CN201381896Y - Oil seal structure of turbocharger - Google Patents
Oil seal structure of turbocharger Download PDFInfo
- Publication number
- CN201381896Y CN201381896Y CN200920078917U CN200920078917U CN201381896Y CN 201381896 Y CN201381896 Y CN 201381896Y CN 200920078917 U CN200920078917 U CN 200920078917U CN 200920078917 U CN200920078917 U CN 200920078917U CN 201381896 Y CN201381896 Y CN 201381896Y
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- oil
- turbine
- seal
- seal ring
- bearing seat
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Abstract
The utility model provides an oil seal structure of a turbocharger, which belongs to a component of the turbocharger of a diesel engine for an internal combustion engine and aims at solving the problem that the reliability of the oil seal structure of the present turbocharger is poor. The oil seal structure comprises a first sealing ring, an oil throwing disc, an oil return channel of a bearing seat at the end of an air compressor, an oil return channel at the 10-DEG oil throwing part of a main shaft, an oil return channel at the reverse thread oil sealing part, an oil return channel at the clearance of a turbine air seal ring, and an oil return channel of the bearing seat at the end of a turbine. The first sealing ring is arranged in an outer-wall ring groove of an oil seal at the end of the air compressor, and the oil throwing disc is arranged at the inner side of the oil seal; a second sealing ring is arranged in the outer-wall ring groove of the oil seal, a ring groove is arranged on an inner cavity of the bearing seat at the end of the turbine, a sealing ring is arranged in the ring groove, a pressing cover is arranged at the outer side of the sealing ring, and the pressing cover is fixedly connected with the bearing seat at the end of the turbine by three M5 screws so as to axially fix the sealing ring. The diameter of the inner cavity of the oil return channel of the bearing seat at the end of the air compressor is within 94 to 100mm, the diameter of the inner cavity of the oil return channel of the bearing seat at the end of the turbine is within 100 to 110mm, and the clearance between the reverse thread oil sealing part of the main shaft and the turbine air seal ring is within 0.125 to 0.142mm.
Description
Technical field
The utility model belongs to the parts of the turbosupercharger of diesel fuel for internal combustion engines machine, particularly the oil seal structure of turbosupercharger.
Background technique
The turbosupercharger oil seal structure of existing diesel fuel for internal combustion engines machine as shown in Figure 3, comprise that (" first " herein only is in order to express easily for the disc 3 of the gas compressor end that is installed in main shaft 7 and first seal ring 2 on the oil sealing 1 outer wall annular groove, there is not special implication), promptly, adopt first seal ring, the 2 mechanical oil sealings that one alloy cast iron is made by after disc 3 oil sealings; Turbine end adopts 10 ° of inclined-planes on the main shaft 7 to get rid of oily position 10 and left-hand thread oil sealing position 9, and is equipped with the mechanical clearance oil sealing of 0.09～0.1065mm between left-hand thread oil sealing position 9 and the turbine gas seal 6.The gas compressor end causes leakage of oil because first seal ring 2 weares and teares, and then enters into the gas compressor active wheel; Turbine end is because easily wipe with turbine gas seal 6 at the left-hand thread oil sealing position 9 on the main shaft 7 rubs, so its mutual gap can not be too small, easily causes the oil sealing weak effect again but this gap is excessive, and then it is dead admittedly to cause carbon distribution to increase the formation rotor.
And the gas compressor step bearing seat intracavity diameter of existing turbosupercharger is that drainback passage, the turbine end bearing support intracavity diameter of 89mm is the drainback passage of 96mm, and dimensional structure is too small, and the oil that throws away can not be discharged through drainback passage swimmingly.
Thereby, the poor reliability of the oil seal structure of existing turbosupercharger.
The model utility content
The purpose of this utility model is the problem that solves existing turbosupercharger oil seal structure poor reliability, and a kind of improved turbosupercharger oil seal structure is provided, and has compact structure, assembles simply, processes economy, the reliable advantage of oil sealing.
The purpose of this utility model realizes by following technical proposals:
The turbosupercharger oil seal structure, comprise first seal ring in the oil sealing outer wall annular groove that is arranged on the gas compressor end, be installed in the disc of oil sealing inboard, the drainback passage of gas compressor step bearing seat, and 10 ° of being arranged on main shaft get rid of oily position, left-hand thread oil sealing position and with the gap of turbine gas seal, the drainback passage of turbine end bearing support, also be provided with second seal ring in the outer wall annular groove of described oil sealing, offer annular groove on the inner chamber of turbine end bearing support, be provided with seal ring in it, the outside of seal ring is equipped with gland, gland is connected with the screw of turbine end bearing support by three M5, with seal ring at axial restraint.
The drainback passage intracavity diameter of described gas compressor step bearing seat is 94mm～100mm, and the drainback passage intracavity diameter of turbine end bearing support is 100mm～110mm.
Gap between described left-hand thread oil sealing position and the turbine gas seal is 0.125mm～0.142mm.
The external diameter of described disc is 70mm～80mm, and getting rid of oily inclined-plane is 20～25 °.
Described second seal ring is a mouth of hook structure.
Described seal ring is a graphite-seal ring.
The utility model adopts said structure, the gas compressor end adopts the oily major part that the disc of high speed rotating will flow out in the hole of compressorshaft bearing to get rid of into its oil back chamber, by its drainback passage relative and prior art increases, remaining oil stain flows into oil back chamber with gas compressor end bearing cover annular groove, and only a few oil gas is reached from the pressure air of gas compressor end introducing by first seal ring, second seal ring and effectively seals.
Turbine end of the present utility model has constituted multistage oil sealing, and turbine end is carried out the oil sealing first time by the graphite-seal ring that is arranged in the turbine end bearing support inner chamber annular groove; The oil stain of scurrying out gets rid of the oil back chamber that is got rid of back the turbine end bearing support in oily position 10 ° of main shaft and carries out the secondary oil sealing, and through the quick oil return of drainback passage of increased in size; Remaining oil stain carries out three oil sealings through the gap throttling of main shaft and turbine gas seal again; Along with oil stain to turbine end scurry out and on main shaft the pumping effect at left-hand thread oil sealing position get rid of Huis oil pocket and carry out the 4th oil sealing; Only a few oil causes turbine end by the gas compressor end again on gas outlet hausing high-pressure air pushes back oil back chamber and carries out the 5th oil sealing, has formed comprehensive sealing oil system reliably.And, increased the gap between left-hand thread oil sealing position and the turbine gas seal, avoided the wiping at this position to rub, rub in oil sealing effect and wiping and obtained better balance between the wearing and tearing.
As seen, adopt the utility model of said structure, compared with prior art, have more reliable oil-sealing performance, and compact structure, assembling is simple, processing is economical.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the local enlarged diagram at A place among Fig. 1;
Fig. 3 is the prior art constructions schematic representation;
Number in the figure: the 1st, oil sealing, 2 is first seal rings, the 3rd, disc, the 4th, gas compressor step bearing seat, the 5th, gas outlet hausing, the 6th, turbine gas seal, the 7th, main shaft, the 8th, the turbine end bearing support, the 9th, main shaft left-hand thread oil sealing position, the 10th, main shaft gets rid of oily position for 10 °, and 11 is second seal rings, the 12nd, seal ring, the 13rd, gland.
Embodiment
Below in conjunction with specific embodiments and the drawings the utility model is further described.
Embodiment 1:
As shown in Figure 1, the turbosupercharger oil seal structure comprise be arranged on the gas compressor end oil sealing 1 outer wall annular groove in first seal ring 2 and second seal ring 11 (first, second in this specification only is in order to express easily, do not have special implication), be installed in the disc 3 of oil sealing 1 inboard, the drainback passage on the gas compressor step bearing seat 4, and be arranged on the main shaft 7 10 ° get rid of oily position 10, left-hand thread oil sealing position 9 and with the gap of turbine gas seal 6, the drainback passage of turbine end bearing support 8, the gas outlet hausing 5 of supporting two end axles bearing also has oil back chamber.
Offer annular groove on the inner chamber of turbine end bearing support 8, be provided with the seal ring 12 of graphite system in it, the outside of seal ring 12 is equipped with gland 13, gland 13 is connected with the screw of turbine end bearing support 8 by three M5, when being installed in gland 13 on the turbine shaft bearing 8 with seal ring 12 at axial restraint.
As shown in Figure 2, in order to add second seal ring 11, the width of the outer wall annular groove of oil sealing 1 is compared the width widen of existing like product, and second seal ring 11 is a mouth of hook structure.
The oil return intracavity diameter of gas compressor step bearing seat 4 is 94mm; The oil return intracavity diameter of turbine end bearing support 8 is 100mm; Gap on the main shaft 7 between left-hand thread oil sealing position 9 and the turbine gas seal 6 is 0.125mm; The external diameter of disc 3 is compared existing like product and is increased, and long-pending to increase the retaining pasta, its value is 70mm, and getting rid of oily inclined-plane is 20 °.
Embodiment 2:
The structure of present embodiment is with embodiment 1, wherein the drainback passage intracavity diameter of gas compressor step bearing seat 4 is 96mm, the drainback passage intracavity diameter of turbine end bearing support 8 is 105mm, and the gap on the main shaft 7 between left-hand thread oil sealing position 9 and the turbine gas seal 6 is 0.131mm; The external diameter of disc 3 is 75mm, and getting rid of oily inclined-plane is 22 °.
Embodiment 3:
The structure of present embodiment is with embodiment 1, wherein the drainback passage intracavity diameter of gas compressor step bearing seat 4 is 98mm, the drainback passage intracavity diameter of turbine end bearing support 8 is 107mm, and the gap on the main shaft 7 between left-hand thread oil sealing position 9 and the turbine gas seal 6 is 0.138mm; The external diameter of disc 3 is 78mm, and getting rid of oily inclined-plane is 23 °.
Embodiment 4:
The structure of present embodiment is with embodiment 1, wherein the drainback passage intracavity diameter of gas compressor step bearing seat 4 is 100mm, the drainback passage intracavity diameter of turbine end bearing support 8 is 110mm, and the gap on the main shaft 7 between left-hand thread oil sealing position 9 and the turbine gas seal 6 is 0.142mm; The external diameter of disc 3 is 80mm, and getting rid of oily inclined-plane is 25 °.
Claims (6)
1, the turbosupercharger oil seal structure, comprise first seal ring (2) in oil sealing (1) the outer wall annular groove that is arranged on the gas compressor end, be installed in the inboard disc (3) of oil sealing (1), the drainback passage of gas compressor step bearing seat (4), and 10 ° of being arranged on main shaft (7) get rid of oily position (10), left-hand thread oil sealing position (9) and with the gap of turbine gas seal (6), the drainback passage of turbine end bearing support (8), it is characterized in that, also be provided with second seal ring (11) in the outer wall annular groove of described oil sealing (1), offer annular groove on the inner chamber of turbine end bearing support (8), be provided with seal ring (12) in it, the outside of seal ring (12) is equipped with gland (13), gland (13) is fixedlyed connected with turbine end bearing support (8), with seal ring (12) at axial restraint.
2, turbosupercharger oil seal structure according to claim 1 is characterized in that the drainback passage intracavity diameter of described gas compressor step bearing seat (4) is 94mm～100mm, and the drainback passage intracavity diameter of turbine end bearing support (8) is 100mm～110mm.
3, turbosupercharger oil seal structure as claimed in claim 1 or 2 is characterized in that left-hand thread oil sealing position (9) on the described main shaft (7) and the gap between the turbine gas seal (6) are 0.125mm～0.142mm.
4, as turbosupercharger oil seal structure as described in the claim 3, it is characterized in that the external diameter of described disc (3) is 70mm～80mm, getting rid of oily inclined-plane is 20～25 °.
5, turbosupercharger oil seal structure according to claim 1 is characterized in that described second seal ring (11) is a mouth of hook structure.
6, turbosupercharger oil seal structure according to claim 1 is characterized in that described seal ring (12) is a graphite-seal ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920078917U CN201381896Y (en) | 2009-02-05 | 2009-02-05 | Oil seal structure of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200920078917U CN201381896Y (en) | 2009-02-05 | 2009-02-05 | Oil seal structure of turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201381896Y true CN201381896Y (en) | 2010-01-13 |
Family
ID=41525373
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200920078917U Expired - Fee Related CN201381896Y (en) | 2009-02-05 | 2009-02-05 | Oil seal structure of turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201381896Y (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101787902A (en) * | 2010-04-09 | 2010-07-28 | 杭州汽轮机股份有限公司 | Oil sealing device on end part of steam turbine shaft |
| CN101975185A (en) * | 2010-10-21 | 2011-02-16 | 湖南天雁机械有限责任公司 | Compressor seal structure of small turbocharger |
| CN103032347A (en) * | 2011-09-28 | 2013-04-10 | 珠海格力电器股份有限公司 | Centrifugal compressor with insulation structure |
| CN108843405A (en) * | 2018-06-22 | 2018-11-20 | 苏州诺迅汽车零部件有限公司 | A kind of nozzle ring structure of turbocharger |
-
2009
- 2009-02-05 CN CN200920078917U patent/CN201381896Y/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101787902A (en) * | 2010-04-09 | 2010-07-28 | 杭州汽轮机股份有限公司 | Oil sealing device on end part of steam turbine shaft |
| CN101787902B (en) * | 2010-04-09 | 2013-12-18 | 杭州汽轮机股份有限公司 | Oil sealing device on end part of steam turbine shaft |
| CN101975185A (en) * | 2010-10-21 | 2011-02-16 | 湖南天雁机械有限责任公司 | Compressor seal structure of small turbocharger |
| CN103032347A (en) * | 2011-09-28 | 2013-04-10 | 珠海格力电器股份有限公司 | Centrifugal compressor with insulation structure |
| CN103032347B (en) * | 2011-09-28 | 2015-08-19 | 珠海格力电器股份有限公司 | There is the centrifugal compressor of isolation structure |
| CN108843405A (en) * | 2018-06-22 | 2018-11-20 | 苏州诺迅汽车零部件有限公司 | A kind of nozzle ring structure of turbocharger |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20100113 Termination date: 20140205 |