CN210013989U

CN210013989U - High-pressure-level gear of aircraft engine

Info

Publication number: CN210013989U
Application number: CN201920267446.9U
Authority: CN
Inventors: 周勇; 张波; 万慧嘉
Original assignee: Nanjing Rue Aviation Machinery Equipment Co Ltd
Current assignee: Nanjing Rue Aviation Machinery Equipment Co Ltd
Priority date: 2019-03-04
Filing date: 2019-03-04
Publication date: 2020-02-04
Anticipated expiration: 2029-03-04

Abstract

The utility model discloses a transmission gear box for an aeroengine, a connecting cavity is arranged in the transmission gear box, a gear shaft and a bearing are arranged in the connecting cavity, one end of the gear shaft is connected on the bearing, the other end is connected with a transmission gear, and the outer ring of the bearing is in interference fit with the inner wall of the connecting cavity; the gear shaft is provided with an oil inlet, a hollow pipe is arranged inside the gear shaft along the axial direction, and the hollow pipe is communicated with the oil inlet; the transmission gear is provided with a plurality of radial holes along the radial direction, the plurality of radial holes penetrate through the top of the transmission gear, and the plurality of radial holes are communicated with the hollow pipe. The utility model discloses a drive gear's the teeth of a cogwheel provide sufficient, even lubrication, avoid gear top wearing and tearing, improved the security of drive gear box work, prolonged drive gear box's life simultaneously.

Description

High-pressure-level gear of aircraft engine

Technical Field

The utility model relates to a gear drive technical field, concretely relates to aeroengine high pressure level gear.

Background

The gear is used for transmitting motion and power between the shafts, the airplane needs larger power when in operation, the gear is needed to be used in a power transmission system of the airplane, and the power output by the gear in transmission is more direct. However, the teeth in the common gear are designed into a right-angle shape, are not wear-resistant, cannot be well lubricated and cooled by contact lubricating oil in transmission, and are extremely easy to wear in the long-time rotating process, so that the problems of serious tooth wear, power reduction, precision reduction and the like in the gear are caused.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aeroengine high pressure level gear to solve one of the above-mentioned multinomial defect or defect that leads to among the prior art.

The high-pressure gear of the aircraft engine comprises a gear, a gear shaft and an internal gear, wherein the gear shaft and the internal gear are integrally formed;

the gear is of a hollow structure, a fixing sleeve is arranged at one end of the gear, the fixing sleeve and the gear are integrally formed, external threads are arranged inside the gear, internal threads are arranged at one end, away from the internal gear, of the gear shaft, the internal threads are matched with the external threads, and the gear is mounted on the gear shaft;

the gear includes the tooth, the cross-section of tooth is established to the square, the tooth includes profile of tooth and dedendum, profile of tooth and dedendum are integrated into one piece, profile of tooth is equipped with the radian of outside hunch-up, the four corners of dedendum all is equipped with the chamfer.

Preferably, the fixing sleeve is provided with a fixing hole.

Preferably, one end of the gear shaft close to the inner gear is provided with a spline groove for fixing.

Preferably, the gear shaft is internally provided with a hollow structure.

Preferably, a fixing pin is arranged in the fixing hole and extends to the inside of the gear shaft.

Preferably, the gear is made of SCM chromium molybdenum alloy steel.

Preferably, the pitch of the gear is 15 mm.

Preferably, the surface roughness of the gear is 1.0 um.

Compared with the prior art, the utility model discloses the beneficial effect who reaches:

1. the tooth profile of the gear is outwards provided with a certain radian, so that the contact area between the teeth is reduced, the friction of the gear is further reduced, and the service life of the gear is prolonged;

2. the tooth profile of the gear is outwards provided with a certain radian, which is beneficial to improving the lubrication and reducing the temperature generated by friction;

3. the gear and the gear shaft are more convenient to disassemble due to the arrangement of the internal thread and the external thread.

4. The abrasion of the gear is reduced, and the precision of the gear in operation is improved.

Drawings

FIG. 1 is a block diagram of the present invention;

FIG. 2 is a gear structure view;

FIG. 3 is a gear shaft schematic;

fig. 4 is an enlarged schematic view of the teeth.

In the figure: 1. a gear; 2. a gear shaft; 3. a spline groove; 4. an internal gear; 5. a fixing hole; 6. an internal thread; 7. an external thread; 8. a fixing pin; 11. teeth; 111. tooth profile; 112. a tooth root; 1121. chamfering; 12. and (4) fixing sleeves.

Detailed Description

The present invention will be further described with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.

It should be noted that, in the description of the present invention, the terms "front", "rear", "left", "right", "upper", "lower", "inner", "outer", etc. indicate the directions or positional relationships based on the directions or positional relationships shown in the drawings, and are only for convenience of description of the present invention but do not require the present invention to be constructed and operated in a specific direction, and thus, should not be construed as limiting the present invention. As used in the description of the present invention, the terms "front," "back," "left," "right," "up," "down" and "in" refer to directions in the drawings, and the terms "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.

As shown in fig. 1-4, the high-pressure-stage gear of the aircraft engine comprises a gear 1, a gear shaft 2 and an internal gear 4, wherein the gear shaft 2 and the internal gear 4 are integrally formed; the design of the internal gear 4 can improve the universality of the gear shaft 2, and when the gear 1 is used as a driven gear, other rotating devices can be driven by the internal gear 4;

the gear 1 is internally hollow, one end of the gear 1 is provided with a fixing sleeve 12 which is internally hollow and is used for being sleeved on the gear shaft 2, the fixing sleeve 12 and the gear 1 are integrally formed, external threads 7 are arranged inside the gear 1, threads are also arranged inside the fixing sleeve 12, one end of the gear shaft 2, which is far away from the internal gear 4, is provided with internal threads 6, the internal threads 6 are matched with the external threads 7, the gear 1 is arranged on the gear shaft 2, and the gear 1 is in threaded connection with the gear shaft 2, so that the disassembly is convenient;

the gear 1 comprises teeth 11, the section above the teeth 11 is square, the gears 1 are prevented from sliding when being meshed, the teeth 11 comprise tooth profiles 111 and tooth roots 112, the teeth 11, the tooth profiles 111 and the tooth roots 112 are integrally formed, the machining process is simplified, the toughness degree and the service life of the gears 1 are improved, the tooth profiles 111 are provided with outwards arched radians, the abrasion caused by mutual friction of the teeth 11 is reduced when the teeth 11 and the tooth profiles 111 of the gears 1 are in contact, and chamfers 1121 are arranged at four corners of the tooth roots 112, so that stress caused by transmission is reduced.

In this embodiment, the fixing sleeve 12 is provided with a fixing hole 5, and the fixing hole 5 is arranged corresponding to the fixing hole on the gear shaft 2, so as to prevent the gear 1 from being damaged due to the gap generated when the gear 1 rotates. One end of the gear shaft 2 close to the internal gear 4 is provided with a spline groove 3 for fixing, and the spline groove 3 can fix the gear shaft 2 and other transmission equipment through splines, so that the transmission effect is more obvious. The gear shaft 2 is internally of a hollow structure, so that the weight is reduced. A fixing pin 8 is arranged in the fixing hole 5, the fixing pin 8 extends into the gear shaft 2, and the gear 1 and the gear shaft 2 are fixed again through the fixing pin 8. Gear 1's material is SCM440 chromium molybdenum alloy steel, and ordinary material causes the snap of tooth 11 easily when long-time use to lead to producing and producing the hidden danger in the safety, SCM440 chromium molybdenum alloy steel can improve gear 1's life, reduces the potential safety hazard, and improve equipment operation rate further improves the efficiency of work. The pitch of the gear 1 is 15 mm; the surface roughness of gear is 1.0um, improves and turns to than, and is more accurate at driven process, reduces the error when gear 11 moves.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be considered as the protection scope of the present invention.

Claims

1. The high-pressure-level gear of the aircraft engine is characterized by comprising a gear (1), a gear shaft (2) and an internal gear (4), wherein the gear shaft (2) and the internal gear (4) are integrally formed;

the gear (1) is of a hollow structure, a fixing sleeve (12) is arranged at one end of the gear (1), the fixing sleeve (12) and the gear (1) are integrally formed, external threads (7) are arranged inside the gear (1), internal threads (6) are arranged at one end, away from the internal gear (4), of the gear shaft (2), the internal threads (6) are matched with the external threads (7), and the gear (1) is installed on the gear shaft (2);

the gear (1) comprises teeth (11), the cross section of each tooth (11) is square, each tooth (11) comprises a tooth profile (111) and a tooth root (112), the tooth profiles (111) and the tooth roots (112) are integrally formed, each tooth profile (111) is provided with an outwards arched radian, and four corners of each tooth root (112) are provided with chamfers (1121); the fixed sleeve (12) is provided with a fixed hole (5); and a spline groove (3) for fixing is formed in one end, close to the inner gear (4), of the gear shaft (2).

2. An aeroengine high pressure stage gear according to claim 1, wherein the gear shaft (2) is internally hollow.

3. An aircraft engine high pressure stage gear according to claim 1, characterised in that a fixing pin (8) is provided in the fixing hole (5) and the fixing pin (8) extends to the inside of the gear shaft (2).

4. An aircraft engine high-pressure stage gear according to claim 1, characterized in that the material of the gear (1) is SCM440 chrome molybdenum alloy steel.

5. An aeroengine high pressure stage gear according to claim 1, wherein the pitch of the gear (1) is 15 mm.

6. An aircraft engine high pressure stage gear according to claim 1, characterised in that the surface roughness of the gear (1) is 1.0 um.