CN108952951B - Pressure gas balance system structure of turbocharger - Google Patents
Pressure gas balance system structure of turbocharger Download PDFInfo
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- CN108952951B CN108952951B CN201810847658.4A CN201810847658A CN108952951B CN 108952951 B CN108952951 B CN 108952951B CN 201810847658 A CN201810847658 A CN 201810847658A CN 108952951 B CN108952951 B CN 108952951B
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- Prior art keywords
- gas
- compressor
- pressure gas
- balance
- channel
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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
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
- F01D11/06—Control thereof
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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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a pressure gas balance system structure of a turbocharger, which comprises: the device comprises a pressure gas inlet channel arranged on the intermediate body and a balance channel communicated with the pressure gas inlet channel, wherein one end of the balance channel is connected with an annular cavity of a compressor air seal ring at the end of a compressor, and the other end of the balance channel is communicated with an oil-gas sealing structure at the end of a turbine. The invention can simultaneously or independently solve the problems of the cooling function of the blade back of the impeller of the gas compressor and the oil-gas seal sealing function of the turbine end. The invention can simultaneously solve the problem that the cooling function of the impeller back of the gas engine and the oil-gas seal sealing function of the turbine end are not related or even conflict and interfere with each other on the premise of not increasing other parts, not damaging the integral structure of the supercharger and not influencing the performance and the reliability of the whole supercharger.
Description
Technical Field
The invention relates to the technical field of turbochargers, in particular to a pressure gas balance system structure of a turbocharger.
Background
Along with the increase of the load of the internal combustion engine, the operating speed and the operating pressure ratio of the turbocharger are increased, the temperature of the surface material of the impeller, which is generated by friction between the impeller and sucked compressed air when the traditional aluminum alloy material air compressor impeller of the turbocharger works, is increased under the application background of high speed and large diameter, and the mechanical property and the fatigue life of the aluminum alloy material of the air compressor impeller can be obviously reduced after the air compressor impeller is operated at the high speed and the high speed for a long time, so that the operating reliability of the turbocharger and the internal combustion engine is influenced.
The sealing structure at the vortex end of the turbocharger can reduce the oil sealing capacity due to carbon deposition in long-term use, and the turbocharger can also have weak sealing capacity due to a reverse thread labyrinth structure caused by too low rotating speed in low-rotating-speed use, so that lubricating oil in an oil return cavity of a bearing shell overflows through the gap of the sealing structure, and the oil leakage or the carbon deposition of the turbocharger is serious.
Disclosure of Invention
The invention provides a pressure gas balance system structure of a turbocharger, which aims to overcome the technical problems.
The invention relates to a pressure gas balance system structure of a turbocharger, which comprises:
the device comprises a pressure gas inlet channel arranged on the intermediate body and a balance channel communicated with the pressure gas inlet channel, wherein one end of the balance channel is connected with an annular cavity of a compressor air seal ring at the end of a compressor, and the other end of the balance channel is communicated with an oil-gas sealing structure at the end of a turbine.
Further, still include:
and the one-way valves are arranged at two ends of the balance channel and are used for proportionally regulating the flow of gas to the gas compressor end and the turbine end after the pressure gas enters the balance channel.
Further, the press machine air seal ring is also provided with a vent hole, and the vent hole is communicated with the annular cavity.
Further, the vent holes are uniformly distributed on the press machine air seal ring.
Furthermore, O-shaped rings are arranged inside and outside the annular cavity.
The pressure gas balance system of the turbocharger can simultaneously solve the problem that the blade back cooling function of an impeller of an air engine and the oil-gas seal sealing function of a turbine end are not associated or even conflict and interfere with each other on the premise of not increasing other parts, not damaging the integral structure of the turbocharger and not influencing the overall performance and reliability of the turbocharger. The pressure booster is suitable for axial-flow and radial-flow superchargers with various sizes, can be used under the condition of having or not having an external pressure gas source, and is convenient to implement.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of a turbocharger pressure gas balancing system according to the present invention;
1. a bearing housing; 2. a pressurized gas inlet channel; 3. a pressure gas balance channel; 4. an annular cavity; 5. a gas seal ring of the gas compressor; 6. drilling holes are uniformly distributed on the gas seal ring of the gas compressor; 7. sealing the O-shaped ring; 8. connecting a fastener; 9. a compressor-end check valve; 10. turbine-end check valves.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a schematic structural diagram of a turbocharger pressure-gas balance system according to the present invention, and as shown in fig. 1, the structure of the present embodiment may include:
the device comprises a pressure gas inlet channel arranged on the intermediate body and a balance channel communicated with the pressure gas inlet channel, wherein one end of the balance channel is connected with an annular cavity of a compressor air seal ring at the end of a compressor, and the other end of the balance channel is communicated with an oil-gas sealing structure at the end of a turbine.
Specifically, the air compressor air seal ring is installed on one side of the pressure end of the bearing shell and is in axial compression connection with the bearing shell through a bolt. The annular cavity is communicated with the outside in a drilling mode on the supporting body, so that the pressure gas can smoothly enter the annular cavity from an external gas source without leakage. Pressure gas enters from a gas channel of the bearing shell and is subjected to gas diversion along a pressure gas balance channel, one part of the pressure gas flows to a ring cavity at the end of the compressor to participate in cooling of the blade back, and the other part of the pressure gas flows to the end of the turbine to participate in lubricating oil sealing at the end of the turbine. The distribution flow of the pressure gas at the two ends is adjusted by setting the outlet areas at the two ends of the balance channel in advance according to actual needs. By forming a pressure gas flow channel in the support body, pressure gas can enter the turbine end from the outside via this channel and participate in the oil seal.
Further, still include:
and the one-way valves are arranged at two ends of the balance channel and are used for proportionally regulating the flow of gas to the gas compressor end and the turbine end after the pressure gas enters the balance channel.
Specifically, the compressor-end check valve and the turbine-end check valve of the embodiment can simultaneously perform the cooling function of the blade back of the compressor and the sealing and reinforcing function of the turbine end, and one of the functions can be selected to work independently.
Further, the press machine air seal ring is also provided with a vent hole, and the vent hole is communicated with the annular cavity.
Specifically, the compressor air seal ring is matched with the bearing shell to form a ring of annular cavity, and inclined drill holes are uniformly distributed in the compressor air seal ring to communicate the annular cavity with the blade back cavity of the compressor impeller. The gas compressor air seal ring and the bearing shell are tightly pressed together through the connecting fastener to form an annular cavity, pressure gas flowing to the end of the gas compressor is gathered in the annular cavity, the pressure gas is prevented from leaking by virtue of the inner and outer sealing O-shaped rings, the gas flows along the circumferential direction, and enters and directly acts on a high-temperature area of the blade back of the impeller of the gas compressor after passing through holes uniformly distributed on the circumference of the gas compressor air seal ring, so that the temperature of the high-temperature area on the surface is reduced to an ideal range, and the purpose of cooling the blade back is achieved. On the premise of an external pressure air source, if the blade back cooling function is not needed, only the one-way check valve at the end of the compressor is required to be completely closed, or the air seal ring of the compressor is uniformly provided with the drill holes and is not processed, or the process is used for blocking, the pressure air cannot flow into the end of the compressor, and only can completely enter the turbine end to participate in sealing.
On the premise of no external pressure air source, if the blade back cooling function is not needed, the one-way check valve at the end of the compressor is required to be completely closed, or the starting end of the pressure air inlet channel is additionally provided with a plug seal to prevent the bearing shell from leaking air. When the supercharger works, pressure gas generated by the compressor impeller is uniformly distributed and drilled through the compressor gas seal ring to enter the annular cavity, and then enters the vortex end through the pressure gas balance channel to participate in sealing.
Furthermore, the vent holes are uniformly distributed on the air seal ring of the press machine, and the opening direction of the vent holes is the same as the rotation direction of the impeller.
Specifically, the opening direction of the vent hole of the present embodiment is the same direction as the rotation direction of the impeller, further improving the cooling efficiency.
Furthermore, O-shaped rings are arranged inside and outside the annular cavity.
Specifically, the annular cavity is radially sealed by an inner O-ring and an outer O-ring. Ensuring that the pressure gas in the cavity can not flow out.
The invention has the advantages that: the novel pressure gas balance system structure integrating the traditional compressor blade back cooling technology and the turbine end air-entraining sealing structure can simultaneously play the compressor blade back cooling function and the turbine end sealing strengthening function and can also select one of the two to work independently. The system structure is attached to the original supercharger bearing shell and oil-gas seal structure, no new parts are added, and the performance and reliability of the supercharger are not affected.
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; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (3)
1. A turbocharger pressure-gas balance system structure, comprising:
the device comprises a pressure gas inlet channel arranged on an intermediate body and a balance channel communicated with the pressure gas inlet channel, wherein one end of the balance channel is connected with an annular cavity of a compressor air seal ring at the end of a compressor, and the other end of the balance channel is communicated with an oil-gas sealing structure at the end of a turbine;
further comprising:
the check valves are arranged at two ends of the balance channel and used for proportionally regulating the flow of gas to a gas compressor end and a turbine end after the pressure gas enters the balance channel;
the press machine air seal ring is further provided with vent holes, the vent holes are communicated with the annular cavity, and the vent holes are used for communicating the annular cavity of the press machine air seal ring with a blade back cavity of the compressor impeller.
2. The structure of claim 1, wherein the vent holes are evenly distributed on the press gas seal ring.
3. The structure of claim 1, wherein O-rings are provided inside and outside the annular cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810847658.4A CN108952951B (en) | 2018-07-27 | 2018-07-27 | Pressure gas balance system structure of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810847658.4A CN108952951B (en) | 2018-07-27 | 2018-07-27 | Pressure gas balance system structure of turbocharger |
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| Publication Number | Publication Date |
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| CN108952951A CN108952951A (en) | 2018-12-07 |
| CN108952951B true CN108952951B (en) | 2020-07-17 |
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| CN201810847658.4A Active CN108952951B (en) | 2018-07-27 | 2018-07-27 | Pressure gas balance system structure of turbocharger |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113530889B (en) * | 2021-08-31 | 2024-06-04 | 中车大连机车研究所有限公司 | Automatic cooling function structure of working wheel of compressor of turbocharger |
| CN113864223B (en) * | 2021-11-01 | 2024-05-14 | 中车大连机车研究所有限公司 | Structure and method for measuring back pressure of turbocharger wheel |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61142328A (en) * | 1984-12-17 | 1986-06-30 | Mitsubishi Heavy Ind Ltd | Lubrication mechanism in exhaust turbine supercharger |
| CN1239192A (en) * | 1998-05-25 | 1999-12-22 | 亚瑞亚·勃朗勃威力有限公司 | Centrifugal compressor |
| EP1394365A1 (en) * | 2002-09-02 | 2004-03-03 | BorgWarner Inc. | Turbocharger shaft sealing |
| CN102926824A (en) * | 2012-11-15 | 2013-02-13 | 湖南天雁机械有限责任公司 | Gas compressor end sealing structure of turbocharger |
| EP2730744A1 (en) * | 2012-11-08 | 2014-05-14 | ABB Turbo Systems AG | Exhaust gas turbo charger |
| CN104454143A (en) * | 2013-09-25 | 2015-03-25 | 现代自动车株式会社 | Turbo charger having cooling structure |
| CN104595246A (en) * | 2015-01-05 | 2015-05-06 | 珠海格力电器股份有限公司 | Centrifugal compressor with recooling structure |
-
2018
- 2018-07-27 CN CN201810847658.4A patent/CN108952951B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61142328A (en) * | 1984-12-17 | 1986-06-30 | Mitsubishi Heavy Ind Ltd | Lubrication mechanism in exhaust turbine supercharger |
| CN1239192A (en) * | 1998-05-25 | 1999-12-22 | 亚瑞亚·勃朗勃威力有限公司 | Centrifugal compressor |
| EP1394365A1 (en) * | 2002-09-02 | 2004-03-03 | BorgWarner Inc. | Turbocharger shaft sealing |
| EP2730744A1 (en) * | 2012-11-08 | 2014-05-14 | ABB Turbo Systems AG | Exhaust gas turbo charger |
| CN102926824A (en) * | 2012-11-15 | 2013-02-13 | 湖南天雁机械有限责任公司 | Gas compressor end sealing structure of turbocharger |
| CN104454143A (en) * | 2013-09-25 | 2015-03-25 | 现代自动车株式会社 | Turbo charger having cooling structure |
| CN104595246A (en) * | 2015-01-05 | 2015-05-06 | 珠海格力电器股份有限公司 | Centrifugal compressor with recooling structure |
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| CN108952951A (en) | 2018-12-07 |
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Effective date of registration: 20210325 Address after: 116000 no.5-3, Haoyang South Street, Lushunkou District, Dalian City, Liaoning Province Patentee after: Dalian CRRC Zetong Machinery Co.,Ltd. Patentee after: CRRC DALIAN INSTITUTE Co.,Ltd. Address before: 116000 No. 49 Zhongzhong Street, Shahekou District, Dalian City, Liaoning Province Patentee before: CRRC DALIAN INSTITUTE Co.,Ltd. |