IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0752079
(2010-03-31)
|
등록번호 |
US-8220588
(2012-07-17)
|
발명자
/ 주소 |
- Thrash, Patrick J.
- Miller, David Michael
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
9 |
초록
The different advantageous embodiments provide an inner barrel structure comprising an outer skin, an inner skin, a number of septa, and a truss core.
대표청구항
▼
1. An inner barrel structure of an engine nacelle, the inner barrel structure comprising: an inner skin formed by laying down a number of layers of an inner skin fabric around a steel mold tool and using a number of banding threads to hold the inner skin against a steel mold tool in tension; A truck
1. An inner barrel structure of an engine nacelle, the inner barrel structure comprising: an inner skin formed by laying down a number of layers of an inner skin fabric around a steel mold tool and using a number of banding threads to hold the inner skin against a steel mold tool in tension; A truck core disposed with respect to the inner skin to define a cavity; andA septum disposed in the cavity. 2. The inner barrel structure of claim 1, wherein the truss core is disposed at an inner surface of the inner skin such that a plurality of cavities are defined therebetween, further comprising a plurality of septa respectively disposed in the plurality of cavities. 3. The inner barrel structure of claim 2, wherein the plurality of septa are configured for attenuating noise. 4. The inner barrel structure of claim 1 further comprising: an outer skin disposed in a space relationship with the inner skin; anda radial ply closeout disposed between the inner and outer skins. 5. The inner barrel structure of claim 1, further comprising absorber material disposed in the cavity. 6. The inner barrel structure of claim 5, wherein the absorber material is disposed between the truss core and the septum. 7. The inner barrel structure of claim 1, wherein the septum includes a stiffening portion. 8. The inner barrel structure of claim 7, wherein the stiffening portion is configured substantially channel-like. 9. The inner barrel structure of claim 7, wherein the stiffening portion includes acoustically configured perforations. 10. The inner barrel structure of claim 7, wherein the stiffening portion contacts the inner skin. 11. An engine nacelle comprising the inner barrel structure according to claim 1. 12. An aircraft comprising a plurality of engine nacelles according to claim 1. 13. A method for assembling a barrel structure, the method comprising: laying down a number of layers of an inner skin fabric around a steel mold tool to form an inner skin;installing a number of mandrel sections with encapsulated septum detail on the inner skin;installing a first number of radial ply closeouts between each of the number of mandrel sections with encapsulated septum detail installed;laying down a number of layers of truss core fabric over the number of mandrel sections with encapsulated septum detail to form a truss core;installing a number of mandrel sections on the truss core; installing a second number of radial ply closeouts betweer each of the number of mandrel sections; andlaying down a number of layers of an outer skin fabric against the number of mandrel sections to form an outer skin;banding the inner skin using a number of banding ihreads to hold the inner skin against the steel mold tool in tension. 14. The method of claim 13 further comprising: laying down an aft doubler and a forward doubler against the outer skin. 15. A method of fabricating an inner barrel structure of an engine nacelle, the method comprising infusing with resin a portion of the inner barrel structure according to any of claim 14. 16. The method of claim 15 further comprising utilizing sacrificial mandrel sections that are removable by melting. 17. The method of claim 15 further comprising holding the inner skin against a mold tool. 18. The method of claim 15 further comprising holding the truss core against the mandrel sections with encapsulated septum detail in tension. 19. The method of claim 15, wherein the infusing step occurs at a temperature that is lower than the melting point of a number of wax mandrels in the inner barrel. 20. The method of claim 15, wherein the curing step cure occurs at a temperature higher than the temperature used for the infusing step, but lower than a temperature at which the number of wax mandrels is engineered to melt. 21. The method of claim 13, wherein the number of banding threads are selected from at least one of vectran fiber, carbon, and cotton. 22. A method of attenuating engine noise comprising installing onto an aircraft a plurality of engine nacelles according to claim 21. 23. The method of claim 13, further comprising: banding the number of mandrel sections with encapsulated septum detail using a number of banding threads to hold the number of mandrel sections with encapsulated septum detail against the inner skin in tension. 24. The method of claim 13 further comprising: banding the truss core using the number of banding thread; to hold the truss core against the number of mandrel sections with encapsulated septum detail in tension. 25. The method of claim 13 further comprising: banding the outer skin using the number of banding threads to hold the outer skin against the number of mandrel sections in tension. 26. The method of claim 13, wherein the inner skin fabric is at least one of a woven fabric, a uni-directional tape, warp/knit fabric, braided fabric, stitched fabric, and/or any other suitable fabric. 27. The method of claim 13, wherein the outer skin fabric is at least one of a woven fabric, a uni-directional tape, warp/knit fabric, braided fabric, stitched fabric, and/or any other suitable fabric. 28. The method of claim 27 wherein said forming further comprises disposing a truss core at an inner skin of the barrel structure such that the plurality of cavities are defined therebetween. 29. The method of claim 27 wherein said disposing further comprises disposing a plurality of perforated septa respectively in the cavities. 30. The method of claim 27 further comprising disposing absorbing material in the cavities. 31. The method of claim 13, wherein the truss core fabric is at least one of a woven fabric, a uni-directional tape, warp/knit fabric, braided fabric, stitched fabric, and/or any other suitable fabric. 32. The method of claim 13, wherein the first number of radial ply closeouts is installed perpendicular to the length of the number of mandrel sections with encapsulated septum detail to form a wall or divide between each of the number of mandrel sections with encapsulated septum detail as they are installed around the inner skin on the steel mold tool. 33. The method of claim 32 wherein said disposing further comprises disposing a plurality of septa each including a stiffening portion. 34. The method of claim 13, wherein the second number of radial ply closeouts is installed perpendicular to the length of the number of mandrel sections to form a wall or divide between each of the number of mandrel sections as they are installed around the truss core on the steel mold tool. 35. A method for forming a barrel structure, the method comprising: installing a vacuum bag over a dry three-dimensional preform inner barrel structure on a steel mold tool, the preform inner barrel structure having an inner skin formed by laying down a number of layers of an inner skin fabric around the steel mold tool and using a number of banding threads to hold the inner skin against the steel mold tool in tension; placing the dry three-dimensional preform inner barrel structure inside an oven;infusing the dry three-dimensional preform inner barrel structure with resin to form a resin-infused inner barrel structure;curing the resin-infused inner barrel structure to form an inner barrel; removing the inner barrel from the oven; removing the vacuum bag; removing the release ply from the inner barrel and discarding a release ply and flow media;removing the inner barrel from the steel mold tool; anddrilling a number of holes in at least one of an inner skin and an outer skin of the inner barrel. 36. The method of claim 35 further comprising: placing the inner barrel with the number of holes in the oven;melting out a number of wax mandrels from the inner barrel through the number of holes drilled;removing the inner barrel from the oven; andremoving residual wax film from the inner barrel. 37. The method of claim 36 further comprising: applying additional acoustic treatment to the inner barrel. 38. The method of claim 36, wherein the number of wax mandrels is engineered to maintain rigidity at one atmosphere of applied pressure by the vacuum bag and a temperature used for the infusing step and a temperature used for the curing step, and wherein the number of wax mandrels is engineered to melt at a temperature higher than the temperature used for the infusing step and the temperature used for the curing step. 39. The method of claim 36, wherein the removing residual wax film from the inner barrel step uses a technique selected from at least one of a solvent bath and ultrasonic cleaning. 40. A method of manufacturing an inner barrel structure of an engine nacelle, the method comprising: forming a plurality of cavities between an inner skin and an outer skin of the barrel structure, the inner barrel structure having an inner skin formed by laying down a number of layers of an inner skin fabric around the steel mold tool and using a number of banding thread to hold the inner skin against the steel mold tool in tension; anddisposing a noise-attenuating structure within the cavities.
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