| 摘要 |
A mounting assembly for attaching a ducted fan gas turbine engine that includes an intake, a propulsive fan, a fan case surrounding the fan, and a core engine. The air intake is attached to the front of the fan case such that loads acting on the air intake are transmitted to the fan case. The mounting assembly includes: a support structure extending in an axial direction of the engine and having a rearward region adapted to attach to the aircraft; and a load distribution ring coaxial with and rearward of the fan case, adapted to join to the fan case, and joined to a forward region of the support structure. The support structure and the load distribution ring are adapted such that the primary load path for the loads transmitted to the fan case by the air intake is through the load distribution ring and the support structure. |
| 主权项 |
1. A mounting assembly for attaching a ducted fan gas turbine engine to an aircraft, the engine having an air intake, a propulsive fan, a fan case surrounding the fan, and a core engine, the air intake being attached to the front of the fan case such that loads acting on the air intake are primarily transmitted to the fan case, wherein the assembly includes:
a support structure extending in an axial direction of the engine and having a rearward region which is adapted to attach to the aircraft, and a front engine mount comprising a load distribution ring that is coaxial with, and perpendicular to, the fan case and a thrust reverse unit and that is rearward of the fan case and forward of the thrust reverse unit, the load distribution ring integrally forming a single, non-disassemblable body with the fan case, and being joined to a forward region of the support structure; and wherein, in use, the support structure and the load distribution ring provide a primary load path for the loads transmitted to the fan case by the air intake, and thence to the aircraft. |
