RU2005140463A - TWO-CIRCUIT TURBOREACTIVE ENGINE - Google Patents

TWO-CIRCUIT TURBOREACTIVE ENGINE Download PDF

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Publication number
RU2005140463A
RU2005140463A RU2005140463/06A RU2005140463A RU2005140463A RU 2005140463 A RU2005140463 A RU 2005140463A RU 2005140463/06 A RU2005140463/06 A RU 2005140463/06A RU 2005140463 A RU2005140463 A RU 2005140463A RU 2005140463 A RU2005140463 A RU 2005140463A
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RU
Russia
Prior art keywords
inner movable
nozzle
movable bodies
movable housing
fairing
Prior art date
Application number
RU2005140463/06A
Other languages
Russian (ru)
Other versions
RU2315887C2 (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.)
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Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2005140463/06A priority Critical patent/RU2315887C2/en
Publication of RU2005140463A publication Critical patent/RU2005140463A/en
Application granted granted Critical
Publication of RU2315887C2 publication Critical patent/RU2315887C2/en

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Claims (1)

Турбореактивный двигатель сверхвысокой степени двухконтурности, включающий реверсивное устройство наружного контура, содержащее отклоняющую решетку, неподвижные и подвижные корпуса с уплотнительным элементом между ними, поворотные створки, шарнирно соединенные двухзвенным рычажным механизмом с неподвижным корпусом и с контактными площадками, а также обтекатель газогенератора, отличающийся тем, что наружный и внутренний подвижные корпуса соединены между собой и образуют выходную кромку регулируемого по площади сопла, обтекатель газогенератора на срезе сопла выполнен конусным с углом образующей, равным 15-30°, ниже по потоку от уплотнительного элемента на внешней поверхности внутреннего подвижного корпуса установлено дополнительное уплотнительное устройство, а на переднем торце внутреннего подвижного корпуса выполнена заходная фаска, при этом между неподвижным и наружным подвижным корпусами выполнена открытая в сторону сопла щелевая полость, причем h/δ=0,6-2, где h - радиальная высота заходной фаски; δ - радиальный зазор между внутренним подвижным корпусом и отклоняющей решеткой реверсивного устройства.An ultrahigh bypass turbojet engine comprising an external contour reversing device comprising a deflecting grate, fixed and movable bodies with a sealing element between them, rotary flaps pivotally connected by a two-link lever mechanism with a fixed body and contact pads, as well as a gas generator fairing, characterized in that the outer and inner movable bodies are interconnected and form the output edge of a nozzle that is adjustable in area, the fairing g the generator at the nozzle exit is made conical with a generatrix angle of 15-30 °, an additional sealing device is installed downstream of the sealing element on the outer surface of the inner movable housing, and a lead-in chamfer is made at the front end of the inner movable housing, between the stationary and the outer movable bodies made a slit cavity open towards the nozzle, with h / δ = 0.6-2, where h is the radial height of the entry chamfer; δ is the radial clearance between the inner movable housing and the deflecting grating of the reversing device.
RU2005140463/06A 2005-12-23 2005-12-23 High by-pass ratio turbojet engine RU2315887C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2005140463/06A RU2315887C2 (en) 2005-12-23 2005-12-23 High by-pass ratio turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2005140463/06A RU2315887C2 (en) 2005-12-23 2005-12-23 High by-pass ratio turbojet engine

Publications (2)

Publication Number Publication Date
RU2005140463A true RU2005140463A (en) 2007-06-27
RU2315887C2 RU2315887C2 (en) 2008-01-27

Family

ID=38315251

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005140463/06A RU2315887C2 (en) 2005-12-23 2005-12-23 High by-pass ratio turbojet engine

Country Status (1)

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RU (1) RU2315887C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2445490C2 (en) * 2007-11-06 2012-03-20 Эрбюс Операсьон (Сас) Method for improving characteristics of double-flow jet turbine engine

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008045072A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Dual function cascade integrated variable area fan nozzle and thrust reverser
FR2929998B1 (en) * 2008-04-14 2011-08-12 Aircelle Sa DOUBLE FLOW TURBOREACTOR NACELLE
US8695920B2 (en) * 2008-06-02 2014-04-15 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
FR2936222B1 (en) * 2008-09-24 2011-04-01 Aircelle Sa NACELLE WITH VARIABLE TUBE SECTION
FR2949141B1 (en) * 2009-08-14 2011-07-15 Aircelle Sa PUSH REVERSING DEVICE
FR2957979B1 (en) * 2010-03-25 2012-03-30 Aircelle Sa PUSH REVERSING DEVICE
FR2960600B1 (en) * 2010-06-01 2013-10-25 Aircelle Sa ACTUATING SYSTEM OF A PUSH REVERSING DEVICE
FR2960917B1 (en) * 2010-06-03 2012-05-18 Aircelle Sa THRUST INVERTER WITH LOCKABLE VARIABLE TUBE SECTION
FR2978991A1 (en) * 2011-08-08 2013-02-15 Snecma THRUST INVERSION DEVICE FOR COMPACT PIPE
BR102012028749B1 (en) * 2011-12-21 2022-01-18 United Technologies Corporation GAS TURBINE ENGINE
SG11201402663XA (en) * 2012-01-09 2014-09-26 United Technologies Corp Gas turbine engine with geared architecture
FR3007800B1 (en) * 2013-07-01 2017-10-20 Aircelle Sa THRUST INVERTER OF A TURBOJET NACELLE COMPRISING PARTIALLY INTEGRATED GRIDS IN HOODS

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2445490C2 (en) * 2007-11-06 2012-03-20 Эрбюс Операсьон (Сас) Method for improving characteristics of double-flow jet turbine engine

Also Published As

Publication number Publication date
RU2315887C2 (en) 2008-01-27

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20091224