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RU2006111012A - TWO-CIRCUIT TURBOREACTIVE ENGINE - Google Patents

TWO-CIRCUIT TURBOREACTIVE ENGINE Download PDF

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Publication number
RU2006111012A
RU2006111012A RU2006111012/06A RU2006111012A RU2006111012A RU 2006111012 A RU2006111012 A RU 2006111012A RU 2006111012/06 A RU2006111012/06 A RU 2006111012/06A RU 2006111012 A RU2006111012 A RU 2006111012A RU 2006111012 A RU2006111012 A RU 2006111012A
Authority
RU
Russia
Prior art keywords
circuit
fairing
nacelle
external
annular element
Prior art date
Application number
RU2006111012/06A
Other languages
Russian (ru)
Other versions
RU2316666C1 (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 RU2006111012/06A priority Critical patent/RU2316666C1/en
Publication of RU2006111012A publication Critical patent/RU2006111012A/en
Application granted granted Critical
Publication of RU2316666C1 publication Critical patent/RU2316666C1/en

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  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (1)

Турбореактивный двигатель сверхвысокой степени двухконтурности с расположенным в нижней по течению части внешней гондолы подвижным в осевом направлении кольцевым элементом и размещенным радиально внутри гондолы коническим центральным обтекателем, отличающийся тем, что обтекатель выполнен по его наружной поверхности на длине L с углом образующей конуса α=15-25° на выходе из сопла наружного контура с плавным переходом к углу β=0-15° на срезе обтекателя, причем L/l=0,5-2,5, где l - величина осевого перемещения кольцевого элемента внешней гондолы.An ultrahigh bypass turbojet engine with an axially movable annular element located in the downstream part of the external nacelle and arranged radially inside the nacelle by a conical central fairing, characterized in that the fairing is made along its outer surface at a length L with a cone angle α = 15- 25 ° at the exit of the nozzle of the external circuit with a smooth transition to the angle β = 0-15 ° at the cut of the fairing, with L / l = 0.5-2.5, where l is the axial displacement of the annular element of the external nacelle.
RU2006111012/06A 2006-04-05 2006-04-05 Superhigh by-pass ratio turbojet engine RU2316666C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006111012/06A RU2316666C1 (en) 2006-04-05 2006-04-05 Superhigh by-pass ratio turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006111012/06A RU2316666C1 (en) 2006-04-05 2006-04-05 Superhigh by-pass ratio turbojet engine

Publications (2)

Publication Number Publication Date
RU2006111012A true RU2006111012A (en) 2007-10-10
RU2316666C1 RU2316666C1 (en) 2008-02-10

Family

ID=38952669

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006111012/06A RU2316666C1 (en) 2006-04-05 2006-04-05 Superhigh by-pass ratio turbojet engine

Country Status (1)

Country Link
RU (1) RU2316666C1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964703B1 (en) * 2010-09-13 2012-08-24 Aircelle Sa LOCKING / UNLOCKING DEVICE FOR SLIDING HOOD WITH SLIDING COVER AND ADAPTIVE TUBE FOR AN AIRCRAFT ENGINE NACELLE

Also Published As

Publication number Publication date
RU2316666C1 (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: 20110406