RU2017121550A - Turbofan engine - Google Patents

Turbofan engine Download PDF

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Publication number
RU2017121550A
RU2017121550A RU2017121550A RU2017121550A RU2017121550A RU 2017121550 A RU2017121550 A RU 2017121550A RU 2017121550 A RU2017121550 A RU 2017121550A RU 2017121550 A RU2017121550 A RU 2017121550A RU 2017121550 A RU2017121550 A RU 2017121550A
Authority
RU
Russia
Prior art keywords
gas generator
auxiliary
gears
compressor
shaft
Prior art date
Application number
RU2017121550A
Other languages
Russian (ru)
Other versions
RU2711895C2 (en
RU2017121550A3 (en
Inventor
Изфат Изфатович Мифтахов
Борис Анатольевич Середа
Original Assignee
Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение"
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 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" filed Critical Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение"
Priority to RU2017121550A priority Critical patent/RU2711895C2/en
Publication of RU2017121550A publication Critical patent/RU2017121550A/en
Publication of RU2017121550A3 publication Critical patent/RU2017121550A3/ru
Application granted granted Critical
Publication of RU2711895C2 publication Critical patent/RU2711895C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (1)

Двухконтурный турбореактивный двигатель, содержащий газогенератор внутреннего контура с компрессором, камерой сгорания и турбиной, соединенной валом газогенератора с компрессором, промежуточный корпус и вентилятор, соединенный валом с турбиной вентилятора, вспомогательные агрегаты с приводом от вала газогенератора внутреннего контура через центральный конический привод и набор шестерен, отличающийся тем, что вспомогательные агрегаты установлены на кольцевом разделителе промежуточного корпуса, а набор шестерен для привода вспомогательных агрегатов размещен внутри кольцевого разделителя.A dual-circuit turbojet engine containing an internal circuit gas generator with a compressor, a combustion chamber and a turbine connected by a gas generator shaft to a compressor, an intermediate casing and a fan connected by a shaft with a fan turbine, auxiliary units driven by an internal circuit gas generator shaft through a central bevel drive and a set of gears, characterized in that the auxiliary units are mounted on an annular spacer of the intermediate housing, and a set of gears for driving the auxiliary The underbody units are located inside the annular separator.
RU2017121550A 2017-06-19 2017-06-19 Double-flow jet turbine engine RU2711895C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2017121550A RU2711895C2 (en) 2017-06-19 2017-06-19 Double-flow jet turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2017121550A RU2711895C2 (en) 2017-06-19 2017-06-19 Double-flow jet turbine engine

Publications (3)

Publication Number Publication Date
RU2017121550A true RU2017121550A (en) 2019-08-19
RU2017121550A3 RU2017121550A3 (en) 2019-08-19
RU2711895C2 RU2711895C2 (en) 2020-01-23

Family

ID=67640719

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2017121550A RU2711895C2 (en) 2017-06-19 2017-06-19 Double-flow jet turbine engine

Country Status (1)

Country Link
RU (1) RU2711895C2 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926947A (en) * 1961-11-27 1963-05-22 Rolls Royce Improvements relating to gas turbine engine casings
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
RU2157905C2 (en) * 1994-01-17 2000-10-20 Акционерное общество закрытого типа "Энерготех" Gas-turbine engine
FR2824362B1 (en) * 2001-05-03 2003-09-05 Snecma Moteurs ARRANGEMENT FOR MOUNTING TWO COAXIAL SHAFT LINES
US20050183540A1 (en) * 2004-02-25 2005-08-25 Miller Guy W. Apparatus for driving an accessory gearbox in a gas turbine engine
FR2907167B1 (en) * 2006-10-13 2011-11-18 Snecma GEARBOX DRIVE SHAFT OF AUXILIARY MACHINES OF A TURBOJET ENGINE; MODULAR SUPPLEMENTARY AUXILIARY MACHINE

Also Published As

Publication number Publication date
RU2711895C2 (en) 2020-01-23
RU2017121550A3 (en) 2019-08-19

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