RU2347092C2 - Gas turbine engine reducer - Google Patents

Gas turbine engine reducer Download PDF

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Publication number
RU2347092C2
RU2347092C2 RU2007106634/06A RU2007106634A RU2347092C2 RU 2347092 C2 RU2347092 C2 RU 2347092C2 RU 2007106634/06 A RU2007106634/06 A RU 2007106634/06A RU 2007106634 A RU2007106634 A RU 2007106634A RU 2347092 C2 RU2347092 C2 RU 2347092C2
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RU
Russia
Prior art keywords
gear
gears
gearbox
reducer
driven
Prior art date
Application number
RU2007106634/06A
Other languages
Russian (ru)
Other versions
RU2007106634A (en
Inventor
Валерий Алексеевич Кузнецов (RU)
Валерий Алексеевич Кузнецов
Original Assignee
Открытое акционерное общество "Авиадвигатель"
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Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель"
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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Abstract

FIELD: engines and pumps.
SUBSTANCE: gas-turbine engine reducer comprises drive gear installed on input shaft and engaged to fixed intermediate gears, which, in their turn, are engaged to driven gear of internal engagement installed on output shaft of reducer. Intermediate gears are made as double and comprising gears with larger and smaller external diameter of toothing. Larger gear is engaged with drive gear and driven gear of internal engagement, which is installed on external output shaft of reducer. Gear with smaller diameter installed closer to output from reducer is engaged with driven gear of external engagement, which is installed on internal output shaft of reducer. Drive and driven gears are telescopically fixed on shafts with the possibility of self-adjustment on intermediate gears. Intermediate gears are installed in reducer gear on roller bearing on the input side and ball bearing on the output side. At that number of double intermediate gears makes from 3 to 5, and ratio of larger intermediate gear toothing width along pitch circle to width of internal engagement driven gear toothing along pitch circle makes from 1.5 to 3.
EFFECT: higher reliability of reducer.
1 dwg

Description

The invention relates to gearboxes for aircraft turbojet engines.
Known planetary differential gearbox for driving coaxial propellers of an aircraft gas turbine engine (S. A. Vyunov. Design and design of aircraft gas turbine engines, Moscow, "Mechanical Engineering", 1981, p. 497, Fig. 11.7d).
A disadvantage of the known design is its low reliability and increased complexity, since in order to maintain a constant gear ratio from the turbine to the front and rear screws, the rotor blades must be rotated relative to the rotor hub, for this a complex rotor rotor control system is located in the gearbox.
Closest to the claimed one is a coaxial planetary gear with a stopped carrier, in which the drive gear of internal gear mounted on the input shaft is engaged with fixed intermediate (satellite) gears, which are mounted on sliding bearings and in turn are engaged with the driven gear internal gear mounted on the output shaft (US patent No. 6622473 BB dated 12/05/2001).
A disadvantage of the known design adopted for the prototype is its low reliability due to the increased loads on the plain bearings of the intermediate (satellite) gears, which are subject to circumferential forces from both the driving and driven gears, and also due to the unevenness of the loads transmitted from the drive gear to the intermediate (satellite) gears.
The technical problem to which the claimed invention is directed is to increase the reliability of the gearbox of a gas turbine engine by reducing the loads on the bearings of the intermediate (satellite) gears and balancing the loads on these gears.
The essence of the technical solution lies in the fact that in 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 the driven gear of internal gearing mounted on the output shaft of the gearbox, according to the invention, the intermediate gears are double and consisting of a larger and smaller in the outer diameter of the gear ring gears, and the large gear is meshed with the buckets gears with a driven gear of internal gear installed on the external output shaft of the gearbox, and a gear with a smaller diameter located closer to the output from the gearbox is meshed with the driven gear of external gearing installed on the internal output shaft of the gearbox, while the drive gear and driven gears are fixed on the shafts telescopically with the possibility of self-installation on the intermediate gears, and the intermediate gears are installed in the gearbox on the roller on the input side and the ball on the sides exit bearings, wherein: K = 3 ... 5, a H / h = 1,5 ... 3, wherein:
K is the number of double intermediate gears,
H is the width of the gear ring of the larger intermediate gear in a pitch circle.
h is the width of the ring gear of the driven gear of the internal gearing along the pitch circle.
The double gears can be used to divide the power supplied to the gearbox by a larger number of flows (~ 2 times) compared to the gearbox with single-row gears, which reduces the peripheral load on the tooth of the driven gears and increases the reliability of the gearbox.
The implementation of the intermediate gears with a larger and smaller outer diameter of the ring gear allows minimizing the difference in the speed of the external and internal output shafts of the gearbox, which increases the reliability of the fan and gearbox of the gas turbine engine.
Engaged with a larger intermediate gear, the driven gear of internal gearing and located closer to the output of the gearbox, the intermediate gear with a smaller diameter of the ring gear, meshed with the driven gear of the external gear, create circular forces on the teeth of the driven gears, directed in opposite directions, which significantly several times, reduces the load on the axis and on the bearings on which the intermediate gears are installed in the gear housing, which increases the reliability of the gear scrap.
The installation of the intermediate gears in the gear case on roller and ball bearings allows the intermediate gears to be fixed in axial and radial directions and reduces the amount of oil necessary for lubricating the gearbox, thereby increasing the reliability of the gearbox, especially in autorotation modes of a gas turbine engine in conditions of lack of lubrication. In this case, in view of the minimum loads on the support from the output side of the gearbox, the bearing of the intermediate gears from the output side of the gearbox is made ball-shaped, since it has a lower bearing capacity compared to roller.
The installation of the drive and driven gears on the shafts telescopically, with the possibility of self-installation of these gears on the circumferential gears located around the circumference, makes it possible to equalize the transmitted load between all the intermediate gears, which increases the reliability of the gas turbine engine gearbox.
When the number of double intermediate gears K <3, the reliability of the gearbox decreases due to an increase in contact and bending stresses in the teeth of the gearbox, and when K> 5 the gear ratio of the gearbox is reduced, which reduces the efficiency and reliability of the gas turbine engine and gearbox.
At H / h <1.5, the weight of the gearbox unnecessarily increases and reliability decreases due to the increased power transmitted to the external output shaft of the gearbox, and at H / h> 3 the reliability of the gearbox decreases due to increased stresses in the teeth of the driven gear of internal gearing.
The drawing shows a longitudinal section of the gearbox of a gas turbine engine.
The gearbox 1 of the gas turbine engine consists of a pinion gear 2 mounted telescopically, with axial and radial clearances, with the possibility of self-installation using a spline connection 3 on the input shaft 4, as well as driven gears 5 and 6 of the external and internal gears, respectively, mounted telescopically, with the possibility of self-installation using splined joints 7 and 8 on the internal 9 and external 10 output shafts of the gearbox 1. Output shafts 9 and 10 are mounted on rolling bearings 11 and 12, respectively. The drive gear 2 and the driven gears 5 and 6 are meshed with circumferentially arranged double intermediate gears 13, the drive gear 2 and the driven gear 6 of the internal gearing with gear ring 14 are engaged with the larger gear diameter 16 of the outer gear 16 of the intermediate gear 17, located on the side of the input shaft 4, and the driven gear 5 of the external gearing is engaged with a smaller outer diameter of the ring gear 18 of the intermediate gear 19 located on the side of the output shafts 9 and 10. the gears 17 and 19, forming a double intermediate gear 13, are installed in the stationary housing 20 of the gearbox 1 using a ball bearing 21 located on the side of the output shafts 9 and 10, and also using a roller bearing 22 located on the side of the input shaft 4. The number is evenly located around the circumference of the double intermediate gears 13 is selected equal to 3 ... 5, which provides the gear ratio of the gearbox necessary for the gas turbine engine, reduces the load on the gears 16 and 18 of the gears 17 and 19, and also ensures equal Measuring load distribution between the intermediate gears 13.
The device operates as follows. When the gearbox 1 of the gas turbine engine is operating, the transmitted power to the gearbox 1 is transmitted through the shaft 4 through the drive gear 2, which, due to radial clearances along the spline connection 3 with the shaft 4, can self-adjust between the intermediate gears 17 located around the circumference, which contributes to the uniform distribution of the load on these gears , thus increasing the reliability of the gearbox 1. Similarly, the driven gears 5 and 6 are self-adjusting along the intermediate gears 19 and 17. Uniform load distribution m Between the intermediate gears 13 also contributes to the radial compliance of the gears 2, 5 and 6, which are made with a small thickness of the rim. Since the output shafts 9 and 10 of the gearbox 1 rotate in opposite directions, the circumferential forces of the intermediate gear 19 of smaller diameter are partially parried by the circumferential forces of the gears 2 and 4, which significantly reduces the load on the bearings 21 and 22, thereby increasing the reliability of the gearbox 1.

Claims (1)

  1. 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 the internal gear driven gear mounted on the output shaft of the gearbox, characterized in that the intermediate gears are double and consist of a larger and smaller in the outer diameter of the gear ring of gears, the larger gear being engaged with the pinion gear and the driven gear of the internal gear mounted on the external output shaft of the gearbox, and a gear with a smaller diameter located closer to the output from the gearbox is engaged with the driven gear of external gearing mounted on the internal 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 housing on the roller bearings from the input side and ball bearings from the output side, with: K = 3 ... 5, a H / h = 1,5 ... 3, where K is the number double intermediate gears
    N is the width of the gear ring of the larger intermediate gear along the pitch circle,
    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 RU2007106634A (en) 2008-08-27
RU2347092C2 true RU2347092C2 (en) 2009-02-20

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2528236C1 (en) * 2013-08-27 2014-09-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Planetary differential reduction gearbox
RU2532089C1 (en) * 2013-10-29 2014-10-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Differential speed reduction gear of turbo-propeller engine
RU2629620C2 (en) * 2012-05-04 2017-08-30 Пань-чиэнь ЛИНЬ Single-step reduction gearbox with large ratio for aircraft engine
RU2664086C2 (en) * 2013-09-06 2018-08-15 Сафран Эркрафт Энджинз Rotating assembly containing transmission mechanism and oil distribution system
RU2681824C2 (en) * 2014-03-24 2019-03-12 Сафран Эркрафт Энджинз Transmission assembly including transmission member and oil distribution system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2629620C2 (en) * 2012-05-04 2017-08-30 Пань-чиэнь ЛИНЬ Single-step reduction gearbox with large ratio for aircraft engine
RU2528236C1 (en) * 2013-08-27 2014-09-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Planetary differential reduction gearbox
RU2664086C2 (en) * 2013-09-06 2018-08-15 Сафран Эркрафт Энджинз Rotating assembly containing transmission mechanism and 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
RU2681824C2 (en) * 2014-03-24 2019-03-12 Сафран Эркрафт Энджинз Transmission assembly including transmission member and oil distribution system

Also Published As

Publication number Publication date
RU2007106634A (en) 2008-08-27

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

Effective date: 20110222