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RU2006103474A - TWO-CIRCUIT EXTRA TURBOREACTIVE ENGINE WITH A REDUCED ANTI-VIRTUAL ROTARY FAN - Google Patents

TWO-CIRCUIT EXTRA TURBOREACTIVE ENGINE WITH A REDUCED ANTI-VIRTUAL ROTARY FAN Download PDF

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Publication number
RU2006103474A
RU2006103474A RU2006103474/06A RU2006103474A RU2006103474A RU 2006103474 A RU2006103474 A RU 2006103474A RU 2006103474/06 A RU2006103474/06 A RU 2006103474/06A RU 2006103474 A RU2006103474 A RU 2006103474A RU 2006103474 A RU2006103474 A RU 2006103474A
Authority
RU
Russia
Prior art keywords
fan
gear
rotary fan
reduced anti
virtual rotary
Prior art date
Application number
RU2006103474/06A
Other languages
Russian (ru)
Other versions
RU2316667C2 (en
Inventor
Валерий Алексеевич Кузнецов (RU)
Валерий Алексеевич Кузнецов
Александр Адольфович Пожаринский (RU)
Александр Адольфович Пожаринский
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
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 "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2006103474/06A priority Critical patent/RU2316667C2/en
Publication of RU2006103474A publication Critical patent/RU2006103474A/en
Application granted granted Critical
Publication of RU2316667C2 publication Critical patent/RU2316667C2/en

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  • Rolling Contact Bearings (AREA)
  • Gear Transmission (AREA)

Claims (1)

Турбореактивный двигатель сверхвысокой степени двухконтурности с двухрядным вентилятором противоположного вращения, роторы которого через редуктор связаны с турбиной низкого давления, отличающийся тем, что ведущее центральное колесо редуктора через промежуточные шестерни соединено с установленной на первом роторе вентилятора ведомой шестерней внешнего зацепления и с установленной на втором роторе вентилятора ведомой шестерней внутреннего зацепления, промежуточные шестерни установлены на комбинированном подшипниковом узле, состоящем из двух подшипников скольжения с размещенным между ними подшипником качения, причем внутреннее кольцо подшипника качения установлено на оси промежуточных шестерен с помощью упругого элемента и Dш/Dк=2÷5, где Dш - диаметр начальной окружности ведомой шестерни внутреннего зацепления; Dк - диаметр начальной окружности ведущего центрального колеса.An ultrahigh bypass turbojet engine with a double-row opposite-rotation fan, the rotors of which are connected to a low-pressure turbine through a reducer, characterized in that the drive central gear wheel is connected via intermediate gears to the driven external gear mounted on the first fan rotor and to the fan mounted on the second rotor driven gear internal gears, intermediate gears mounted on a combined bearing assembly, co oyaschem of two sliding bearings arranged between them with a rolling bearing, the rolling bearing inner ring is mounted on the intermediate axle gear by an elastic member, and D w / D k = 2 ÷ 5, wherein D w - internal diameter of the driven gear meshing pitch circle; D to - the diameter of the initial circumference of the driving Central wheel.
RU2006103474/06A 2006-02-06 2006-02-06 Superhigh by-pass ratio turbojet engine with drive reduction gear of double-row opposite rotation fan RU2316667C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006103474/06A RU2316667C2 (en) 2006-02-06 2006-02-06 Superhigh by-pass ratio turbojet engine with drive reduction gear of double-row opposite rotation fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006103474/06A RU2316667C2 (en) 2006-02-06 2006-02-06 Superhigh by-pass ratio turbojet engine with drive reduction gear of double-row opposite rotation fan

Publications (2)

Publication Number Publication Date
RU2006103474A true RU2006103474A (en) 2007-08-27
RU2316667C2 RU2316667C2 (en) 2008-02-10

Family

ID=38596941

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006103474/06A RU2316667C2 (en) 2006-02-06 2006-02-06 Superhigh by-pass ratio turbojet engine with drive reduction gear of double-row opposite rotation fan

Country Status (1)

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RU (1) RU2316667C2 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9228535B2 (en) * 2012-07-24 2016-01-05 United Technologies Corporation Geared fan with inner counter rotating compressor
RU2528236C1 (en) * 2013-08-27 2014-09-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Planetary differential reduction gearbox
RU2532089C1 (en) * 2013-10-29 2014-10-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Differential speed reduction gear of turbo-propeller engine

Also Published As

Publication number Publication date
RU2316667C2 (en) 2008-02-10

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Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20100207