CN114635761B - Aviation starter transmission system - Google Patents
Aviation starter transmission system Download PDFInfo
- Publication number
- CN114635761B CN114635761B CN202210343696.2A CN202210343696A CN114635761B CN 114635761 B CN114635761 B CN 114635761B CN 202210343696 A CN202210343696 A CN 202210343696A CN 114635761 B CN114635761 B CN 114635761B
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- Prior art keywords
- shaft
- clutch
- oil
- inner shaft
- adapter sleeve
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 49
- 239000007858 starting material Substances 0.000 title claims abstract description 27
- 239000003921 oil Substances 0.000 claims abstract description 61
- 239000010687 lubricating oil Substances 0.000 claims abstract description 15
- 238000005086 pumping Methods 0.000 claims description 25
- 239000003638 chemical reducing agent Substances 0.000 claims description 10
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000005192 partition Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000005461 lubrication Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/02—Adaptations for driving vehicles, e.g. locomotives
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
- Retarders (AREA)
Abstract
The invention relates to an aviation starter transmission system which comprises a turbine rotor, a planetary gear assembly, a mounting 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 passing hole for conveying lubricating oil to the overrunning clutch is formed in 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 a central connecting sleeve, a lubricating oil pump comprises a shell, an impeller and a pump oil shaft, the shell is fixedly connected with the mounting frame, 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 rotation fit with the shell, and the front end of the pump oil shaft stretches into the tail end of the clutch inner shaft and is in transmission fit with the clutch inner shaft.
Description
Technical Field
The invention relates to the field of air turbine starter transmission systems, in particular to an aviation starter transmission system.
Background
An air turbine starter is included as part of an aeronautical auxiliary power system. The working principle is that the turbine of the air turbine starter is impacted by high-pressure air flow to drive the turbine to rotate, and the power of a shaft is output to a transmission chain of an engine starting system to drive the engine to start. When the belt-driven engine reaches a certain rotating speed, the air turbine starter stops working and is separated from the transmission chain of the engine starting system, and in the process, the engagement 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 aeroengines, air turbine starters play an increasingly important role as important component parts of aeroengine starting systems, and the development of starter technology also increasingly develops towards miniaturization, light weight, high power-to-weight ratio, high reliability, strong environmental adaptability, large power ductility, high output torque and the like, so that miniaturization and light weight gradually draw great importance, and the miniaturization and light weight put higher demands on lubrication and heat dissipation of starter transmission systems.
Disclosure of Invention
The invention aims to solve the technical problem of providing an aviation starter transmission system which is simple in structure and easy to lubricate and radiate.
In order to solve the technical problems, the aviation starter transmission system comprises a turbine rotor, a planetary gear assembly, a mounting frame, a center 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 center adapter sleeve, the overrunning clutch is arranged in the center adapter sleeve, the clutch inner shaft 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 clutch inner shaft, the tail end of the split type output shaft assembly is in transmission fit with the front end of the center adapter sleeve, the lubricating oil pump comprises a shell, an impeller and a pump oil shaft, the shell is fixedly connected with the mounting frame, 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 stretches into the tail end of the clutch inner shaft and is in transmission fit with the clutch inner shaft, so that the clutch inner shaft drives the pump oil shaft and rotates, one side of the mounting frame is in transmission fit with the inner shaft, an oil inlet channel communicated with the inner shaft of the overrunning clutch inner shaft is in transmission sleeve, an oil passing hole is formed in the shell, and the overrunning clutch inner shaft is driven by the clutch inner shaft and the clutch inner shaft through the clutch sleeve, and the clutch inner shaft is driven by the clutch inner shaft to rotate, and the overrunning clutch sleeve, and the overrunning clutch passes through the clutch inner shaft and the clutch sleeve, and the clutch oil pump sleeve rotates.
Further, the planetary gear assembly comprises a driving gear, three duplex planetary gears and a gear ring, wherein 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 center of each duplex planetary gear is in running fit with the mounting frame through a gear shaft so that the turbine rotor drives the gear ring to rotate.
Further, the tail end of the clutch inner shaft is provided with a partition board, the front end of the oil pumping shaft is square, and a square hole matched with the oil pumping shaft is formed in the center of the partition board, so that after the oil pumping shaft is in plug-in fit with the partition board, the clutch inner shaft drives the oil pumping shaft and the impeller to rotate.
Further, split type output shaft subassembly includes output major axis, output minor axis and thin safe axle, and the tail end of output minor axis sets up and peg graft complex spline with the clutch in, and the protrusion sets up a plurality of transmission ladder teeth on the terminal surface of minor axis front end, and the tail end of output major axis sets up a plurality of transmission recesses with transmission ladder tooth looks adaptation, and the axle center of output major axis and output minor axis sets up the shaft hole along the axial, and the both ends of thin safe axle are fixed respectively in the shaft hole of output major axis and output minor axis.
The invention has the technical effects that: (1) Compared with the prior art, the aviation starter transmission system has the advantages that the planetary gear assembly is arranged to reduce speed and increase torque, and the overrunning clutch is connected with the split type output shaft assembly through the inner shaft of the clutch, so that the effects of coaxial output, automatic power disengagement at a given rotating speed and bidirectional overload protection are achieved; compared with the reduction gearbox in the traditional sense, the reliability of the whole transmission system is improved and the breakthrough of technologies such as miniaturization and light weight of the starter are striven for on the premise of realizing the most basic speed reduction and torque increase; (2) The normal running state of the whole transmission system is that a turbine rotor is connected with a sun gear (a driving gear) of a fixed-axis quasi-planetary gear train 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 instead of revolve, so that the transmission ratio can be conveniently designed, and the high stress problem caused by high rotating speed is remarkably reduced; (3) An inclined strut overrunning clutch is arranged between the central adapter sleeve and the clutch inner shaft, when the rotation speed of the engine is higher than that of the starter, the inner ring and the outer ring of the inclined strut clutch are disengaged, the clutch inner shaft 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 designed with a thin safety shaft as an overload protection device, once the overrunning clutch fails and cannot be separated in time, the thin safety shaft can be twisted off at the shear section, so that the damage of the starter and internal components of the engine is effectively prevented; (5) The lubricating oil pump is arranged, the oil pumping shaft and the impeller are driven to rotate through the clutch inner shaft, the oil pumping function is realized, and the lubricating oil is pumped into the overrunning clutch through the oil passing channel and the oil passing hole, so that lubrication and heat dissipation are realized.
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 starter drive system of the present invention;
In the figure: the device comprises a turbine casing 1, a speed reducer casing 2, a turbine rotor 3, a driving gear 4, a duplex planetary gear 5, a gear shaft 6, a roller 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 frame 18.
Detailed Description
Example 1
As shown in fig. 1, the aviation starter transmission system of the embodiment comprises a turbine casing 1, a speed reducer 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 type 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 reducer casing 2; the front end of the turbine rotor 3 stretches 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 running 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, wherein a turbine rotor spline is arranged at the front end of the turbine rotor 3, and a driving gear spline groove matched with the turbine rotor spline is arranged at the axis of the driving gear 4, so that the turbine rotor 3 can drive the driving gear 4 to rotate after the turbine rotor 3 is in plug-in fit with the driving gear 4, and the driving gear is used as a power input source of the planetary gear assembly; the three duplex planetary gears 5 are uniformly distributed on the same circumference of the edge of the mounting frame 18, the centers of the duplex planetary gears 5 are respectively provided with a gear shaft 6, two ends of the gear shaft 6 are fixedly connected with the mounting frame 18, and the duplex planetary gears 5 are in rotary fit with the gear shaft 6 through the roller bearings 7 so that the duplex planetary gears 5 are formed into 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, wherein 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, an adapter sleeve spline is arranged on the outer side wall of the connecting disc, a gear ring spline groove matched with the adapter sleeve spline is arranged on the inner wall of the front end of the gear ring 8, the connecting disc is in plug-in 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 rotary 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 rotary 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 overrunning clutch, the diagonal bracing overrunning clutch comprises an outer ring, a plurality of wedge blocks and an inner ring, the outer ring of the diagonal bracing overrunning clutch is nested in the sleeve, an inner shaft spline of the clutch is arranged on the outer side wall of the middle part of the inner shaft 14 of the clutch, an inner ring spline groove matched with the inner shaft spline of the clutch is arranged on the inner ring, and clutch transmission is carried out by the inner ring and the inner shaft 14 of the clutch after the inner shaft 14 of the clutch is in plug-in fit with the inner ring; the two sides of the overrunning clutch 13 are respectively provided with a third bearing 12, the clutch inner shaft 14 is in running fit with the inner wall of the sleeve through the third bearing 13, and the third bearing 13 is a roller bearing.
The lubricating oil pump 16 comprises a shell, an impeller and an oil pumping shaft, wherein 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 oil pumping shaft, the front end of the oil pumping shaft penetrates through the shell and is in running fit with the shell so that the impeller can be rotatably arranged in the shell, an oil inlet channel 17 communicated with the shell is arranged on one side of the mounting frame 18 and is used for providing lubricating oil for the shell, the axial center of the oil pumping shaft is provided with an oil passing channel penetrating through the oil passing channel along the axial direction, the tail end of the clutch inner shaft 14 is provided with a baffle plate, the front end of the oil pumping shaft is square, the center of the baffle plate is provided with a square hole matched with the oil pumping shaft, so that after the oil pumping shaft is in plug-in fit with the baffle plate, the clutch inner shaft 14 can drive the oil pumping shaft and the impeller to rotate, the lubricating oil is led 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, and an oil passing hole used for conveying lubricating oil to the overrunning clutch 13 is arranged on the side wall in the middle of the clutch inner shaft 14, and lubricating and radiating the overrunning clutch 13 is carried out through the oil passing through the oil hole.
The split output shaft assembly 15 comprises an output long shaft, an output short shaft and a thin An Quanzhou, wherein 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 provided with a plurality of transmission ladder teeth in a protruding mode, the tail end of the output long shaft is provided with a plurality of transmission grooves matched with the transmission ladder teeth, the axes of the output long shaft and the output short shaft are provided with shaft holes along the axial direction, and two ends of the thin safety shaft are respectively fixedly arranged in the shaft holes of the output long shaft and the output short shaft through pins and used for achieving overload protection.
The front end of the turbine casing 1 is fixedly connected with the tail end of the speed reducer casing 2 and is sealed, the front end of the speed reducer casing 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 turbine rotor is decelerated by the planetary gear assembly and then drives the center adapter sleeve 9 to rotate, the center 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 and the pump oil shaft to rotate, lubricating oil in the oil inlet channel is introduced into the shell and then pumped into the clutch inner shaft 14 through the oil channel, and is sent into the overrunning clutch 13 through the oil hole to lubricate and dissipate heat of the overrunning clutch 13; when the rotation 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 clutch inner shaft 14 continues to rotate 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 separated in time, the thin safety shaft of the split output shaft assembly 15 is twisted off, the embedded separation surfaces of the output long shaft and the output short shaft are rapidly separated, secondary damage to the starter is avoided, overload protection is realized, and the safety of the starter is protected.
It is apparent that the above examples are merely illustrative of the present invention and are not limiting of the embodiments of the present invention. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious changes and modifications which come within the spirit of the invention are desired to be protected.
Claims (3)
1. The utility model provides an aviation starter transmission system, its characterized in that includes turbine shell, speed reduction box, turbine rotor, planetary gear assembly, mounting bracket, central adapter sleeve, overrunning clutch, clutch inner shaft, split type output shaft subassembly, turbine rotor and planetary gear assembly's input transmission cooperation, planetary gear assembly's output with the tail end transmission cooperation of central adapter sleeve, overrunning clutch is arranged in central adapter sleeve, clutch inner shaft with overrunning clutch's inner circle transmission cooperation, clutch inner shaft's lateral wall is provided with and is used for to overrunning clutch carries lubricating oil's oil passing hole, split type output shaft subassembly's tail end and central adapter sleeve's front end transmission cooperation, and the lubricating oil pump includes casing, impeller and pump oil axle, the shell is fixedly connected with the mounting 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 running fit with the shell, the front end of the oil pumping shaft stretches into the tail end of the clutch inner shaft and is in transmission fit with the clutch inner shaft, so that the clutch inner shaft drives the oil pumping shaft and the impeller to rotate, one side of the mounting frame is provided with an oil inlet channel communicated with the shell, the axle center of the oil pumping shaft is provided with a penetrating oil passage, when the oil pumping device is used, the turbine rotor drives the center adapter sleeve to rotate after being decelerated by the planetary gear assembly, the center adapter sleeve drives the overrunning clutch and the clutch inner shaft to rotate, the clutch inner shaft drives the split type output shaft assembly, the oil pumping shaft and the impeller to rotate, lubricating oil in the oil inlet channel is pumped into the clutch inner shaft through the oil passage after being led into the shell, and is sent into the overrunning clutch through the oil hole;
The tail end of the clutch inner shaft is provided with a baffle plate, the front end of the oil pumping shaft is square, and the center of the baffle plate is provided with a square hole matched with the oil pumping shaft, so that the oil pumping shaft and the baffle plate are in plug-in fit, and the clutch inner shaft drives the oil pumping shaft and the impeller to rotate;
The planetary gear assembly comprises a driving gear, three duplex planetary gears and a gear ring, wherein 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 center of each duplex planetary gear is in running fit with the mounting frame through a gear shaft so that the turbine rotor drives the gear ring to rotate;
the center adapter sleeve comprises a connecting disc and a sleeve which are integrally formed, an adapter sleeve spline is arranged on the outer side wall of the connecting disc, a gear ring spline groove matched with the adapter sleeve spline is formed in the inner wall of the front end of the gear ring, the connecting disc is in plug-in fit with the gear ring, so that the gear ring can drive the center adapter sleeve to rotate, and the outer wall of the sleeve is in running fit with the speed reducer casing through a bearing, so that the center adapter sleeve can be rotatably arranged in the speed reducer casing.
2. The aircraft starter transmission system according to claim 1, wherein the overrunning clutch comprises an outer ring, a plurality of wedges and an inner ring, the outer ring of the overrunning clutch is nested in the sleeve, an inner shaft spline of the clutch is arranged on the outer side wall of the middle part of the inner shaft of the clutch, an inner ring spline groove matched with the inner shaft spline of the clutch is arranged on the inner ring, and the inner shaft of the clutch is engaged with the inner ring in a plugging manner and then is driven by the inner ring and the inner shaft of the clutch; and the two sides of the overrunning clutch are respectively provided with a third bearing, and the inner shaft of the clutch is in running fit with the inner wall of the sleeve through the third bearings.
3. The transmission system of claim 1 or 2, wherein the split output shaft assembly comprises an output long shaft, an output short shaft and a thin safety shaft, the tail end of the output short shaft is provided with a spline which is in plug-in fit with the clutch inner shaft, the end face of the front end of the short shaft is provided with a plurality of transmission ladder teeth in a protruding mode, the tail end of the output long shaft is provided with a plurality of transmission grooves which are matched with the transmission ladder teeth, the axes of the output long shaft and the output short shaft are provided with shaft holes along the axial direction, and two ends of the thin safety shaft are respectively fixedly arranged in the shaft holes of the output long shaft and the output short shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210343696.2A CN114635761B (en) | 2020-10-10 | 2020-10-10 | Aviation starter transmission system |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011079044.XA CN112196674B (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system |
| CN202210343696.2A CN114635761B (en) | 2020-10-10 | 2020-10-10 | Aviation starter transmission system |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011079044.XA Division CN112196674B (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114635761A CN114635761A (en) | 2022-06-17 |
| CN114635761B true CN114635761B (en) | 2024-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011079044.XA Active CN112196674B (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system |
| CN202210343696.2A Active CN114635761B (en) | 2020-10-10 | 2020-10-10 | Aviation starter transmission system |
| CN202210345424.6A Pending CN115126553A (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system easy to lubricate |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011079044.XA Active CN112196674B (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210345424.6A Pending CN115126553A (en) | 2020-10-10 | 2020-10-10 | Aviation air turbine starter transmission system easy to lubricate |
Country Status (1)
| Country | Link |
|---|---|
| CN (3) | CN112196674B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112196674B (en) * | 2020-10-10 | 2022-04-29 | 中国航发常州兰翔机械有限责任公司 | Aviation air turbine starter transmission system |
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| US5199309A (en) * | 1990-12-28 | 1993-04-06 | Mitsubishi Denki K.K. | Starter unit |
| CN201277131Y (en) * | 2008-11-04 | 2009-07-22 | 槐立明 | 24V permanent magnet speed reduction starter for vehicle and agricultural vehicle |
| CN201582026U (en) * | 2009-12-23 | 2010-09-15 | 郑州金辰机电技术有限公司 | Cantilever-type planetary reduction mining explosion-proof starter |
| CN103899366A (en) * | 2014-03-17 | 2014-07-02 | 夏兴旺 | Turbo machinery stepless speed regulator |
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| CN112196674A (en) * | 2020-10-10 | 2021-01-08 | 中国航发常州兰翔机械有限责任公司 | Aviation air turbine starter transmission system |
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| US5267433A (en) * | 1992-03-25 | 1993-12-07 | Allied-Signal, Inc. | Air turbine starter having a dual clutch |
| AT4792U1 (en) * | 2000-05-17 | 2001-11-26 | Tesma Motoren Getriebetechnik | REDUCTION GEARBOX FOR A STARTER GENERATOR OF AN INTERNAL COMBUSTION ENGINE |
| US8105018B2 (en) * | 2008-02-13 | 2012-01-31 | Honeywell International Inc. | Decoupler devices to prevent backdrive in air turbine starters |
| US8475116B2 (en) * | 2010-07-23 | 2013-07-02 | Hamilton Sundstrand Corporation | Anti-rotation feature for air turbine starter |
| CN105402070B (en) * | 2015-12-14 | 2018-05-29 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of air turbine starter clutch transmission |
| US10495182B2 (en) * | 2017-05-09 | 2019-12-03 | Unison Industries, Llc | Planetary gear system and air turbine starter |
| US20190032566A1 (en) * | 2017-07-26 | 2019-01-31 | Unison Industries, Llc | Air turbine starter |
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2020
- 2020-10-10 CN CN202011079044.XA patent/CN112196674B/en active Active
- 2020-10-10 CN CN202210343696.2A patent/CN114635761B/en active Active
- 2020-10-10 CN CN202210345424.6A patent/CN115126553A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5199309A (en) * | 1990-12-28 | 1993-04-06 | Mitsubishi Denki K.K. | Starter unit |
| CN201277131Y (en) * | 2008-11-04 | 2009-07-22 | 槐立明 | 24V permanent magnet speed reduction starter for vehicle and agricultural vehicle |
| CN201582026U (en) * | 2009-12-23 | 2010-09-15 | 郑州金辰机电技术有限公司 | Cantilever-type planetary reduction mining explosion-proof starter |
| CN103899366A (en) * | 2014-03-17 | 2014-07-02 | 夏兴旺 | Turbo machinery stepless speed regulator |
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| CN204783412U (en) * | 2015-06-17 | 2015-11-18 | 象山欧泰汽车电器有限公司 | High lubricated planetary gear reducer starter |
| CN109219695A (en) * | 2016-05-24 | 2019-01-15 | 赛峰直升机发动机公司 | The aircraft turbine engine of planetary reduction gear with variable deceleration ratio |
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| CN115126553A (en) * | 2020-10-10 | 2022-09-30 | 中国航发常州兰翔机械有限责任公司 | Aviation air turbine starter transmission system easy to lubricate |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114635761A (en) | 2022-06-17 |
| CN112196674B (en) | 2022-04-29 |
| CN112196674A (en) | 2021-01-08 |
| CN115126553A (en) | 2022-09-30 |
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