초록

A mounting system for a gas turbine engine assembly includes a plurality of mounting links attached the gas turbine engine along a single plane transverse to the engine centerline for separating the loads from the core engine.

대표청구항 ▼

1. A mounting system for securing a gas turbine engine to an aircraft support structure comprising: an outer link assembly attachable to the aircraft support structure and the gas turbine engine, the outer link assembly including first and second links disposed in a first plane transverse to the cen

1. A mounting system for securing a gas turbine engine to an aircraft support structure comprising: an outer link assembly attachable to the aircraft support structure and the gas turbine engine, the outer link assembly including first and second links disposed in a first plane transverse to the centerline of the gas turbine engine;an upper thrust link disposed along the centerline, wherein the outer link assembly supports vertical loads produced by the gas turbine engine, wherein vertical loads of the gas turbine engine are only supported by structures disposed within the first plane and the upper thrust link extends from an axial forward surface through a slot defined through an outer case of the gas turbine engine within the first plane and into a pocket defined on the aircraft support structure and is secured within the slot and the pocket by at least one fastener extending through the slot, pocket and upper thrust link; andat least one lower thrust link attachable to the aircraft support structure and the gas turbine engine, the at least one lower thrust link attached to the gas turbine engine at a mount location within the first plane transverse to the centerline of the gas turbine engine, wherein the at least one lower thrust link transfers thrust loads produced by the gas turbine engine, and does not support vertical loads produced by the gas turbine engine. 2. The mounting system as recited in claim 1, wherein the first and second links of the outer link assembly are attached on one end to outer surface of the outer case of the gas turbine engine and at a second end to a fixed link secured to the support structure. 3. The mounting system as recited in claim 2, wherein one of the first and second links are pivotally secured to the fixed link for movement within the first plane transverse to the centerline of the gas turbine engine. 4. The mounting system as recited in claim 2, wherein one of the first and second links is secured to the fixed link to constrain movement within the first plane transverse to the centerline of the gas turbine engine. 5. The mounting system as recited in claim 2, wherein the first and second links are attached to the outer case at circumferentially spaced apart locations within the first plane. 6. The mounting system as recited in claim 2, wherein the upper thrust link is attached to the outer case parallel to the centerline of the gas turbine engine and on a second end to the aircraft support structure. 7. The mounting system as recited in claim 1, wherein the at least one lower thrust link comprises first and second lower thrust links securable to a front case of the gas turbine engine within the first plane. 8. The mounting system as recited in claim 7, wherein each of the first and second lower thrust links are securable to an outer perimeter of the front case at a location within the first plane on a side opposite the gas turbine engine centerline from the outer link assembly. 9. The mounting system as recited in claim 7, wherein each of the first and second lower thrust links are securable to the aircraft support structure at a location centered over the gas turbine engine centerline. 10. The mounting system as recited in claim 9, including a center thrust link attachable to the aircraft support structure at the location where the first and second lower thrust links are secured and to a position on the support structure aft of the location where the first and second lower thrust links are secured. 11. The mounting system as recited in claim 1, including a core support securable to a front case of the gas turbine engine within the first plane and including a support link attached to a core portion of the gas turbine engine spaced axially aft from the first plane. 12. The mounting system as recited in claim 11, wherein the core support is securable at a second location to an intermediate case of the gas turbine engine disposed between the front case and the support link. 13. The mounting system as recited in claim 1 wherein the outer link assembly is secured to the aircraft support structure at a location forward of the location at which the at least one lower thrust link is attached to the aircraft support structure. 14. A gas turbine engine comprising: a core engine assembly including a fan case and a front case disposed along an engine centerline;a support structure mountable to an aircraft;an outer link assembly attached to the fan case and to the support structure along a first plane transverse to the centerline, the outer link supporting vertical loads produced by the gas turbine engine transverse to the engine centerline, wherein vertical loads of the gas turbine engine are only supported by structures disposed within the first plane;an upper thrust link attached to the fan case and to the support structure along the centerline within the first plane, wherein the upper thrust link extends through a slot defined on the fan case within the first plane and into a pocket defined on the support structure and is secured within the slot and the pocket by at least one fastener extending through the slot, pocket and upper thrust link; andfirst and second lower thrust links attached to the front case within the first plane at a first end and to the support structure at a second end, wherein the first and second lower thrust links transfer thrust to the support structure, and do not support vertical loads produced by the gas turbine engine. 15. The gas turbine engine as recited in claim 14, wherein the outer link assembly includes first and second links attached to the fan case on one end and to a fixed link on a second end, the fixed link attached to the support structure and the first and second links spaced circumferentially apart from each other. 16. The gas turbine engine as recited in claim 15, wherein the first link is pivotally attached to both the fan case and the fixed link to constrain relative vertical movement between the core engine and the support structure and the second link includes two attachment points to the fixed link to constrain vertical and side movement of the core engine relative to the support structure. 17. The gas turbine engine as recited in claim 14, including a core support securable to the front case of the gas turbine engine within the first plane and including a support link attached to a core portion of the gas turbine engine spaced axially aft from the first plane, wherein the core support is securable at a second location to an intermediate case of the gas turbine engine disposed between the inner case and the support link.