초록 ▼

A mounting system and method capable of reducing backbone deflection in a high-bypass turbofan engine. The system includes a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected t

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

대표청구항 ▼

1. A system for mounting an engine to an engine support structure of an aircraft, the engine being a turbomachine having an inlet diameter at an inlet thereof, the system comprising a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to

1. A system for mounting an engine to an engine support structure of an aircraft, the engine being a turbomachine having an inlet diameter at an inlet thereof, the system comprising a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to the engine support structure, the first and second links being configured to define a focal point thereof at a location that is a distance of not more than 15% of the inlet diameter from a centerline of the engine and aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver, the location of the focal point causing a moment of a thrust load of the engine and a moment of the inlet load to oppose each other and thereby reduce backbone bending of the engine during the climb maneuver. 2. The system according to claim 1, wherein the focal point is located below the centerline of the engine and within a fan inlet assembly of the engine that defines the inlet of the engine and the inlet diameter thereof. 3. The system according to claim 1, wherein the first link is pivotally coupled to the rigid structure above the second link and adapted to be pivotally connected to the engine support structure of the aircraft the second link. 4. The system according to claim 3, wherein the second link is a thrust link, the linkage mechanism further comprising a third link that is aligned with the thrust link, is pivotally coupled to the rigid structure below the first link, and is adapted to be pivotally connected to the engine support structure below the first link. 5. The system according to claim 1, wherein the engine is a turbofan engine, and the system further comprises means for coupling the rigid structure to a fan case of the turbofan engine. 6. The system according to claim 5, further comprising means for coupling the second link to a core engine of the turbofan engine. 7. The system according to claim 5, further comprising means for coupling the core engine to the engine support structure of the aircraft. 8. The system according to claim 7, wherein the coupling means supports a portion of the weight of the turbofan engine. 9. The system according to claim 8, wherein the coupling means is not subjected to a load greater than the portion of the weight of the turbofan engine during the climb maneuver. 10. The system according to claim 1, wherein the rigid structure has a downwardly-tapering exterior shape. 11. The system according to claim 1, wherein the rigid structure has a hexagonal cross-section configured to promote rigidity of the rigid structure. 12. The system according to claim 1, wherein the system is mounted to the engine and to the engine support structure of the aircraft, the focal point of the first and second links is located below the centerline of the engine and aft of the vector of the inlet load to which the engine is subjected when the aircraft is in the climb maneuver so that the moments of the thrust and inlet loads oppose each other. 13. The system according to claim 12, wherein the engine support structure of the aircraft is mounted to a wing of the aircraft. 14. The system according to claim 13, wherein the engine is a turbofan engine comprising a nacelle and a core engine, and the focal point is located at a fan inlet of the nacelle. 15. The system according to claim 14, wherein the first link is pivotally coupled to the rigid structure above the second link and pivotally connected to the engine support structure of the aircraft above the second link, the second link is a thrust link that is coupled to the core engine of the turbofan engine, and the linkage mechanism further comprises a third link that is aligned with the thrust link, is pivotally coupled to the rigid structure below the first link, and is pivotally connected to the engine support structure below the first link. 16. The system according to claim 14, further comprising means for coupling the rigid structure to a fan case of the turbofan engine. 17. The system according to claim 14, further comprising means for directly coupling the core engine to the engine support structure of the aircraft. 18. A method of mounting an engine to a engine support structure of an aircraft, the engine being a turbomachine having an inlet diameter at an inlet thereof, the method using a system comprising a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to the engine support structure, the method comprising coupling the system to the engine and to the engine support structure of the aircraft so that the first and second links are pivotally connected to the rigid structure, the first link is pivotally connected to the engine support structure of the aircraft, the second link is pivotally connected to the engine, and the first and second links to define a focal point thereof at a location that is a distance of not more than 15% of the inlet diameter from a centerline of the engine and aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver, the location of the focal point causing a moment of a thrust load of the engine and a moment of the inlet load to oppose each other and thereby reduce backbone bending of the engine during the climb maneuver. 19. The method according to claim 18, further comprising providing a third link that is aligned with the second link, is pivotally coupled to the rigid structure below the first link, and is pivotally connected to the engine support structure below the first link. 20. The method according to claim 18, wherein the engine is a turbofan engine and the method further comprises: coupling the rigid structure to a fan case of the turbofan engine;coupling the second link to a core engine of the turbofan engine; anddirectly coupling the core engine to the engine support structure of the aircraft.