CN108487941A - A kind of turbocharger taper variable-nozzle assembly - Google Patents
A kind of turbocharger taper variable-nozzle assembly Download PDFInfo
- Publication number
- CN108487941A CN108487941A CN201810509263.3A CN201810509263A CN108487941A CN 108487941 A CN108487941 A CN 108487941A CN 201810509263 A CN201810509263 A CN 201810509263A CN 108487941 A CN108487941 A CN 108487941A
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- Prior art keywords
- nozzle
- ring
- turbocharger
- aperture
- vane
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- 238000003756 stirring Methods 0.000 claims description 4
- 238000000429 assembly Methods 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 241001672694 Citrus reticulata Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/148—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of rotatable members, e.g. butterfly valves
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a kind of turbocharger taper variable-nozzle assemblies, it is related to field of turbochargers, including positioning pin, cover board, aperture ring and nozzle ring, nozzle ring includes base plate, nozzle vane and air inlet duct, for cover board with nozzle vane by positioning pin connection, the circumference side of nozzle vane is designed as taper.Amount of parts of the present invention is few, simple in structure, and cost of parts and assembly cost are greatly reduced；Aeroperformance can further be improved, improve efficiency.
Description
Technical field
The present invention relates to field of turbochargers more particularly to a kind of turbocharger taper variable-nozzle assemblies.
Background technology
Turbocharger is the device being used in combination with internal combustion engine, and engine charge is transported to for passing through compression
Mouthful air mix with fuel and burning increases the power output of engine within the engine.Turbocharger includes peace
Mounted in compressor impeller in compressor housing and the turbine in turbine cylinder.Wherein, turbine cylinder and compressor
Shell is separately formed, and also has another middle casing to be connected between turbine cylinder and compressor housing, is used for axis
The installation held and cooling and lubricating.Turbine cylinder limits the general toroidal runner for surrounding turbine, and exhaust is from engine into becoming a mandarin
Road simultaneously blows to turbine, and drives turbine rotation, and turbine drives coaxially connected compressor to rotate.Air passes through compressor impeller
It is compressed, is then connected to from housing outlets to engine intake.
Come one of booster aspect of performance challenge it is being entire work model in engine using turbocharger
Enclose the interior engine power output for realizing desired size.It has been found that utilizing the turbocharger of fixed nozzle size usually not
It is easy to reach the purpose；By adjusting the inlet air flow of the turbine of turbocharger, improving control from turbocharger to correlation
Well known operational advantages are provided in terms of the ability of the supercharging amount of internal combustion engine conveying.By leading to the spray in turbine wheel
Variable geometry is combined in mouth, realizes the adjusting to backblast turbine.By changing the size in Flow in Nozzle region,
The adjustable flow into turbine wheel, to adjust the total boost provided by the compressor of turbocharger.
The nozzle of geometry-variable for turbocharger is generally divided into two main Types at present：Variable-vane sprays
Mouth and sliding plunger nozzle.Blade is typically included in turbine nozzle, for guiding exhaust into turbine along advantageous direction.
For variable-vane nozzle, row's circumferentially spaced bucket extends axially through nozzle, and can be driven with driven device
It rotates synchronously.Exhaust from volute flow passage flows through the access between blade radially inward, and blade can change
The direction of air-flow flowing, to be flowed into turbine wheel along desired direction guiding exhaust gas.In most of variable-vane nozzles,
Blade, which can enclose, to be rotated about the axis thereof, to change the angle set by blade, to change the flow region of access between blade.It is variable
Blade cut-out governing is more flexible, but complicated structure limits the use scope of variable-vane nozzle, due to movement zero
Part is more, easily occurs the risk of clamping stagnation failure at high temperature, so the use temperature range of variable-vane nozzle is restricted；
Simultaneously as variable-vane nozzle is complicated, cost is relatively high, equally also limits its application range.
In the nozzle of sliding-piston type, nozzle can also include blade, but blade is fixed on suitable position.It is logical
The piston that slides axially slided in the hole in turbine shroud is crossed, the change in Flow in Nozzle region is realized.Piston is tubulose
, and it is located just at the inner radial of nozzle.The axial movement of piston effectively changes the axis of the introducing turbine wheel of nozzle
To degree, to change " throat region " in turbine wheel inlet.When blade is included in nozzle, piston can be neighbouring
It slides at the inner radial edge (that is, rear) of blade；Alternately, piston and blade can be radially overlapped, and piston can
Including notch, at least part for accommodating blade when piston slides axially to adjust nozzle.It lives for this sliding
Plunger type nozzle, is not widely used, mainly since its control structure is difficult to be arranged, since its piston is needed in axial direction
Sliding, so control mechanism is also required to be axial control, since volute side is connected with middle case, side and vent gas treatment pipe
Road is connected, so control mechanism is difficult to be disposed in axial direction.
The variable-nozzle of variable-vane type and sliding-piston type, the two all have merits and demerits.For example, with rotatable
The variable-vane nozzle of blade usually has good aerodynamic quality, but since there are many quantity of movable members, so
It is mechanically very complicated.Sliding-piston type variable nozzle is mechanically much simpler, has seldom movable members, but usually in sky
Be not as good as variable-vane nozzle on aerodynamic force.
Our company has been filed on patent application, and (Patent No. 201810373619.5, patent name is " for turbocharger
Variable-nozzle and its control method and turbocharger "), with feasible design structure, gathers blade type nozzle and lived with sliding
The advantages of plunger type nozzle, simple in structure, production cost is low, and control is easy to implement.In order to further increase aeroperformance and efficiency,
Those skilled in the art is that the patented product devises a kind of turbocharger taper variable-nozzle assembly.
Invention content
In view of the drawbacks described above of the prior art, the technical problem to be solved by the present invention is to further improve pneumatic property
Can, improve pneumatic efficiency.
To achieve the above object, the present invention provides a kind of turbocharger taper variable-nozzle assembly, including positioning pin,
Cover board, aperture ring and nozzle ring, nozzle ring include base plate, nozzle vane and air inlet duct, the circumference lateral layout of nozzle vane
For taper.Nozzle ring is at basic cirque structure, and circumferentially array is located on the one side of nozzle ring several nozzle vanes,
And nozzle vane is a part for nozzle ring, and nozzle vane and nozzle ring become one formula；Aperture ring is annular, aperture ring
On the outside of the nozzle ring, nozzle opening size is controlled.
Further, the angle of nozzle vane is fixed nonadjustable, opening portion, that is, air inlet between adjacent blades
Slot, for guiding exhaust gas to blow to turbine, nozzle vane angle is fixed as optimum efficiency incidence angle.
Further, aperture ring design is the annular same or about with nozzle vane circumference face cone degree.
Further, aperture ring diameter size is slightly larger than nozzle ring, and aperture ring is circumferentially being evenly arranged with several open slots,
Quantity is equal with nozzle vane quantity, and the air inlet well width between the circumferential width and nozzle vane of open slot is equal, open slot
Height it is equal with the height of nozzle vane, the area that the air inlet duct between aperture slot and nozzle vane on aperture ring overlaps is determined
The opening size of nozzle assembly is determined.
Further, gap is designed between aperture ring circular conical surface and nozzle vane circumference side, preferred gap range is
0.2~1mm.
Further, aperture annulate shaft is designed with shift fork to side, and shift fork stirs aperture ring rotary motion in the position, adjusts
Nozzle assembly opening size.
Further, there are many type of drive of shift fork, it can be electric actuator driving, can also be pneumatic actuator
Driving.
Further, nozzle vane circumference sided pyramidal preferred inclination angle range α=10 °~40 °.
Further, cover board is fixed with blade by positioning pin or other on-fixed connection types are assemblied in one
It rises.
The present invention can obtain following technique effect：
1, amount of parts is few, simple in structure, and cost of parts and assembly cost are greatly reduced；
2, it can further improve aeroperformance, improve efficiency.
The technique effect of the design of the present invention, concrete structure and generation is described further below with reference to attached drawing, with
It is fully understood from the purpose of the present invention, feature and effect.
Description of the drawings
Fig. 1 is the nozzle ring schematic diagram that nozzle vane circumference side is cylinder；
Fig. 2 is the taper variable-nozzle assembly explosive view of the preferred embodiment of the present invention；
Fig. 3 is that the nozzle vane circumference side of the preferred embodiment of the present invention is the nozzle ring schematic diagram of taper；
Fig. 4 is that the aperture ring of the preferred embodiment of the present invention is the schematic diagram of taper；
Fig. 5 is the taper variable-nozzle assembly scheme of installation of the preferred embodiment of the present invention；
Fig. 6 is the taper variable-nozzle assembly partial enlarged view of the preferred embodiment of the present invention.
Specific implementation mode
Multiple preferred embodiments that the present invention is introduced below with reference to Figure of description, keep its technology contents more clear and just
In understanding.The present invention can be emerged from by many various forms of embodiments, and protection scope of the present invention not only limits
The embodiment that Yu Wenzhong is mentioned.
In the accompanying drawings, the identical component of structure is indicated with same numbers label, everywhere the similar component of structure or function with
Like numeral label indicates.The size and thickness of each component shown in the drawings are to be arbitrarily shown, and there is no limit by the present invention
The size and thickness of each component.In order to keep diagram apparent, some places suitably exaggerate the thickness of component in attached drawing.
As shown in Figure 1, the nozzle vane circumference side of nozzle ring in the prior art is cylinder.
As shown in Fig. 2, one embodiment of the present invention includes positioning pin 1, cover board 2, aperture ring 3 and nozzle ring 4, such as scheme
Shown in 3, nozzle ring 4 includes base plate 41, air inlet duct 42 and nozzle vane 43, and the circumference side of nozzle vane 43 is designed as boring
Shape.Nozzle ring 4 is at basic cirque structure, and circumferentially array is located on the one side of nozzle ring 4 several nozzle vanes 43,
And nozzle vane 43 is a part for nozzle ring 4, and nozzle vane 43 and nozzle ring 4 become one formula.Nozzle vane 43
Angle is fixed nonadjustable, opening portion, that is, air inlet duct between adjacent blades, for guiding exhaust gas to blow to turbine, nozzle
43 angle of blade is approximately equal to optimum efficiency incidence angle.
As shown in figure 4, aperture ring 3 is loop configuration, diameter dimension is slightly larger than nozzle, 4, between aperture ring 3 and nozzle ring 4
It will be there are gap, to prevent high temperature from aperture ring being caused to generate clamping stagnation with nozzle ring.Aperture ring 3 is circumferential be designed with several open slots
Aperture slot 32 is done, quantity is consistent with 43 quantity of nozzle vane, the air inlet duct between the circumferential width and nozzle vane of aperture slot 32
42 width are roughly the same, and the height of aperture slot 32 is equal with the height of nozzle vane 43.Aperture slot 32 on aperture ring 3 and nozzle
The area that air inlet duct 42 between blade 43 overlaps determines the opening size of nozzle assembly.The axial side of aperture ring 3 is designed with
Shift fork 33, shift fork 33 stir 3 rotary motion of aperture ring, that is, adjust opening size in the position；The mode of shift fork is automatically controlled
Actuator driven.
As shown in fig. 6, inclination alpha=10 ° of 43 circumference sided pyramidal of nozzle vane.Cover board 2 passes through positioning pin with nozzle ring 4
1 connection.
Fig. 5 is the taper variable-nozzle assembly that each component of one embodiment of the present invention is installed together.
Difference lies in 43 circumference sided pyramidals of nozzle vane for second embodiment and one embodiment of the present invention
Inclination angle is different.Text description specific as follows.
As shown in Fig. 2, second embodiment of the present invention includes positioning pin 1, cover board 2, aperture ring 3 and nozzle ring 4, such as scheme
Shown in 3, nozzle ring 4 includes base plate 41, air inlet duct 42 and nozzle vane 43, and the circumference side of nozzle vane 43 is designed as boring
Shape.Nozzle ring 4 is at basic cirque structure, and circumferentially array is located on the one side of nozzle ring 4 several nozzle vanes 43,
And nozzle vane 43 is a part for nozzle ring 4, and nozzle vane 43 and nozzle ring 4 become one formula.Nozzle vane 43
Angle is fixed nonadjustable, opening portion, that is, air inlet duct between adjacent blades, for guiding exhaust gas to blow to turbine, nozzle
43 angle of blade is approximately equal to optimum efficiency incidence angle.
As shown in figure 4, aperture ring 3 is loop configuration, diameter dimension is slightly larger than nozzle, 4, between aperture ring 3 and nozzle ring 4
It will be there are gap, to prevent high temperature from aperture ring being caused to generate clamping stagnation with nozzle ring.Aperture ring 3 is circumferential be designed with several open slots
Aperture slot 32 is done, quantity is consistent with 43 quantity of nozzle vane, the air inlet duct between the circumferential width and nozzle vane of aperture slot 32
42 width are roughly the same, and the height of aperture slot 32 is equal with the height of nozzle vane 43.Aperture slot 32 on aperture ring 3 and nozzle
The area that air inlet duct 42 between blade 43 overlaps determines the opening size of nozzle assembly.The axial side of aperture ring 3 is designed with
Shift fork 33, shift fork 33 stir 3 rotary motion of aperture ring, that is, adjust opening size in the position；The mode of shift fork is automatically controlled
Actuator driven.
As shown in fig. 6, inclination alpha=40 ° of 43 circumference sided pyramidal of nozzle vane.Cover board 2 passes through positioning pin with nozzle ring 4
1 connection.
The preferred embodiment of the present invention has been described in detail above.It should be appreciated that the ordinary skill of this field is without wound
The property made labour, which according to the present invention can conceive, makes many modifications and variations.Therefore, all technician in the art
Pass through the available technology of logical analysis, reasoning, or a limited experiment on the basis of existing technology under this invention's idea
Scheme, all should be in the protection domain being defined in the patent claims.
Claims (10)
1. a kind of turbocharger taper variable-nozzle assembly, which is characterized in that including positioning pin, cover board, aperture ring and nozzle
Ring, the nozzle ring include base plate, nozzle vane and air inlet duct, and the cover board passes through the positioning pin with the nozzle vane
It is connected and fixed, the nozzle ring is circular ring shape, and circumferentially uniform array is located at the nozzle ring to several described nozzle vanes
On one side, the circumference side of the nozzle vane is designed as taper；The aperture ring is annular, and the aperture ring is located at described
On the outside of nozzle ring, nozzle opening size is controlled.
2. turbocharger taper variable-nozzle assembly as described in claim 1, which is characterized in that the nozzle vane is institute
State a part for nozzle ring, the nozzle vane and the nozzle ring become one formula, and the angle of the nozzle vane is not
It is adjustable.
3. turbocharger taper variable-nozzle assembly as claimed in claim 1 or 2, which is characterized in that the nozzle vane
Angle is fixed as optimum efficiency incidence angle.
4. turbocharger taper variable-nozzle assembly as described in claim 1, which is characterized in that the aperture ring design is
Annular identical with the nozzle vane circumference face cone degree.
5. turbocharger taper variable-nozzle assembly as claimed in claim 4, which is characterized in that the aperture ring diameter ruler
Very little to be slightly larger than the jet blade, the aperture ring is circumferentially being evenly arranged with several aperture slots, the aperture slot number amount with
The nozzle vane quantity is equal, and the air inlet well width between the circumferential width and the nozzle vane of the aperture slot is equal,
The height of the aperture slot is equal with the height of the nozzle vane.
6. turbocharger taper variable-nozzle assembly as claimed in claim 4, which is characterized in that the aperture ring circular conical surface
Gap is designed between nozzle vane circumference side, the interstice coverage is 0.2~1mm.
7. turbocharger taper variable-nozzle assembly as claimed in claim 4, which is characterized in that the aperture annulate shaft is to one
Side is designed with shift fork, and the shift fork stirs the aperture ring rotary motion in the position, adjusts nozzle assembly opening size.
8. turbocharger taper variable-nozzle assembly as claimed in claim 7, which is characterized in that the driving side of the shift fork
Formula is electric actuator driving.
9. turbocharger taper variable-nozzle assembly as claimed in claim 7, which is characterized in that the driving side of the shift fork
Formula is pneumatic actuator driving.
10. turbocharger taper variable-nozzle assembly as described in claim 1, which is characterized in that the nozzle vane circle
All sided pyramidal preferred inclination angle ranges α=10 °~40 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509263.3A CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509263.3A CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108487941A true CN108487941A (en) | 2018-09-04 |
| CN108487941B CN108487941B (en) | 2024-04-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810509263.3A Active CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108487941B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111156052A (en) * | 2020-01-03 | 2020-05-15 | 清华大学 | Rotary variable nozzle part air inlet radial turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3127909A (en) * | 1962-07-18 | 1964-04-07 | Honeywell Regulator Co | Rotary gate valve |
| CN103958837A (en) * | 2011-12-01 | 2014-07-30 | Ihi供应系统国际有限责任公司 | Fluid energy machine, in particular for exhaust-gas turbocharger, with obliquely arranged rotatable guide element |
| CN105927290A (en) * | 2016-06-29 | 2016-09-07 | 江苏毅合捷汽车科技股份有限公司 | Variable-section nozzle assembly for turbocharger |
| CN208416620U (en) * | 2018-05-24 | 2019-01-22 | 奕森科技（上海）有限公司 | A kind of turbocharger taper variable-nozzle assembly |
-
2018
- 2018-05-24 CN CN201810509263.3A patent/CN108487941B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3127909A (en) * | 1962-07-18 | 1964-04-07 | Honeywell Regulator Co | Rotary gate valve |
| CN103958837A (en) * | 2011-12-01 | 2014-07-30 | Ihi供应系统国际有限责任公司 | Fluid energy machine, in particular for exhaust-gas turbocharger, with obliquely arranged rotatable guide element |
| CN105927290A (en) * | 2016-06-29 | 2016-09-07 | 江苏毅合捷汽车科技股份有限公司 | Variable-section nozzle assembly for turbocharger |
| CN208416620U (en) * | 2018-05-24 | 2019-01-22 | 奕森科技（上海）有限公司 | A kind of turbocharger taper variable-nozzle assembly |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111156052A (en) * | 2020-01-03 | 2020-05-15 | 清华大学 | Rotary variable nozzle part air inlet radial turbine |
| CN111156052B (en) * | 2020-01-03 | 2021-07-09 | 清华大学 | Rotary variable nozzle part air inlet radial turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108487941B (en) | 2024-04-09 |
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Effective date of registration: 20210330 Address after: 215506 no.1150, Southeast Avenue, Southeast street, Changshu City, Suzhou City, Jiangsu Province Applicant after: Eason Technology (Jiangsu) Co.,Ltd. Address before: 201703 1st floor, building 1, 518 Songhui Road, Qingpu District, Shanghai Applicant before: ISEM TECHNOLOGIES (SHANGHAI) Co. |
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