RU97109857A - HELICOPTER SCREW DRIVE REDUCER - Google Patents

HELICOPTER SCREW DRIVE REDUCER

Info

Publication number
RU97109857A
RU97109857A RU97109857/28A RU97109857A RU97109857A RU 97109857 A RU97109857 A RU 97109857A RU 97109857/28 A RU97109857/28 A RU 97109857/28A RU 97109857 A RU97109857 A RU 97109857A RU 97109857 A RU97109857 A RU 97109857A
Authority
RU
Russia
Prior art keywords
screw drive
drive reducer
gears
input shafts
bevel gears
Prior art date
Application number
RU97109857/28A
Other languages
Russian (ru)
Other versions
RU2146636C1 (en
Inventor
Н.Л. Кокшаров
Н.П. Трушников
Е.В. Хромин
Р.З. Хасанов
В.Я. Дворкин
Original Assignee
Открытое акционерное общество "Авиадвигатель"
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель"
Priority to RU97109857A priority Critical patent/RU2146636C1/en
Priority claimed from RU97109857A external-priority patent/RU2146636C1/en
Publication of RU97109857A publication Critical patent/RU97109857A/en
Application granted granted Critical
Publication of RU2146636C1 publication Critical patent/RU2146636C1/en

Links

Claims (1)

Редуктор привода несущего винта вертолета с входными валами для передачи мощности от двигателей, содержащий несколько ступеней и включающий зубчатые передачи и устройство деления подводимого крутящего момента на части, равные числу двигателей, отличающийся тем, что устройство деления выполнено в виде общего вала и конических шестерен, ведомые конические шестерни закреплены на общем валу, а ведущие - на входных валах редуктора, причем число пар конических шестерен в устройстве деления равно числу входных валов редуктора.A helicopter rotor drive reducer with input shafts for transmitting power from engines, comprising several stages and including gears and a device for dividing the input torque into parts equal to the number of engines, characterized in that the division device is made in the form of a common shaft and bevel gears, driven bevel gears are fixed on a common shaft, and the drive gears are fixed on the input shafts of the gearbox, and the number of pairs of bevel gears in the division device is equal to the number of input shafts of the gearbox.
RU97109857A 1997-06-11 1997-06-11 Helicopter rotor gearbox RU2146636C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU97109857A RU2146636C1 (en) 1997-06-11 1997-06-11 Helicopter rotor gearbox

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU97109857A RU2146636C1 (en) 1997-06-11 1997-06-11 Helicopter rotor gearbox

Publications (2)

Publication Number Publication Date
RU97109857A true RU97109857A (en) 1999-05-10
RU2146636C1 RU2146636C1 (en) 2000-03-20

Family

ID=20194098

Family Applications (1)

Application Number Title Priority Date Filing Date
RU97109857A RU2146636C1 (en) 1997-06-11 1997-06-11 Helicopter rotor gearbox

Country Status (1)

Country Link
RU (1) RU2146636C1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2998542B1 (en) * 2012-11-26 2015-07-17 Eurocopter France METHOD AND AIRCRAFT WITH ROTARY WING WITH THREE ENGINES
FR2998543B1 (en) * 2012-11-26 2015-07-17 Eurocopter France METHOD AND AIRCRAFT WITH ROTATING WING WITH TWO MAIN TURBOMOTORS AND A LOWER-POWERED SECONDARY TURBOMOTOR
RU2613099C1 (en) * 2016-02-20 2017-03-15 Акционерное общество "АВИАЦИОННЫЕ РЕДУКТОРА И ТРАНСМИССИИ - ПЕРМСКИЕ МОТОРЫ" (АО "РЕДУКТОР - ПМ") Main reduction gear of helicopter
RU2646696C1 (en) * 2016-11-02 2018-03-06 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Method of synchronization and provision of symmetry of propellers thrust of aircraft power plant and electric synchronizing transmission for its realization

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