CN214196977U

CN214196977U - Compressor bearing bush oiling structure

Info

Publication number: CN214196977U
Application number: CN202022857375.3U
Authority: CN
Inventors: 曹坡坡; 石德勋; 程亚亚; 任小兵; 赵周露; 程瑶
Original assignee: Chongqing Gas Compressor Factory Co Ltd
Current assignee: Chongqing Gas Compressor Factory Co Ltd
Priority date: 2020-12-01
Filing date: 2020-12-01
Publication date: 2021-09-14
Anticipated expiration: 2030-12-01

Abstract

The utility model provides a compressor axle bush oiling structure, including installing the oiling manifold in the fuselage outside and seting up the oiling mouth in fuselage axle bush below, intercommunication between oiling mouth and the oiling manifold, oiling mouth and axle bush place space intercommunication. Because the oiling collector in this scheme sets up outside the fuselage in this scheme, when carrying out the jam inspection of pipeline like this, just need not to unpack whole fuselage apart, it is convenient to overhaul, reduces cost of maintenance. Because set up the organism on the organism under the axle bush with the oiling mouth, and oiling mouth and axle bush place space intercommunication, so not only can realize the heat dissipation and the lubrication etc. of axle bush, can also make pipeline such as oiling point and oiling manifold avoid the bent axle, compare with current set up the oiling point in the bearing cap position, avoid pipeline and compressor bent axle to bump, reduced the oil leak possibility, use safe and reliable more.

Description

Compressor bearing bush oiling structure

Technical Field

The utility model belongs to the compressor field especially relates to a compressor axle bush oiling structure

Background

The oil injection points of the existing compressor bearing bush are generally arranged on a bearing cap outside the machine body, then all the oil injection points are led into the machine body through a connecting pipe and communicated with an oil injection manifold arranged in the machine body, and the oil injection manifold is connected to the bearing bush position of the compressor so as to lubricate and cool the bearing bush. However, as the pipelines (such as a connecting pipe and an oil injection manifold) of lubricating oil in the machine body are more, the machine body is very easy to collide with a crankshaft of the compressor, and when the pipeline blockage condition of the lubricating oil or other faults are detected, the whole machine body needs to be disassembled to judge the blockage position or fault position of the lubricating oil pipeline inside the machine body, and the checking process is troublesome and labor-consuming.

SUMMERY OF THE UTILITY MODEL

In view of the above prior art's shortcoming, the utility model aims to provide a compressor axle bush oiling structure for solve prior art compressor pipeline and bump scheduling problem with the bent axle easily.

In order to realize above-mentioned purpose and other relevant purposes, the utility model provides a compressor axle bush oiling structure, including installing the oiling manifold in the fuselage outside and seting up the oiling mouth in fuselage axle bush below, communicate between oiling mouth and the oiling manifold, oiling mouth and axle bush place space intercommunication.

Furthermore, oiling mouths are formed in two sides of the machine body, and two oiling mouths are correspondingly arranged on each bearing bush.

Furthermore, two oil injection ports corresponding to each bearing bush are communicated through an oil pipe, and the oil pipe is communicated with the space where the bearing bush is located.

Furthermore, both sides of the machine body are provided with oil injection manifolds, and the oil injection manifolds are communicated with oil injection ports on the corresponding side of the oil injection manifolds.

Furthermore, the oil filling manifold is communicated with the oil filling port through a flow dividing pipe.

Further, the oil filling header is communicated with the oil tank.

As above, the utility model discloses a compressor axle bush oiling structure has following beneficial effect:

because the oiling manifold in this scheme sets up outside the fuselage, when carrying out the jam inspection of pipeline like this, just need not to unpack whole fuselage apart, it is convenient to overhaul, reduces cost of maintenance.

Because set up the organism on the organism under the axle bush with the oiling mouth, and oiling mouth and axle bush place space intercommunication, so not only can realize the heat dissipation and the lubrication etc. of axle bush, can also make pipeline such as oiling point and oiling manifold avoid the bent axle, compare with current set up the oiling point in the bearing cap position, avoid pipeline and compressor bent axle to bump, reduced the oil leak possibility, use safe and reliable more.

Drawings

Fig. 1 is the utility model discloses a schematic diagram of the section of compressor axle bush oiling structure in the embodiment.

Fig. 2 is a cross-sectional view taken at a-a in fig. 1.

Fig. 3 is the utility model discloses the structural schematic diagram of compressor axle bush oiling structure in the embodiment.

Detailed Description

Reference numerals in the drawings of the specification include: the oil injection device comprises a machine body 1, an oil injection port 2, a bearing bush 3, a crankshaft 4, an oil pipe 5, a bearing cap 6, an oil injection manifold 7 and a shunt pipe 9.

The following description is provided for illustrative purposes, and other advantages and features of the present invention will become apparent to those skilled in the art from the following detailed description.

Examples

As shown in fig. 1 to 3, the present embodiment provides a compressor bearing shell oil injection structure, including: the oil injection port 2 is arranged outside the machine body 1, the oil injection ports 2 are arranged on two sides of the outside of the machine body 1 below the bearing bush 3, the oil injection ports 2 on two sides of the machine body 1 are arranged on the same horizontal line and communicated through an oil pipe 5, and the oil pipe 5 is communicated with the space where the bearing bush 3 is arranged. Both sides are provided with oiling manifold 7 respectively outside fuselage 1, and oiling manifold 7 is connected with each oiling mouth 2 of its place one side, and two oiling manifolds 7 collect and communicate between the oil tank (the crankcase of compressor acts as the oil tank effect, and the crankcase is just the oil tank in this scheme promptly). Two oiling mouths 2 have been seted up to 1 both sides of fuselage to each bearing bush 3 correspondence promptly, and two oiling mouths 2 all are located on its fuselage 1 that corresponds under bearing bush 3, and each oiling mouth 2 all realizes the intercommunication with oiling tandem 7 through shunt tubes 9.

During the concrete implementation, because the oiling collector 7 in this scheme sets up outside fuselage 1, when carrying out the jam inspection of pipeline like this, just need not to unpack whole fuselage 1 apart, the inspection is convenient. In addition, set up oiling mouth 2 on fuselage 1 under axle bush 3, then realize the intercommunication with axle bush 3 space through oil pipe 5, just so avoided bent axle 4 like this, compare with current set up oiling point in bearing cap 6 position, avoid pipeline and compressor bent axle 4 to bump, reduced the oil leak possibility.

The above embodiments are merely illustrative of the principles and effects of the present invention, and are not to be construed as limiting the invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.

Claims

1. The utility model provides a compressor axle bush oiling structure which characterized in that, including installing the oiling manifold in the fuselage outside and seting up the oiling mouth in fuselage axle bush below, communicate between oiling mouth and the oiling manifold, oiling mouth and axle bush place the space intercommunication.

2. The compressor bearing shell oil injection structure according to claim 1, wherein oil injection ports are formed in both sides of the machine body, and two oil injection ports are correspondingly formed in each bearing shell.

3. The compressor bearing shell oil injection structure according to claim 2, wherein two oil injection ports corresponding to each bearing shell are communicated with each other through an oil pipe, and the oil pipe is communicated with a space where the bearing shell is located.

4. The compressor bearing shell oil injection structure according to claim 3, wherein oil injection manifolds are arranged on both sides of the machine body, and the oil injection manifolds are communicated with the oil injection ports on the corresponding sides of the oil injection manifolds.

5. The compressor bearing shell oil injection structure according to any one of claims 1 to 4, wherein the oil injection manifold and the oil injection port are communicated through a shunt pipe.

6. The compressor bearing shell oil injection structure according to claim 1, wherein the oil injection manifold is communicated with an oil tank.