CN112196674B

CN112196674B - Aviation air turbine starter transmission system

Info

Publication number: CN112196674B
Application number: CN202011079044.XA
Authority: CN
Inventors: 朱露群; 刘彦雪; 袁文科; 李开隆
Original assignee: China Hangfa Changzhou Lanxiang Machinery Co ltd
Current assignee: China Hangfa Changzhou Lanxiang Machinery Co ltd
Priority date: 2020-10-10
Filing date: 2020-10-10
Publication date: 2022-04-29
Anticipated expiration: 2040-10-10
Also published as: CN114635761A; CN115126553A; CN114635761B; CN112196674A

Abstract

The invention relates to an aviation air turbine starter transmission system, which comprises a turbine rotor, a planetary gear assembly, a mounting rack and a central adapter sleeve, the turbine rotor is in transmission fit with the input end of the planetary gear assembly, the output end of the planetary gear assembly is in transmission fit with the tail end of the central adapter sleeve, the overrunning clutch is arranged in the central adapter sleeve, the inner shaft of the clutch is in transmission fit with the inner ring of the overrunning clutch, an oil passing hole for conveying lubricating oil to the overrunning clutch is formed in the side wall of the inner shaft of the clutch, the tail end of the split output shaft assembly is in transmission fit with the front end of the central adapter sleeve, the lubricating oil pump comprises a shell, an impeller and an oil pumping shaft, the shell is fixedly connected with an installation frame, the impeller is fixedly connected with the tail end of the oil pumping shaft, the front end of the oil pumping shaft penetrates through the shell and is in rotation fit with the shell, and the front end of the oil pumping shaft extends into the tail end of the inner shaft of the clutch and is in transmission fit with the inner shaft of the clutch.

Description

Aviation air turbine starter transmission system

Technical Field

The invention relates to the field of air turbine starter transmission systems, in particular to an aviation air turbine starter transmission system.

Background

An air turbine starter is included as part of an aviation auxiliary power system. The working principle of the engine starting system is that high-pressure airflow impacts a turbine of an air turbine starter to drive the turbine to rotate, and power of a transmission chain of the engine starting system is output to drive an engine to start. When the belt-driven starter reaches a certain rotating speed, the air turbine starter stops working and is separated from a transmission chain of an engine starting system, and in the process, the connection and the separation of the transmission chain of the air turbine starter and the transmission chain of the engine starting system are required to be completed; with the development of aircraft engines, the air turbine starter plays an increasingly important role as an important component of an aircraft engine starting system, the development of the starter technology is also developing towards miniaturization, light weight, high power-to-weight ratio, high reliability, strong environmental adaptability, large power ductility, high output torque and the like, the miniaturization and the light weight gradually draw high attention, and the miniaturization and the light weight provide higher requirements for lubrication and heat dissipation of a starter transmission system.

Disclosure of Invention

The invention aims to provide an aviation air turbine starter transmission system which is simple in structure and easy to lubricate and dissipate heat.

In order to solve the technical problem, the aviation air turbine starter transmission system provided by the invention comprises a turbine rotor, a planetary gear assembly, an installation frame, a central adapter sleeve, an overrunning clutch, a clutch inner shaft and a split type output shaft assembly, wherein the turbine rotor is in transmission fit with the input end of the planetary gear assembly, the output end of the planetary gear assembly is in transmission fit with the tail end of the central adapter sleeve, the overrunning clutch is arranged in the central adapter sleeve, the clutch inner shaft is in transmission fit with the inner ring of the overrunning clutch, an oil through hole for conveying lubricating oil to the overrunning clutch is arranged on the side wall of the clutch inner shaft, the tail end of the split type output shaft assembly is in transmission fit with the front end of the central adapter sleeve, a lubricating oil pump comprises a shell, an impeller and a pump oil shaft, the shell is fixedly connected with the installation frame, and the impeller is fixedly connected with the tail end of the pump oil shaft, the front end of the pump oil shaft penetrates through the shell and is in running fit with the shell, the front end of the pump oil shaft extends into the tail end of the inner shaft of the clutch and is in running fit with the inner shaft of the clutch, so that the inner shaft of the clutch drives the pump oil shaft and the impeller to rotate, one side of the mounting frame is provided with an oil inlet channel communicated with the shell, the axis of the pump oil shaft is provided with a through oil passing channel, when the pump oil shaft is used, the turbine rotor is decelerated by the planetary gear assembly and then drives the central adapter sleeve to rotate, the central adapter sleeve drives the overrunning clutch and the inner shaft of the clutch to rotate, the inner shaft of the clutch drives the split output shaft assembly, the pump oil shaft and the impeller to rotate, lubricating oil in the oil inlet channel is introduced into the shell and then pumped into the inner shaft of the clutch through the oil channel, the lubricating oil is sent into the overrunning clutch through the oil hole, and the overrunning clutch is lubricated and cooled.

Furthermore, the planetary gear assembly comprises a driving gear, three duplex planetary gears and a gear ring, the driving gear is in transmission fit with the turbine rotor, the duplex planetary gears comprise a first gear meshed with the driving gear and a second gear meshed with the gear ring, and the axle centers of the duplex planetary gears are in running fit with the mounting rack through gear shafts so that the turbine rotor drives the gear ring to rotate.

Furthermore, the tail end of the clutch inner shaft is provided with a partition plate, the front end of the pump oil shaft is in a square shape, and the center of the partition plate is provided with a square hole matched with the pump oil shaft, so that the pump oil shaft and the partition plate are in plug-in fit, and then the clutch inner shaft drives the pump oil shaft and the impeller to rotate.

Furthermore, the split type output shaft assembly comprises an output long shaft, an output short shaft and a thin safety shaft, wherein a spline which is matched with an inner shaft of the clutch in an inserting mode is arranged at the tail end of the output short shaft, a plurality of transmission ladder teeth are convexly arranged on the end face of the front end of the short shaft, a plurality of transmission grooves matched with the transmission ladder teeth are arranged at the tail end of the output long shaft, shaft holes are axially formed in the shaft centers of the output long shaft and the output short shaft, and two ends of the thin safety shaft are fixedly arranged in the shaft holes of the output long shaft and the output short shaft respectively.

The invention has the technical effects that: (1) compared with the prior art, the aviation air turbine starter transmission system has the advantages that the planetary gear assembly is arranged to reduce speed and increase torque, the overrunning clutch and the clutch inner shaft are connected with the split type output shaft assembly, and the effects of coaxial output, automatic power disengagement at a set rotating speed and overload bidirectional protection are achieved; compared with a reduction gearbox in the traditional sense, the reliability of the whole transmission system is improved and breakthroughs of technologies such as miniaturization and light weight of a starter are strived to be obtained on the premise of realizing the most basic speed reduction and torque increase; (2) the normal operation state of the whole transmission system is that a turbine rotor is connected with a sun gear (driving gear) of a fixed-axis quasi-planetary gear system through an internal spline and an external spline, three duplex planetary gears are arranged outside the sun gear and meshed with the sun gear to improve the strength and rigidity of the whole structure, and a gear ring is connected outside the duplex planetary gears, generally speaking, the planetary gears only rotate and do not revolve, so that the transmission ratio can be conveniently designed, and the problem of high stress caused by high rotating speed can be remarkably reduced; (3) when the rotating speed of the engine is higher than that of the starter, the inner ring and the outer ring of the diagonal-bracing clutch are disengaged, the inner shaft of the clutch continues to rotate along with the engine, and the turbine rotor of the starter and the planetary gear assembly are isolated; (4) the split type output shaft assembly is provided with a thin safety shaft as an overload protection device, and once the overrunning clutch fails and cannot be timely disengaged, the thin safety shaft can be twisted off at a shear-bearing section, so that the damage to the starter and internal components of the engine is effectively prevented; (5) the setting of lubricating oil pump drives pump oil axle and impeller rotation through the clutch inner shaft, realizes the pump oil function to through setting up oily passageway and oil passing hole, pump lubricating oil into freewheel clutch, realize lubricated and heat dissipation.

Drawings

The invention is described in further detail below with reference to the drawings of the specification:

FIG. 1 is a schematic cross-sectional view of an aircraft air turbine starter drive system according to the present invention;

in the figure: the turbine gearbox comprises a turbine casing 1, a speed reduction casing 2, a turbine rotor 3, a driving gear 4, a duplex planetary gear 5, a gear shaft 6, a rolling rod bearing 7, a gear ring 8, a central adapter sleeve 9, a first bearing 10, a second bearing 11, a third bearing 12, an overrunning clutch 13, a clutch inner shaft 14, a split type output shaft assembly 15, a lubricating oil pump 16, an oil inlet channel 17 and a mounting rack 18.

Detailed Description

Example 1

As shown in fig. 1, the aviation air turbine starter transmission system of the embodiment includes a turbine casing 1, a speed reduction casing 2, a turbine rotor 3, a planetary gear assembly, a central adapter sleeve 9, an overrunning clutch 13, a clutch inner shaft 14, and a split output shaft assembly 15, wherein a cage-shaped mounting frame 18 is arranged at the front end of the turbine casing 1, and the mounting frame 18 extends into the speed reduction casing 2; the front end of the turbine rotor 3 extends into the mounting frame 18, and a support bearing is arranged between the turbine rotor 3 and the mounting frame 18, so that the turbine rotor 3 is in rotating fit with the mounting frame 18; the planetary gear assembly comprises a driving gear 4, three duplex planetary gears 5 and a gear ring 8, a turbine rotor spline is arranged at the front end of the turbine rotor 3, a driving gear spline groove matched with the turbine rotor spline is arranged on the axis of the driving gear 4, so that the driving gear 4 can be driven to rotate by the turbine rotor 3 after the turbine rotor 3 is in splicing fit with the driving gear 4 and is used as a power input source of the planetary gear assembly; three duplex planetary gears 5 are uniformly distributed on the same circumference of the edge of the mounting rack 18, a gear shaft 6 is respectively arranged at the center of each duplex planetary gear 5, two ends of each gear shaft 6 are fixedly connected with the mounting rack 18, and the duplex planetary gears 5 are in running fit with the gear shafts 6 through rolling rod bearings 7 so that the duplex planetary gears 5 become fixed-axis planetary gears; each duplex planetary gear 5 comprises a first gear meshed with the driving gear 4 and a second gear meshed with the gear ring 8, the first gear and the second gear are coaxially arranged, the first gear is meshed with the outer wall of the driving gear 4, and the second gear is meshed with the inner wall of the gear ring 8, so that the turbine rotor 3 can drive the gear ring 8 to rotate through the three duplex planetary gears 5.

The central adapter sleeve 9 comprises a connecting disc and a sleeve which are integrally formed, the outer side wall of the connecting disc is provided with an adapter sleeve spline, the inner wall of the front end of the gear ring 8 is provided with a gear ring spline groove matched with the adapter sleeve spline, the connecting disc is in splicing fit with the gear ring 8 so that the gear ring 8 can drive the central adapter sleeve 9 to rotate, the middle part of the outer wall of the sleeve is in rotating fit with the speed reducer casing 2 through a first bearing 10, and the front end of the outer wall of the sleeve is in rotating fit with the speed reducer casing 2 through a second bearing 11 so that the central adapter sleeve 9 can be rotatably arranged in the speed reducer casing 2; wherein the first bearing 10 is a roller bearing without an inner ring, and the second bearing 11 is a roller bearing.

The overrunning clutch 13 is a diagonal bracing type overrunning clutch, the diagonal bracing type overrunning clutch comprises an outer ring, a plurality of wedge blocks and an inner ring, the outer ring of the diagonal bracing type overrunning clutch is nested in the sleeve, a clutch inner shaft spline is arranged on the outer side wall of the middle part of a clutch inner shaft 14, the inner ring is provided with an inner ring spline groove matched with the clutch inner shaft spline, and the clutch inner shaft 14 is in clutch transmission with the clutch inner shaft 14 by the inner ring after being in splicing fit with the inner ring; and third bearings 12 are respectively arranged on two sides of the overrunning clutch 13, an inner shaft 14 of the clutch is in running fit with the inner wall of the sleeve through the third bearings 13, and the third bearings 13 are roller bearings.

The lubricating oil pump 16 comprises a shell, an impeller and a pump oil shaft, the shell is fixedly arranged at the center of a mounting frame 18 through a pin, the impeller is fixedly connected with the tail end of the pump oil shaft, the front end of the pump oil shaft penetrates through the shell and is in rotating fit with the shell, so that the impeller is rotatably arranged in the shell, one side of the mounting frame 18 is provided with an oil inlet channel 17 communicated with the shell and used for providing lubricating oil for the shell, the axis of the pump oil shaft is axially provided with a penetrating oil passage, the tail end of a clutch inner shaft 14 is provided with a partition plate, the front end of the pump oil shaft is arranged in a square shape, the center of the partition plate is provided with a square hole matched with the pump oil shaft, so that after the pump oil shaft is in inserting fit with the partition plate, the clutch inner shaft 14 can drive the pump oil shaft and the impeller to rotate, the lubricating oil is introduced into the shell through the oil inlet channel 17 by the impeller and is sent into the clutch inner shaft 14 through the oil passage, the oil passage is arranged on the side wall in the middle of the clutch inner shaft 14, an oil passing hole used for conveying the lubricating oil to the overrunning clutch 13 is arranged on the side wall in the middle part of the clutch inner shaft 14, lubricating oil enters the overrunning clutch 13 through the oil hole to lubricate and dissipate heat of the overrunning clutch 13.

The split type output shaft assembly 15 comprises an output long shaft, an output short shaft and a thin safety shaft, a spline groove is formed in the middle of the clutch inner shaft 14, and a spline which is in plug-in fit with the spline groove in the clutch inner shaft 14 is arranged at the tail end of the output short shaft, so that the tail end of the output short shaft is in spline fit with the middle of the clutch inner shaft 14; the end face of the front end of the output short shaft is convexly provided with a plurality of transmission ladder teeth, the tail end of the output long shaft is provided with a plurality of transmission grooves matched with the transmission ladder teeth, the axial centers of the output long shaft and the output short shaft are axially provided with shaft holes, and two ends of the thin safety shaft are fixedly arranged in the shaft holes of the output long shaft and the output short shaft through pins respectively for realizing overload protection.

The front end of the turbine case 1 is fixedly connected with the tail end of the speed reducing case 2 and sealed, the front end of the speed reducing case 2 is provided with a graphite seal, and the front end of the output long shaft extends out of the graphite seal.

When the turbine rotor 3 is used, the speed of the turbine rotor is reduced by the planetary gear assembly, the central adapter sleeve 9 is driven to rotate, the central adapter sleeve 9 drives the overrunning clutch 13 and the clutch inner shaft 14 to rotate, the clutch inner shaft 14 drives the split output shaft assembly 15, the oil pumping shaft and the impeller to rotate, lubricating oil in the oil inlet channel is introduced into the shell, then the lubricating oil is pumped into the clutch inner shaft 14 through the oil channel and is sent into the overrunning clutch 13 through the oil hole, and the overrunning clutch 13 is lubricated and cooled; when the rotating speed of the engine is higher than that of the starter, the inner ring and the outer ring of the inclined strut clutch 13 are disengaged, the inner shaft 14 of the clutch continuously rotates along with the engine and the split type output shaft assembly 15, and the turbine rotor 3 of the starter and the planetary gear assembly are isolated; once the overrunning clutch 13 fails and cannot be timely disengaged, the thin safety shaft of the split output shaft assembly 15 is twisted off, and the embedded separation surface of the output long shaft and the output short shaft is rapidly separated, so that secondary damage to the starter is avoided, overload protection is realized, and the safety of the starter is protected.

It should be understood that the above examples are only for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And such obvious variations or modifications which fall within the spirit of the invention are intended to be covered by the scope of the present invention.

Claims

1. An aviation air turbine starter transmission system is characterized by comprising a turbine rotor, a planetary gear assembly, an installation frame, a central adapter sleeve, an overrunning clutch, a clutch inner shaft and a split output shaft assembly, wherein the turbine rotor is in transmission fit with an input end of the planetary gear assembly, an output end of the planetary gear assembly is in transmission fit with a tail end of the central adapter sleeve, the overrunning clutch is arranged in the central adapter sleeve, the clutch inner shaft is in transmission fit with an inner ring of the overrunning clutch, an oil passing hole for conveying lubricating oil to the overrunning clutch is formed in the side wall of the clutch inner shaft, a tail end of the split output shaft assembly is in transmission fit with the front end of the central adapter sleeve, a lubricating oil pump comprises a shell, an impeller and a pump oil shaft, the shell is fixedly connected with the installation frame, and the impeller is fixedly connected with the tail end of the pump oil shaft, the front end of the pump oil shaft penetrates through the shell and is in running fit with the shell, the front end of the pump oil shaft extends into the tail end of the inner shaft of the clutch and is in running fit with the inner shaft of the clutch, so that the inner shaft of the clutch drives the pump oil shaft and the impeller to rotate, one side of the mounting frame is provided with an oil inlet channel communicated with the shell, the axis of the pump oil shaft is provided with a through oil passing channel, when the pump oil shaft is used, the turbine rotor is decelerated by the planetary gear assembly and then drives the central adapter sleeve to rotate, the central adapter sleeve drives the overrunning clutch and the inner shaft of the clutch to rotate, the inner shaft of the clutch drives the split type output shaft assembly, the pump oil shaft and the impeller to rotate, lubricating oil in the oil inlet channel is introduced into the shell and then is pumped into the inner shaft of the clutch through the oil channel, and then is sent into the overrunning clutch through the oil hole;

the tail end of the clutch inner shaft is provided with a partition plate, the front end of the pump oil shaft is in a square shape, and the center of the partition plate is provided with a square hole matched with the pump oil shaft, so that the pump oil shaft and the partition plate are in plug-in fit, and then the clutch inner shaft drives the pump oil shaft and the impeller to rotate.

2. The aircraft air turbine starter drive system of claim 1 wherein the planetary gear assembly includes a drive gear in driving engagement with the turbine rotor, three duplicate planet gears including a first gear in meshing engagement with the drive gear and a second gear in meshing engagement with the ring gear, and a ring gear, the axis of each duplicate planet gear being in rotational engagement with the mounting bracket via a gear shaft such that the turbine rotor drives the ring gear to rotate.

3. The aviation air turbine starter transmission system according to claim 1 or 2, wherein the split output shaft assembly comprises an output long shaft, an output short shaft and a thin safety shaft, a spline which is in plug fit with the clutch inner shaft is arranged at the tail end of the output short shaft, a plurality of transmission stepped teeth are convexly arranged on the end surface of the front end of the short shaft, a plurality of transmission grooves which are matched with the transmission stepped teeth are arranged at the tail end of the output long shaft, shaft holes are axially arranged at the axes of the output long shaft and the output short shaft, and two ends of the thin safety shaft are respectively and fixedly arranged in the shaft holes of the output long shaft and the output short shaft.