Patent ID: 8979491
Filing Date: 2015-03-17
Classification: B64D,F01D,F02K,F05D,Y02T

Abstract:
1. A turbofan gas turbine engine comprising: a front mounting structure attached to an annular bypass duct wall at a front axial position adjacent an inlet of a bypass air passage, the bypass air passage defined by and radially between the bypass duct wall and an inner case of a core portion of the engine, the front mounting structure supporting the core portion within the bypass duct wall; a rear mounting structure having a mounting apparatus attached to the bypass duct wall at a rear axial position adjacent to an outlet of the bypass air passage, the rear mounting structure including three pairs of first and second rods each having opposed inner and outer ends, the rods extending across the bypass air passage and interconnecting the bypass duct wall and the inner case of the core portion, wherein the first rods extend from the outer end to the inner end thereof in substantially tangential directions with respect to the core portion, corresponding to a first circumferential direction, and the second rods extend from the outer end to the inner end thereof in substantially tangential directions with respect to the core portion, corresponding to a second circumferential direction opposite to the first circumferential direction; and wherein the bypass duct wall includes two axially spaced flanges, radially and outwardly extending from the bypass duct wall, three circumferentially spaced apart connecting brackets being attached to the bypass duct wall and positioned axially between and affixed to the two flanges, each pair of the rods being connected at the outer ends thereof to the bypass duct wall by one of the connecting brackets.