wherein an aft section of the vane includes walls defining a serpentine flow path therein, the serpentine flow path in fluid communication with at least one trailing edge passage disposed at a trailing edge of the vane. 6. The fairing of claim 1 wherein the nose piece and the tail piece are cast from a metallic alloy. 7. A turbine frame assembly for a gas turbine engine, comprising: (a) a turbine frame including: (i) an outer ring;(ii) a hub;(ii) a plurality of struts extending between the hub and the outer ring; and(b) a two-piece strut fairing surrounding each of the struts, comprising: (i) an inner band;(ii) an outer band; and(iii) a hollow, airfoil-shaped vane extending between the inner and outer bands, wherein the strut 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 transverse plan, 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; and(iv) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other;(c) a slotted buckle which surrounds and clamps together pairs of the tabs. 8. The turbine frame assembly of claim 7 wherein the outer ring, the hub, and the struts are a single integral casting. 9. The turbine frame assembly of claim 7 further comprising a strut baffle pierced with impingement cooling holes disposed between each of the struts and the vane of the associated strut fairing. 10. The turbine frame assembly of claim 7 wherein a pin passes through the buckle and one of the tabs. 11. A turbine frame assembly for a gas turbine engine, comprising: (a) a turbine frame including: (i) an outer ring;(ii) a hub;(ii) a plurality of struts extending between the hub and the outer ring; and(b) a two-piece strut fairing surrounding each of the struts, comprising: (i) an inner band;(ii) an outer band; and(iii) a hollow, airfoil-shaped vane extending between the inner and outer bands, wherein the strut 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, and 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 transverse plane; and(iv) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other, wherein mating surfaces of the sidewalls have a non-planar shape. 12. The turbine frame assembly of claim 7 wherein the nose piece and the tail piece carry mating flanges adapted to be coupled together by one or more fasteners. 13. The turbine frame assembly of claim 7 wherein an aft section of the vane includes walls defining a serpentine flow path therein, the serpentine flow path in fluid communication with at least one trailing edge passage disposed at a trailing edge of the vane. 14. The turbine frame assembly of claim 7 wherein the nose piece and the tail piece are cast from a metallic alloy. 15. A turbine frame assembly for a gas turbine engine, comprising: (a) a turbine frame including: (i) an outer ring;(ii) a hub;(ii) a plurality of struts extending between the hub and the outer ring; and(b) a two-piece strut fairing surrounding each of the struts, comprising: (i) an inner band;(ii) an outer band; and(iii) a hollow, airfoil-shaped vane extending between the inner and outer bands, wherein the strut 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; and(iv) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other, wherein the strut fairings are secured to the turbine frame by spaced-apart annular forward and aft nozzle hangers which engage the outer bands of the strut fairings.