Patent ID: 8313293

Claim:
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; and wherein 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.