CN113154007A - Central transmission bevel gear shaft of aero-engine and mounting structure thereof - Google Patents
Central transmission bevel gear shaft of aero-engine and mounting structure thereof Download PDFInfo
- Publication number
- CN113154007A CN113154007A CN202110512266.4A CN202110512266A CN113154007A CN 113154007 A CN113154007 A CN 113154007A CN 202110512266 A CN202110512266 A CN 202110512266A CN 113154007 A CN113154007 A CN 113154007A
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- Prior art keywords
- bevel gear
- gear shaft
- central
- engine
- conical part
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- Pending
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 66
- 238000013016 damping Methods 0.000 claims abstract description 9
- 238000000354 decomposition reaction Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 6
- 238000009434 installation Methods 0.000 description 9
- 238000013024 troubleshooting Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H55/00—Elements with teeth or friction surfaces for conveying motion; Worms, pulleys or sheaves for gearing mechanisms
- F16H55/02—Toothed members; Worms
- F16H55/17—Toothed wheels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/021—Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Gear Transmission (AREA)
Abstract
The application provides an aeroengine central authorities transmission bevel gear axle includes: the bevel gear shaft body is provided with a conical part forming a preset angle with the axis of the engine, the end part of the conical part is provided with a transmission gear, and a back conical part is formed between the transmission gear and the conical part; the bevel gear shaft comprises a bevel gear shaft body, wherein one side of a transmission gear of the bevel gear shaft body is provided with a first bulge extending towards the axis direction of an engine, a drawing groove used for assembling and disassembling a central transmission bevel gear shaft is formed between the first bulge and a conical part, and an annular groove capable of installing a damping ring is formed in a back conical part. The central transmission bevel gear shaft can remarkably improve the decomposition manufacturability, can avoid the problems of damage to the back conical surface, stress concentration and the like in the decomposition process of the central transmission bevel gear, and improves the service performance and the service life of the central transmission bevel gear shaft.
Description
Technical Field
The application belongs to the technical field of aero-engine transmission structures, and particularly relates to a central transmission bevel gear shaft of an aero-engine and a mounting structure of the central transmission bevel gear shaft.
Background
The central transmission gear shaft is an important force transmission component between an aircraft engine rotor and an accessory transmission system, and mainly has the functions of transmitting power and torque between the engine rotor shaft and an engine accessory, the central transmission driving bevel gear shaft is positioned in an engine and matched with a high-pressure rotor, the structural size is limited by the structural space in a bearing cavity of the engine, the working time is the same as that of the engine, and the performance of the central transmission gear shaft directly influences the service performance and the service life of the engine.
A typical central drive bevel gear shaft 20 is shown in fig. 1, and generally has only a basic structure for accomplishing power and torque transmission, and does not design a functional structure considering manufacturability, adaptability such as decomposition, and the like. As shown in fig. 2, the central drive bevel gear shaft 20 is mated to a high pressure spool 21, which is supported by bearings 22 on a mounting block 23, the mounting block 23 being mounted to a case 24.
However, since the central driving bevel gear shaft 20 is inside the aircraft engine, the working environment is complicated and harsh due to the influence of vibration, temperature and rotation speed changes when the engine works, and the disassembly and assembly processes of each engine need to be completed along with the disassembly and reassembly of the engine. The central transmission driving bevel gear shaft in the prior art is realized by drawing the back conical surface when being disassembled, has poor decomposition manufacturability, is easy to cause surface damage of the back conical surface and generate stress concentration, and influences the service performance and the service life of the bevel gear shaft; and the bevel gear shaft does not have the function of adjusting the resonance rotating speed, and when the resonance failure occurs in the working process, the bevel gear shaft which can be replaced in situ in the engine needs to be newly designed, so that the workload is large, the cost is high, and the period is long.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine central drive bevel gear shaft and mounting structure therefor to address or mitigate at least one of the problems of the background art.
In one aspect, the present application provides an aircraft engine central drive bevel gear shaft, the central drive bevel gear shaft includes:
the bevel gear shaft body is provided with a conical part forming a preset angle with the axis of the engine, the end part of the conical part is provided with a transmission gear, and a back conical part is formed between the transmission gear and the conical part;
the bevel gear shaft comprises a bevel gear shaft body, wherein one side of a transmission gear of the bevel gear shaft body is provided with a first bulge extending towards the axis direction of an engine, a drawing groove used for assembling and disassembling a central transmission bevel gear shaft is formed between the first bulge and a conical part, and an annular groove capable of installing a damping ring is formed in a back conical part.
Further, the preset angle between the conical part and the engine axis is adjusted according to the structural parameters of the central transmission of the aircraft engine.
In a preferred embodiment of the present application, the first protrusion has a rectangular cross section.
Further, the height of the first protrusion is not less than 5 mm.
In a preferred embodiment of the present application, the annular groove has a rectangular cross-section.
In the preferred embodiment of this application, the one side that the bevel gear axle body kept away from the driving tooth has the second arch to keeping away from the extension of engine axis direction, the second arch is used for forming the bearing axis limit structure who installs on central transmission bevel gear axle.
On the other hand, the application provides a mounting structure who has aeroengine central authorities transmission bevel gear axle as above arbitrary, its characterized in that: the high-pressure rotor is installed on the inner side of the central transmission bevel gear shaft, the supporting bearing is installed on the outer side of the central transmission bevel gear shaft, the supporting bearing is installed on the bearing installation seat, and the bearing installation seat is fixed on the casing.
The central transmission bevel gear shaft can remarkably improve the decomposition manufacturability, can avoid the problems of damage to a back conical surface, stress concentration and the like in the decomposition process of the central transmission bevel gear, and improves the service performance and the service life of the central transmission bevel gear shaft; in addition, if the central transmission structure is found to have resonance in the test and working processes, a damping ring can be directly added on the central transmission bevel gear shaft to adjust the resonance rotating speed, the structural adaptability is obviously improved, and the problems of repeated design, long troubleshooting period and the like are solved.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of a central drive bevel gear shaft structure of the prior art.
Fig. 2 is a schematic view of a central drive bevel gear shaft mounting structure of the prior art.
Fig. 3 is a schematic view of the central drive bevel gear shaft structure of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve the problems that the central transmission bevel gear shaft in the prior art has poor installation manufacturability and is easy to damage, and after vibration is generated in a test, the test period length caused by disassembly and repair processing is long, the application provides the central transmission bevel gear shaft capable of overcoming the aeroengine.
As shown in fig. 3, the central driving bevel gear shaft 10 provided by the present application includes a bevel gear shaft body 11, the bevel gear shaft body 11 has a taper portion forming a predetermined angle with the engine axis, the end portion of the taper portion has a driving gear 12, a back taper portion 18 is formed between the driving gear 12 and the taper portion, wherein the bevel gear shaft body 11 has a first protrusion 13 extending toward the engine axis on one side of the driving gear 12, a drawing groove 14 for mounting and dismounting the central driving bevel gear shaft 10 is formed between the first protrusion 13 and the taper portion, and meanwhile, an annular groove 15 capable of mounting a damping ring 16 is formed on the back taper portion 18 of the gear shaft body 11.
The utility model provides a draw groove 14 through having set up at central transmission bevel gear axle 10, can with the dress card of central transmission bevel gear axle 10 decompose frock (not shown) cooperation to improve the decomposition efficiency and the manufacturability of central transmission bevel gear axle 10, solved drawing back of typical central transmission bevel gear axle 20 the conical surface and decomposed the problem that the gear shaft led to the fact the damage, improved the performance and the life-span of central transmission bevel gear axle.
In addition, the annular groove 15 is arranged at the back cone 18 of the central transmission bevel gear shaft 10, so that a damping ring (a damping ring structure is shown by a dotted line) for adjusting the resonance rotating speed is installed on the damping ring, if the resonance problem of the central transmission structure (a driving bevel gear and a driven bevel gear) is found in the test and working process of an aeroengine, the damping ring 16 can be directly added on the central transmission bevel gear shaft 20 to adjust the resonance rotating speed, the adaptability of the central transmission structure is obviously improved, and the problems of repeated design, long troubleshooting period and the like are solved.
It should be noted that, in the central transmission bevel gear shaft of the present application, the preset angle between the conical portion and the engine axis may be adjusted according to structural parameters of the central transmission of the aircraft engine, such as the installation space size of the central transmission, or the transmission power of the central transmission.
In the preferred embodiment of the present application, the first protrusion 13 of the left inner portion of the bevel gear shaft body 11 has a rectangular cross-section. It is understood that the cross section of the first protrusion 13 may have other shapes, such as a trapezoid, but the first protrusion 13 with a trapezoid structure and the drawing slot 14 formed by the bevel gear shaft body 11 are easy to slide when being assembled with a disassembling tool, and the use effect is not as good as that of the first protrusion 13 with a rectangular structure.
In a further preferable mode of the above embodiment, the height of the first protrusion 13 is not less than 5mm, so that the disassembling tool can form a larger contact surface with the first protrusion 13.
Furthermore, one side of the bevel gear shaft body 11, which is far away from the transmission gear 12, is provided with a second protrusion 17 extending towards the direction far away from the axis of the engine, and the second protrusion 17 is used for forming a bearing axis limiting structure installed on the central transmission bevel gear shaft 10.
Finally, the application also provides an installation structure of the central transmission bevel gear shaft 10 of the aircraft engine, in the installation structure, a high-pressure rotor is installed on the inner side of the central transmission bevel gear shaft 10, a support bearing is installed on the outer side of the central transmission bevel gear shaft 10, the support bearing is installed on a bearing installation seat, and the bearing installation seat is fixed on a casing, so that the installation of the central transmission bevel gear shaft 10 is realized.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A central drive bevel gear shaft for an aircraft engine, characterized in that said central drive bevel gear shaft (10) comprises:
a bevel gear shaft body (11), wherein the bevel gear shaft body (11) is provided with a conical part forming a preset angle with the axis of the engine, the end part of the conical part is provided with a transmission gear (12), and a back conical part (18) is formed between the transmission gear (12) and the conical part;
the bevel gear shaft comprises a bevel gear shaft body (11), wherein one side of a transmission gear (12) is provided with a first protrusion (13) extending towards the axial direction of an engine, a drawing groove (14) used for assembling and disassembling a central transmission bevel gear shaft (10) is formed between the first protrusion (13) and a conical part, and an annular groove (15) capable of installing a damping ring (16) is formed in a back conical part (18).
2. The aircraft engine central transmission bevel gear shaft according to claim 1 wherein the predetermined angle between said tapered portion and the engine axis is adjusted according to structural parameters of the aircraft engine central transmission.
3. The central driving bevel gear shaft for aircraft engines according to claim 1, characterized in that the first elevation (13) has a rectangular cross section.
4. The aeroengine central transmission bevel gear shaft according to claim 3 wherein the height of said first projection (13) is not less than 5 mm.
5. The central transmission bevel gear shaft of an aircraft engine according to claim 1, characterized in that the annular groove (15) is rectangular in cross-section.
6. The aircraft engine central drive bevel gear shaft according to claim 1, characterized in that the side of the bevel gear shaft body (11) remote from the drive teeth (12) is provided with a second projection (17) extending in a direction remote from the engine axis, said second projection (17) being intended to form a bearing axis stop mounted on the central drive bevel gear shaft (10).
7. A mounting structure having the central drive bevel gear shaft (10) of an aircraft engine according to any one of claims 1 to 6, characterized in that: the high-pressure rotor is installed to the inboard of central transmission bevel gear axle (10) the support bearing is installed to the outside of central transmission bevel gear axle (10), the support bearing is installed in the bearing mount pad, the bearing mount pad is fixed in on the machine casket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110512266.4A CN113154007A (en) | 2021-05-11 | 2021-05-11 | Central transmission bevel gear shaft of aero-engine and mounting structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110512266.4A CN113154007A (en) | 2021-05-11 | 2021-05-11 | Central transmission bevel gear shaft of aero-engine and mounting structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113154007A true CN113154007A (en) | 2021-07-23 |
Family
ID=76874428
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110512266.4A Pending CN113154007A (en) | 2021-05-11 | 2021-05-11 | Central transmission bevel gear shaft of aero-engine and mounting structure thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113154007A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001162551A (en) * | 1999-12-08 | 2001-06-19 | Sharp Corp | Gear drawout tool |
| CN205315667U (en) * | 2016-01-15 | 2016-06-15 | 中国航空动力机械研究所 | Main drive bevel gear mechanism |
| CN208276824U (en) * | 2018-05-30 | 2018-12-25 | 湖南中特液力传动机械有限公司 | Draw horse screw rod and variable speed fluid coupling maintenance with drawing horse |
| CN208831643U (en) * | 2018-09-14 | 2019-05-07 | 杭州意美汽车部件有限公司 | A kind of noise abatement bevel gear with spherical involute configuration |
| CN209195932U (en) * | 2018-11-29 | 2019-08-02 | 深圳市金骏腾科技有限公司 | A kind of reducer output shaft gear |
| CN111022611A (en) * | 2019-12-05 | 2020-04-17 | 中国航发四川燃气涡轮研究院 | Aviation bevel gear opening damping ring |
-
2021
- 2021-05-11 CN CN202110512266.4A patent/CN113154007A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001162551A (en) * | 1999-12-08 | 2001-06-19 | Sharp Corp | Gear drawout tool |
| CN205315667U (en) * | 2016-01-15 | 2016-06-15 | 中国航空动力机械研究所 | Main drive bevel gear mechanism |
| CN208276824U (en) * | 2018-05-30 | 2018-12-25 | 湖南中特液力传动机械有限公司 | Draw horse screw rod and variable speed fluid coupling maintenance with drawing horse |
| CN208831643U (en) * | 2018-09-14 | 2019-05-07 | 杭州意美汽车部件有限公司 | A kind of noise abatement bevel gear with spherical involute configuration |
| CN209195932U (en) * | 2018-11-29 | 2019-08-02 | 深圳市金骏腾科技有限公司 | A kind of reducer output shaft gear |
| CN111022611A (en) * | 2019-12-05 | 2020-04-17 | 中国航发四川燃气涡轮研究院 | Aviation bevel gear opening damping ring |
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Application publication date: 20210723 |