RU2004117516A - AIRCRAFT ENGINE CHANNEL - Google Patents

AIRCRAFT ENGINE CHANNEL Download PDF

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Publication number
RU2004117516A
RU2004117516A RU2004117516/11A RU2004117516A RU2004117516A RU 2004117516 A RU2004117516 A RU 2004117516A RU 2004117516/11 A RU2004117516/11 A RU 2004117516/11A RU 2004117516 A RU2004117516 A RU 2004117516A RU 2004117516 A RU2004117516 A RU 2004117516A
Authority
RU
Russia
Prior art keywords
aircraft engine
honeycomb
gap
panels
layer
Prior art date
Application number
RU2004117516/11A
Other languages
Russian (ru)
Other versions
RU2297369C2 (en
Inventor
Геннадий Владимирович Степанов (RU)
Геннадий Владимирович Степанов
Анатолий Лукич Доброскоков (RU)
Анатолий Лукич Доброскоков
Виктор Васильевич Зюскин (RU)
Виктор Васильевич Зюскин
Евгений Алексеевич Ефимов (RU)
Евгений Алексеевич Ефимов
Original Assignee
Открытое Акционерное Общество " Авиационный комплекс им. С.В. Ильюшина" (RU)
Открытое Акционерное Общество " Авиационный комплекс им. С.В. Ильюшина"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Открытое Акционерное Общество " Авиационный комплекс им. С.В. Ильюшина" (RU), Открытое Акционерное Общество " Авиационный комплекс им. С.В. Ильюшина" filed Critical Открытое Акционерное Общество " Авиационный комплекс им. С.В. Ильюшина" (RU)
Priority to RU2004117516/11A priority Critical patent/RU2297369C2/en
Publication of RU2004117516A publication Critical patent/RU2004117516A/en
Application granted granted Critical
Publication of RU2297369C2 publication Critical patent/RU2297369C2/en

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  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Rigid Pipes And Flexible Pipes (AREA)

Claims (1)

Воздухозаборный канал двигателя летательного аппарата, содержащий профилированный цилиндрический патрубок, включающий в себя основание, внутреннюю и среднюю перфорированные обшивки и два слоя сотового заполнителя, контактирующие по торцам с замкнутыми кольцевыми фланцами, отличающийся тем, что внутренняя и средняя обшивки, выполненные в виде цилиндрических элементов, установлены концентрично с кольцевым зазором между ними, в зазоре расположен первый слой упомянутого сотового заполнителя, выполненный в форме сплошного, замкнутого по кольцу, цилиндрического элемента, а второй слой сотового заполнителя выполнен в виде панелей, которые размещены по периметру средней обшивки с зазором относительно друг друга, при этом на внешней поверхности каждой панели установлены металлические основания, соответствующие по конфигурации внешним поверхностям сотовых панелей.The air intake channel of the aircraft engine, comprising a profiled cylindrical pipe, including a base, an inner and middle perforated casing, and two honeycomb layers in contact at the ends with closed annular flanges, characterized in that the inner and middle casing, made in the form of cylindrical elements, installed concentrically with an annular gap between them, in the gap there is a first layer of said honeycomb core made in the form of a continuous, closed ring, the cylindrical member and the second layer of honeycomb core is made in the form of panels, which are placed around the perimeter of the middle cladding with a gap relative to each other, wherein the outer surface of each metal base panel installed on respective outer surfaces of the configuration of honeycomb panels.
RU2004117516/11A 2004-06-08 2004-06-08 Air intake passage for flying vehicle engine RU2297369C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2004117516/11A RU2297369C2 (en) 2004-06-08 2004-06-08 Air intake passage for flying vehicle engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2004117516/11A RU2297369C2 (en) 2004-06-08 2004-06-08 Air intake passage for flying vehicle engine

Publications (2)

Publication Number Publication Date
RU2004117516A true RU2004117516A (en) 2005-11-20
RU2297369C2 RU2297369C2 (en) 2007-04-20

Family

ID=35866916

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2004117516/11A RU2297369C2 (en) 2004-06-08 2004-06-08 Air intake passage for flying vehicle engine

Country Status (1)

Country Link
RU (1) RU2297369C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2537998C2 (en) * 2008-05-16 2015-01-10 Эрсель Aircraft power plant and its air intake

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2925118B1 (en) * 2007-12-14 2009-12-25 Snecma ABRADABLE SUPPORT PANEL IN A TURBOMACHINE
FR2949820B1 (en) * 2009-09-04 2011-10-14 Aircelle Sa STRUCTURING ASSEMBLY FOR AN EJECTION TUBE.
DE102012001571A1 (en) * 2012-01-26 2013-08-01 Rolls-Royce Deutschland Ltd & Co Kg Engine casing of an aircraft gas turbine with sound attenuation elements in the fan inflow area
RU2522661C1 (en) * 2012-11-23 2014-07-20 Государственный научный центр Российской Федерации-федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" Air intake power unit device of hypersonic aircraft
RU180269U1 (en) * 2017-08-29 2018-06-07 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Gas turbine engine intake duct

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2537998C2 (en) * 2008-05-16 2015-01-10 Эрсель Aircraft power plant and its air intake

Also Published As

Publication number Publication date
RU2297369C2 (en) 2007-04-20

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