CN105298551B - Exhaust gas bypass turbine with stator - Google Patents
Exhaust gas bypass turbine with stator Download PDFInfo
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- CN105298551B CN105298551B CN201510768130.4A CN201510768130A CN105298551B CN 105298551 B CN105298551 B CN 105298551B CN 201510768130 A CN201510768130 A CN 201510768130A CN 105298551 B CN105298551 B CN 105298551B
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Abstract
The invention discloses the exhaust gas bypass turbine with stator, including turbine case, position on power turbine and air inlet runner, the turbine case close to power turbine afterbody is installed in the turbine case and is provided with the non-blade nozzle that air inlet runner is imported into the gas for importing power turbine；It is provided with close to the position of non-blade nozzle in the turbine case and can adjust the guide vane assembly of the through-current capability of turbine case by changing the number of stator, size, angle, arrangement, so, one serial booster only uses a kind of turbine case, its through-current capability is adjusted by the number of stator, size, angle, arrangement, not only greatly reduce die cost, and through-current capability can also be fine-tuned, it is optimal matching performance.Along with the stator conformity of production of hot investment casting is good, it is easier to meet after discharge upgrading state IV, state V to booster pressure ratio, the coherence request of flow.
Description
Technical field
The present invention relates to a kind of turbine in turbocharger, more particularly to a kind of exhaust gas bypass whirlpool with stator
Turbine, belongs to field of internal combustion engine.
Background technology
The vehicular engine range of speeds is wide, and turbocharger is limited by engine and booster characteristic, it is difficult to high and low
Fast end obtains optimal matching.If by the matching of high speed end, low speed end boost pressure is not enough, in order to not make smoke emission
Energy etc. deteriorates, it has to limit fuel delivery（Pass through smoking limitator）, so as to sacrifice low speed torque and influence vehicle low speed to drive
Sail performance.Exhaust gas bypass turbocharger is exactly for the product for solving diesel engine low-speed dynamic deficiency and developing, and it is with low
Fast end carries out best match, and low speed boost pressure is high, and smoking limitator does not work（Do not subtract oil）, therefore low speed torque is big,
Exhaust emission is low, and solves the problem of resulting speed end boost pressure is too high by by-passing valve, so as to take into account height
The performance at fast end.
Exhaust gas bypass turbocharger basic functional principle is identical with general turbocharger, but it many one in turbine
Exhaust gas by-pass valve at import and the executing agency for being turned on, being closed by Pressure control.It will be seen from figure 1 that useless
Gas bypath valve 9 and the unitary rotation of driver blade 10, and pass through push rod 6 and actuator 5（It is fixed on support 4 in pressurizer shell）
One end of middle spring is connected, and the other end of actuator 5 then exports boost pressure by sebific duct 3 and compressor 2 and communicated.
When engine 7 is in low speed, underload, low pressure, exhaust gas bypass valve 9 is closed, and is performed
Spring in device 5 has certain pretightning force.When boost pressure reaches to a certain degree, it is sufficient to overcome initial tension of spring and reach one
During fixed dynamic balance, active force will open exhaust gas bypass valve 9 by push rod 6, trundle 8, driver blade 10, will enter turbine
The portion of machine 1 flows into total air escape pipe through bypass passageways, so as to reduce the waste gas for flowing into power turbine 12, reduces and enters dynamic
The energy of power turbine 12, makes rotating speed and boost pressure decline therewith.
Turbine structure in traditional exhaust gas bypass turbocharger is shown in Fig. 2, Fig. 3, including turbine case 11, heat shield
14th, power turbine 12, non-blade nozzle 19, exhaust gas bypass valve 9, rocking arm 15, axle sleeve 13, driver blade 10, trundle 8, push rod 6,
Actuator 5, boost pressure promotes push rod 6 by actuator 5, and push rod 6 promotes driver blade 10, rocking arm 15 to rotate by trundle 8,
Rocking arm 15 drives exhaust gas bypass valve 9 to open and close.
The through-current capability of turbine case is adjusted by turbine case A/R change, and A, R concept signal are shown in that Fig. 4, A are turbines
The sectional area of shell zero, R is zero section barycenter to turbine case axle center distance.
For the Engine Matching with different displacements, power, a serial turbocharger will match multiple differences
A/R turbine, especially for dual channel impulse turbine machine, will also set different A/R, not only in the property done in different runners
When can test matching, mould cost is limited by, it is impossible to process too many turbine case and carry out fine match, do not reach performance most
It is excellent, moreover, in batch production in later stage, a series of different turbine cases of A/R are had, mould is numerous, not only causes cost to increase,
Add management difficulty.
Along with the upgrading of present draining technology, state IV, the discharge of state V are gradually transitions, will to the flow and pressure ratio of booster
It is all sand casting to seek more strict, traditional exhaust gas bypass structure turbine case, it is difficult to ensure that conformity of production.
The content of the invention
The technical problem to be solved in the present invention is that the disadvantages mentioned above for being directed to exhaust gas bypass turbocharger is led there is provided a kind of band
The exhaust gas bypass turbocharger of leaf, the through-current capability of turbine case is adjusted by the number of stator, size, angle, arrangement, no
But a serial booster can share a kind of turbine case, greatly reduce die cost, and essence can also be carried out to through-current capability
Thin tuning, is optimal matching performance.
In order to solve the above problems, the present invention uses following technical scheme：
Power turbine is installed in a kind of exhaust gas bypass turbine with stator, including turbine case, the turbine case and entered
It is provided with and is imported into the gas for importing power turbine close to the position of power turbine afterbody on flow channel, the turbine case
The non-blade nozzle of air inlet runner；
Being provided with the turbine case close to the position of non-blade nozzle can be by changing the number of stator, size, angle, row
Cloth adjusts the guide vane assembly of the through-current capability of turbine case.
Further optimization the following is the present invention to such scheme：
The rear end of power turbine turbine wheel shaft is provided with heat shield close to the position of guide vane assembly.
Further optimization：Position in the turbine case close to inlet air flow road junction is provided with turbine case vortex tongue, turbine case whirlpool
Air inlet runner is partitioned into left runner and right runner by tongue.
Further optimization：The guide vane assembly includes a toroidal membrane, is led if the side of toroidal membrane is provided with dry plate
Leaf, if opposite side is provided with stator under dry plate, guide vane assembly hot investment casting is integral.
Further optimization：The lower stator is provided with connecting shaft, and lower stator is by connecting shaft and heat shield grafting into one
It is overall.
Further optimization：Dividing plate is provided with the deep gouge for being provided with step, turbine case vortex tongue and cooperation being thought with step, it is ensured that two
Runner not gas blowby.
So, a serial booster only use a kind of turbine case, its through-current capability by the number of stator, size,
Angle, arranging is adjusted, and not only greatly reduces die cost, and through-current capability can also be fine-tuned, and makes matching
It can be optimal.Along with the stator conformity of production of hot investment casting is good, it is easier to meet after discharge upgrading state IV, state V to increasing
The coherence request of depressor pressure ratio, flow.
Another optimization：If guide vane assembly includes the stator that dry plate is arranged in a ring, the stator is directly cast with heat shield
Integrally.This structure is relatively easy.
Further optimization：The vortex tongue top is plane, and directly distance is 0.1~0.3mm with the tip of stator.
Another optimization：
Air inlet runner in the turbine case is single channel.
Further optimization：If guide vane assembly includes the stator that dry plate is arranged in a ring, the stator is directly cast with heat shield
Integrally.
Another optimization：By-pass prot and inlet flange are provided with the turbine case, the by-pass prot is arranged on air inlet method
Lan Shang.The side of turbine case is no longer arranged in, can be away from aditus laryngis, it is to avoid flow perturbation.
Another optimization：Stator includes long stator and short-range missile leaf, and the length of long stator is more than the length of short-range missile leaf, long stator
Set with short-range missile interlobar septum.
The size of long stator and short-range missile leaf is determined according to flow analysis, but is to widen flow with the benefit of vanelets, similar
In the deviated splitter vane of compressor impeller, reduce and block.
Another optimization：If in dry plate stator, at interval of a stator, a guiding gutter, water conservancy diversion are offered on stator
The direction of groove is consistent with stator, to increase the flow of point at a high speed.
Another optimization：In order to increase driving energy, if the dry plate stator applies not all-round on non-all-round runner
Uniform arrangement.If the dry plate stator is evenly spaced in small flow channels.In the case where there is stator, airflow direction is concentrated, and
Air-flow is also smaller than without stator by area, so can be relatively low energy（Small flow channels are mainly used in the low speed segment of engine, energy
It is small）Put together.
Another optimization：In order to increase driving energy, if the dry plate stator is applied on non-all-round runner and using not
Uniform arrangement.If the arrangement density that dry plate stator is located in small flow channels side is more than the arrangement density positioned at big runner side.
The present invention adjusts the through-current capability of turbine case by adjusting the number of stator, size, angle, arrangement, not only subtracts
Small cost, accelerate research and development speed, improve matching precision, being more that of obtaining the important breakthrough in principle, not only one is
The booster of row can share a kind of turbine case, greatly reduce die cost, and through-current capability can also be fine-tuned, and make
Matching performance is optimal.
The invention will be further described with reference to the accompanying drawings and examples.
Brief description of the drawings
Accompanying drawing 1 is the schematic diagram of exhaust gas bypass turbocharger in background of invention；
Accompanying drawing 2 is the structural representation of exhaust gas bypass turbocharger in background of invention；
Accompanying drawing 3 is the upward view of accompanying drawing 2；
Accompanying drawing 4 is the schematic diagram of A, R on turbine case in background of invention；
Accompanying drawing 5 is the structural representation of the embodiment of the present invention 1；
Accompanying drawing 6 is the connection diagram of actuator and driver blade in the embodiment of the present invention 1；
Accompanying drawing 7 is the structural representation of guide vane assembly in the embodiment of the present invention 1；
Accompanying drawing 8 is the layout viewing of stator in the embodiment of the present invention 1；
Accompanying drawing 9 is the boss on the median septum of the embodiment of the present invention 1 and the deep gouge cooperation schematic diagram in turbine case vortex tongue；
The structural representation of the embodiment of the present invention 2 of accompanying drawing 10；
Accompanying drawing 11 is the structural representation of the embodiment of the present invention 3.
Accompanying drawing 12 is the structural representation of the embodiment of the present invention 4；
Accompanying drawing 13 is the structural representation of the embodiment of the present invention 5；
Accompanying drawing 14 is the layout viewing of stator in the embodiment of the present invention 5；
Accompanying drawing 15 is the structural representation of the embodiment of the present invention 6；
Accompanying drawing 16 is the structural representation of the embodiment of the present invention 7；
Accompanying drawing 17 is the arrangement schematic diagram of stator in the embodiment of the present invention 7.
Accompanying drawing 18 is the structural representation of the embodiment of the present invention 8.
In figure：1- turbines；2- compressors；3- sebific ducts；4- supports；5- actuators；6- push rods；7- engines；8- is driven
Pin；9- exhaust gas bypass valves；10- driver blades；11- turbine cases；12- power turbines；13- axle sleeves；14- heat shields；15- rocking arms；
16- dividing plates；Stator under 17-；18- turbine case vortex tongues；19- non-blade nozzles；The upper stators of 20-；21- guide vane assembly；22- connecting shafts；
23- steps；24- stators；25- by-pass prots；26- inlet flanges；The long stators of 27-；28- short-range missile leaves；29- guiding gutters；30- rills
Road；The big runners of 31-；32- deep gouges.
Embodiment
Embodiment 1, as shown in Fig. 5,6,7,8, a kind of exhaust gas bypass turbine with stator, including turbine case 11, it is described
Position on power turbine 12 and air inlet runner, the turbine case 11 close to the afterbody of power turbine 12 is installed in turbine case 11 to set
It is equipped with the non-blade nozzle 19 that air inlet runner is imported into the gas for importing power turbine 12, the turbine case 11 close to nothing
The position of foliar spray mouth 19, which is provided with, to adjust the through-current capability of turbine case by changing the number of stator, size, angle, arrangement
Guide vane assembly 21.
The guide vane assembly 21 includes a toroidal membrane 16, if the side of toroidal membrane 16 is provided with stator 20 on dry plate,
If opposite side is provided with stator 17 under dry plate, the hot investment casting of guide vane assembly 21 is integral.
The arrangement angle B of upper stator 20 is 68 °~80 °.Lower stator 17 has same arrangement angle with upper stator 20.
The side of the turbine case 11 is provided with by-pass prot 25, by-pass prot 25 and is provided with by exhaust gas bypass valve 9, waste gas
Port valve door 9 is connected with actuator 5.
Exhaust gas bypass valve 9 and the unitary rotation of driver blade 10, and pass through push rod 6 and actuator 5（Increasing is fixed on support 4
On depressor housing）One end of middle spring is connected, and the other end of actuator 5 then exports boost pressure phase by sebific duct 3 with compressor 2
It is logical.
Boost pressure promotes push rod 6 by actuator 5, and push rod 6 promotes driver blade 10, rocking arm 15 to rotate by trundle 8,
Rocking arm 15 drives exhaust gas bypass valve 9 to open and close.
The rear end of the turbine wheel shaft of power turbine 12 is provided with heat shield 14, the lower stator 17 close to the position of guide vane assembly 21
It is provided with connecting shaft 22, lower stator 17 is by connecting shaft 22 and the grafting of heat shield 14 into an entirety.
Position in the turbine case 11 close to inlet air flow road junction is provided with turbine case vortex tongue 18, and turbine case vortex tongue 18 will be entered
Flow channel is partitioned into left runner and right runner, and dividing plate 16 is provided with to be provided with step 23, turbine case vortex tongue 18 to be thought with step 23
The deep gouge 32 of cooperation, it is ensured that two runners not gas blowby.
Upper stator 20, lower stator 17 are separately designed according to matching needs, and the number of stator, size, angle, arrangement can
It is different.
So, a serial booster only use a kind of turbine case, its through-current capability by the number of stator, size,
Angle, arranging is adjusted, and not only greatly reduces die cost, and through-current capability can also be fine-tuned, and makes matching
It can be optimal.Along with the stator conformity of production of hot investment casting is good, it is easier to meet after discharge upgrading state IV, state V to increasing
The coherence request of depressor pressure ratio, flow.
Although the structures such as early stage existing single blade nozzle ring, exhaust gas bypass, as the present invention, are solved from principle
The certainly trickle matching of booster, the skill of careful matching is carried out by the number of stator blade, size, angle, arrangement to booster
Art, not only reduces cost, accelerates research and development speed, improves matching precision, be more that of obtaining the important breakthrough in principle, belong to
Obvious upperseat concept invention.Stator in the present invention, can also using blade, uniform, half cycle does not have leaf half cycle without leaf, length leaf
The various ways such as piece are arranged, specifically used finally to be determined according to simulation calculating and matching test result.
In embodiment 2, above-described embodiment 1, guide vane assembly 21 is made shown in Figure 10, dividing plate 16 is not provided with, stator 24 is straight
Connect with the cast solid of heat shield 14, the top car of vortex tongue 18 put down, with the 0.1~0.3mm of distance between two tips of stator 24.This structure is relatively simple
Single, matching precision is slightly inferior to embodiment 1.
Embodiment 3, as shown in figure 11, single channel turbine case is applied to by the scheme of embodiment 2.
Embodiment 4, as shown in figure 12, the by-pass prot 25 of turbine case are moved on inlet flange 26, are no longer arranged in other realities
The side shown in example is applied, can be away from aditus laryngis, it is to avoid flow perturbation.
Embodiment 5, as shown in Figure 13,14, stator is divided into 28 two kinds of long stator 27, short-range missile leaf, and is spaced apart.
The arrangement angle B of long stator 27 is 68 °~80 °, the arrangement angle B of long stator 27 and the arrangement angle of short-range missile leaf 28
A differential seat angle is：B-A=0 °~5 °, stator 17 has same arrangement angle with upper stator 20.
The size of long stator 27 and short-range missile leaf 28 is determined according to flow analysis, but is to widen flow with the benefit of vanelets,
Similar to the deviated splitter vane of compressor impeller, reduce and block.
Embodiment 6, as shown in figure 15, if in dry plate stator 24, at interval of a stator 24, one is offered on stator 24
Individual guiding gutter 29, the direction of guiding gutter 29 is consistent with stator 24, to increase the flow of point at a high speed.
Embodiment 7, as shown in Figure 16, Figure 17, stator 24 is not that whole circumference has, and non-all-round row is carried out as needed
Cloth.
This structure is mainly used on non-all-round runner, and stator 24 is mainly arranged in small flow channels 30, without stator
It is arranged on big runner 31.Effect is main or in order to increase driving energy, in the case of having stator, and airflow direction is concentrated, and
And air-flow is also smaller than without stator by area, so can be relatively low energy（Small flow channels are mainly used in the low speed segment of engine, energy
Amount is small）Put together.
Embodiment 8, as shown in figure 18, stator 24 use uneven arrangement.This structure be also be mainly used in it is non-all-round
On runner, in small flow channels side, arrange closeer（But stator can not be contacted directly）, in big runner side, arrange more loose.Make
With same as Example 7, it is provided to increase driving energy.
Invention is described in detail according to national patent method for we now, for those skilled in the art
The improvement or replacement of specific embodiment disclosed herein can be recognized.These modifications are within the spirit and scope of the present invention.
Claims (5)
1. the exhaust gas bypass turbine with stator, including turbine case（11）, the turbine case（11）Power turbine is inside installed
（12）And air inlet runner, the turbine case（11）Upper close power turbine（12）The position of afterbody is provided with to by power turbine
（12）The gas of importing imported into the non-blade nozzle of air inlet runner（19）；It is characterized in that：The turbine case（11）Interior close nothing
Foliar spray mouth（19）Position be provided with and can adjust the through-flow energy of turbine case by changing the number of stator, size, angle, arrangement
The guide vane assembly of power（21）；Power turbine（12）The rear end of turbine wheel shaft is close to guide vane assembly（21）Position heat shield is installed
（14）；The turbine case（11）Interior air inlet runner is single channel；Guide vane assembly（21）If including leading that dry plate is arranged in a ring
Leaf（24）, the stator（24）Directly and heat shield（14）Cast solid；The turbine case（11）On be provided with by-pass prot（25）
And inlet flange（26）, the by-pass prot（25）It is arranged on inlet flange（26）On；
Stator（24）Including long stator（27）With short-range missile leaf（28）, long stator（27）Length be more than short-range missile leaf（28）Length,
Long stator（27）With short-range missile leaf（28）It is arranged at intervals；
If dry plate stator（24）In, at interval of a stator, in stator（24）On offer a guiding gutter（29）, guiding gutter
（29）Direction and stator（24）Unanimously.
2. the exhaust gas bypass turbine according to claim 1 with stator, it is characterised in that：
If the dry plate stator（24）Apply the not all-round uniform arrangement on non-all-round runner.
3. the exhaust gas bypass turbine with stator according to claim 2, it is characterised in that：If the dry plate stator
（24）It is evenly spaced in small flow channels（30）On.
4. the exhaust gas bypass turbine according to claim 1 with stator, it is characterised in that：If the dry plate stator
（24）Apply on non-all-round runner and use uneven arrangement.
5. the exhaust gas bypass turbine according to claim 1 with stator, it is characterised in that：Long stator（27）Arrangement
Angle B is 68 °~80 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510768130.4A CN105298551B (en) | 2014-11-20 | 2014-11-20 | Exhaust gas bypass turbine with stator |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410667139.1A CN104389643B (en) | 2014-11-20 | 2014-11-20 | With the exhaust gas bypass turbo machine of stator |
| CN201510768130.4A CN105298551B (en) | 2014-11-20 | 2014-11-20 | Exhaust gas bypass turbine with stator |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410667139.1A Division CN104389643B (en) | 2014-11-20 | 2014-11-20 | With the exhaust gas bypass turbo machine of stator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105298551A CN105298551A (en) | 2016-02-03 |
| CN105298551B true CN105298551B (en) | 2017-09-19 |
Family
ID=52607592
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410667139.1A Active CN104389643B (en) | 2014-11-20 | 2014-11-20 | With the exhaust gas bypass turbo machine of stator |
| CN201510768130.4A Active CN105298551B (en) | 2014-11-20 | 2014-11-20 | Exhaust gas bypass turbine with stator |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410667139.1A Active CN104389643B (en) | 2014-11-20 | 2014-11-20 | With the exhaust gas bypass turbo machine of stator |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN104389643B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN110094238B (en) * | 2019-06-05 | 2024-07-26 | 无锡康明斯涡轮增压技术有限公司 | Exhaust gas turbocharger volute assembly |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4053189A (en) * | 1976-06-17 | 1977-10-11 | United Technologies Corporation | Turbine construction |
| US4821506A (en) * | 1987-10-08 | 1989-04-18 | Sundstrand Corporation | Radial turbine with variable axial nozzle |
| JP2000045784A (en) * | 1998-07-29 | 2000-02-15 | Hitachi Ltd | Variable capacity type turbo supercharger |
| DE10028732A1 (en) * | 2000-06-09 | 2001-12-13 | Daimler Chrysler Ag | Exhaust gas turbine comprises a running wheel which rotates in a turbine housing having a spiral-like inlet channel connected to an annular chamber into which a guiding mesh can be pushed |
| CN101975105B (en) * | 2010-09-14 | 2012-08-22 | 康跃科技股份有限公司 | Double-channel turbine bypass bleeding device |
| CN101949326A (en) * | 2010-09-14 | 2011-01-19 | 康跃科技股份有限公司 | Variable section double-channel air intake turbine |
| CN202181948U (en) * | 2011-08-15 | 2012-04-04 | 无锡凯迪增压器配件有限公司 | Turbine supercharger for double-blade spray nozzle system |
| CN202391494U (en) * | 2011-12-26 | 2012-08-22 | 康跃科技股份有限公司 | Double-channel variable-section volute device with guide vane |
| CN102562185B (en) * | 2011-12-26 | 2014-10-22 | 康跃科技股份有限公司 | Two-channel variable-section volute device with flow-guiding blades |
| CN202417628U (en) * | 2012-01-11 | 2012-09-05 | 康跃科技股份有限公司 | Asymmetric flow-variable turbine housing with non-blade nozzle ring |
| CN202500651U (en) * | 2012-02-29 | 2012-10-24 | 康跃科技股份有限公司 | Multilayer variable geometric volute device |
| CN102787872B (en) * | 2012-05-07 | 2015-09-09 | 康跃科技股份有限公司 | Thermal insulation device for turbine end of turbocharger |
| CN204312138U (en) * | 2014-11-20 | 2015-05-06 | 康跃科技股份有限公司 | A kind of exhaust gas bypass turbo machine with stator |
-
2014
- 2014-11-20 CN CN201410667139.1A patent/CN104389643B/en active Active
- 2014-11-20 CN CN201510768130.4A patent/CN105298551B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104389643B (en) | 2016-03-02 |
| CN105298551A (en) | 2016-02-03 |
| CN104389643A (en) | 2015-03-04 |
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Effective date of registration: 20201223 Address after: No.1 luoqian street, Gucheng street, Shouguang City, Weifang City, Shandong Province Patentee after: Kangyue Technology (Shandong) Co.,Ltd. Address before: No.01 luoqian street, Shouguang Economic Development Zone, Weifang City, Shandong Province 262700 Patentee before: KANGYUE TECHNOLOGY Co.,Ltd. |