CN107740710B - Turbine shell structure - Google Patents
Turbine shell structure Download PDFInfo
- Publication number
- CN107740710B CN107740710B CN201711130133.0A CN201711130133A CN107740710B CN 107740710 B CN107740710 B CN 107740710B CN 201711130133 A CN201711130133 A CN 201711130133A CN 107740710 B CN107740710 B CN 107740710B
- Authority
- CN
- China
- Prior art keywords
- turbine shell
- turbine
- channel
- waste gas
- gas bypass
- 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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- 239000002912 waste gas Substances 0.000 claims abstract description 56
- 230000007704 transition Effects 0.000 claims abstract description 39
- 238000007789 sealing Methods 0.000 claims abstract description 4
- 239000007789 gas Substances 0.000 claims description 36
- 230000007246 mechanism Effects 0.000 claims description 8
- 239000002699 waste material Substances 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 abstract description 7
- 239000000446 fuel Substances 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 description 8
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 8
- 230000006872 improvement Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
- F02B37/183—Arrangements of bypass valves or actuators therefor
-
- 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
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
- F02B37/183—Arrangements of bypass valves or actuators therefor
- F02B37/186—Arrangements of actuators or linkage for bypass valves
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention belongs to the technical field of engine turbochargers, and relates to a turbine shell structure, which comprises a turbine shell, wherein an outlet of the turbine shell is connected with a transition joint in a sealing way, a transition joint cavity is formed between the transition joint and the turbine shell, a first turbine shell waste gas bypass channel is arranged at the inner upper part of the turbine shell, an air inlet end of the first turbine shell waste gas bypass channel is communicated with the bottom of the turbine shell, a first turbine shell air inlet channel is arranged at the air outlet end of the first turbine shell waste gas bypass channel is communicated with the transition joint cavity, a waste gas bypass valve used for controlling the opening and closing of the first turbine shell waste gas bypass channel is arranged in the turbine shell, and a second turbine shell air inlet channel is also arranged at the bottom of the turbine shell. The structure realizes the selection and the switching of the two structures by adjusting the structures of the transition joint and the turbine shell, thereby improving the overall combustion efficiency of the engine, further improving the fuel economy and simultaneously reducing the risk of overhigh boost pressure and supercharger rotating speed.
Description
Technical Field
The invention belongs to the technical field of engine turbochargers, and relates to a turbine shell structure.
Background
Turbochargers are effectively air compressors that compress air to increase the amount of engine intake air. The turbine drives a coaxial impeller by utilizing the inertial impulse of waste gas discharged by the engine, and the impeller presses and sends air sent by an air filter pipeline to boost the air into a cylinder. When the rotation speed of the engine is increased, the exhaust gas discharge speed and the rotation speed of the turbine are synchronously increased, the impeller compresses more air to enter the cylinder, more fuel can be combusted by increasing the pressure and the density of the air, and the output power of the engine can be increased by correspondingly increasing the fuel quantity and adjusting the rotation speed of the engine. The asymmetric double-runner design is based on an exhaust gas recirculation technique, which is a technique of reintroducing a portion of exhaust gas generated after combustion of the engine into the engine cylinder through an air intake duct. By reducing the amount of oxygen in the engine combustion chamber, the combustion temperature is reduced, thereby reducing nitrogen oxides (NOx) in the engine exhaust. In order to fully mix the exhaust gas after combustion of the engine with the high-pressure air delivered by the turbocharger impeller, the exhaust gas pressure needs to be increased. By the asymmetric double-runner design of the turbine shell of the turbocharger, the smaller runner can block the exhaust of the engine exhaust gas, so that the exhaust gas pressure is improved. When the engine is in a high-speed and high-load state, in order to avoid the over-high boost pressure and the over-high speed of the supercharger, a part of waste gas is usually discharged through a waste gas bypass valve, and the part of waste gas does not work through a turbine but is directly bypassed to a turbine shell outlet, so that the boost pressure and the speed of the supercharger are controlled within a safe range. However, in the technology, under the working condition of high rotation speed of the engine, the exhaust gas discharged through the bypass valve does not participate in turbine work, and the partial exhaust gas energy is not directly utilized, so that the overall supercharging efficiency of the supercharger is reduced.
The design of the waste gas balance valve can also avoid the too high boost pressure and the rotating speed of the supercharger. The design of the exhaust balancing valve is specially designed for an asymmetric double-flow-passage supercharger. In an asymmetric double-flow-passage turbocharger, the pressure of exhaust gas in a smaller flow passage is higher, the air flow speed is higher, the influence on the rotating speed of the turbocharger is large, and the pressure and the air flow speed of a larger flow passage are relatively smaller. When the engine is in a high-speed and large-load state, the small flow passage is communicated with the large flow passage through the exhaust gas balance valve, and exhaust gas with higher pressure in the small flow passage enters the large flow passage, so that the pressure in the small flow passage and the air flow speed are reduced, the turbine speed is reduced, and the supercharging pressure and the supercharger rotating speed are controlled within a safe range. Although the technology can avoid the problem that the waste gas bypass technology reduces the supercharging efficiency, when the engine is turned over too high, the pressure and the flow velocity in the large and small flow channels can not be controlled within a reliable range through the waste gas balance valve, namely the supercharging pressure and the supercharger rotating speed can not be controlled within a safe range.
For the turbine housing inlet exhaust gas control valve, a patent similar to the structure of the invention is CN 200880022691.8, and in the structure described in the patent, a bypass channel does not have long-range channel drainage, so compared with the invention, the technology has the advantage that the impact of exhaust gas on a bypass valve plate due to pulse is larger. And the technology can only realize the balance function, and compared with the invention, the technology can not realize the switching between bypass and balance.
Disclosure of Invention
The invention aims at the problems and provides a turbine shell structure, which realizes the selection and switching of two structures by adjusting the structures of a transition joint and a turbine shell, thereby improving the overall combustion efficiency of an engine, further improving the fuel economy and simultaneously reducing the risks of high supercharging pressure and high supercharger rotating speed.
According to the technical scheme of the invention: a turbine shell housing structure, characterized by: including the turbine shell, the export sealing connection transition joint of turbine shell forms the transition joint cavity between transition joint and the turbine shell, and upper portion is equipped with first turbine shell waste gas bypass passageway in the turbine shell, and the inlet end intercommunication turbine shell bottom of first turbine shell waste gas bypass passageway sets up first turbine shell air inlet channel, and the outlet end intercommunication transition joint cavity of first turbine shell waste gas bypass passageway is equipped with the waste gas bypass valve that is used for controlling first turbine shell waste gas bypass passageway switching in the turbine shell, and turbine shell bottom still is provided with second turbine shell air inlet channel.
As a further improvement of the invention, a second turbine shell waste gas bypass channel is also arranged at the upper part in the turbine shell, and two ends of the second turbine shell waste gas bypass channel are respectively communicated with a second turbine shell air inlet flow channel and an excessive joint cavity.
As a further improvement of the invention, a transition joint waste gas bypass channel is arranged on the transition joint, one end of the transition joint waste gas bypass channel is communicated with the transition joint cavity, and the other end of the transition joint waste gas bypass channel is communicated with the turbine shell outlet.
As a further improvement of the invention, a bushing is fixed on the turbine shell, a rocker arm shaft is rotatably arranged in the bushing, the inner end of the rocker arm shaft is connected with the waste gate valve, the outer end of the rocker arm shaft is connected with the rocker arm, and the rocker arm is driven by a pneumatic actuating mechanism to act.
As a further improvement of the invention, the pneumatic actuating mechanism comprises a cylinder and a connecting rod connected with a piston rod of the cylinder, and the connecting rod is connected with a rocker arm.
As a further improvement of the invention, the first turbine waste gas bypass channel comprises an upper channel and a lower channel which are mutually communicated, wherein the upper channel is a round hole with uniform inner diameter, the upper end of the upper channel is communicated with the transition joint cavity, the lower channel is an arc-shaped channel, and the lower channel is communicated with the first turbine shell air inlet channel.
As a further improvement of the present invention, the cross-sectional area of the first turbine housing inlet flow passage is smaller than the cross-sectional area of the second turbine housing inlet flow passage.
As a further improvement of the present invention, the inlet of the waste gate of the first turbine housing coincides with the inlet direction of the inlet flow passage of the first turbine housing.
The invention has the technical effects that: the invention has simple, compact and reasonable structure, can realize the rapid switching of the two functions of waste gas balance and waste gas bypass by only adjusting the machining of the individual characteristics of the transition joint and the turbine shell, and has lower manufacturing and adjusting cost; the invention can balance and control the pressure difference of the two flow channels, and can effectively reduce the supercharging pressure and the rotation speed of the supercharger, thereby improving the integral combustion efficiency of the engine; meanwhile, the long-range waste gas bypass channel is adopted, so that waste gas pulse can be effectively slowed down, impact abrasion of bypass airflow to the valve plate of the bypass valve is reduced, and the service life and reliability of the valve plate of the waste gas bypass valve are improved.
Drawings
FIG. 1 is a cross-sectional view of a valve plate of an exhaust balancing valve according to the present invention.
Fig. 2 is a sectional view showing the closing of the valve plate of the wastegate valve according to the present invention.
Fig. 3 is a closed perspective view of the valve plate of the exhaust gas balance valve of the present invention.
FIG. 4 is an opening cross-sectional view of a valve plate of an exhaust balancing valve according to the present invention.
Fig. 5 is an opening cross-sectional view of a valve plate of the wastegate valve of the present invention.
Fig. 6 is a side sectional view of the first wastegate runner when the wastegate valve of the present invention is opened.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings.
In fig. 1 to 6, the turbine housing comprises a turbine housing 1, a first turbine housing waste gas bypass passage 2a, an upper passage 2a-1, a lower passage 2a-2, a second turbine housing waste gas bypass passage 2b, a first turbine housing intake runner 3a, a second turbine housing intake runner 3b, a waste gas bypass valve 4, a pneumatic actuator 5, a rocker arm 6, a rocker arm shaft 7, a bushing 8, a transition joint 9, a transition joint cavity 10, a transition joint waste gas bypass passage 11, and the like.
As shown in fig. 1-6, the turbine shell structure of the invention comprises a turbine shell 1, an outlet of the turbine shell 1 is in sealing connection with a transition joint 9, a transition joint cavity 10 is formed between the transition joint 9 and the turbine shell 1, a first turbine shell waste gas bypass channel 2a is arranged at the upper part in the turbine shell 1, an air inlet end of the first turbine shell waste gas bypass channel 2a is communicated with the bottom of the turbine shell 1, a first turbine shell air inlet channel 3a is arranged at the bottom of the turbine shell 1, an air outlet end of the first turbine shell waste gas bypass channel 2a is communicated with the transition joint cavity 10, a waste gas bypass valve 4 for controlling the opening and closing of the first turbine shell waste gas bypass channel 2a is arranged in the turbine shell 1, and a second turbine shell air inlet channel 3b is also arranged at the bottom of the turbine shell 1.
The upper part in the turbine shell 1 is also provided with a second turbine shell waste gas bypass channel 2b, two ends of the second turbine shell waste gas bypass channel 2b are respectively communicated with a second turbine shell air inlet flow channel 3b and an excessive joint cavity 10, and the cross section area of the first turbine shell air inlet flow channel 3a is smaller than that of the second turbine shell air inlet flow channel 3 b. At this time, an exhaust gas balancing function is realized.
The transition joint 9 is provided with a transition joint waste gas bypass channel 11, one end of the transition joint waste gas bypass channel 11 is communicated with the transition joint cavity 10, and the other end is communicated with the outlet of the turbine shell 1. At this time, the waste gate function is realized.
The turbine shell 1 is fixedly provided with a bushing 8, a rocker arm shaft 7 is rotatably arranged in the bushing 8, the inner end of the rocker arm shaft 7 is connected with the waste gate valve 4, the outer end of the rocker arm shaft 7 is connected with a rocker arm 6, and the rocker arm 6 is driven by a pneumatic actuator 5 to act.
The pneumatic actuating mechanism 5 comprises a cylinder and a connecting rod connected with a piston rod of the cylinder, and the connecting rod is connected with the rocker arm 6.
The first turbine wastegate passage 2a includes an upper passage 2a-1 and a lower passage 2a-2 which are communicated with each other, the upper passage 2a-1 is a circular hole having a uniform inner diameter, the upper end of the upper passage 2a-1 is communicated with the transition joint cavity 10, the lower passage 2a-2 is an arc-shaped passage, and the lower passage 2a-2 is communicated with the first turbine housing intake runner 3a.
The working process of the invention is as follows: when the engine is in a low-speed region, in order to obtain enough boost pressure and exhaust gas pressure, the exhaust gas and high-pressure air are guaranteed to be fully mixed, the torque of the engine is improved, the nitrogen oxides are reduced, the waste gas bypass valve 4 is in a closed state under the action of the pneumatic actuating mechanism 5, and the two bypass channels are closed, so that all the exhaust gas does work through the turbine. When the engine is in a high-speed and heavy-load working condition, the speed of exhaust gas discharged by the engine is increased, the small flow passage is not required to be continuously used for improving the flow rate of the exhaust gas, and an exhaust gas balance valve or a waste gate valve technology is required to be used for controlling the supercharging pressure and the supercharger rotating speed within a specified range. When the exhaust gas pressure balancing technique is used according to the customer's needs, the second turbine housing exhaust gas bypass passage is machined, and the transition joint exhaust gas bypass passage is not machined. Under the action of the pneumatic actuating mechanism 5 and the exhaust pressure at the inlet of the turbine shell 1, the exhaust gas bypass valve 4 turns over around the axis of the rocker shaft 7, and exhaust gas in the first turbine shell air inlet flow channel 3a with smaller cross section area enters a transition joint cavity 10 formed by the turbine shell 1 and the transition joint 9 through the first turbine shell exhaust gas bypass channel 2a due to larger pressure, and then enters the second turbine shell air inlet flow channel with larger cross section area through the second turbine shell exhaust gas bypass channel 2 b. At this time, the exhaust gas pressure reducing speed is reduced in the first turbine housing intake runner 3a with the smaller cross-sectional area due to exhaust gas discharge, and the work done by the exhaust gas in the first turbine housing intake runner 3a with the smaller cross-sectional area on the turbine is reduced, so that the boost pressure and the supercharger speed are controlled. When the customer demands use of the wastegate technology, the second turbine housing wastegate passage 2b is not processed, and the transition joint wastegate passage 11 is processed. Under the action of the pneumatic actuating mechanism 5 and the exhaust pressure at the inlet of the turbine shell 1, the exhaust gas bypass valve 4 turns over around the axis of the rocker shaft 7 and is opened, the exhaust gas in the first turbine shell air inlet flow passage is discharged through the first turbine shell exhaust gas bypass passage and is discharged to the turbine shell outlet through the transition joint cavity without acting through a turbine, and thus the supercharging pressure and the supercharger rotating speed are controlled.
Meanwhile, the first turbine shell waste gas bypass channel is a long-range channel, so that the impact of waste gas pulse on the bypass valve plate can be effectively reduced, and the reliability and the service life of the bypass valve plate are improved.
The invention adopts the long-range waste gas bypass channel, can effectively reduce the impact of waste gas pulse on the bypass valve plate, thereby improving the reliability and the service life of the bypass valve plate. Meanwhile, the invention can realize the switching of the balance valve and the bypass valve through simple machining switching. The functions are more and more comprehensive, various requirements of customers are met, the switching is simple and convenient, the development cost and the switching cost are reduced, and the processing is convenient. The inlet of the first turbine housing waste gas bypass passage 2a is consistent with the inlet direction of the first turbine housing air inlet flow passage 3a, so that waste gas bypass efficiency can be effectively improved.
Claims (6)
1. A turbine shell housing structure, characterized by: the turbine shell comprises a turbine shell (1), an outlet of the turbine shell (1) is connected with a transition joint (9) in a sealing way, a transition joint cavity (10) is formed between the transition joint (9) and the turbine shell (1), a first turbine shell waste gas bypass channel (2 a) is arranged at the inner upper part of the turbine shell (1), a first turbine shell air inlet flow channel (3 a) is arranged at the bottom of the turbine shell (1) communicated with the air inlet end of the first turbine shell waste gas bypass channel (2 a), an air outlet end of the first turbine shell waste gas bypass channel (2 a) is communicated with the transition joint cavity (10), a waste gas bypass valve (4) for controlling the opening and closing of the first turbine shell waste gas bypass channel (2 a) is arranged in the turbine shell (1), and a second turbine shell air inlet flow channel (3 b) is also arranged at the bottom of the turbine shell (1);
the upper part in the turbine shell (1) is also provided with a second turbine shell waste gas bypass channel (2 b), and two ends of the second turbine shell waste gas bypass channel (2 b) are respectively communicated with a second turbine shell air inlet flow channel (3 b) and an excessive joint cavity (10).
2. The turbine housing shell structure of claim 1 wherein: a bushing (8) is fixed on the turbine shell (1), a rocker arm shaft (7) is rotatably arranged in the bushing (8), the inner end of the rocker arm shaft (7) is connected with the waste gate valve (4), the outer end of the rocker arm shaft (7) is connected with the rocker arm (6), and the rocker arm (6) is driven by the pneumatic actuating mechanism (5) to act.
3. The turbine housing structure of claim 2, wherein: the pneumatic actuating mechanism (5) comprises an air cylinder and a connecting rod connected with a piston rod of the air cylinder, and the connecting rod is connected with the rocker arm (6).
4. The turbine housing shell structure of claim 1 wherein: the first turbine exhaust gas bypass channel (2 a) comprises an upper channel (2 a-1) and a lower channel (2 a-2) which are communicated with each other, the upper channel (2 a-1) is a round hole with uniform inner diameter, the upper end of the upper channel (2 a-1) is communicated with the transition joint cavity (10), the lower channel (2 a-2) is an arc-shaped channel, and the lower channel (2 a-2) is communicated with the first turbine shell air inlet flow channel (3 a).
5. The turbine housing shell structure of claim 1 wherein: the cross-sectional area of the first turbine housing air inlet flow channel (3 a) is smaller than the cross-sectional area of the second turbine housing air inlet flow channel (3 b).
6. The turbine housing shell structure of claim 1 wherein: the inlet of the first turbine housing waste gas bypass passage (2 a) is consistent with the inlet direction of the first turbine housing air inlet flow passage (3 a).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711130133.0A CN107740710B (en) | 2017-11-15 | 2017-11-15 | Turbine shell structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711130133.0A CN107740710B (en) | 2017-11-15 | 2017-11-15 | Turbine shell structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107740710A CN107740710A (en) | 2018-02-27 |
| CN107740710B true CN107740710B (en) | 2024-04-19 |
Family
ID=61233316
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711130133.0A Active CN107740710B (en) | 2017-11-15 | 2017-11-15 | Turbine shell structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN107740710B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108547695A (en) * | 2018-06-05 | 2018-09-18 | 无锡康明斯涡轮增压技术有限公司 | Balancing valve apparatus applied to asymmetric path |
| CN113638778B (en) * | 2020-05-11 | 2023-07-25 | 广州汽车集团股份有限公司 | Exhaust gas venting method for turbocharger |
| CN113027598A (en) * | 2021-03-31 | 2021-06-25 | 安徽江淮汽车集团股份有限公司 | Turbocharger and engine system of automobile |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20020029681A (en) * | 2000-10-13 | 2002-04-19 | 이계안 | A turbo-charger providing multiple bypass orifice |
| CN104110300A (en) * | 2014-08-06 | 2014-10-22 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger |
| WO2016078444A1 (en) * | 2014-11-20 | 2016-05-26 | 康跃科技股份有限公司 | Variable geometry wastegate turbine meeting the requirements of egr circulation and guide vane assembly |
| CN106194405A (en) * | 2016-08-29 | 2016-12-07 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger bypass system |
| CN207583447U (en) * | 2017-11-15 | 2018-07-06 | 无锡康明斯涡轮增压技术有限公司 | Turbine case shell structure |
-
2017
- 2017-11-15 CN CN201711130133.0A patent/CN107740710B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20020029681A (en) * | 2000-10-13 | 2002-04-19 | 이계안 | A turbo-charger providing multiple bypass orifice |
| CN104110300A (en) * | 2014-08-06 | 2014-10-22 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger |
| WO2016078444A1 (en) * | 2014-11-20 | 2016-05-26 | 康跃科技股份有限公司 | Variable geometry wastegate turbine meeting the requirements of egr circulation and guide vane assembly |
| CN106194405A (en) * | 2016-08-29 | 2016-12-07 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger bypass system |
| CN207583447U (en) * | 2017-11-15 | 2018-07-06 | 无锡康明斯涡轮增压技术有限公司 | Turbine case shell structure |
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| CN107740710A (en) | 2018-02-27 |
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