CN1459569A - Structure of compressor cylinder cover - Google Patents
Structure of compressor cylinder cover Download PDFInfo
- Publication number
- CN1459569A CN1459569A CN 02117389 CN02117389A CN1459569A CN 1459569 A CN1459569 A CN 1459569A CN 02117389 CN02117389 CN 02117389 CN 02117389 A CN02117389 A CN 02117389A CN 1459569 A CN1459569 A CN 1459569A
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- cylinder
- fuselage
- flange
- compressor
- cylinder head
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Abstract
A structure of cylinder cover for compressor features that after a sylinder sleeve with a flange and a machine body with a smooth end face part, through holes and ring slot are assembled together, said ring slot becomes cooling oil channel, the cylinder cover has a sealing pad and a flange matched with the flange of cylinder sleeve, and a valve installed in cylinder cover can be telescopic in cylinder sleeve. Its advantage is no leakage of cooling oil and high-temp and -perssure gas.
Description
Technical field
The invention belongs to the inflator 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-tupe 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 selected known compressor.It is made up of following component: fuselage 10, and set area at an end of main body 11 and extend and make blunt end part 12, on main body, make through hole 13, and the annular groove 14 concentric with through hole 13; Cylinder 20, in the flange 23 that has an end of the cylinder liner 22 of compression volume to have to set area and cylinder liner 22 thereof can and fuselage through hole 13 and annular groove 14 match; Cylinder head 30, the external diameter of the interior edge face energy of flat cover 31 of cylinder head and the annular boss 24 of cylinder liner matches, 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 has valve 51, and spring 52 is contained in and leans on piston 70 telescopic cylinders, compression volume 21 in the cylinder head flat-top cover 31.
The blunt end part 12 of above-mentioned fuselage is to form a plane at an end of fuselage main part 11, and the through hole 13 of annular groove 14 and main part 11 is concentric, and bigger and the corresponding degree of depth arranged than the internal diameter of through hole 13.The internal diameter of the external diameter of cylinder liner 22 and the through hole of fuselage 13 matches.And the external diameter of above-mentioned cylinder liner flange 23 is littler than the internal diameter of the annular groove 14 of fuselage, and the interior garden cylinder of the outer garden cylinder 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.
Flat-top cover 31 inner undersides of cylinder head are made sealing with installation suitable thickness seal ring 60 between the last plane of groove 33 and the cylinder liner flange 23 that is mated.Material is flexible when with bolt 40 when fastening, and seal ring is compacted and seal.
The working condition of known 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 that to-and-fro motion produces,, discharge again after the suction air compression by valve body 50.From the high temperature and high pressure gas that cylinder compression volume 21 is discharged, discharge through a side exhaust port 34 of cylinder head.Owing to be to form under its cooling oil circuit by the side of the groove 14 of fuselage and the outer garden cylinder and the following of cylinder-head flange 32 of bottom surface 12 cylinder flanges 23, so that being flowing in the oil of oil circuit F leaks easily, the high temperature and high pressure gas of compression volume is also leaked easily and exists and can not adjust and fitted position changes the shortcoming of compression volume 21.
Summary of the invention
The present invention provides a kind of structure of compressor cylinder cover for solving the above 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:
Be shaped on the blunt end part 100b that sets area at the end of fuselage main body 100a and be drilled with through hole 100c, with the concentric annular groove 100d that is provided with of through hole; One end of cylinder liner 112 is shaped on its area than the big flange of annular groove 100d area on the fuselage 100, also is shaped on 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 the flange 120b of cylinder head engages with the flange 113 of cylinder liner, and sealing gasket 130 is housed in the middle of it; Clamping bolt 150 passes the flange 113 and the middle sealing gasket 130 thereof of cylinder head 120, cylinder liner, is fastened on the blunt end part 100b of fuselage end face; Valve body 140 has a valve 141 and spring 142 between cylinder head 120 and cylinder liner 112.
The present invention also takes following technical measures:
Fuselage main body 100a blunt end part 100b is drilled with the tapped hole 100e that matches with bolt 150; Cylinder liner 112 outer garden cylinders match with fuselage through hole 100c garden cylinder.
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 cylinder upper end portion of cooled compressed gas and the cold oil of the oil circuit that forms leaks, prevent the leakage of the high temperature and high pressure gas of cylinder compression volume, and by changing its fitted position, change compression volume, improve the compression efficiency of gas, thereby improve the reliability of compressor.
Description of drawings:
Fig. 1, known technology compressor compresses part end view.
Fig. 2, 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
Embodiment
For further understanding content characteristic of the present invention, effect, conjunction with figs. 2 specify as follows:
The structure of compressor cylinder cover of the present invention is by forming as lower member:
The structural feature of fuselage 100 is as follows: the end of main body 100a is set the blunt end part 100b of area, and is drilled with through hole 100c on its main body 100a, and main body 100a one side is provided with the annular groove 100d of certain depth, and this groove and through hole are concentric.Cylinder 110 is formed, and a side of passing the cylinder sleeve 112 of cylinder and formation compression volume 111 is provided with the area of its area greater than annular groove 114d, and certain thickness flange 113 is arranged; One side of cylinder liner 112 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.The cylinder liner 112 of cylinder 110 is partly packed into, and the blunt end part 112 of its flange plate 113 and fuselage engages within the through hole 113 of fuselage, thereby and the bottom surface and the periphery of the annular groove 114 of fuselage, the outer garden cylinder of the following 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 corresponding size and matches, and the end has and cylinder liner flange 113 flange 120b of the same area between sealing gasket 130 is housed, external diameter with certain thickness external diameter and cylinder liner flange 113 equates, 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.And the side of cylinder head flat-top cover 120a also has relief opening 120c.
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, so and the internal diameter of cylinder head flat-top cover 120a be installed in the leakage that can prevent high temperature and high pressure gas within above-mentioned cylinder compression volume 111 and the cylinder head flat-top cover 120a on the cylinder liner annular boss 114.
And cold oil circuit oil circuit Fa, be below the bottom surface of fuselage annular groove 100d and garden side face and cylinder liner flange 113, so the leakage of the cold oil that can prevent circulating oil path F that the outer cylinder of cylinder liner 112 forms has promptly guaranteed the sealability of cooling oil circuit Fa from configuration aspects.
May adopt the material of adjusting installation dimension in addition between cylinder 110 and the fuselage 100, can improve gas compression efficient, thereby improve the reliability of compressor thereby can change compression volume 110a.
Claims (3)
1, a kind of structure of compressor cylinder cover: it comprises the compressor fuselage, cylinder, cylinder liner, cylinder head, clamping bolt and valve body, an end that it is characterized in that fuselage main body (100a) is shaped on the blunt end part (100b) of setting area and is drilled with through hole (100c), with the concentric annular groove (100d) that is provided with of through hole, one end of cylinder liner (112) is shaped on its area than the big flange of last annular groove (100d) area of fuselage (100), annular boss (114) cylinder head (120) that also is shaped on certain thickness and height is provided with relief opening (120c), the internal diameter of cylinder head (120) matches with the external diameter of cylinder (112) annular boss (114), the flange of cylinder head (120b) engages with the flange (113) of cylinder liner, sealing gasket (130) is housed in the middle of it, clamping bolt (150) passes cylinder head (120), flange of cylinder liner (113) and middle sealing gasket (130) thereof, be 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.
2, compressor cylinder cover structure 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 bolt (150).
3, compressor cylinder cover structure according to claim 1 is characterized in that the outer garden of cylinder liner (112) cylinder matches with fuselage through hole (100c) garden cylinder.
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 true CN1459569A (en) | 2003-12-03 |
| CN1238637C 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 (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454468A (en) * | 2014-12-12 | 2015-03-25 | 常熟市淼泉压缩机配件有限公司 | Sealing cylinder cover |
| CN106286233A (en) * | 2015-06-08 | 2017-01-04 | 珠海格力节能环保制冷技术研究中心有限公司 | Cylinder assembly, compressor and air-conditioner |
| RU172519U1 (en) * | 2015-06-17 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | Piston compressor cylinder liner |
| RU172523U1 (en) * | 2015-03-25 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | CYLINDER LINER |
| RU172522U1 (en) * | 2015-09-22 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | CYLINDER LINER |
| CN108087240A (en) * | 2017-12-13 | 2018-05-29 | 重庆均利密封科技有限公司 | Automobile air conditioner compressor vulcanizes sealing structure and its sulfuration process |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016186235A (en) | 2015-03-27 | 2016-10-27 | 株式会社日本自動車部品総合研究所 | Cylinder rotation type compressor |
-
2002
- 2002-05-22 CN CN 02117389 patent/CN1238637C/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454468A (en) * | 2014-12-12 | 2015-03-25 | 常熟市淼泉压缩机配件有限公司 | Sealing cylinder cover |
| RU172523U1 (en) * | 2015-03-25 | 2017-07-11 | Общество с ограниченной ответственностью "Тегас" | CYLINDER LINER |
| CN106286233A (en) * | 2015-06-08 | 2017-01-04 | 珠海格力节能环保制冷技术研究中心有限公司 | 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 |
| CN108087240A (en) * | 2017-12-13 | 2018-05-29 | 重庆均利密封科技有限公司 | Automobile air conditioner compressor vulcanizes sealing structure and its sulfuration process |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1238637C (en) | 2006-01-25 |
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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 |