| 摘要 |
A mounting system (50) and method capable of reducing backbone deflection in a high-bypass turbofan engine (10). The system (50) includes a rigid structure (54) and a linkage mechanism having at least first and second links (62, 64, 66) that are each pivotally (68, 70, 72) connected to the rigid structure (54) and adapted to be pivotally connected to an engine support structure of the aircraft. The first and second links (62, 64) are configured to define a focal point (Pf) thereof at a location that is a distance from a centerline (40) of the engine (10) of not more than 15% of an inlet diameter at an inlet of the engine (10), and is located aft of a vector of an inlet load to which the engine (10) is subjected when the aircraft is in a climb maneuver. The location of the focal point (Pf) is such that a moment of a thrust load (Ft) of the engine (10) and a moment of the inlet load (FI) oppose each other, thereby reducing backbone bending of the engine (10) during the climb maneuver. |
