CN108999664A - A kind of double entrance turbine boxes of change radial clearance - Google Patents
A kind of double entrance turbine boxes of change radial clearance Download PDFInfo
- Publication number
- CN108999664A CN108999664A CN201810682618.9A CN201810682618A CN108999664A CN 108999664 A CN108999664 A CN 108999664A CN 201810682618 A CN201810682618 A CN 201810682618A CN 108999664 A CN108999664 A CN 108999664A
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- China
- Prior art keywords
- turbine
- airflow channel
- radial clearance
- intermediate bulkhead
- boxes
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- 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
- 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
- F01D25/30—Exhaust heads, chambers, or the like
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a kind of double entrance turbine boxes of change radial clearance, comprising: impeller, left airflow channel, right airflow channel and intermediate bulkhead；The left airflow channel and right airflow channel are arranged side by side in the axial direction of turbine wheel inlet excircle in left and right, and the intermediate bulkhead is set at the meridian plane of turbine box between the left airflow channel and right airflow channel；The axial direction of the intermediate bulkhead is annular in shape, and inward flange is rounded, and outer edge twist, within the scope of radial clearance between the inward flange and turbine wheel inlet of the intermediate bulkhead is 0 °~360 ° circumferential at the vortex tongue can be linearly gradually increased.Present invention decreases the internal gas of the left airflow channel of double entrance turbine boxes and right airflow channel to sew, reduction friction loss is additionally aided simultaneously, increase turbine box cross-sectional flow area, the back pressure that turbine generates when reducing or not improving high engine speeds operation, to reduce the fuel consumption of engine.
Description
Technical field
The present invention relates to turbine box technical field more particularly to a kind of double entrance turbine boxes of change radial clearance.
Background technique
Turbocharging is one of the important way that afterheat of IC engine utilizes, while recycling engine exhaust by turbine
Energy drives compressor operating and compressed air, to improve the pressure and density into the fresh air of engine.Therefore,
The use of turbocharger can effectively improve the power and efficiency of internal combustion engine.Exploitation high performance turbine booster can effectively realize section
Energy emission reduction, has important practical significance.
Turbocharger is made of compressor and turbine, and outer housing includes compressor volute, bear box and whirlpool
Turbine shell.In order to ensure exhaust gas continuously supplies and is avoided that each cylinder exhaust interferes with each other, the exhaust pipe of multi-cylinder engine is logical
Normal packet layout, the turbine cylinder of corresponding turbocharger have multiple entrances.Double entrance turbine boxes are a kind of ratios
The exhaust gas come from two entrances can be imported the entrance of the same turbine wheel in downstream by more typical structure.
For double entrance turbine box structures, the gas come from two entrances is divided in the meridian plane of turbine box by intermediate bulkhead
It opens, and can be supplied with circumferentially 360 ° to turbine wheel, thus the efficiency of turbine is higher.In the prior art, intermediate bulkhead
Inward flange and rotation turbine wheel inlet between radial clearance be constant, i.e., intermediate bulkhead is interior in circumferentially 360 °
Radial clearance between edge and turbine wheel inlet is a steady state value.
The exhaust gas of engine discharge enters from double entrance turbine box vortex tongues, then circumferentially 360 ° supplied to turbine wheel
Gas.Since two entrances are alternately to supply, so a lateral pressure of gas supply is higher than the other side without air supply.In this way, from whirlpool
Tongue starts, and the gas of the high side of pressure will pass through radial clearance δ and flow to the low other side of pressure, causes gas leakage to not
The exhaust pipe of gas supply.The exhaust gas supply on the one hand reducing turbine wheel in this way, on the other hand also disturbs engine section
Cylinder is normally vented.
Summary of the invention
The present invention provides a kind of double entrance turbine boxes of change radial clearance, to overcome above-mentioned technical problem.
The present invention becomes the double entrance turbine boxes of radial clearance, comprising:
Impeller, left airflow channel, right airflow channel and intermediate bulkhead；
The left airflow channel and right airflow channel are in left and right in the axial direction of turbine wheel inlet excircle and arrange
It sets, the intermediate bulkhead is set at the meridian plane of turbine box between the left airflow channel and right airflow channel；
The intermediate bulkhead is annular in shape from booster shaft to seeing, inward flange and the turbine wheel of the intermediate bulkhead enter
It can be linearly gradually increased within the scope of radial clearance between mouthful is 0 °~360 ° circumferential at the vortex tongue.
Further, the radial clearance can be in non-linear gradual increase, the increase within the scope of circumferentially 0 °~360 °
Trend is curve or broken line.
Further, within the scope of circumferentially 0 °~120 °, the ratio of the radial clearance and turbine wheel radius is 5%
~25%.
Further, within the scope of circumferentially 120 °~360 °, the radial clearance and the ratio of turbine wheel radius are
20%~100%.
Present invention decreases the interior leakages for the two side runner gases for becoming the double entrance turbine boxes of radial clearance, and without increasing row
Gas back pressure reduces the cost of engine.Reduction friction loss is additionally aided simultaneously, increases turbine box cross-sectional flow area,
The back pressure that turbine generates when reducing or not improving high engine speeds operation, to reduce the fuel consumption of engine.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is this hair
Bright some embodiments for those of ordinary skill in the art without creative efforts, can be with root
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is the schematic diagram of the radial-flow turbocharger of the prior art；
Fig. 2 is the front view of double entrance turbine boxes of the invention；
Fig. 3 is that double entrance turbine box internal gas of the invention sew schematic diagram；
Fig. 4 is double entrance turbine box meridian plane cross-sectional views of the invention；
Fig. 5 is that the present invention becomes the double one parameter schematic diagrames of entrance turbine box embodiment of radial clearance；
Fig. 6 is that the present invention becomes the double two parameter schematic diagrames of entrance turbine box embodiment of radial clearance；
Fig. 7 is that the present invention becomes the double three parameter schematic diagrames of entrance turbine box embodiment of radial clearance；
Fig. 8 is that the present invention becomes the double entrance turbine box example IV parameter schematic diagrames of radial clearance.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.
The present invention becomes the double entrance turbine boxes of radial clearance
Impeller, left airflow channel, right airflow channel and intermediate bulkhead；
The left airflow channel and right airflow channel are in left and right in the axial direction of turbine wheel inlet excircle and arrange
It sets, the intermediate bulkhead is set at the meridian plane of turbine box between the left airflow channel and right airflow channel；
The intermediate bulkhead is annular in shape from booster shaft to seeing, inward flange is rounded, outer edge twist, it is described in
It can be in line within the scope of radial clearance between the inward flange and turbine wheel inlet of spacing board is 0 °~360 ° circumferential at the vortex tongue
Property is gradually increased.
Specifically, the double entrance turbine boxes of the change radial clearance of the present embodiment are suitable for the radial turbine of multi-cylinder engine
Booster, as shown in Fig. 2, whole includes: double entrance turbine boxes 100), bear box 200) and compressor volute 300).It is described
Double entrance turbine boxes 100) include left airflow channel 101), right airflow channel 102) and intermediate bulkhead 103).Left airflow channel
101) and right airflow channel 102) in turbine wheel 104) axial direction of entrance excircle is arranged side by side in left and right, left air-flow is logical
Road 101) and right airflow channel 102) pass through the intermediate bulkhead 103 that is arranged at turbine box meridian plane) separate.
As shown in figure 4, defining double entrance turbine boxes 100) intermediate bulkhead 103) inward flange and turbine wheel 104) enter
Radial clearance between mouthful is δ, is defined at vortex tongue as 0 ° of circumferential angle.As shown in figure 4, be counterclockwise gas flow direction,
Corresponding circumferential direction angle θ is gradually increased.δ is constant in traditional design, i.e. θ is within the scope of 0 °~360 °, radial clearance δ) it is one
Steady state value.
Variable diameter is to gap delta) refer to double entrance turbine boxes 100) intermediate bulkhead 103) inward flange and turbine wheel 104)
Radial clearance δ between entrance) it is not steady state value.Along gas flow direction, circumferential angle θ is radial within the scope of 0 °~360 °
Gap delta) it is gradually increased.
Radial clearance refers to the gap between the intermediate bulkhead inward flange and turbine wheel inlet of double entrance turbine boxes, passes
This radial clearance δ in the design of system) be constant, i.e., this radial clearance δ in circumferentially 360 °) it is a steady state value.The variable diameter to
Gap delta) refer to radial clearance δ between the intermediate bulkhead inward flange and turbine wheel inlet of double entrance turbine boxes) it is not permanent
Definite value.It counts at vortex tongue as 0 ° of circumferential angle, increases along gas flow direction circumferential direction angle.
The intermediate bulkhead 103) it is annular in shape from booster shaft to seeing, inner edges are rounded, and outer edge is twist.
Double entrance turbine boxes 100) intermediate bulkhead 103) inward flange and turbine wheel 104) there are radial clearance δ) between entrance.Such as
Shown in Fig. 1, the radial-flow turbocharger of prior art multi-cylinder engine, including double entrance turbine boxes 100, bear box 200
With compressor volute 300.
As shown in figure 3, the exhaust gas of engine discharge enters from double entrance turbine box vortex tongues, then circumferentially 360 ° to whirlpool
Engine blade wheel gas supply.Since two entrances are alternately to supply, so a lateral pressure of gas supply is higher than the other side without air supply.
In this way, the gas of the high side of pressure will pass through radial clearance δ since vortex tongue) it is flowed to the low other side of pressure, it causes existing
There is in technology booster gas leakage to exhaust pipe without air supply.On the one hand reduce the exhaust gas supply of turbine wheel in this way,
On the other hand engine section cylinder is also disturbed normally to be vented.
As shown in figure 5, circumferential direction angle θ is linearly gradually increased within the scope of 0 °~360 °.
Circumferential angle θ 0 °~120 ° of 1 value of θ in 0 °~θ, 1 range), characteristic δ/R radial clearance δ and turbine wheel
The ratio of radius R) it can change in 5%~25% range；And circumferential angle is in 360 ° of-θ 1) range, characteristic δ/R is radial
The ratio of gap delta and turbine wheel radius R) it can change in 20%~100% range.
Further, the radial clearance can be in non-linear gradual increase, the increase within the scope of circumferentially 0 °~360 °
Trend is curve or broken line.
Specifically, as shown in fig. 6, circumferential direction angle θ is in convex non-linear gradual increase within the scope of 0 °~360 °.
Circumferential angle θ 0 °~120 ° of 1 value of θ in 0 °~θ, 1 range), characteristic δ/R radial clearance δ and turbine wheel
The ratio of radius R) it can change in 5%~25% range；And circumferential direction angle θ is in 360 ° of-θ 1) range, characteristic δ/R is radial
The ratio of gap delta and turbine wheel radius R) it can change in 20%~100% range.
As shown in fig. 7, circumferential direction angle θ is in recessed non-linear gradual increase within the scope of 0 °~360 °.
Circumferential angle θ 0 °~120 ° of 1 value of θ in 0 °~θ, 1 range), characteristic δ/R radial clearance δ and turbine wheel
The ratio of radius R) it can change in 5%~25% range；And circumferential angle is in 360 ° of-θ 1) range, characteristic δ/R is radial
The ratio of gap delta and turbine wheel radius R) it can change in 20%~100% range.
As shown in figure 8, circumferential direction angle θ is gradually increased within the scope of 0 °~360 ° in broken line.
Circumferential angle θ 0 °~120 ° of 1 value of θ in 0 °~θ, 1 range), characteristic δ/R radial clearance δ and turbine wheel
The ratio of radius R) it can change in 5%~25% range；Circumferential angle θ 180 °~360 ° of 2 value of θ within the scope of 2~360 ° of θ),
The ratio of characteristic δ/R radial clearance δ and turbine wheel radius R) it can change in 20%~100% range；Circumferential angle θ
In 1~θ of θ, 2 range, characteristic δ/R can be by linearly or nonlinearly transition.
Fig. 5 to embodiment illustrated in fig. 8 the utility model has the advantages that gas within the scope of 0 °~360 ° during flow forward, because
The conservation of angular momentum and the principle of mass conservation, flow velocity is being continuously increased, and pressure is constantly reducing, and exhaust gas passes through diameter from for gas side
It is increased to gap delta to the difficulty that non-gas supply side leakage is let out.At this moment, turbine box intermediate bulkhead lower end is gradually increased to enter with turbine wheel
Radial clearance δ between mouthful is also equal to be gradually reduced turbine box intermediate bulkhead because the radius R of turbine wheel is constant
Height L can be improved the centrifugation of intermediate bulkhead as shown in figure 8, even finally cancelling intermediate bulkhead, and it is logical to reduce left air-flow
The internal gas of road and right airflow channel is sewed, while additionally aiding reduction friction loss, and increases turbine box cross-sectional flow
Area, the back pressure that turbine generates when reducing or not improving high engine speeds operation, to reduce the fuel consumption of engine.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (4)
1. a kind of double entrance turbine boxes of change radial clearance characterized by comprising
Impeller, left airflow channel, right airflow channel and intermediate bulkhead；
The left airflow channel and right airflow channel are arranged side by side in the axial direction of turbine wheel inlet excircle in left and right, institute
Intermediate bulkhead is stated between the left airflow channel and right airflow channel, and is set at the meridian plane of turbine box；
The intermediate bulkhead is in booster shaft to annular in shape, the inward flange and turbine wheel inlet of the intermediate bulkhead it
Between radial clearance it is 0 °~360 ° circumferential at the vortex tongue within the scope of can linearly be gradually increased.
2. the double entrance turbine boxes of change radial clearance according to claim 1, which is characterized in that the radial clearance is in circumferential direction
Increase tendency within the scope of 0 °~360 ° is curve or broken line.
3. the double entrance turbine boxes of change radial clearance according to claim 1, which is characterized in that in circumferential 0 °~120 ° ranges
Interior, the ratio of the radial clearance and turbine wheel radius is 5%~25%.
4. the double entrance turbine boxes of change radial clearance according to claim 1, which is characterized in that in circumferential 120 °~360 ° models
In enclosing, the ratio of the radial clearance and turbine wheel radius is 20%~100%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810682618.9A CN108999664B (en) | 2018-06-27 | 2018-06-27 | Variable-radial-clearance double-inlet turbine box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810682618.9A CN108999664B (en) | 2018-06-27 | 2018-06-27 | Variable-radial-clearance double-inlet turbine box |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108999664A true CN108999664A (en) | 2018-12-14 |
| CN108999664B CN108999664B (en) | 2021-06-08 |
Family
ID=64601404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810682618.9A Active CN108999664B (en) | 2018-06-27 | 2018-06-27 | Variable-radial-clearance double-inlet turbine box |
Country Status (1)
| Country | Link |
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Cited By (1)
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2001397A (en) * | 1977-07-21 | 1979-01-31 | Hitachi Ltd | Exhaust gas turbocharger |
| US4143994A (en) * | 1976-11-30 | 1979-03-13 | Kabushiki Kaisha Komatsu Seisakusho | Turbine housing for centrifugal turbosupercharger |
| JPS63215829A (en) * | 1987-03-04 | 1988-09-08 | Hitachi Ltd | Exhaust turbo-supercharger |
-
2018
- 2018-06-27 CN CN201810682618.9A patent/CN108999664B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4143994A (en) * | 1976-11-30 | 1979-03-13 | Kabushiki Kaisha Komatsu Seisakusho | Turbine housing for centrifugal turbosupercharger |
| GB2001397A (en) * | 1977-07-21 | 1979-01-31 | Hitachi Ltd | Exhaust gas turbocharger |
| JPS63215829A (en) * | 1987-03-04 | 1988-09-08 | Hitachi Ltd | Exhaust turbo-supercharger |
Cited By (1)
| 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 |
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|---|---|
| CN108999664B (en) | 2021-06-08 |
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