[특허]Aircraft engine nacelle with translating inlet cowl

Rohr, Inc.

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Aircraft engine nacelle with translating inlet cowl

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-033/02
미국특허분류(USC)	244/053B; 244/129.4; 137/015.1; 060/226.1
출원번호	US-0337209 (2008-12-17)
등록번호	US-8181905 (2012-05-22)
발명자 / 주소	McDonough, Michael Patrick Brown, Keith Towers Gilzean, Scott
출원인 / 주소	Rohr, Inc.
대리인 / 주소	Womble Carlyle
인용정보	피인용 횟수 : 16 인용 특허 : 6

초록
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A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge includes an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge. The inner barrel aft edge is configured to be affixed to the fan case forward edge in a stationary position on the engine. The nacelle also includes a translating inlet cowl having an inlet lip with an aft inlet lip edge and an outer skin with rear edge. The translating inlet cowl is configured to be movably attached to one or more stationary portions of the engine such th...

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1. A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge, the nacelle comprising: (a) an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge, the inner barrel aft edge being configured to be affixed to the fan case forward edge in a stationary position on the engine;(b) a translating inlet cowl having an inlet lip with an aft inlet lip edge and an outer skin with rear edge, the inlet cowl configured to be selectively movable in the forward and aft directions relative to the fan case, between a stowed flight position and an extended service position;c) at least two circumferentially spaced actuators constructed and arranged to generate an output for causing the translating inlet cowl to move in the forward and aft directions; andd) a plurality of electromechanical latches circumferentially spaced around the inner barrel forward edge and configured to engage an aft inner edge periphery of the inlet lip in the stowed flight position and to disengage from the inlet lip in the extended service position, each of the latches having an electrical actuator. 2. A nacelle for a turbofan aircraft engine according to claim 1, wherein: each electromechanical latch includes a catch mounted on a bracket;each bracket is attached to the inlet inner barrel proximate to the inner barrel forward edge; andeach electrical actuator comprises a solenoid to control movement and positioning of the catch. 3. A nacelle for a turbofan aircraft engine according to claim 2, wherein: the catch is pivotally mounted on the bracket; andthe solenoid is a rotary solenoid. 4. A nacelle for a turbofan aircraft engine according to claim 1 further comprising a stationary aft nacelle portion having a front edge, wherein a service opening is formed between the rear edge of the outer skin and the front edge of the aft nacelle portion when the translating inlet cowl is in the extended service position, the service opening being proximate to the engine fan case. 5. A nacelle for a turbofan aircraft engine according to claim 1 further comprising a synchronizing cable connected to the at least two circumferentially spaced actuators and configured to ensure that the actuators generate a synchronized output. 6. A nacelle for a turbofan aircraft engine according to claim 5 wherein; the at least two circumferentially spaced actuators each comprise a ball screw extending between a forward ball screw support and an aft ball screw support;rotation of the ball screws causes the inlet cowl to translate in the forward and aft directions; andthe synchronizing cable ensures that the ball screws rotate in synchrony. 7. A nacelle for a turbofan aircraft engine according to claim 1 further comprising mating seal members on the inner barrel forward edge and the inlet lip aft inner edge that sealingly engage each other when the translating inlet cowl is in the stowed flight position. 8. A nacelle for a turbofan aircraft engine according to claim 1 further comprising at least one stabilizing beam for movably attaching the translating inlet cowl to one or more stationary portions of the engine. 9. A nacelle for a turbofan aircraft engine according to claim 1 further comprising mating fittings on the inner barrel forward edge and the inlet lip aft inner edge that engage each other when the translating inlet cowl is in the stowed flight position. 10. A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge, the nacelle comprising: (a) a translating inlet cowl comprising an inlet lip with an inlet lip aft inner edge and an outer skin with a rear edge, the translating inlet cowl being movable in the forward and aft directions relative to the fan case between a stowed flight position and an extended service position;(b) a stationary aft nacelle portion including a front outer edge;(c) an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge, wherein the inner barrel aft edge is configured to be affixed to the fan case forward edge in a stationary position;(d) at least two circumferentially spaced actuators constructed and arranged to generate an output for causing the translating inlet cowl to move in the forward and aft directions; and(e) a plurality of electromechanical latches circumferentially spaced around the inner barrel forward edge and configured to engage an aft inner edge periphery of the inlet lip in the stowed flight position and to disengage from the inlet lip in the extended service position, each of the latches having an electrical actuator;wherein the inlet lip aft inner edge is adjacent to the inner barrel forward edge when the translating inlet cowl is in the stowed flight position, andwherein a service opening is formed between the rear edge of the outer skin and the front edge of the aft nacelle portion when the translating inlet cowl is in the extended service position. 11. A nacelle for a turbofan aircraft engine according to claim 10 wherein each electromechanical latch includes a catch mounted on a bracket;each bracket is attached to the inlet inner barrel proximate to the inner barrel forward edge; andthe electrical actuator comprises a solenoid to control movement and positioning of the catch. 12. A nacelle for a turbofan aircraft engine according to claim 11, wherein: the catch is pivotally mounted on the bracket; andthe solenoid is a rotary solenoid. 13. A nacelle for a turbofan aircraft engine according to claim 10 wherein the engine includes a pylon, and wherein the translating inlet cowl is at least partially movably supported by the pylon. 14. A nacelle for a turbofan aircraft engine according to claim 10 wherein the translating inlet cowl is at least partially movably supported by the fan case. 15. A nacelle for a turbofan aircraft engine according to claim 10 wherein the at least two circumferentially spaced actuators each comprise a ball screw extending between a forward ball screw support and an aft ball screw support, and wherein rotation of the ball screws causes the inlet cowl to translate in the forward and aft directions. 16. A nacelle for a turbofan aircraft engine according to claim 15 further comprising a synchronizing cable configured between ball screw supports to ensure that the actuators generate a synchronized output and the ball screws rotate in synchrony. 17. A nacelle for a turbofan aircraft engine according to claim 16 wherein the plurality of latches are configured to automatically latch the inlet lip aft inner edge to the inner barrel forward edge when the translating inlet cowl portion is moved from the extended service position to the stowed flight position. 18. A nacelle for a turbofan aircraft engine according to claim 10 further comprising a support beam having a fixed portion affixed to one or more stationary portions of the engine, and a movable portion affixed to the translating inlet cowl. 19. A nacelle for a turbofan aircraft engine according to claim 18 further comprising at least one stabilizing beam disposed between the translating inlet cowl and a stationary portion of the engine. 20. A nacelle for a turbofan aircraft engine according to claim 10 further comprising: a first flange on the inlet inner barrel in abutment with a second flange on the inlet lip;a seal member between the first flange and the second flange; anda plurality of pins for aligning the inlet inner barrel with the inlet lip. 21. A nacelle for a turbofan aircraft engine according to claim 10 wherein the service opening is proximate to the engine fan case. 22. A nacelle for a turbofan aircraft engine according to claim 10 further comprising mating fittings on the inner barrel forward edge and the inlet lip aft inner edge that engage each other when the translating inlet cowl is in the stowed flight position. 23. A nacelle for a turbofan aircraft engine having a fan case, the nacelle comprising: (a) a translating inlet cowl;(b) a support beam affixed to the engine fan case, wherein the support beam substantially supports the translating inlet cowl on the engine, and is configured to permit the translating inlet cowl to be selectively translated in the forward and aft directions relative to the fan case between a stowed flight position and an extended service position;(c) an inner barrel connected to the fan case in a fixed position forward of the fan case, the inner barrel including an inner barrel forward edge, wherein the translating inlet cowl includes an inlet lip with an aft inner edge that engages the inner barrel forward edge when the inlet cowl is in the stowed flight position, and wherein the aft inner edge of the inlet lip is separate from the inner barrel forward edge when the inlet cowl is in the extended service position;(d) at least two circumferentially spaced actuators constructed and arranged to generate a synchronized output for causing the translating inlet cowl to move in the forward and aft directions; and(e) a plurality of electromechanical latches circumferentially spaced around the inner barrel forward edge and configured to engage an aft inner edge periphery of the inlet lip in the stowed flight position and to disengage from the inlet lip in the extended service position, each of the latches having an electrical actuator. 24. A nacelle for a turbofan aircraft engine according to claim 23 wherein the support beam includes a stationary beam portion affixed to the engine fan case and at least one sliding portion slidably engaged on the support beam and affixed to the translating inlet cowl. 25. A nacelle for a turbofan aircraft engine according to claim 23 further comprising a separable seal between the inner barrel forward edge and the aft inner edge of the inner barrel. 26. A nacelle for a turbofan aircraft engine according to claim 23wherein the at least two circumferentially spaced actuators each comprise a ball screw extending between a forward ball screw support and an aft ball screw support, and wherein rotation of the ball screws causes the inlet cowl to translate in the forward and aft directions. 27. A nacelle for a turbofan aircraft engine according to claim 26 further comprising a synchronizing cable configured between ball screw supports to ensure that the ball screws rotate in synchrony. 28. A nacelle for a turbofan aircraft engine according to claim 23 wherein each electromechanical latch includes a catch mounted on a bracket;each bracket is attached to the inlet inner barrel proximate to the inner barrel forward edge; andthe electrical actuator comprises a solenoid to control movement and positioning of the catch. 29. A nacelle for a turbofan aircraft engine according to claim 28, wherein: the catch is pivotally mounted on the bracket; andthe solenoid is a rotary solenoid.

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이 특허를 인용한 특허 피인용횟수: 16

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Aircraft engine nacelle with translating inlet cowl

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