CN110107364A - Exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly - Google Patents
Exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly Download PDFInfo
- Publication number
- CN110107364A CN110107364A CN201910486579.XA CN201910486579A CN110107364A CN 110107364 A CN110107364 A CN 110107364A CN 201910486579 A CN201910486579 A CN 201910486579A CN 110107364 A CN110107364 A CN 110107364A
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- CN
- China
- Prior art keywords
- exhaust
- charger
- volute
- turbo
- flow
- 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
-
- 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
- F01D25/04—Antivibration arrangements
- F01D25/06—Antivibration arrangements for preventing blade vibration
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/10—Stators
- F05B2240/12—Fluid guiding means, e.g. vanes
- F05B2240/123—Nozzles
Abstract
The invention belongs to turbo-charger technical fields, it is related to a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, including volute, volute flow passage is set on volute, volute flow passage is divided into two channels by dividing wall, vortex tongue is set on the inside of the inlet end of volute flow passage, and the radially inner band of volute flow passage forms nozzle, flow-guiding structure is arranged at nozzle on the dividing wall.Product of the present invention can effectively improve the high cycle fatigue reliability of booster turbine, and volute is simple to manufacture, and can be realized by repairing a die.
Description
Technical field
The invention belongs to turbo-charger technical fields, are related to a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly.
Background technique
It is well known that exhaust-driven turbo-charger exhaust-gas turbo charger is the equipment for atmospheric pressure to be pressurized supply air-intake of combustion engine entrance.
The turbine that common booster basically comprises turbine volute and is mounted in volute, the volute is in enmgine exhaust
Downstream.The rotation of turbine drives the pressure impeller for being mounted on coaxial other end rotation to compress air and collect by compressor casing
It is transported to engine intake manifold.Turbine wheel shaft is usually by the floating bearing and thrust in the middle case of connection turbine and compressor
Bearing support.
During turbocharger operation, turbine shroud adjusts exhaust gas motion profile by the helical structure of turbine interior, from
And so that exhaust gas is generated when pushing turbine rotation and export maximum power, therefore turbine flow channel shape is to exhaust gas pressure field
Distribution play the role of very important, and booster turbine is due to the influence for the field that is under pressure, especially because turbine flow
The impact of pressure shock wave at the vortex tongue in road, turbo blade can produce very big vibration stress when it resonates humorous secondary revolving speed, from
And the high cycle fatigue failure of turbo blade is resulted in, current turbine inner flow passage design, due to not only to consider the demand of installation
And to consider the demand of performance, therefore very big pressure shock wave is inevitably generated at vortex tongue.For current whirlpool
For wheel design, to meet high-performance simultaneously and resist high exciting force be it is very difficult, the improvement that can be done is than relatively limited.
And for the turbine of fixed nozzle or variable-nozzle, industry more attention is turbo blade in intrinsic frequency
Exciting force under rate, the pressure oscillation in turbo blade inlet are the driving sources of turbine blade vibration, different nozzle forms,
The exciting force of the different harmonic waves of generation has very big difference, and reducing the exciting force under certain harmonic wave by changing design is volute
Emphasis is considered in nozzle design.Turbine during rotation, can all generate a pressure oscillation by vortex tongue every time, therefore for
It is all an activation pressure for turbo blade, and for constant cross-section booster, the pressure at vortex tongue is that turbine turns one
Pressure oscillation maximum position when circle.
Therefore, based on the principle for reducing pressure shock wave at vortex tongue, the optimization of volute changes for what turbine high cycle fatigue failed
It is kind to play crucial effect.The harmonic excitation of turbine can be substantially reduced on basic volute design by the volute of optimization
Power, to reduce turbine high cycle fatigue risk.
Summary of the invention
In view of the above-mentioned problems, providing a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, which can effectively mention the present invention
The high cycle fatigue reliability of high blower turbine, and volute is simple to manufacture, and can be realized by repairing a die.
Technical solution according to the invention: whirlpool is arranged on volute in a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, including volute
Shell runner, volute flow passage are divided into two channels by dividing wall, vortex tongue are arranged on the inside of the inlet end of volute flow passage, volute flow passage
Radially inner band forms nozzle, it is characterised in that: flow-guiding structure is arranged on the dividing wall at nozzle.
As a further improvement of the present invention, the flow-guiding structure is set to dividing wall surface side or is symmetrically disposed on point
Partition surface two sides.
As a further improvement of the present invention, the flow-guiding structure is set to the intermediate shell-side of dividing wall and nozzle simultaneously.
As a further improvement of the present invention, the flow-guiding structure is set to the middle case of volute molded line side and volute simultaneously
Side.
As a further improvement of the present invention, the flow-guiding structure is set to volute molded line side.
As a further improvement of the present invention, the flow-guiding structure is set to the intermediate shell-side of volute.
As a further improvement of the present invention, the flow-guiding structure is set on dividing wall away from axle center 1 again to 2 times of turbine
At radius.
As a further improvement of the present invention, the nozzle that the axial dimension of the flow-guiding structure is 0.1 times to 0.5 times is wide
Degree.
As a further improvement of the present invention, the circumferential machining angle range of the flow-guiding structure is 1 degree to 30 degree.
As a further improvement of the present invention, the flow-guiding structure is protrusion or groove.
As a further improvement of the present invention, the groove passes through vortex tongue, and is connected to the high-voltage end at vortex tongue and low-pressure end.
As a further improvement of the present invention, the machined surface of the flow-guiding structure be square or annular.
As a further improvement of the present invention, the radial section of the flow-guiding structure is rounded.
As a further improvement of the present invention, the radial section of the flow-guiding structure is triangular in shape.
The technical effects of the invention are that: product of the present invention can effectively improve the high cycle fatigue reliability of booster turbine,
And volute is simple to manufacture, and can be realized by repairing a die.
Detailed description of the invention
Fig. 1 is vertical section schematic diagram of the invention.
Fig. 2 is schematic cross section of the invention.
Fig. 3 is vertical section partial enlarged view of the invention.
Specific embodiment
A specific embodiment of the invention is further described with reference to the accompanying drawing.
In Fig. 1 ~ 3, including volute 1, volute flow passage 2, vortex tongue 3, dividing wall 4, nozzle 5, volute molded line 6, protrusion 7 etc..
As shown in Fig. 1 ~ 3, product of the present invention is a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, including volute 1, on volute 1
Volute flow passage 2 is set, and volute flow passage 2 is divided into two channels by dividing wall 4, vortex tongue is arranged on the inside of the inlet end of volute flow passage 2
3, the radially inner band of volute flow passage 2 forms nozzle 5, and flow-guiding structure is arranged at nozzle 5 on the dividing wall 4.
Flow-guiding structure in product of the present invention needs according to the actual situation, and there are many set-up modes, specific as follows: water conservancy diversion knot
Structure is set to 4 surface side of dividing wall or is symmetrically disposed on 4 surface two sides of dividing wall.
Flow-guiding structure can be set to the intermediate shell-side of dividing wall 4 and nozzle 5 simultaneously.
Flow-guiding structure can be set to the intermediate shell-side of 6 side of volute molded line and volute simultaneously, and volute molded line 6 is turbine and whirlpool
The matching surface of shell.
Flow-guiding structure can also only be set to 6 side of volute molded line；Flow-guiding structure can also be set to the middle case of volute
Side；Flow-guiding structure is set on dividing wall 4 away from axle center 1 again at 2 times of turbine radius.
5 width of nozzle that the axial dimension of flow-guiding structure is 0.1 times to 0.5 times；The circumferential machining angle model of flow-guiding structure
Enclose is 1 degree to 30 degree.
Groove passes through vortex tongue 3, and is connected to high-voltage end and low-pressure end at vortex tongue 3.
The machined surface of flow-guiding structure is square or annular；The radial section of flow-guiding structure is rounded or radial section is in triangle
Shape.It is understood that the main purpose of flow-guiding structure is to realize the guiding of air-flow, it can be raised or recessed in specific setting
Slot.
The present invention is a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, and the effect of volute 1 is started by the change of volute flow passage 2
Machine exhaust gas flow direction, the twist structure of volute flow passage 2, and its area from vortex tongue 3 constantly reduce, different cylinders
Exhaust gas is divided into two channels by dividing wall 4, and the effect of dividing wall 4 is the exhaust gas for separating engine difference cylinder, so as to effective
The pulse energy generated using different cylinder exhaust gas.Spiral 2 structure of volute flow passage will make flow rotation advance, two channels
Exhaust gas passes through vortex tongue 3 respectively, and the air-flow near vortex tongue 3 converges at nozzle 5 after being oriented to through volute flow passage 2 by protrusion 7
Together and enter nozzle 5, nozzle 5 is a smooth torus channel, which is completed by machining, and exhaust gas is impacted by nozzle 5
Turbine acting, is supplied to generator terminal kinetic energy of calming the anger.When air-flow passes through vortex tongue 3 and also do not reach nozzle 5, protrusion 7 will receive
Disturbance, and formed and be vortexed at protrusion 7, the vortex of formation can effectively reduce pressure of the air-flow at this, so as to have
Effect reduces the pressure shock wave at former vortex tongue 3.To effectively reduce the high cycle fatigue risk of turbo blade, to improve pressurization
The reliable life of device.
As shown in Figure 1, the protrusion 7 in product of the present invention is close to volute vortex tongue, cross section is rectangle, radial Working position
It is greater than turbine outer diameter, but less than 2 times turbine radiuses apart from turbine axle center.The radial range of work of protrusion 7 is 0.1 times to 1 times
Volute nozzle width, the radial range of work can generate different effects to pressure shock wave at vortex tongue 3 is reduced, and range is wider, generally
In the case of effect it is better, but range is wide influences whether volute entirety aeroperformance, so the radial processing model of protrusions of the present invention 7
It encloses and is limited to 0.1 times to 1 times of volute nozzle width.Protrusions 7 of the present invention are in symmetrical machining on dividing wall, work as pressure shock wave
When being unevenly distributed in the axial direction, can according to actual pressure shock wave form, protrusion 7 two sides height of projection with different height
Processing, it might even be possible to only in the unilateral processing protrusion of dividing wall 4.Not influence volute entirety aeroperformance, by protrusion 7 in the present invention
Height of projection be limited to 0.1 to 0.5 times of volute nozzle width.
It as shown in Figure 1, the protrusion 7 in the present invention is processed on dividing wall 4, and is in symmetrical machining.At volute vortex tongue
When pressure shock wave is simultaneously uneven in the axial direction, which can only be processed in 4 side of dividing wall, it might even be possible to add its protrusion
Work the molded line side of volute nozzle come achieve the effect that reduce pressure shock wave.For binary channels volute, the axial cloth set of protrusion 7
Setting can be respectively arranged in one or more forms in 4 two sides of nozzle two sides and dividing wall according to the characteristics of pressure shock wave.
As shown in Fig. 2, the new design protrusion 7 of the present invention, close to volute vortex tongue, machined surface is in rectangle.The processing of protrusion 7 rises
Beginning positional distance vortex tongue the tip of the tongue circumferential direction angle is 5 degree.The processing initial position of protrusion 7 is determined according to pressure shock wave, can be with
Before and after vortex tongue, any angle is arranged in circumferential direction.It can not also be identical for the position of different volutes, protrusion 7.Protrusion
7 circumferential machining angle range will affect the effect for reducing pressure shock wave at vortex tongue, and range is excessive also to will affect volute integrally gas
Dynamic performance, so limiting the circumferential machining angle range of protrusion 7 in the present invention as 1 degree to 30 degree.
As shown in figure 3, the new design protrusion 7 of the present invention, close to volute vortex tongue, machined surface is in rectangle.The machined surface of protrusion 7
Product can generate different effects to pressure shock wave at vortex tongue is reduced, and area is bigger, and effect is better, but area is excessive influences whether whirlpool
Shell entirety aeroperformance, so 7 working (finishing) area of protrusions of the present invention is limited to 0.1 times to 0.5 times of volute key sectional area.
As shown in Fig. 2, raised 7 features of the new design of the present invention are also possible to notch feature, processing dimension limit with it is convex
It is consistent to play feature.When feature is groove, which can even pass across volute vortex tongue, air-flow before and after connection vortex tongue
High-voltage end and low-pressure end.When air-flow, which flows through vortex tongue, flows to the groove location, by the disturbance of notch feature, reduce at this
Stream pressure, and partial high pressure air-flow directly passes through and mixes at the low pressure after groove flows to vortex tongue with low-pressure gas, balances
The pressure of air-flow before and after vortex tongue, reduces the pressure difference before and after volute vortex tongue, presses to can also reach and be effectively reduced at volute vortex tongue
The effect of power shock wave.
As shown in Fig. 2, the new design protrusion 7 of the present invention is close to volute vortex tongue, and in the circumferential in single arrangement.The protrusion
In addition to the adjustable circumferential range of work, can also by it is multiple it is concatenated in the form of arrange, the circumferential range of work of each protrusion is not
It needs unanimously, but in order to not influence volute entirety aeroperformance, the circumferential range of work of each protrusion is still limited to 1 degree to 30
Degree, and the integral circumferential range for protrusion of connecting is no more than 90 degree.
For constant cross-section booster, engine exhaust enters nozzle by volute vortex tongue, then does work into turbine,
Huge pressure difference will necessarily be generated before and after vortex tongue, this pressure difference is inevitable, and pressure shock wave will be generated when serious.The pressure
Power shock wave can make turbine generate very big blade vibration in its resonance speed, so that the high cycle fatigue for generating turbo blade is lost
Effect.It is all to be utilized in the design of protrusion 7 of the invention by changing the pressure distribution at volute vortex tongue, to reach balance volute whirlpool
Pressure before and after tongue, to reduce and improve the principle of the pressure shock wave at volute vortex tongue.To effectively reduce the input of turbine
Excitation, improves the reliability of turbo blade high cycle fatigue.
Above description is explanation of the invention, is not intended to limit the invention, and limited range of the present invention is referring to right
It is required that within protection scope of the present invention, any type of modification can be made.
The configuration of the present invention is simple, compact and reasonable can effectively improve the reliability of the high cycle fatigue of booster turbine, and volute
Processing and manufacturing is simple.
Claims (14)
1. a kind of exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly, including volute (1), volute flow passage (2) are set on volute (1), volute stream
Road (2) is divided into two channels by dividing wall (4), vortex tongue (3) is arranged on the inside of the inlet end of volute flow passage (2), volute flow passage (2)
Radially inner band form nozzle (5), it is characterised in that: flow-guiding structure is set at nozzle (5) on the dividing wall (4).
2. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is set to point
Partition wall (4) surface side is symmetrically disposed on dividing wall (4) surface two sides.
3. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is arranged simultaneously
In the intermediate shell-side of dividing wall (4) and nozzle (5).
4. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is arranged simultaneously
Intermediate shell-side in volute molded line (6) side and volute.
5. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is set to whirlpool
Shell mould line (6) side.
6. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is set to whirlpool
The intermediate shell-side of shell.
7. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the flow-guiding structure is set to point
On partition wall (4) away from axle center 1 again at 2 times of turbine radius.
8. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the axial ruler of the flow-guiding structure
Very little nozzle (5) width for being 0.1 times to 0.5 times.
9. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the circumferential direction of the flow-guiding structure adds
Work angular range is 1 degree to 30 degree.
10. such as the described in any item exhaust-driven turbo-charger exhaust-gas turbo charger scroll assemblies of claim 1 ~ 9, it is characterised in that: the water conservancy diversion knot
Structure is protrusion or groove.
11. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as claimed in claim 10, it is characterised in that: the groove passes through vortex tongue
And the high-voltage end and low-pressure end that are connected at vortex tongue (3) (3),.
12. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the processing of the flow-guiding structure
Face is square or annular.
13. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the radial direction of the flow-guiding structure
Circular cross section.
14. exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly as described in claim 1, it is characterised in that: the radial direction of the flow-guiding structure
Section is triangular in shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910486579.XA CN110107364A (en) | 2019-06-05 | 2019-06-05 | Exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910486579.XA CN110107364A (en) | 2019-06-05 | 2019-06-05 | Exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110107364A true CN110107364A (en) | 2019-08-09 |
Family
ID=67493953
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910486579.XA Pending CN110107364A (en) | 2019-06-05 | 2019-06-05 | Exhaust-driven turbo-charger exhaust-gas turbo charger scroll assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110107364A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111197504A (en) * | 2020-03-10 | 2020-05-26 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger volute assembly |
| CN113931706A (en) * | 2021-10-20 | 2022-01-14 | 无锡康明斯涡轮增压技术有限公司 | Turbine shell assembly for double-runner turbocharger and turbocharger |
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| DE102013223873A1 (en) * | 2013-11-22 | 2015-05-28 | Continental Automotive Gmbh | Exhaust gas turbocharger with a twin scroll turbine housing |
| CN104956045A (en) * | 2013-02-19 | 2015-09-30 | 博格华纳公司 | A turbocharger internal turbine heat shield having axial flow turning vanes |
| WO2016184617A1 (en) * | 2015-05-21 | 2016-11-24 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Exhaust-gas turbocharger |
| US20180328281A1 (en) * | 2017-05-09 | 2018-11-15 | Honeywell International Inc. | Turbocharger having a meridionally divided turbine housing and a variable turbine nozzle |
| GB2562501A (en) * | 2017-05-16 | 2018-11-21 | Cummins Ltd | Insert element for a turbine of a turbomachine |
| CN113931706A (en) * | 2021-10-20 | 2022-01-14 | 无锡康明斯涡轮增压技术有限公司 | Turbine shell assembly for double-runner turbocharger and turbocharger |
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| JP2000154728A (en) * | 1998-11-19 | 2000-06-06 | Toyota Motor Corp | Variable displacement type turbocharger |
| JP2010121590A (en) * | 2008-11-21 | 2010-06-03 | Ihi Corp | Variable displacement turbocharger |
| CN102536435A (en) * | 2012-03-08 | 2012-07-04 | 康跃科技股份有限公司 | Hybrid flow variable spiral case |
| CN104956045A (en) * | 2013-02-19 | 2015-09-30 | 博格华纳公司 | A turbocharger internal turbine heat shield having axial flow turning vanes |
| CN203476407U (en) * | 2013-05-15 | 2014-03-12 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger volute assembly |
| DE102013223873A1 (en) * | 2013-11-22 | 2015-05-28 | Continental Automotive Gmbh | Exhaust gas turbocharger with a twin scroll turbine housing |
| WO2016184617A1 (en) * | 2015-05-21 | 2016-11-24 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Exhaust-gas turbocharger |
| US20180328281A1 (en) * | 2017-05-09 | 2018-11-15 | Honeywell International Inc. | Turbocharger having a meridionally divided turbine housing and a variable turbine nozzle |
| GB2562501A (en) * | 2017-05-16 | 2018-11-21 | Cummins Ltd | Insert element for a turbine of a turbomachine |
| CN113931706A (en) * | 2021-10-20 | 2022-01-14 | 无锡康明斯涡轮增压技术有限公司 | Turbine shell assembly for double-runner turbocharger and turbocharger |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111197504A (en) * | 2020-03-10 | 2020-05-26 | 无锡康明斯涡轮增压技术有限公司 | Turbocharger volute assembly |
| CN113931706A (en) * | 2021-10-20 | 2022-01-14 | 无锡康明斯涡轮增压技术有限公司 | Turbine shell assembly for double-runner turbocharger and turbocharger |
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