CN1238637C - Structure of compressor cylinder cover - Google Patents
Structure of compressor cylinder cover Download PDFInfo
- Publication number
- CN1238637C CN1238637C CN 02117389 CN02117389A CN1238637C CN 1238637 C CN1238637 C CN 1238637C CN 02117389 CN02117389 CN 02117389 CN 02117389 A CN02117389 A CN 02117389A CN 1238637 C CN1238637 C CN 1238637C
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- cylinder
- compressor
- flange
- fuselage
- main body
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- Expired - Fee Related
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Abstract
The present invention belongs to the field of an air charging device, which particularly relates to a structure of a cylinder cover for a compressor. The present invention is characterized in that a flat end part with a defined area is manufactured at one end of a main body of a compressor body, a through hole is drilled in the compressor body, and one end is provided with an annular groove; one end of a cylinder sleeve with compression space formed in the inner part is provided with a flange of which the area is larger than that of the annular groove. When the cylinder sleeve is arranged in the through hole of the compressor body, the annular groove of the compressor body can form an oil path for cooling oil after the flange of the cylinder sleeve is matched with the flat end surface of the compressor body. The end part of a cylinder cover is provided with a flange with a defined area, which can be matched with the flange of the cylinder sleeve. A sealing pad is clamped in the flange which passes through the component to be fastened to the end part of the plane surface of the compressor body by a bolt. A valve body is arranged in the cylinder cover and can be telescopic in the cylinder sleeve. Because a compressor adopts the structure, the compressor can prevent the phenomenon of oil leakage of the oil path under the condition that cooling oil for cooling compressed air at the upper part of the cylinder and generating high temperature heat quantity flows, and simultaneously, the compressor can also prevent air with high temperature and high pressure in the compression space of the cylinder from leaking. The efficiency and the reliability of the compressor can be improved.
Description
Technical field
The invention belongs to compressor field, particularly relate to a kind of structure of compressor cylinder cover.
Background technique
Present known compressor is the equipment of compressed fluid, and this compressor can be divided into rotary compressor, reciprocal compressor, Scroll-type compressor etc. according to the mode of compressed fluid.When connecting power supply, just make motor produce driving force, and the driving force of motor generation is passed to compressor, in driven compressor, suck air, then compress exhausting air.
Fig. 1 is the compression member schematic representation of prior art compressor.It is by forming with lower member: fuselage 10, and extend and make blunt end part 12 by setting area at an end of main body 11, on main body, be shaped on through hole 13, and the annular groove 14 concentric with through hole 13; The end that the cylinder liner 22 of band compression volume 21 is housed in the cylinder 20 has the flange 23 of setting area; And cylinder liner 22 matches with fuselage through hole 13 and annular groove 14; The interior edge face of the cylinder head flat-top cover 31 of cylinder head 30 matches with the external diameter of the annular boss 24 of cylinder liner, and the one side at its flange 32 and the annular groove place on the fuselage main body 11 matches; A plurality of bolts 40 tighten together cylinder-head flange 32 and fuselage main body 11; Valve body 50 is made up of valve 51, spring 52, is contained in the cylinder head flat-top cover 31, by piston 70 compression cylinders, forms compression volume 21.
The blunt end part 12 of above-mentioned fuselage is to form a plane at an end of fuselage main body 11, and the through hole 13 of annular groove 14 and main body 11 is concentric, and bigger and the corresponding degree of depth arranged than the internal diameter of through hole 13.The external diameter of cylinder liner 22 matches with the internal diameter of the through hole of fuselage 13.The external diameter of cylinder liner flange 23 is littler than the internal diameter of the annular groove 14 of fuselage, and the inner cylindrical surface of the external cylindrical surface of cylinder liner flange 23 and lower plane and annular groove 14 and bottom surface thereof form the oil circuit F of cold oil like this.
Cylinder head flat-top cover 31 inner undersides are shaped on sealing with installation suitable thickness seal ring 60 between the last plane of groove 33 and the cylinder liner flange 23 that is mated, and material is flexible, and when usefulness bolt 40 was fastening, seal ring was compacted and seal.
The working condition of prior art compressor is as follows:
When the driving force of motor passes to piston 70, piston is just done straight reciprocating motion in the scope of the compression volume 21 of cylinder.Along with the variation in pressure of to-and-fro motion generation, by discharging again after the valve body 50 suction air compression.From the high temperature and high pressure gas that cylinder compression volume 21 is discharged, discharge through the exhaust port 34 of cylinder head one side.Because its cooling oil circuit F was formed by the side of fuselage groove 14 and bottom surface 12 external cylindrical surface and the following of cylinder-head flange 32 with cylinder liner flange 23, reveal easily so that be flowing in the oil of oil circuit F, the high temperature and high pressure gas of compression volume is also revealed easily, but also had the shortcoming that to adjust fitted position and change compression volume 21.
Summary of the invention
The present invention provides a kind of structure of compressor cylinder cover for solving the technical problem that exists in the known technology.The technological scheme that the present invention takes for the technical problem that exists in the solution known technology is:
The structure of compressor cylinder cover of the present invention, it comprises compressor fuselage, cylinder, cylinder liner, cylinder head, clamping bolt and valve body; End in the fuselage main body is shaped on the blunt end part of setting area; On main body, be shaped on through hole, and the annular groove concentric with through hole; One end of cylinder liner is shaped on flange, also is provided with the annular boss of certain thickness and height; Cylinder head is provided with relief opening, and the internal diameter of cylinder head matches with the external diameter of cylinder liner annular boss, and cylinder-head flange engages with the cylinder liner flange, and sealing gasket is housed in the middle of it; Clamping bolt passes cylinder head, is fastened on the blunt end part of fuselage end face; Valve body is contained between cylinder head and the cylinder liner, and a valve and spring are arranged; The area of its cylinder liner flange is bigger than the area of annular groove on the fuselage main body.
The present invention can also take following technical measures:
Fuselage main body blunt end part is drilled with the tapped hole that matches with bolt.The cylinder liner external cylindrical surface matches with fuselage through hole cylndrical surface.
Advantage and good effect that the present invention has are:
Owing to taked above technological scheme and technical measures, the structure of compressor cylinder cover of the present invention can prevent the cold oil leakage of the oil circuit that the cylinder upper end portion forms, prevented the leakage of the high temperature and high pressure gas of cylinder compression volume.And, change compression volume by changing its fitted position, improve the compression efficiency of gas, thereby improve the reliability of compressor.
Description of drawings
Fig. 1 is a prior art compressor compresses part end view;
Fig. 2 is a compressor cylinder cover structure end view of the present invention.
Reference character
100 fuselage 100a main body 100b blunt end part 100c through holes
100d annular groove 100e tapped hole 110 cylinders 111 compression volumes
112 cylinder liner, 113 cylinder liner flanges, 114 annular boss, 120 cylinder head
120a cylinder head flat-top cover 120b cylinder-head flange 120c relief opening
130 sealing gaskets, 140 valve bodies, 141 valves, 142 springs
150 bolts, 170 piston Fa oil circuit h holes
For further understanding content characteristic of the present invention, effect, reach embodiment in conjunction with the accompanying drawings and specify as follows:
The structure of compressor cylinder cover of the present invention is by forming as lower member:
Fuselage 100; Packing into, incorporating mill body 100 forms oil circuit Fa within the fuselage 100, and the cylinder 110 of the piston 170 of packing into; Be bonded on the cylinder head 120 above the cylinder 110; Be installed in the sealing gasket 130 between cylinder head 120 and the cylinder 110; Be contained in the valve body 140 in the cylinder head; The bolt 150 of fastening above-mentioned part.
The structural feature of fuselage 100 is as follows: the end of main body 100a has the blunt end part 100b that sets area, and its main body 100a is provided with through hole 100c, and main body 100a one end is provided with the annular groove 100d of certain depth, and annular groove and through hole are concentric.The composition of cylinder 110 is that an end that passes the cylinder liner 112 of cylinder and formation compression volume 111 is provided with the area of its area greater than annular groove 100d, and certain thickness flange 113 is arranged; One end of cylinder liner 112 also is provided with the annular boss 114 of certain thickness and height, and the internal diameter of the internal diameter of its annular boss 114 and compression volume 111 equates.Cylinder liner 112 parts of cylinder 110 are packed in the through hole 100c of fuselage, the blunt end part 100b of its cylinder liner flange 113 and fuselage engages, thereby and bottom surface and the periphery of the annular groove 100d of fuselage, the external cylindrical surface of the following and cylinder liner 112 of cylinder liner flange 113 forms the oil circuit Fa of cold oil.
Cylinder head is made up of following position: the external diameter of the gentle cylinder sleeve annular boss 114 of internal diameter of cylinder head flat-top cover 120a has same size to match, and the end has and cylinder liner flange 113 flange 120b of the same area between sealing gasket 130 is housed, sealing gasket 130 has certain thickness, external diameter equates with the external diameter of cylinder liner flange 113, and the planar annular that the external diameter of the gentle cylinder sleeve annular boss 114 of its internal diameter equates, its material will be selected elastic material for use.The side of cylinder head flat-top cover 120a also has relief opening 120c in addition.
Valve body 140 is made up of the valve 141 and the spring 142 of cylinder compression volume 111.
A plurality of bolts 150 are h holes of passing cylinder-head flange 120b, sealing gasket 130, cylinder liner flange 113, these parts are fastened in the blind tapped hole 100e on the blunt end part 100b of fuselage.
The action effect of compressor cylinder cover of the present invention is as follows:
At first motor force passes on the piston 170, and piston 170 is done straight reciprocating motion in compression volume 111 scopes of cylinder.Along with piston 170 is made straight reciprocating motion generation pressure difference in cylinder compression volume 111, make that valve body 140 is flexible, and the compression volume 111 of cylinder sucks air, and compression back discharge once more.The High Temperature High Pressure air of discharging is discharged through the space of the flat-top cover 120a of cylinder head and the relief opening 120c of one side.The heat that produces during cylinder compression volume 111 air compression is recycled the cold oil in oil circuit Fa and cools off.
Compressor cylinder cover of the present invention is owing to be equipped with sealing gasket 130 between cylinder-head flange 120b and the cylinder liner flange 113, and the internal diameter of cylinder head flat-top cover 120a is installed on the cylinder liner annular boss 114, so can prevent the leakage of high temperature and high pressure gas within cylinder compression volume 111 and the cylinder head flat-top cover 120a.
And cold oil circuit oil circuit Fa, be that the external cylindrical surface by the following and cylinder liner 112 of the bottom surface of fuselage annular groove 100d and circumferential surface and cylinder liner flange 113 forms.So can prevent the leakage of the cold oil of circulating oil path Fa, promptly guarantee the sealability of cooling oil circuit Fa from configuration aspects.
Between cylinder 110 and the fuselage 100, employing can be adjusted the material of installation dimension in addition, thereby can change compression volume 111, can improve gas compression efficient, thereby has improved the reliability of compressor.
Claims (3)
1, a kind of structure of compressor cylinder cover, it comprises compressor fuselage main body, cylinder, cylinder liner, cylinder head, clamping bolt and valve body; End in fuselage main body (100a) is shaped on the blunt end part (100b) of setting area; On the fuselage main body, be shaped on through hole (100c), and the annular groove (100d) concentric with through hole; One end of cylinder liner (112) is shaped on flange, also is provided with the annular boss (114) of certain thickness and height; Cylinder head (120) is provided with relief opening (120c), and the internal diameter of cylinder head (120) matches with the external diameter of cylinder liner (112) annular boss (114), and cylinder-head flange (120b) engages with cylinder liner flange (113), and sealing gasket (130) is housed in the middle of it; Clamping bolt (150) passes cylinder head (120), is fastened on the blunt end part (100b) of fuselage end face; Valve body (140) is contained between cylinder head (120) and the cylinder liner (112), and a valve (141) and spring (142) are arranged; The area that it is characterized in that cylinder liner flange (113) is bigger than the area of the last annular groove (100d) of fuselage main body (100a).
2, the structure of compressor cylinder cover according to claim 1 is characterized in that fuselage main body (100a) blunt end part (100b) is drilled with the tapped hole (100e) that matches with clamping bolt (150).
3, the structure of compressor cylinder cover according to claim 1 is characterized in that cylinder liner (112) external cylindrical surface matches with fuselage through hole (100c) cylndrical surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02117389 CN1238637C (en) | 2002-05-22 | 2002-05-22 | Structure of compressor cylinder cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02117389 CN1238637C (en) | 2002-05-22 | 2002-05-22 | Structure of compressor cylinder cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1459569A CN1459569A (en) | 2003-12-03 |
| CN1238637C true CN1238637C (en) | 2006-01-25 |
Family
ID=29426571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 02117389 Expired - Fee Related CN1238637C (en) | 2002-05-22 | 2002-05-22 | Structure of compressor cylinder cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1238637C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101931627B1 (en) | 2015-03-27 | 2018-12-21 | 가부시키가이샤 덴소 | Rotating cylinder type compressor |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454468B (en) * | 2014-12-12 | 2016-11-09 | 常熟市淼泉压缩机配件有限公司 | Seal cylinder cap |
| RU172523U1 (en) * | 2015-03-25 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | CYLINDER LINER |
| CN106286233B (en) * | 2015-06-08 | 2018-10-02 | 珠海格力电器股份有限公司 | Cylinder assembly, compressor and air conditioner |
| RU172519U1 (en) * | 2015-06-17 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | Piston compressor cylinder liner |
| RU172522U1 (en) * | 2015-09-22 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | CYLINDER LINER |
| CN108087240B (en) * | 2017-12-13 | 2024-02-09 | 重庆均利密封科技有限公司 | Vulcanizing sealing structure of automobile air conditioner compressor and vulcanizing process thereof |
-
2002
- 2002-05-22 CN CN 02117389 patent/CN1238637C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101931627B1 (en) | 2015-03-27 | 2018-12-21 | 가부시키가이샤 덴소 | Rotating cylinder type compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1459569A (en) | 2003-12-03 |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20060125 |