The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring c
The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.
대표청구항▼
1. A nacelle for a turbofan aircraft engine, the nacelle comprising: a stationary forward nacelle portion having an inlet end and an opposed aft end, the forward nacelle portion configured for mounting adjacent to a fan;a translating fan nozzle sleeve comprising a first arcuate fan nozzle sleeve por
1. A nacelle for a turbofan aircraft engine, the nacelle comprising: a stationary forward nacelle portion having an inlet end and an opposed aft end, the forward nacelle portion configured for mounting adjacent to a fan;a translating fan nozzle sleeve comprising a first arcuate fan nozzle sleeve portion having a first end and a second end, and a second arcuate fan nozzle sleeve portion having a third end and a fourth end; the fan nozzle sleeve being movably disposed aft of the forward nacelle portion, the fan nozzle sleeve being movable between a forward position, in which the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion are proximate to the aft end of the forward nacelle portion, and one or more extended positions in which a forward boundary of an upstream bypass flow exit is defined by the aft end of the stationary forward nacelle portion and an aft boundary of the upstream bypass flow exit is defined by the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion of the fan nozzle sleeve;a plurality of fan nozzle actuators extending from the stationary forward nacelle portion to the fan nozzle sleeve and being operable to selectively move the first arcuate fan nozzle sleeve portion between the forward position and the one or more extended positions, and wherein the fan nozzle actuators are operable to selectively move the second fan nozzle sleeve portion fan nozzle sleeve between the forward position and the one or more extended positions;a plurality of spaced extendable guide tubes, the guide tubes being separate from and circumferentially spaced apart from each of the fan nozzle actuators, and axially extending between the fan nozzle sleeve and the forward nacelle, the guide tubes being configured to permit longitudinal translating movement of the fan nozzle sleeve, and to inhibit movement of the fan nozzle sleeve in directions that are transverse to the direction of the longitudinal translating movement of the fan nozzle sleeve;a high pressure seal disposed between the aft edge of the forward nacelle portion and the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion; anda blister fairing extending along the aft end of the forward nacelle portion and comprising a plurality of upstream fairings each at least partially shrouding a respective actuator opening, and a plurality of downstream fairings each at least partially shrouding a portion of a respective fan nozzle actuator that is coupled to the fan nozzle sleeve, the downstream fairings disposed on an outer surface of the fan nozzle sleeve, the blister fairing at least partially overlapping the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion when the fan nozzle sleeve is in the forward position, and wherein each of the plurality of fan nozzle actuators extends through one of the respective actuator openings in the upstream blister fairings towards the fan nozzle sleeve. 2. A nacelle for a turbofan aircraft engine, the nacelle comprising: a stationary forward nacelle portion having an inlet end and an opposed aft end, the forward nacelle portion configured for mounting adjacent to a fan;a translating fan nozzle sleeve having comprising a first arcuate fan nozzle sleeve portion having a first end and a second end, and a second arcuate fan nozzle sleeve portion having a third end and a fourth end; the fan nozzle sleeve being movably disposed aft of the forward nacelle portion, the fan nozzle sleeve being movable between a forward position, in which the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion are proximate to the aft end of the forward nacelle portion, and one or more extended positions in which an upstream bypass flow exit is partially defined by the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion of the fan nozzle sleeve;a plurality of fan nozzle actuators extending from the stationary forward nacelle portion to the fan nozzle sleeve and being operable to selectively move the first arcuate fan nozzle sleeve portion between the forward position and the one or more extended positions, and wherein the fan nozzle actuators are operable to selectively move the second fan nozzle sleeve portion between the forward position and the one or more extended positions;a plurality of spaced extendable guide tubes, the guide tubes being separate from and circumferentially spaced apart from each of the fan nozzle actuators, and axially extending between the fan nozzle sleeve and a part of the nacelle located towards the inlet end, the guide tubes being configured to permit longitudinal translating movement of the fan nozzle sleeve, and to inhibit movement of the fan nozzle sleeve in directions that are transverse to the direction of the longitudinal translating movement of the fan nozzle sleeve;a thrust reverser comprising:(i) a cascade array of cascade vanes disposed aft of the forward nacelle portion;(ii) a thrust reverser sleeve disposed aft of the forward nacelle portion, the thrust reverser sleeve being selectively movable between a stowed position and a deployed position, wherein in the stowed position the thrust reverser sleeve substantially covers the cascade vanes, and in the deployed position, at least a portion of the cascade vanes are not covered by the thrust reverser sleeve; and(iii) at least one thrust reverser actuator configured to selectively move the thrust reverser sleeve between the stowed position and the deployed position;wherein the fan nozzle sleeve is disposed aft of the thrust reverser sleeve and is selectively movable between the forward position and the one or more extended positions, wherein a forward boundary of the upstream bypass flow exit is defined by an aft edge of the thrust reverser sleeve, and an aft boundary of the upstream bypass flow exit is defined by the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion of the fan nozzle sleeve when the fan nozzle sleeve is in the one or more extended positions;a high pressure seal disposed between the aft edge of the thrust reverser sleeve and the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion; anda blister fairing extending along the aft end of the forward nacelle portion and comprising a plurality of upstream fairings each at least partially shrouding a respective actuator opening formed on an outer surface of the thrust reverser sleeve, and a plurality of downstream fairings each at least partially shrouding a portion of a respective fan nozzle actuator that is coupled to the fan nozzle sleeve, the downstream fairings disposed on an outer surface of the fan nozzle sleeve, the blister fairing at least partially overlapping the first end of the first arcuate fan nozzle sleeve portion and the third end of the second arcuate fan nozzle sleeve portion position when the fan nozzle sleeve is in the forward position, and wherein each of the plurality of fan nozzle actuators extends through one of the respective actuator openings in the upstream blister fairings towards the fan nozzle sleeve. 3. The nacelle according to claim 2, wherein: the at least one thrust reverser actuator is extending from the forward nacelle portion to the thrust reverser sleeve, and/ora fan nozzle actuator of the plurality of fan nozzle actuators extends from the thrust reverser sleeve to the fan nozzle sleeve, and/or the fan nozzle actuator extends from the forward nacelle portion to the fan nozzle sleeve. 4. The nacelle according to claim 2, wherein: the at least one thrust reverser actuator is extending from the forward nacelle portion to the thrust reverser sleeve. 5. The nacelle according to claim 2 further comprising: a transverse bulkhead on the forward nacelle portion, wherein at least one of the thrust reverser sleeve and the fan nozzle sleeve are movably connected to the transverse bulkhead by means of:a beam attached to the transverse bulkhead, the beam having at least a first guide track;a first track bar attached to the thrust reverser sleeve, the first track bar being slidably engaged in the first guide track;a second guide track attached to the thrust reverser sleeve; anda second track bar attached to the fan nozzle sleeve, the second track bar being slidably engaged in the second guide track. 6. The nacelle according to claim 2, wherein the thrust reverser sleeve comprises a first thrust reverser sleeve portion and a second thrust reverser sleeve portion, wherein the at least one thrust reverser actuator is operable to selectively move the first thrust reverser sleeve portion between the stowed position and the deployed position, and wherein at least one thrust reverser actuator is operable to selectively move the second thrust reverser sleeve portion between the stowed position and the deployed position. 7. The nacelle according to claim 2, wherein the plurality of spaced extendable guide tubes axially extend between the thrust reverser sleeve and the fan nozzle sleeve. 8. The nacelle according to claim 2, wherein the cascade array comprises a plurality of substantially parallel longitudinally spaced cascade vanes, wherein the cascade vanes comprise variable depths. 9. The nacelle according to claim 8, wherein the depths of the cascade vanes progressively decrease from a deepest forward-most vane to a shallowest aft-most vane. 10. The nacelle according to claim 2, wherein a fan nozzle actuator of the plurality of fan nozzle actuators comprises: a fan nozzle sleeve drive mechanism;a forward gear box operably connected to the fan nozzle sleeve drive mechanism, the forward gear box being located forward of the thrust reverser sleeve;an aft gear box positioned proximate to a front edge of a first fan nozzle sleeve segment;a splined coupling rotatably connecting the forward gear box to the aft gear box, the splined coupling being axially extendable; andat least one actuator cable operably connecting at least a portion of the at least one fan nozzle actuator to the aft gear box;whereby the fan nozzle sleeve drive mechanism is operably coupled to at least a portion of the fan nozzle actuator and is capable of effecting translation of the first fan nozzle sleeve segment between its forward and extended positions. 11. The nacelle according to claim 10, wherein the fan nozzle sleeve drive mechanism comprises a motor coupled to a motor gear box, the motor gear box being operably connected to the forward gear box, wherein selective rotation of the motor causes rotation of the forward gear box and actuation of the of the at least one fan nozzle sleeve actuator. 12. The nacelle according to claim 11 further comprising at least one controller coupled to the motor, the controller being configured to selectively control translation of the first fan nozzle sleeve portion and a second fan nozzle sleeve portion. 13. The nacelle according to claim 12 further comprising an upper guide structure slidably supporting the upper ends of the first and second fan nozzle sleeve portions, and a lower guide structure slidably supporting the lower ends of the first and second fan nozzle sleeve portions.
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