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RU2011136388A - Способ изготовления структуры с ячеистыми сердцевинами для гондолы турбореактивного двигателя - Google Patents

Способ изготовления структуры с ячеистыми сердцевинами для гондолы турбореактивного двигателя Download PDF

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RU2011136388A
RU2011136388A RU2011136388/05A RU2011136388A RU2011136388A RU 2011136388 A RU2011136388 A RU 2011136388A RU 2011136388/05 A RU2011136388/05 A RU 2011136388/05A RU 2011136388 A RU2011136388 A RU 2011136388A RU 2011136388 A RU2011136388 A RU 2011136388A
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lateral
walls
formation
connecting walls
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Бертран ДЕЖУАЙО
Тьерри ДЕШАМ
Джон МУТЬЕ
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Эрсель
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    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Multimedia (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
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Abstract

1. Способ изготовления структуры (2; 102; 202) с ячеистыми сердцевинами, которая может быть использована в конструктивной панели (1; 101) гондолы турбореактивного двигателя и которая содержит по меньшей мере один блок (А, В) с ячеистыми сердцевинами, имеющий центральную часть (5а, 5а', 5b, 5b') с серединными луночными ячейками (7а, 7а', 7b, 7b') и по меньшей мере две боковые части (9а, 9а', 9b, 9b'), каждая из которых имеет боковые луночные ячейки (11a, 11a', 11b, 11b'),включающий следующие этапы:A) формирование соединительных стенок (36) на боковых луночных ячейках (11a, 11a', 11b, 11b'), причем соединительные стенки (36) обладают возможностью взаимодействия друг с другом с формированием соединительной зоны (13; 113; 213),B) разгибание сформированных указанным образом соединительных стенок (36),C) соединение торцом к торцу разогнутых стенок (46), принадлежащих двум разным боковым частям (9а, 9а', 9b, 9b'), осуществляемое таким образом, что указанные соединительные стенки (46) перемежаются друг с другом с формированием соединительной зоны (13; 113; 213).2. Способ по п.1, в котором длина (е) каждой соединительной стенки (46) больше или равна наибольшей длине (l) боковых (11a, 11a', 11b, 11b') и/или серединных (7а, 7а', 7b, 7b') луночных ячеек.3. Способ по п.1 или 2, в котором соединяют торцом к торцу боковые части (9а, 9b), принадлежащие блокам (А, В) с ячеистыми сердцевинами, у которых боковые (11a, 11a', 11b, 11b') и серединные (7а, 7а', 7b, 7b') луночные ячейки имеют разные размеры.4. Способ по п.1 или 2, в котором на этапе А раскрывают краевые луночные ячейки (33a, 33b), находящиеся на краях боковой части (9а, 9а', 9b, 9b') подлежащего присоединению блока, и луночные ячейки (34а, 34b), смежные с указанными краевыми луночными ячейками (33a, 33b), формируя т�

Claims (11)

1. Способ изготовления структуры (2; 102; 202) с ячеистыми сердцевинами, которая может быть использована в конструктивной панели (1; 101) гондолы турбореактивного двигателя и которая содержит по меньшей мере один блок (А, В) с ячеистыми сердцевинами, имеющий центральную часть (5а, 5а', 5b, 5b') с серединными луночными ячейками (7а, 7а', 7b, 7b') и по меньшей мере две боковые части (9а, 9а', 9b, 9b'), каждая из которых имеет боковые луночные ячейки (11a, 11a', 11b, 11b'),
включающий следующие этапы:
A) формирование соединительных стенок (36) на боковых луночных ячейках (11a, 11a', 11b, 11b'), причем соединительные стенки (36) обладают возможностью взаимодействия друг с другом с формированием соединительной зоны (13; 113; 213),
B) разгибание сформированных указанным образом соединительных стенок (36),
C) соединение торцом к торцу разогнутых стенок (46), принадлежащих двум разным боковым частям (9а, 9а', 9b, 9b'), осуществляемое таким образом, что указанные соединительные стенки (46) перемежаются друг с другом с формированием соединительной зоны (13; 113; 213).
2. Способ по п.1, в котором длина (е) каждой соединительной стенки (46) больше или равна наибольшей длине (l) боковых (11a, 11a', 11b, 11b') и/или серединных (7а, 7а', 7b, 7b') луночных ячеек.
3. Способ по п.1 или 2, в котором соединяют торцом к торцу боковые части (9а, 9b), принадлежащие блокам (А, В) с ячеистыми сердцевинами, у которых боковые (11a, 11a', 11b, 11b') и серединные (7а, 7а', 7b, 7b') луночные ячейки имеют разные размеры.
4. Способ по п.1 или 2, в котором на этапе А раскрывают краевые луночные ячейки (33a, 33b), находящиеся на краях боковой части (9а, 9а', 9b, 9b') подлежащего присоединению блока, и луночные ячейки (34а, 34b), смежные с указанными краевыми луночными ячейками (33a, 33b), формируя таким образом соединительные стенки (46).
5. Способ по п.4, в котором краевые (33) и смежные (34а, 34b) луночные ячейки раскрывают путем рассечения боковой стороны и/или стенки луночной ячейки (33a, 33b; 34а, 34b).
6. Способ по пп.1, 2, 5, включающий в себя дополнительный этап D, на котором состояние перемежения, достигнутое на этапе С, поддерживают с помощью скоб или скреп.
7. Конструктивная панель (1; 101) для гондолы, окружающей турбореактивный двигатель, отличающаяся тем, что она снабжена по меньшей мере одной структурой (2; 102; 202) с ячеистыми сердцевинами, изготовленной способом по любому из предшествующих пунктов.
8. Панель по п.7, представляющая собой акустическую панель, в которой указанные структура или структуры (2; 102; 202) с ячеистыми сердцевинами покрыты с одной из своих сторон воздухонепроницаемой внешней обшивкой (4), а с другой своей стороны - воздухопроницаемой перфорированной внутренней обшивкой (3).
9. Панель по п.7 или 8, содержащая по меньшей мере две наложенные друг на друга структуры (102) с ячеистыми сердцевинами.
10. Гондола двигателя летательного аппарата, отличающаяся тем, что она содержит по меньшей мере одну конструктивную панель (1; 101) по любому из пп.7-9.
11. Гондола по п.10, отличающаяся тем, что указанные конструктивная панель или конструктивные панели (1; 101) размещены в зоне воздухозаборника этой гондолы.
RU2011136388/05A 2009-02-05 2010-01-08 Способ изготовления структуры с ячеистыми сердцевинами для гондолы турбореактивного двигателя RU2515750C2 (ru)

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PCT/FR2010/000019 WO2010089471A1 (fr) 2009-02-05 2010-01-08 Procédé de fabrication d'une structure a âmes alvéolaires pour une nacelle de turboréacteur

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