Sound-damping arrangement for an engine nacelle and engine nacelle comprising such an arrangement
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/24
B64D-033/02
F02C-007/045
B64D-029/00
출원번호
US-0851734
(2015-09-11)
등록번호
US-9500131
(2016-11-22)
우선권정보
DE-10 2014 218 350 (2014-09-12)
발명자
/ 주소
Richter, Christoph
출원인 / 주소
ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
대리인 / 주소
Shuttleworth & Ingersoll, PLC
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
A sound-absorbing arrangement for an engine nacelle includes a first damping structure that includes a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section that are arranged behind one anot
A sound-absorbing arrangement for an engine nacelle includes a first damping structure that includes a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section that are arranged behind one another in the axial direction. The arrangement further includes a second damping structure that is formed in a ring-shaped manner and adjoins the first damping structure in the second section of the same in the radially external direction. The second damping structure is formed by multiple hollow chambers that adjoin each other in the circumferential direction, wherein the hollow chambers are formed without a honeycomb structure.
대표청구항▼
1. A sound-absorbing arrangement for an engine nacelle, comprising: a first damping structure that comprises a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section which are arranged behind
1. A sound-absorbing arrangement for an engine nacelle, comprising: a first damping structure that comprises a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section which are arranged behind each other in an axial direction, anda second damping structure that is formed in a ring-shaped manner and adjoining the second section of the first damping structure externally in a radial direction, wherein the second damping structure is formed by multiple hollow chambers adjacent to each other in a circumferential direction, wherein the hollow chambers are formed without an internal honeycomb structure, wherein at least one of the hollow chambers includes a hollow open interior with a first the at least one hollow chamber to fluidly couple the interior of the at least one hollow chamber to the first damping structure, the second side of the at least one hollow chamber being fluidly closed to the first damping structure except through the first side. 2. The arrangement according to claim 1, wherein the hollow chambers are separated from each other in the circumferential direction by separation walls. 3. The arrangement according to claim 1, wherein the honeycomb structure of the first damping structure has a different configuration in the second section, which is adjoined by the second damping structure, than in the first section. 4. The arrangement according to claim 1, wherein, in the first section between the inner layer and the outer layer, the honeycomb structure of the first damping structure has at least two layers in honeycomb shape that are separated from each other by a perforated septum. 5. The arrangement according to claim 4, wherein the honeycomb shapes in the two layers are arranged so as to be offset with respect to one another. 6. The arrangement according to claim 1, wherein, between the inner layer and the outer layer in the second section that is adjoined by the second damping structure, the honeycomb structure of the first damping structure forms exactly one layer in honeycomb shape, which has honeycombs that extend continuously from the inner layer to the outer layer. 7. The arrangement according to claim 6, wherein, in the second section that is adjoined by the second damping structure, the outer layer of the first damping structure is at least partially provided with perforations. 8. The arrangement according to claim 7, wherein the perforations are formed as holes with a diameter between 2 mm and 5 mm. 9. The arrangement according to claim 7, wherein the perforations constitute between 8% and 25% of a surface of the outer layer of the first damping structure in the perforated section. 10. The arrangement according to claim 7, wherein the perforations in the outer layer of the first damping structure have an arrangement that does not correspond to an arrangement of the honeycombs of the layer in honeycomb shape. 11. The arrangement according to claim 7, wherein the outer layer of the first damping structure has a greater thickness in the second section that is adjoined by the second damping structure. 12. The arrangement according to claim 11, wherein, in the second section that is adjoined by the second-damping structure, the perforated inner layer of the first damping structure has perforations that have a smaller size than the perforations that are formed in the outer layer. 13. The arrangement according to claim 1, wherein the sound-damping honeycomb structure is interrupted in the second section of the first damping structure. 14. The arrangement according to claim 1, wherein the hollow chambers are formed as symmetrical or asymmetrical double chambers and for this purpose have respectively one separating wall that extends in the radial direction. 15. The arrangement according to claim 1, wherein the second damping structure has a larger extension in the axial than in the radial direction. 16. The arrangement according to claim 15, wherein the hollow chambers of the second damping structure are formed in an L-shaped manner. 17. The arrangement according to claim 1, wherein the second damping structure is formed by a fibrous composite material comprising a glass fiber or carbon fiber matrix. 18. An engine nacelle of a turbofan engine, comprising a sound-damping arrangement with the features of claim 1, wherein the first damping structure forms a sound-damping inner lining of the engine nacelle and the second damping structure is arranged inside the engine nacelle radially externally with respect to the first damping structure.
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