RU2007106634A - GAS TURBINE ENGINE REDUCER - Google Patents

GAS TURBINE ENGINE REDUCER Download PDF

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Publication number
RU2007106634A
RU2007106634A RU2007106634/06A RU2007106634A RU2007106634A RU 2007106634 A RU2007106634 A RU 2007106634A RU 2007106634/06 A RU2007106634/06 A RU 2007106634/06A RU 2007106634 A RU2007106634 A RU 2007106634A RU 2007106634 A RU2007106634 A RU 2007106634A
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RU
Russia
Prior art keywords
gear
gearbox
gears
intermediate gears
driven
Prior art date
Application number
RU2007106634/06A
Other languages
Russian (ru)
Other versions
RU2347092C2 (en
Inventor
Валерий Алексеевич Кузнецов (RU)
Валерий Алексеевич Кузнецов
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
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Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2007106634/06A priority Critical patent/RU2347092C2/en
Publication of RU2007106634A publication Critical patent/RU2007106634A/en
Application granted granted Critical
Publication of RU2347092C2 publication Critical patent/RU2347092C2/en

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Claims (1)

Редуктор газотурбинного двигателя с установленной на входном валу ведущей шестерней, находящейся в зацеплении с неподвижными промежуточными шестернями, которые, в свою очередь, находятся в зацеплении с ведомой шестерней внутреннего зацепления, установленной на выходном валу редуктора, отличающийся тем, что промежуточные шестерни выполнены двойными и состоящими из большей и меньшей по внешнему диаметру зубчатого венца шестерен, причем большая шестерня находится в зацеплении с ведущей шестерней и с ведомой шестерней внутреннего зацепления, установленной на внешнем выходном валу редуктора, а расположенная ближе к выходу из редуктора шестерня с меньшим диаметром находится в зацеплении с ведомой шестерней внешнего зацепления, установленной на внешнем выходном валу редуктора, при этом ведущая и ведомые шестерни закреплены на валах телескопически с возможностью самоустановки на промежуточных шестернях, а промежуточные шестерни установлены в корпусе редуктора на роликовом со стороны входа и шариковом со стороны выхода подшипниках, при этом: K=3...5, a H/h=1,5...3,The gearbox of a gas turbine engine with a drive gear installed on the input shaft, meshed with stationary intermediate gears, which, in turn, are meshed with an internal gear driven gear mounted on the output shaft of the gearbox, characterized in that the intermediate gears are double and consisting of the larger and smaller gears in the outer diameter of the ring gear, the larger gear meshing with the pinion gear and with the driven gear of the inner gear a gear mounted on the external output shaft of the gearbox, and a gear with a smaller diameter located closer to the output of the gearbox is engaged with the driven gear of external gearing mounted on the external output shaft of the gearbox, while the drive and driven gears are telescopically mounted on the shafts with the possibility of self-installation on intermediate gears, and intermediate gears are installed in the gear case on the roller from the input side and ball bearings from the output side, with: K = 3 ... 5, a H / h = 1,5 ... 3, где K - число двойных промежуточных шестерен,where K is the number of double intermediate gears, Н - ширина зубчатого венца большей промежуточной шестерни по делительной окружности,N is the width of the gear ring of the larger intermediate gear along the pitch circle, h - ширина зубчатого венца ведомой шестерни внутреннего зацепления по делительной окружности.h is the width of the ring gear of the driven gear of the internal gearing along the pitch circle.
RU2007106634/06A 2007-02-21 2007-02-21 Gas turbine engine reducer RU2347092C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2007106634/06A RU2347092C2 (en) 2007-02-21 2007-02-21 Gas turbine engine reducer

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2007106634/06A RU2347092C2 (en) 2007-02-21 2007-02-21 Gas turbine engine reducer

Publications (2)

Publication Number Publication Date
RU2007106634A true RU2007106634A (en) 2008-08-27
RU2347092C2 RU2347092C2 (en) 2009-02-20

Family

ID=40531960

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2007106634/06A RU2347092C2 (en) 2007-02-21 2007-02-21 Gas turbine engine reducer

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RU (1) RU2347092C2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TW201346155A (en) * 2012-05-04 2013-11-16 Pan-Chien Lin Single-stage large-ratio reducer gearbox for aero engine
RU2528236C1 (en) * 2013-08-27 2014-09-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Planetary differential reduction gearbox
FR3010449B1 (en) * 2013-09-06 2015-09-25 Snecma ROTARY ASSEMBLY COMPRISING A TRANSMISSION MEMBER AND AN OIL DISTRIBUTION SYSTEM
RU2532089C1 (en) * 2013-10-29 2014-10-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Differential speed reduction gear of turbo-propeller engine
FR3018861B1 (en) * 2014-03-24 2016-04-08 Snecma TRANSMISSION ASSEMBLY COMPRISING A TRANSMISSION MEMBER AND AN OIL DISTRIBUTION SYSTEM

Also Published As

Publication number Publication date
RU2347092C2 (en) 2009-02-20

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

Effective date: 20110222