A multi-surface blocker door system for a thrust reverser of an aircraft is provided. The system may comprise one or more first blocker doors coupled to the inner fixed structure. The first blocker doors may be configured to obstruct a fan duct area adjacent the engine. The system may also comprise
A multi-surface blocker door system for a thrust reverser of an aircraft is provided. The system may comprise one or more first blocker doors coupled to the inner fixed structure. The first blocker doors may be configured to obstruct a fan duct area adjacent the engine. The system may also comprise one or more second blocker doors coupled to a translating sleeve. The second blocker doors may be configured to obstruct a fan duct area adjacent to an inlet of the nacelle.
대표청구항▼
1. A multi-surface blocker door system, comprising: a first blocker door rotatably coupled to an inner fixed surface about a forward end of the first blocker door, wherein the first blocker door is configured to rotate about the forward end of the first blocker door such that an aft end of the first
1. A multi-surface blocker door system, comprising: a first blocker door rotatably coupled to an inner fixed surface about a forward end of the first blocker door, wherein the first blocker door is configured to rotate about the forward end of the first blocker door such that an aft end of the first blocker door rotates radially outward, with respect to a longitudinal axis of the inner fixed surface, and wherein, when deployed, the first blocker door is configured to block a first portion of bypass air in a fan air duct, the first blocker door operatively coupled to a first drive mechanism, wherein the first drive mechanism is configured to deploy the first blocker door, wherein the first blocker door is located forward of an aft end of a translating sleeve; anda second blocker door rotatably coupled to the translating sleeve about a forward end of the second blocker door, wherein the second blocker door is configured to rotate about the forward end of the second blocker door such that an aft end of the second blocker door rotates radially inward, with respect to the longitudinal axis of the inner fixed surface, and wherein, when deployed, the second blocker door is configured to block a second portion of bypass air in the fan air duct, the second blocker door operatively coupled to a second drive mechanism, wherein the second drive mechanism is configured to deploy the second blocker door;wherein when the first blocker door and the second blocker door are deployed, a portion of the fan air duct defined radially, with respect to the longitudinal axis of the inner fixed surface, between the aft end of the first blocker door and the aft end of the second blocker door is unobstructed by the first blocker door and the second blocker door. 2. The multi-surface blocker door system of claim 1, wherein the first blocker door is configured to obstruct a fan duct area adjacent an engine installed within a nacelle, and wherein the fan duct area is defined by the inner fixed surface and the translating sleeve. 3. The multi-surface blocker door system of claim 1, wherein the second blocker door is configured to obstruct a fan duct area adjacent to an outer diameter of a nacelle. 4. The multi-surface blocker door system claim 1, wherein the first blocker door is one of a plurality of first blocker doors. 5. The multi-surface blocker door system claim 1, wherein the second blocker door is one of a plurality of second blocker doors. 6. The multi-surface blocker door system claim 1, wherein the first drive mechanism is at least one of a first link-less deployment mechanism and a first linear actuator and wherein the second drive mechanism is at least one of a second link-less deployment mechanism and a second linear actuator. 7. A thrust reverser system, comprising: a translating sleeve;an inner fixed structure, wherein the translating sleeve and the inner fixed structure define a fan air duct;a first blocker door located within the fan air duct, wherein a forward end of the first blocker door is rotatably coupled to the inner fixed structure, wherein the first blocker door is configured to rotate about the forward end of the first blocker door such that an aft end of the first blocker door rotates radially outward, with respect to a longitudinal axis of the inner fixed structure, and wherein, when deployed, the first blocker door is configured to block a first portion of bypass air in the fan air duct; anda second blocker door located within the fan air duct, wherein a forward end of the second blocker door is rotatably coupled to the translating sleeve, wherein the second blocker door is configured to rotate about the forward end of the second blocker door such that an aft end of the second blocker door rotates radially inward, with respect to the longitudinal axis of the inner fixed structure, and wherein, when deployed, the second blocker door is configured to block a second portion of bypass air in the fan air duct;wherein when the first blocker door and the second blocker door are deployed, a portion of the fan air duct defined radially, with respect to the longitudinal axis of the inner fixed structure, between the aft end of the first blocker door and the aft end of the second blocker door is unobstructed by the first blocker door and the second blocker door. 8. The thrust reverser system of claim 7, wherein a drive mechanism is located radially inward of the first blocker door and is configured to deploy the first blocker door. 9. The thrust reverser system of claim 7, wherein a drive mechanism is located radially outward of the second blocker door and is configured to deploy the second blocker door. 10. The thrust reverser system of claim 7, wherein the inner fixed structure is coupled to a plurality of first blocker doors. 11. The thrust reverser system of claim 10, wherein the translating sleeve is coupled to a plurality of second blocker doors. 12. The thrust reverser system of claim 7, wherein the first blocker door is configured to obstruct an area adjacent to the inner fixed structure. 13. The thrust reverser system of claim 12, wherein the second blocker door is configured to obstruct an area adjacent to the translating sleeve. 14. The thrust reverser system of claim 7, wherein the thrust reverser system is operatively installed in an aircraft nacelle. 15. The thrust reverser system of claim 7, wherein the first blocker door and the second blocker door are configured to define a flow area for area match to an engine mass flow requirement for the thrust reverser system. 16. An aircraft nacelle, comprising: a translating sleeve;an inner fixed structure defining a fan air duct between the inner fixed structure and the translating sleeve;a plurality of first blocker doors located within the fan air duct, wherein a forward end of each first blocker door of the plurality of first blocker doors is rotatably coupled to the inner fixed structure, wherein each first blocker door of the plurality of first blocker doors is configured to rotate about the forward end of each first blocker door of the plurality of first blocker doors such that an aft end of each first blocker door rotates radially outward, with respect to a longitudinal axis of the inner fixed structure, and wherein, when deployed, the plurality of first blocker doors are configured to block a first portion of bypass air in the fan air duct; anda plurality of second blocker doors located within the fan air duct and rotatably coupled to the translating sleeve about a forward end of each second blocker door of the plurality of second blocker doors such that an aft end of each second blocker door rotates radially inward, with respect to the longitudinal axis of the inner fixed structure, and wherein, when deployed, the plurality of second blocker doors are configured to block a second portion of bypass air in the fan air duct;wherein when the plurality of first blocker doors and the plurality of second blocker doors are deployed, a portion of the fan air duct defined radially, with respect to the longitudinal axis of the inner fixed structure, between the aft ends of the plurality of first blocker doors and the aft ends of the plurality of second blocker doors is unobstructed by the plurality of first blocker doors and the plurality of second blocker doors. 17. The aircraft nacelle of claim 16, further comprising an engine. 18. The aircraft nacelle of claim 17, wherein the plurality of first blocker doors are configured to obstruct an area of the fan air duct adjacent to the engine. 19. The aircraft nacelle of claim 16, further comprising a drive mechanism installed radially outward of the plurality of second blocker doors. 20. The aircraft nacelle of claim 16, further comprising a drive mechanism installed radially inward of the plurality of first blocker doors.
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이 특허에 인용된 특허 (8)
Hapke ; Donald W., Combination primary and fan air thrust reversal control systems for long duct fan jet engines.
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