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The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape,

The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall.

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1. A turbofan gas turbine engine comprising: a front mounting structure attached to an annular bypass duct wall at a front axial position of a bypass air passage defined radially between the bypass duct wall and a core portion of the engine, the front mounting structure supporting the core portion w

1. A turbofan gas turbine engine comprising: a front mounting structure attached to an annular bypass duct wall at a front axial position of a bypass air passage defined radially between the bypass duct wall and a core portion of the engine, the front mounting structure supporting the core portion within the bypass duct wall; anda rear mounting structure attached to the bypass duct wall at a rear axial position of the bypass air passage, the rear mounting structure including a plurality of link rods extending across the bypass air passage and interconnecting the bypass duct wall and the core portion, each link rod having a hot end fitting, a cold end, and an elongated and tubular strut body of composite material secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing connected to the core portion, and the cold end housing a spherical bearing connected to the bypass duct wall, wherein the composite material has a higher percentage of fibers oriented parallel to the length of the strut, and a lower percentage of fibers oriented transversally to the length of the strut, the lower percentage of transversal fibers being adapted to provide a transversal coefficient of thermal expansion comparable to a coefficient of thermal expansion of the metal. 2. The turbofan gas turbine engine of claim 1 wherein the hot end fitting has a male portion extending toward the cold end, and the strut body has a female end portion snugly receiving the male portion. 3. The turbofan gas turbine engine of claim 2 wherein the male portion has at least one annular bulge spaced from the hot end fitting spherical bearing by a narrower neck section, and the female end portion snugly surrounds at least a portion of both the annular bulge and the narrower neck section. 4. The turbofan gas turbine engine of claim 3 wherein the male portion has at least a second narrower neck section snugly surrounded by the female end portion and spaced from the spherical bearing of the hot end fitting by the annular bulge, wherein the annular bulge allows the transmission of both compressive and tension loads between the strut body and the hot end fitting. 5. The turbofan gas turbine engine of claim 2 wherein the hot end fitting has an elongated cooling portion extending between the spherical bearing of the hot end fitting and the male portion, the elongated cooling portion extending into the bypass air passage. 6. The turbofan gas turbine engine of claim 2 wherein the hot end fitting has at least one bore extending therein from an opening located on an end of the male portion located inside the strut body. 7. The turbofan gas turbine engine of claim 1 wherein the metal body of the hot end fitting is made of titanium or a titanium-based alloy. 8. The turbofan gas turbine engine of claim 1 wherein the composite material has carbon/epoxy composite material. 9. The turbofan gas turbine engine of claim 1 wherein the strut body has an ellipsoid-like aerodynamic elongated cross-sectional contour shape with a long axis perpendicular to a short axis in a cross-sectional plane, the long axis being oriented parallel to a direction of air flow in the air passage. 10. The turbofan gas turbine engine of claim 1 wherein the cold end has a male portion extending toward the hot end fitting, and the strut body has a female cold end portion snugly receiving the male portion of the cold end. 11. The turbofan gas turbine engine of claim 10 wherein the female cold end portion has an inner wall extending straight, parallel to a length of the strut body, and forming an engagement path for the male portion of the cold end, and the cold end male portion has a straight neck portion mating with the inner wall for sliding engagement therewith, the straight neck portion being adhered to the inner wall. 12. The turbofan gas turbine engine of claim 11 wherein the cold end includes a cold end fitting having a metal body. 13. The turbofan gas turbine engine of claim 1 wherein the cold end is a composite material extension to the strut body. 14. A mounting structure for supporting an engine core portion within an annular bypass duct wall of a turbofan gas turbine engine at an axial position of a bypass air passage defined radially between the bypass duct wall and the core portion, the mounting structure comprising a plurality of link rods extending across the bypass air passage when interconnecting the bypass duct wall and the core portion, each link rod having a hot end fitting, a cold end, and an elongated and tubular strut body of composite material secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing connected to the core portion, and the cold end housing a spherical bearing connected to the bypass duct wall, wherein the composite material has a higher percentage of fibers oriented parallel to the length of the strut, and a lower percentage of fibers oriented transversally to the length of the strut, the lower percentage of transversal fibers being adapted to provide a transversal coefficient of the thermal expansion comparable to a coefficient of thermal expansion of the metal. 15. A link rod for a turbofan gas turbine engine having a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall, wherein the composite material has a higher percentage of fibers oriented parallel to the length of the strut, and a lower percentage of fibers oriented transversally to the length of the strut, the lower percentage of transversal fibers being adapted to provide a transversal coefficient of thermal expansion comparable to a coefficient of thermal expansion of the metal. 16. The link rod of claim 15 having a boot snugly surrounding a portion of the cold end, and having a gap-covering extension protruding transversally around the link rod and having an annular flat surface abuttable against the bypass duct wall. 17. The link rod of claim 15 having a boot snugly surrounding a portion of the cold end, the boot having a male member snugly receivable in an aperture of the annular bypass duct wall to cooperate therewith in maintaining the orientation of the strut body relative to airflow in the bypass air passage. 18. The turbofan gas turbine engine of claim 15 wherein the hot end fitting has a male portion extending toward the cold end, and the strut body has a female end portion snugly receiving the male portion, the male portion having at least one annular bulge spaced from the hot end fitting spherical bearing by a narrower neck section, and the female end portion snugly surrounds at least a portion of both the annular bulge and the narrower neck section. 19. The turbofan gas turbine engine of claim 18 the male portion has at least a second narrower neck section snugly surrounded by the female end portion and spaced from the hot end fitting spherical bearing by the annular bulge, wherein the annular bulge allows the transmission of both compressive and tension loads between the strut body and the hot end fitting.