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A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass du

A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.

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1. A turbofan gas turbine engine comprising: a front mounting assembly attached to an annular bypass duct wall at a front axial position close to an inlet of a bypass air passage defined radially between the bypass duct wall and a core portion of the engine, the core portion being supported within t

1. A turbofan gas turbine engine comprising: a front mounting assembly attached to an annular bypass duct wall at a front axial position close to an inlet of a bypass air passage defined radially between the bypass duct wall and a core portion of the engine, the core portion being supported within the bypass duct wall by the front mounting assembly;a rear mounting assembly having a mounting apparatus affixed to the bypass duct wall at a rear axial position adjacent to an outlet of the bypass air passage, the rear mounting assembly including a plurality of rods having opposed inner and outer ends, the rods lying substantially tangential to the core portion of the engine and extending across the bypass air passage, the rods interconnecting the bypass duct wall and a mid turbine frame (MTF) of the core portion to form a load transfer path from the core portion to the bypass duct wall for normal engine operation; andwherein the bypass duct wall includes two axially spaced flanges, radially and outwardly extending from the bypass duct wall, a plurality of circumferentially spaced apart connecting brackets being attached to the bypass duct wall and positioned axially between and affixed to the two flanges, the rods being connected at the outer ends thereof to the bypass duct wall by the connecting brackets. 2. The engine as defined in claim 1 wherein at least one of the connecting brackets comprises a mounting portion with at least one mounting opening defined therein to form said mounting apparatus. 3. The engine as defined in claim 2 wherein the connecting brackets are accessible from an inside of the bypass air passage through respective openings defined in the bypass duct wall for connection with the respective rods. 4. The engine as defined in claim 2 wherein the mounting portion of the at least one connecting bracket extends radially and outwardly from the annular bypass duct wall. 5. The engine as defined in claim 1 wherein each of the rods is connected at the inner end thereof to the MTF by an adjustable connecting device in order to ensure a concentricity of the bypass duct wall and the core portion. 6. The engine as defined in claim 2 wherein the rods comprise a first group of rods extending from the outer end to the inner end thereof in substantially tangential directions to the core portion, corresponding to a first circumferential direction and a second group of rods extending from the outer end to the inner end thereof in substantially tangential directions to the core portion, corresponding to a second circumferential direction opposite to the first circumferential direction. 7. The engine as defined in claim 6 wherein each of the connecting brackets connects with one rod of the first group and one rod of the second group. 8. The engine as defined in claim 1 wherein each of the rods has an aerodynamic profile defined by side surfaces extending between leading and trailing edges with respect to the bypass air passage, the profile having a dimension between the side surfaces smaller than a dimension between the leading and trailing edges. 9. A turbofan gas turbine engine comprising: a core portion including at least first and second turbine assemblies, and a mid turbine frame (MTF) positioned axially between the first and second turbine assemblies; an annular bypass duct wall surrounding and supporting the core portion, to thereby define a bypass air passage radially between the core portion and the bypass duct for directing a bypass air flow passing therethrough;means for transferring core portion related inertia-induced loads from the MTF in a short circuit across the bypass air passage in a radial plane defined by the MTF to the bypass duct wall during normal engine operation, thereby reducing distortion of the core portion caused by the inertia-induced loads and reducing carcass bending of the core portion; andwherein the annular duct wall includes two axially spaced flanges radially and outwardly extending from the annular bypass duct wall, a plurality of circumferentially spaced connecting brackets being attached to an outer side of the bypass duct wall, the connecting brackets being axially positioned between and affixed to the two flanges. 10. The turbofan gas turbine engine as defined in claim 9 wherein the means transfers the core portion related inertia-induced loads directly to an axial location of the bypass duct wall substantially determined by a vertical rear mounting plane of the engine, the rear mounting plane being located close to an outlet of the annular bypass air passage with respect to a substantially vertical front mounting plane of the engine which is located close to an inlet of the bypass air passage. 11. The turbofan gas turbine engine as defined in claim 10 wherein the means comprises a plurality of rods having opposed inner and outer ends lying substantially tangential to the core portion and extending across the annular bypass air passage, and the outer ends of respective rods being connected to the annular bypass duct wall by means of the connecting brackets and the inner ends of the respective rods being connected to the MTF, the rods thereby forming said short circuit. 12. The turbofan gas turbine engine as defined in claim 11 wherein each of the connecting brackets is connected to two adjacent rods. 13. The turbofan gas turbine engine as defined in claim 11 wherein the means further comprises a plurality of circumferentially spaced connecting bases attached to the MTF for connecting the inner ends of the respective rods, each connecting base being connected to two adjacent rods. 14. The turbofan gas turbine engine as defined in claim 11 wherein the rods comprise a first group of rods extending from the outer ends to the inner ends thereof in substantially tangential directions to the core portion, corresponding to a first circumferential direction and a second group of rods extending from the outer ends to the inner ends thereof in substantially tangential directions to the core portion, corresponding to a second circumferential direction opposite to the first circumferential direction. 15. The turbofan gas turbine engine as defined in claim 12 wherein the connecting brackets are accessible from an inside of the bypass air passage through respective openings defined in the bypass duct wall for connection with the respective rods. 16. The turbofan gas turbine engine as defined in claim 15 wherein at least one of the connecting brackets comprises a mounting portion with at least one mounting opening defined therein, the mounting portion extending radially and outwardly from the annular bypass duct wall. 17. The turbofan gas turbine engine as defined in claim 13 wherein each of the rods is connected at the inner end thereof to the MTF by a single pin attached to one of the connecting bases.