CN114251299A - End sealing device for compressor of turbocharger - Google Patents
End sealing device for compressor of turbocharger Download PDFInfo
- Publication number
- CN114251299A CN114251299A CN202111454133.2A CN202111454133A CN114251299A CN 114251299 A CN114251299 A CN 114251299A CN 202111454133 A CN202111454133 A CN 202111454133A CN 114251299 A CN114251299 A CN 114251299A
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- CN
- China
- Prior art keywords
- shaft seal
- oil
- cavity
- ring
- sleeve seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02B39/14—Lubrication of pumps; Safety measures therefor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/12—Shaft sealings using sealing-rings
- F04D29/122—Shaft sealings using sealing-rings especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The utility model provides a turbo charger compressor end sealing device, relates to sealing device technical field, locates the cover seat on the bearing seal including bearing seal and cover, has seted up the cavity on the cover seat, and coaxial rigid coupling has the bearing seal boss that extends to in the cavity on the bearing seal, and the upper end that the cover seat is close to edge in the cavity offsets with the lateral wall friction of bearing seal boss. The invention solves the technical problems that the turbocharger in the traditional technology has poor sealing effect at the end of the compressor and is easy to leak oil under the working condition of high negative pressure.
Description
Technical Field
The invention relates to the technical field of sealing devices, in particular to a turbocharger compressor end sealing device.
Background
The exhaust gas turbocharger has the advantages of improving the power of an engine, reducing fuel consumption, reducing emission and the like, and is widely applied to diesel engines at present. Along with the development of emission regulations, the power per liter of an engine is larger and larger, the pressure ratio of a turbocharger matched with the engine is required to be further improved, and for the high pressure ratio, the bearing capacity of a bearing of the turbocharger needs to be correspondingly enhanced, so that the flow of lubricating oil is increased, the space of a bearing system is limited, and the oil leakage risk of the turbocharger is further increased, particularly shown at the end of a compressor. The engine application occasions are more and more, for example, the dust of a mining engine is large, the negative pressure of air inlet of a turbocharger is large, and the oil leakage fault of the compressor end of the turbocharger is often caused.
The patent that chinese national intellectual property office disclosed an application number is CN203321670U, this scheme includes the sealed dish of fixed mounting on the turbo charger midbody, a side of sealed dish has an annular groove, be fixed with the seal cover on turbo charger's the turbine shaft, the one end interval of seal cover is equipped with annular installation arch and annular seal arch, sealed dish suit is on annular installation arch, annular seal arch is installed in annular groove, be close to inlet port one side on the midbody on the sealed dish and be equipped with the arc and keep off the oil cover, the arc keeps off the oil cover and sets up in the bellied periphery of annular seal. The beneficial effect of this scheme: simple structure, reasonable in design, convenient to use, it is sealed effectual.
The device gradually exposes the defects of the technology along with the use, and mainly shows the following aspects:
at present, the end of a gas compressor of the turbocharger generally adopts a shaft seal, a sleeve seat and a sealing ring to be mutually matched for sealing, the shaft seal adopts a double-ring double-groove structure, but when the gas is in a high negative pressure working condition, the pressure end of the turbocharger cannot avoid engine oil leakage.
In view of the above, the prior art is obviously inconvenient and disadvantageous in practical use, and needs to be improved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention solves the technical problems of poor sealing effect at the end of a compressor and easy oil leakage of the turbocharger in the traditional technology under the working condition of high negative pressure.
In order to solve the above problems, the present invention provides the following technical solutions:
a turbo charger compressor end sealing device comprises a shaft seal and a sleeve seat sleeved on the shaft seal, wherein a cavity is formed in the sleeve seat, a shaft seal boss extending into the cavity is coaxially and fixedly connected to the shaft seal, and the upper end part, close to the inner edge of the cavity, of the sleeve seat is in friction fit with the side wall of the shaft seal boss.
As an optimized scheme, a shaft seal ring is fixedly connected to the shaft seal, and an oil return groove is formed in an area between the shaft seal ring and the shaft seal boss.
As an optimized scheme, an upward oil blocking bulge is fixedly connected to the upper end part of the sleeve seat close to the inner edge of the cavity, and an annular groove is formed between the oil blocking bulge and the end wall of the cavity.
As an optimized scheme, an oil guide protruding ring is further arranged on the outer edge of the boss and faces towards the oil blocking protrusion, the oil guide protruding ring covers the oil blocking protrusion, and a gap is formed between the upper end portion of the oil blocking protrusion and the inner edge of the oil guide protruding ring.
As an optimized scheme, an oil drainage groove is arranged between the lower end part of the sleeve seat close to the inner edge of the cavity and the side wall of the shaft seal boss, and is communicated with the oil drainage groove to communicate the oil return groove with the cavity.
As an optimized scheme, the sleeve seat is fixed on a middle shell, an oil return cavity is further arranged on the middle shell, and the oil return cavity is communicated with the cavity at the lower part.
As an optimized scheme, two sealing ring grooves are formed in the shaft seal in parallel, a sealing ring is arranged in each sealing ring groove, and the outer ring of each sealing ring is in friction fit with the inner hole of the sleeve seat.
As an optimized scheme, a counter bore for wrapping the shaft seal ring and the oil return groove is further arranged on an inner hole of the sleeve seat.
As an optimized scheme, a sealing ring is arranged at a butt joint gap between the sleeve seat and the middle shell.
As an optimized scheme, a thrust sleeve abutting against the shaft seal is further arranged in the middle shell, and a thrust bearing is sleeved on the thrust sleeve.
As an optimized scheme, a rotor shaft penetrating through the thrust sleeve and the shaft seal is further arranged in the middle shell, and the outer end part of the rotor shaft is connected with an impeller.
Compared with the prior art, the invention has the beneficial effects that:
the thrust bearing is connected to the middle shell through a screw on the sleeve seat, and a gap between the sleeve seat and the middle shell is sealed through a sealing ring arranged on a sealing groove of the sleeve seat, so that oil and gas in the middle shell are prevented from entering the gas compressor, and meanwhile, air of the gas compressor is prevented from entering the middle shell;
the shaft seal is in clearance fit with the sleeve seat and is sealed by matching three axial structures, three radial structures and a sealing ring,
the oil blocking bulge and the oil guide bulge ring form a first radial matching sealing structure respectively;
the side end face of the shaft seal boss is matched with the end face of the sleeve seat to form a first axial sealing structure;
the shaft seal ring, the oil return groove and the counter bore form a second radial matching sealing structure;
the side surface of the shaft seal ring and the side wall of the counter bore form a second axial seal structure;
the sealing ring groove, the sealing ring and the sleeve seat inner hole form a double-ring double-groove structure which is a third radial and third axial matching sealing structure, and the six sealing structures can prevent oil from entering a compressor end from the oil cavity;
the first radial matching sealing structure is provided with a convex structure to prevent lubricating oil above the oil cavity from splashing and dripping into a sealing gap, and the lubricating oil flowing downstream above the oil cavity is guided to the oil return cavity through the annular groove, so that the lubricating oil is greatly reduced from entering the gap at the sealing position;
the second part is radially matched with an oil return groove of a shaft seal in the sealing structure to relieve pressure of entering lubricating oil, so that the lubricating oil is greatly reduced from continuously flowing to a pressure end; the double-ring double-groove structure is the last ring, and prevents very little lubricating oil entering the double-ring double-groove structure from leaking to the end of the compressor; through six oil blocking and oleophobic structures, the anti negative pressure ability of turbo charger has been strengthened, has solved the compressor end and has leaked the problem under the high negative pressure condition, and its simple structure does not account for the space, and makes and assemble not have the degree of difficulty.
The oil drainage groove is arranged below the oil return groove in the radial matching structure at the second position, so that the entering lubricating oil can be smoothly thrown out to the oil return cavity, the lubricating oil entering the sealing structure is prevented from entering the end of the compressor, the leakage of the lubricating oil is further avoided, and the structure is simple, free of processing difficulty and easy to realize.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural diagram of an oil drainage groove of the present invention.
In the figure: 1-an impeller; 2-sleeve seat; 21-inner hole; 22-counter bore; 23-ring groove, 24-oil drainage groove; 25-oil blocking bulge; 26-oil guide bulge loop; 3-sealing ring; 4-an intermediate shell; 5-a thrust bearing; 6-thrust sleeve; 7-shaft seal; 71-shaft seal boss, 72-shaft seal ring; 73 sealing the ring groove; 74-oil return groove; 8-a sealing ring; 9-oil return cavity; 10-cavity.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1 and 2, the turbocharger compressor end sealing device includes a shaft seal 7 and a sleeve seat 2 sleeved on the shaft seal 7, a cavity 10 is formed in the sleeve seat 2, a shaft seal boss 71 extending into the cavity 10 is coaxially and fixedly connected to the shaft seal 7, and an upper end portion of the sleeve seat 2 close to an inner edge of the cavity 10 is in friction contact with a side wall of the shaft seal boss 71.
The shaft seal 7 is fixed with a shaft seal ring 72, and an oil return groove 74 is formed through the area between the shaft seal ring 72 and the shaft seal boss 71.
The upper end part of the sleeve seat 2 close to the inner edge of the cavity 10 is fixedly connected with an upward oil baffle bulge 25, and a ring groove 23 is formed between the oil baffle bulge 25 and the end wall of the cavity 10.
An oil guide bulge ring 26 is further arranged on the outer edge of the boss and faces the oil baffle bulge 25, the oil guide bulge ring 26 covers the oil baffle bulge 25, and a gap is formed between the upper end part of the oil baffle bulge 25 and the inner edge of the oil guide bulge ring 26.
An oil drainage groove 24 is arranged between the lower end part of the sleeve seat 2 close to the inner edge of the cavity 10 and the side wall of the shaft seal boss 71, and the oil drainage groove 24 is communicated to connect the oil return groove 74 with the cavity 10.
The sleeve seat 2 is fixed on the middle shell 4, an oil return cavity 9 is further arranged on the middle shell 4, and the oil return cavity 9 is communicated with a cavity 10 at the lower part.
Two sealing ring grooves 73 are formed in the shaft seal 7 in parallel, a sealing ring 3 is arranged in each sealing ring groove 73, and the outer ring of each sealing ring 3 is in friction contact with the inner hole 21 of the sleeve seat 2.
The inner hole 21 of the sleeve seat 2 is also provided with a counter bore 22 for covering the shaft seal ring 72 and the oil return groove 74.
A sealing ring 3 is arranged at the butt joint gap between the sleeve seat 2 and the middle shell 4.
A thrust sleeve 6 which is propped against the shaft seal 7 is also arranged in the middle shell 4, and a thrust bearing 5 is sleeved on the thrust sleeve 6.
A rotor shaft penetrating through the thrust sleeve 6 and the shaft seal 7 is also arranged in the middle shell 4, and the outer end part of the rotor shaft is connected with the impeller 1.
The working principle of the device is as follows:
lubricating oil enters the thrust bearing 5 from the main oil duct of the middle shell 4, the lubricating oil is thrown out by the shaft seal 7 at the matching surface of the shaft seal 7 and the thrust bearing 5, part of the lubricating oil directly falls into the oil return cavity 9 due to gravity, the other part of the lubricating oil is thrown onto the wall surface of the cavity 10 of the sleeve seat 2 to cause the lubricating oil to splash, drip and flow back along the wall, the splashed and dripped lubricating oil can fall back onto the shaft seal 7, the shaft seal boss 71 and the oil guide bulge ring 26 on the shaft seal 7 prevent the lubricating oil from entering a sealing gap between the shaft seal 7 and the sleeve seat 2, the oil leakage risk is reduced, the lubricating oil slides into the ring groove 23 along the shaft seal boss 71 and then directly flows into the oil return cavity 9, the lubricating oil reflowing along the wall flows back to the ring groove 23 along the wall surface of the cavity 10 or directly flows into the oil return cavity 9, the structure can effectively control the flow path of the lubricating oil, and the negative pressure resistance of the end of the compressor is improved.
When the high negative pressure operation of booster compressor import or booster toward compressor end inclination is too big, lubricating oil can get into oil gallery 74, because annular groove 23 pressure release, lubricating oil can't continue to flow toward the pressure end, be provided with oil drainage groove 24 with oil gallery 74 complex cover seat 2 below, the lubricating oil that gets into oil gallery 74 flows back oil cavity 9 under the effect of gravity and rotatory centrifugal force, the lubricating oil that this place structure got into bearing seal 7 under the abnormal conditions (circumstances such as high negative pressure) carries out the pressure release, avoid leaking toward the compressor end.
When a small amount of lubricating oil in the oil return groove 74 continuously leaks to the end of the compressor under the conditions of high negative pressure and the like, the lubricating oil leaked from the direction of the groove 23 of the shaft seal ring 72 is prevented from entering the compressor in the radial direction and the axial direction by a double-ring double-groove sealing structure consisting of the sealing ring groove 73 of the shaft seal 7, the inner hole 21 of the sleeve seat 2 and the sealing ring 8, and the lubricating oil returns through a gap, flows out through the oil drain groove 24, returns to the oil return cavity 9 and flows back to an engine oil tank;
the shaft seal 7 is in clearance fit with the sleeve seat 2 and is sealed by matching three axial structures, three radial structures and a sealing ring 8,
the oil blocking bulge 25 and the oil guide bulge ring 26 form a first radial matching sealing structure respectively;
the side end surface of the shaft seal boss 71 is matched with the end surface of the sleeve seat 2 to form a first axial sealing structure;
the shaft seal ring 72 and the oil return groove 74 form a second radial matching sealing structure with the counter bore 22;
the side surface of the shaft seal ring 72 and the side wall of the counter bore 22 form a second axial sealing structure;
the sealing ring groove 73, the sealing ring 8 and the inner hole 21 of the sleeve seat 2 form a double-ring double-groove structure which is a third radial and third axial matching sealing structure, and the six sealing structures can prevent oil from entering the compressor end from the oil cavity;
the first radial matching sealing structure is provided with a convex structure to prevent lubricating oil above the oil cavity from splashing and dripping into a sealing gap, and the lubricating oil flowing downstream above the oil cavity is guided to the oil return cavity 9 through the annular groove 23, so that the lubricating oil is greatly reduced from entering the gap at the sealing position;
the oil return groove 74 of the shaft seal 7 in the second radial matching sealing structure relieves the pressure of the entering lubricating oil, and the lubricating oil is greatly reduced from continuously flowing to the pressure end; the double-ring double-groove structure is the last ring, and prevents very little lubricating oil entering the double-ring double-groove structure from leaking to the end of the compressor; through six oil blocking and oleophobic structures, the anti negative pressure ability of turbo charger has been strengthened, has solved the compressor end and has leaked the problem under the high negative pressure condition, and its simple structure does not account for the space, and makes and assemble not have the degree of difficulty.
The oil drainage groove 24 is arranged below the oil return groove 74 in the second radial matching structure, so that the entering lubricating oil can be smoothly thrown out to the oil return cavity 9, the lubricating oil entering the sealing structure is prevented from entering the end of the compressor, the leakage of the lubricating oil is further solved, and the structure is simple, has no processing difficulty and is easy to realize.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (10)
1. The utility model provides a turbo charger compressor end sealing device which characterized in that: the shaft seal structure comprises a shaft seal (7) and a sleeve seat (2) sleeved on the shaft seal (7), wherein a cavity (10) is formed in the sleeve seat (2), a shaft seal boss (71) extending into the cavity (10) is coaxially and fixedly connected to the shaft seal (7), and the upper end part of the sleeve seat (2), which is close to the inner edge of the cavity (10), is in friction fit with the side wall of the shaft seal boss (71).
2. The turbocharger compressor end seal according to claim 1, wherein: a shaft seal ring (72) is fixedly connected to the shaft seal (7), and an oil return groove (74) is formed through an area between the shaft seal ring (72) and the shaft seal boss (71).
3. The turbocharger compressor end seal according to claim 1, wherein: the upper end portion that cover seat (2) are close to in cavity (10) edge rigid coupling ascending fender oil arch (25), and pass through keep off oil arch (25) with form annular (23) between the end wall of cavity (10).
4. A turbocharger compressor end seal according to claim 3, wherein: an oil guide bulge ring (26) is further arranged on the outer edge of the shaft seal boss (71) and faces the oil blocking bulge (25), and the oil guide bulge ring (26) covers the oil blocking bulge (25).
5. The turbocharger compressor end seal according to claim 2, wherein: an oil drainage groove (24) is formed between the lower end part of the sleeve seat (2), close to the inner edge of the cavity (10), and the side wall of the shaft seal boss (71), and is communicated with the oil drainage groove (24), so that the oil return groove (74) is communicated with the cavity (10).
6. The turbocharger compressor end seal according to claim 1, wherein: the sleeve seat (2) is fixed on the middle shell (4), an oil return cavity (9) is further formed in the middle shell (4), and the oil return cavity (9) is communicated with the cavity (10) located on the lower portion.
7. The turbocharger compressor end seal according to claim 1, wherein: two sealing ring grooves (73) are formed in the shaft seal (7) in parallel, a sealing ring (3) is arranged in each sealing ring groove (73), and the outer ring of each sealing ring (3) is in friction fit with the inner hole (21) of the sleeve seat (2).
8. The turbocharger compressor end seal according to claim 2, wherein: and a counter bore (22) for coating the shaft seal ring (72) and the oil return groove (74) is also arranged on the inner hole (21) of the sleeve seat (2).
9. The turbocharger compressor end seal according to claim 6, wherein: and a sealing ring (3) is arranged at the butt joint gap between the sleeve seat (2) and the middle shell (4).
10. The turbocharger compressor end seal according to claim 6, wherein: a thrust sleeve (6) which is abutted against the shaft seal (7) is further arranged in the middle shell (4), and a thrust bearing (5) is sleeved on the thrust sleeve (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111454133.2A CN114251299A (en) | 2021-11-27 | 2021-11-27 | End sealing device for compressor of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111454133.2A CN114251299A (en) | 2021-11-27 | 2021-11-27 | End sealing device for compressor of turbocharger |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114251299A true CN114251299A (en) | 2022-03-29 |
Family
ID=80791511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111454133.2A Withdrawn CN114251299A (en) | 2021-11-27 | 2021-11-27 | End sealing device for compressor of turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114251299A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116624271A (en) * | 2023-07-24 | 2023-08-22 | 成都中科翼能科技有限公司 | Bearing oil baffle assembly of gas turbine shaft |
-
2021
- 2021-11-27 CN CN202111454133.2A patent/CN114251299A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116624271A (en) * | 2023-07-24 | 2023-08-22 | 成都中科翼能科技有限公司 | Bearing oil baffle assembly of gas turbine shaft |
| CN116624271B (en) * | 2023-07-24 | 2023-09-15 | 成都中科翼能科技有限公司 | Bearing oil baffle assembly of gas turbine shaft |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20220329 |
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| WW01 | Invention patent application withdrawn after publication |