CN106870018A - A kind of turbocharger variable nozzle ring and its assembly method - Google Patents
A kind of turbocharger variable nozzle ring and its assembly method Download PDFInfo
- Publication number
- CN106870018A CN106870018A CN201710231445.4A CN201710231445A CN106870018A CN 106870018 A CN106870018 A CN 106870018A CN 201710231445 A CN201710231445 A CN 201710231445A CN 106870018 A CN106870018 A CN 106870018A
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- Prior art keywords
- nozzle
- blade
- outer shroud
- ring
- spacer sleeve
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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
- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
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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 turbocharger variable nozzle ring, including integrally formed blade assembly, nozzle inner ring and nozzle outer shroud；One end of blade assembly is blade, and centre is rotating shaft, and the other end is rocking arm, and rocking arm drives blade movement by rotating shaft；Nozzle outer shroud is set in outside nozzle inner ring so that the semi-circular recesses on the inwall of nozzle outer shroud are combined into manhole with the semi-circular recesses on the outer wall of nozzle inner ring；Rotating shaft matching is arranged in manhole, and blade and rocking arm stretch out the two ends of manhole respectively.The invention also discloses its assembly method.The present invention, using integrally formed blade assembly, eliminates single rocker design while the exhaust that the set angle regulation for changing blade flows to turbine is flowed, amount of parts is reduced, overall reliability is improve, assembly technology is simplified, cost is reduced, with wide market prospects.
Description
Technical field
The invention belongs to mechanical field, more particularly, to a kind of turbocharger variable nozzle ring and its assembly method.
Background technology
Turbocharger is the device being used in combination with internal combustion engine, for being transported to engine charge by compression
The air of mouth increases the power output of engine to mix with fuel and to burn within the engine.Turbocharger includes peace
Mounted in compressor impeller in compressor housing and the turbine in turbine cylinder.Wherein, turbine cylinder and compressor
Housing is separately formed, and also has another middle casing to be connected between turbine cylinder and compressor housing, for axle
The installation held.Turbine cylinder limits the general toroidal runner for surrounding turbine.Turbine assembly is led in turbine including runner
Nozzle.Exhaust flows to turbine from runner by the nozzle, and drives turbine rotation.Turbine drives coaxially connected compressor
Rotate.Air is compressed by compressor impeller, is then connected to engine intake from housing outlets.
Come one of booster aspect of performance challenge it is being whole work model in engine using turbocharger
Enclose the interior engine power output for realizing desired size.It has been found that usual not using the turbocharger of fixed nozzle size
The purpose is easily reached, therefore ordering about for a greater degree of control this purpose is provided in the boosting amount provided turbocharger
Under, have been developed for the turbocharger of variable-nozzle size.A type of variable-sized turbocharger is variable spray
Mouth turbocharger (VNT), it includes one group of variable-vane in turbomachine injection nozzle.These blades are installed in rotation on nozzle
In ring and it is connected to the drive mechanism that blade angle is changed.Change the set angle of blade to changing turbomachine injection nozzle
In effective flowing area have influence, therefore, it is possible to flow to the exhaust stream of turbine to adjust by controlling blade relative position
It is dynamic.In this way, the power output of turbine can be adjusted, this is caused and the turbocharger institute using fixed nozzle size
What usually can be realized compares, and can to a greater extent control the output of engine power.
Usually, variable blade component includes nozzle ring, and the nozzle ring is supported and nozzle ring in rotatable mode
One faces near blade.Blade has the rotating shaft of the mounting hole extended through in nozzle ring, and blade rocking arm is rigidly solid
Due to the end of the opposing face for extending over nozzle ring of the axis body.Therefore, it is possible to make blade by rotating blade rocking arm
Around the axis rotation limited by the rotating shaft, so as to change the set angle of blade.
Variable-nozzle assembly another side is numerous due to amount of parts, and requirement on machining accuracy is high, and assembly technology is multiple
Miscellaneous, the reliability of product receives rigors, and current variable-nozzle technology is widely used on Turbochargers in Diesel Engines, but
It is that current design structure cannot ensure the reliability and of product when temperature turbocharger for gasoline engine higher is faced
Cause property, meanwhile, the variable nozzle ring in existing diesel turbocharger is also due to its complicated technique causes parts cost
It is high.
The variable-nozzle ring design of existing blade assembly formula, its blade is used with rocking arm and separates production and processing, then is carried out
Assembling, assembling is using welding or rivets, and this design structure has the disadvantages that：
1st, blade and sub-rocker arm open up meter, largely increased amount of parts, reduce reliability；
2nd, blade and rocking arm are typically assembled using welding or riveting process, and a how many blade are accomplished by welding/riveting
How many times are connect, assembly difficulty is increased, while also increasing installation time, the cost of product is improve；
3rd, the angle of assembling of blade and rocking arm ensures that frock has larger error in itself, therefore assembling is completed mainly by frock
There is a problem of that blade is poor with the angle agreement of rocking arm afterwards, each blade opening can be caused inconsistent, so as to cause booster
Performance inconsistency.
The content of the invention
The present invention provides a kind of new structure, the simpler variable-nozzle assembly of technique, by reducing amount of parts,
Simplify parts production and assembly technology, reach reduction parts cost, improve the purpose of part reliability.The present invention is logical
Cross following technical scheme realization, a kind of turbocharger variable nozzle ring, including integrally formed blade assembly, nozzle inner ring and
Nozzle outer shroud；One end of blade assembly is blade, and centre is rotating shaft, and the other end is rocking arm, and rocking arm drives blade to transport by rotating shaft
It is dynamic；Nozzle outer shroud is set in outside nozzle inner ring so that the outer wall of semi-circular recesses and nozzle inner ring on the inwall of nozzle outer shroud
On semi-circular recesses be combined into manhole；Rotating shaft matching is arranged in manhole, and blade and rocking arm stretch out circle respectively
The two ends of through hole.The quantity of blade assembly can carry out matching primitives and draw according to different booster types, can be 9,
Can also be 11, or other any appropriate quantity；All blade assemblies on same turbocharger variable nozzle ring
Be of similar shape and size, joined end to end after the completion of the assembling of each blade assembly, by previous blade assembly tail end with it is rear
Exhausted air quantity and waste gas angle that aperture control between one front end of blade assembly passes through.Blade is made for air-flow provides guiding
With blade could be arranged to different shapes, can be plane, or curved surface.The length of blade and the height of blade are needed
To be calculated according to the air inflow of booster, waste gas is maximized turbine mechanical efficiency.Rotating shaft is connected with blade and is connected in
Integrally, for blade opening and closing provides rotational support.Preferably rotating shaft is cylindrical.Rocking arm provides driving force, rocking arm for blade is rotated
One end is integrally connected with rotating shaft.
Further, rotating shaft is divided into first paragraph, interlude and the 3rd section；The external diameter of interlude is outer less than first paragraph
Footpath and the 3rd section of external diameter.Because rotating shaft is very high to diameter dimension required precision, it is necessary to carry out accurate working process, interlude sets
Being calculated as path section can reduce the labor content of rotating shaft, reduce processing cost, at the same time it can also pass through to reduce rotating shaft with circle
The contact area of through hole reduces loss of friction.The semi-circular recesses diameter of nozzle inner ring is slightly larger than the first paragraph of rotating shaft and the
Three sections of diameter, and, two semi-circular recesses (i.e. the half of nozzle inner ring identical with the semi-circular recesses diameter of nozzle outer shroud
Circular groove and a semi-circular recesses for nozzle outer shroud) assembling after the completion of can form a manhole, for blade assembly
Rotational support.
Further, the external diameter at the position that rocking arm is connected with rotating shaft is less than the external diameter of the 3rd section of rotating shaft, so as to ensure to install
It is convenient.Preferably, the external diameter of rotating shaft first paragraph and the external diameter of the 3rd section of rotating shaft are equal.
Further, connect and smoothly transit using plane body between rocking arm two ends.
Further, blade assembly carries out integral production and forms by casting.Can also be other suitable methods.Blade
Each part of component is made of identical material, it is therefore an objective to ensure the intensity of blade assembly.
Further, also including synchronous ring；Inwardly, the other end of rocking arm is outwardly for that one end that rocking arm is connected with rotating shaft；Shake
Arm is arranged in the groove of the inwall of synchronous ring so that rocking arm can be rotated and moved with synchronous ring, so that driving blade is moved.
Further, also including insert and spacer sleeve；Insert is connected by spacer sleeve with nozzle outer shroud；Spacer sleeve according to
It is secondary to be divided into the first spacer sleeve section, the second spacer sleeve section and the 3rd spacer sleeve section；The external diameter of the second spacer sleeve section is more than the first interval
Cover the external diameter of external diameter and the 3rd the spacer sleeve section of section；The hole matched with the external diameter of the first spacer sleeve section is provided with insert to supply
The section insertion of first spacer sleeve；The hole matched with the external diameter of the 3rd spacer sleeve section is provided with nozzle outer shroud for the 3rd spacer sleeve section
Insertion；Blade is arranged in the space that the second spacer sleeve section is surrounded with insert, nozzle outer shroud, and blade can be transported in the space
It is dynamic.The size in the space just reaches blade movement.Nozzle outer shroud towards the one side of blade be plane, mainly with blade bottom
Portion coordinates, and by two planes (i.e. nozzle outer shroud towards blade and insert towards blade while) gap it is big
Small (i.e. the space size that the second spacer sleeve section is surrounded with insert, nozzle outer shroud) control leakage rate of the waste gas from the gap.Such as
Fruit gap-ratio is larger, and exhaust gas leakage amount is relatively more, causes turbine efficiency to reduce, particularly evident when blade is closed, if gap
Smaller, can deposit causes clamping stagnation because of expansion at high temperature, so that disabler.Suitable interstice coverage is in 0.1~0.2mm.
The Main Function of spacer sleeve is for insert provides support, it is ensured that the gap between insert and nozzle outer shroud and nozzle inner ring.
Further, it is provided with piston ring on insert.It is convenient to be tightly connected with the miscellaneous part of turbocharger.Insertion
Part is located between blade and the volute of turbocharger.Wherein, insert is in the form of annular discs towards one end of blade, for blade is provided
Sealing and axially protection, and have certain gap and the upper surface of blade between, prevent from causing blade clamping stagnation because of high-temperature expansion.
One end of insert dorsad blade is designed as in cylindrical shape, and the columnar steam vent of cylinder-like structure insertion volute.
Piston ring is arranged on insert on the part inserted in volute aiutage, is caused for reducing gap between insert and volute
Exhaust leak.The quantity of piston ring is 1 road or multiple tracks.When for multiple tracks, its axial direction is arranged in inserts volute on insert
On part in aiutage.Preferably twice.
Further, the quantity of spacer sleeve is >=3.It is preferred that 3-5.
Further, outer shroud boss is provided with the inwall of nozzle outer shroud, the inner ring with setting on the outer wall of nozzle inner ring
Boss is matched connect in the axial direction so that nozzle inner ring is provided on axial direction by inner ring boss and outer shroud boss to nozzle outer shroud
Support force.Outer shroud boss is arranged on one side of the nozzle outer shroud towards rocking arm, is annular.The internal diameter of the outer shroud boss and nozzle outer shroud
Internal diameter it is identical, the external diameter of outer shroud boss is larger than the maximum radial dimension of the semi-circular recesses of nozzle outer shroud, i.e., outer ring convex
Platform will completely include the semi-circular recesses of nozzle outer shroud；The outer shroud boss Main Function is positioned for rocking arm provides axially support,
And by reducing the friction loss between contact area reduction rocking arm and nozzle outer shroud.Inner ring boss is arranged on nozzle inner ring court
It is annular to the one side of rocking arm.
Further, nozzle inner ring is towards heat shield positioning boss is provided with the inwall of the one side of blade, and heat shield is fixed
Position boss is annular.Heat shield positioning boss is used for when nozzle inner ring is assembled to turbocharger, by heat shield by should be every
Hot cover positioning boss provides axially support for nozzle inner ring.
Further, the distance of one side of the plane that inner ring boss connects with outer shroud boss to nozzle inner ring towards blade
(H1), it is less than the distance (H2) of the one side of plane that outer shroud boss connects with inner ring boss to nozzle outer shroud towards blade.From
And prevent blade from producing interference with nozzle inner ring in rotation process, and influence of the nozzle inner ring to air-flow can be reduced.
Further, blade is greater than towards the end face and rocking arm of rocking arm towards the spacing (H3) between the end face of blade
The distance (H2) of one side of the plane that outer shroud boss connects with inner ring boss to nozzle outer shroud towards blade, is preferably slightly larger than.
In this way, can just ensure that blade assembly is successfully installed on nozzle outer shroud, and will not be because of high-temperature expansion in rotation process
And clamping stagnation.
Further, the quantity of blade assembly is 8-16；In semi-circular recesses and nozzle on the inwall of nozzle outer shroud
Quantity of the quantity of the semi-circular recesses on the outer wall of ring with blade assembly is identical.Have on synchronous ring it is equal with blade quantity simultaneously
And the groove coordinated with rocking arm end, for the motion of driving blade synchronous rocker.
Further, the external diameter at the position that rocking arm is connected with rotating shaft is less than the external diameter of the 3rd section of rotating shaft, so as to ensure to install
It is convenient.As described below, the external diameter of the external diameter less than the 3rd section of rotating shaft at the position being connected with rotating shaft due to rocking arm is just so that step 2
Middle nozzle inner ring can be inserted by the rocking arm abutting end of nozzle outer shroud, and otherwise outer annular recess cannot be connected by rocking arm with rotating shaft
Position.Connect and smoothly transit using plane body between rocking arm two ends.
The invention also discloses a kind of assembly method of turbocharger variable nozzle ring as described above, including following step
Suddenly：
On step one, the semicircle groove being assembled to blade assembly on nozzle outer shroud so that rocking arm is towards outside；
Step 2, by nozzle inner ring by nozzle outer shroud rocking arm abutting end insert, until nozzle inner ring inner ring boss with
The outer shroud boss of nozzle outer shroud is in contact, and the composition so that the semicircle groove of nozzle inner ring aligns with the semicircle groove of nozzle outer shroud
Manhole；
Step 3, clipping room spacer and insert；
Step 4, the synchronous ring of installation；
Step 3 and step 4 do not exist sequencing.
Further, step 3 is specially and is inserted on nozzle outer shroud and the 3rd interval the 3rd spacer sleeve section of spacer sleeve
Cover in the hole of external diameter matching of section, be then again inserted on insert and the first spacer sleeve the first spacer sleeve section of spacer sleeve
In the hole of the external diameter matching of section.
Its advantage is：
1st, blade, rotating shaft and rocking arm are used and integrally produce mach method for designing again, the blade assembly being formed in one,
Single rocker design is eliminated, amount of parts is reduced, overall reliability is improve.
2nd, nozzle ring is designed as nozzle inner ring and nozzle outer shroud two parts, for the assembling of integral type blade assembly, structure
Simply, it is easy to assembly.
3rd, the angle and gap of variable nozzle ring blade and rocking arm mainly by mould and machine guarantee, relative to assembling
Frock uniformity is more preferable.
4th, to reduce accurate mach workload, the interlude design of rotating shaft does not need mach path section, rotating shaft
Two ends design need processing big footpath section.
Brief description of the drawings
Fig. 1 is the structural decomposition diagram one of turbocharger variable nozzle ring of the invention.
Fig. 2 is the structural representation of blade assembly of the invention.
Fig. 3 is the cutting structural representation of blade assembly of the invention.
Fig. 4 is the structural representation one of nozzle outer shroud of the invention.
Fig. 5 is the structural representation two of nozzle outer shroud of the invention.
Fig. 6 is the structural representation one of nozzle inner ring of the invention.
Fig. 7 is the structural representation two of nozzle inner ring of the invention.
Fig. 8 is the structural representation that nozzle inner ring of the invention assembles partial enlargement with nozzle outer shroud.
Fig. 9 is the structural decomposition diagram two of turbocharger variable nozzle ring of the invention.
Figure 10 is the structural representation of blade assembly of the invention and the assembling of nozzle outer shroud.
Figure 11 is the structural representation that nozzle inner ring of the invention is assembled on blade assembly and nozzle outer shroud.
Figure 12 is the cutting structural representation of turbocharger variable nozzle ring of the invention.
Figure 13 is variable-nozzle turbocharger assembly cutting structural representation.
Figure 14 is variable-nozzle turbocharger whirlpool end cutting structural representation.
Specific embodiment
The present invention is elaborated below in conjunction with the accompanying drawings.
Fig. 1 shows a specific embodiment of the invention.In this embodiment, turbocharger variable nozzle ring includes
Insert 1, blade assembly 2, nozzle outer shroud 3, nozzle inner ring 4, synchronous ring 5 and spacer sleeve 6.2 road pistons are provided with insert 1
Ring 11.The structure that blade assembly 2 is formed in one, its one end is blade 21, and centre is rotating shaft 22, and the other end is rocking arm 23.This
Turbocharger variable nozzle ring in embodiment includes 11 identical blade assemblies 2.It is variable in different turbocharger
In nozzle ring, the quantity of blade assembly can be not limited to 11 with different.As shown in figure 1, including rotating shaft 22, rocking arm 23 to
Outward.
Insert 1 is in the form of annular discs towards one end of blade 21, is that blade 21 provides sealing and axially protection, and and blade
There is certain gap between 21 upper surface, prevent from causing blade clamping stagnation because of high-temperature expansion.One end of the dorsad blade 21 of insert 1
Cylindrical shape is designed as, 2 road piston ring 11 is axially arranged on the cylinder-like structure of insert 1.
Semi-circular recesses 31 on the inwall of nozzle outer shroud 3 are combined with the semi-circular recesses 41 on the outer wall of nozzle inner ring 4
Circular through hole.The matching of rotating shaft 22 is arranged in manhole, and blade 21 and rocking arm 23 are exposed at the two ends of manhole respectively.
The quantity of rotating shaft 22 is identical with the quantity of manhole.
Inwardly, the other end of rocking arm 23 is outwardly for that one end that rocking arm 23 is connected with rotating shaft 22.Set on the inwall of synchronous ring 5
There is the groove 51 for being matched with rocking arm 23, the tail end of rocking arm 23 is disposed therein.23 turns of the motion rocker arm of band when synchronous ring 5 is rotated
It is dynamic, drive blade 21 to rotate by rotating shaft 22, so as to adjust blade angle, regulation flows to the exhaust flowing of turbine.
Spacer sleeve 6 is divided into the first spacer sleeve the 61, second spacer sleeve of section section 62 and the 3rd spacer sleeve section 63, such as Figure 12 institutes
Show.The external diameter of the second spacer sleeve section 62 is more than the external diameter of the first spacer sleeve section 61 and the external diameter of the 3rd spacer sleeve section 63.Insert 1
On be provided with it is (as shown in Figure 9) with the hole 13 that match of external diameter of the first spacer sleeve section 61 for the insertion of the first spacer sleeve section 61；Spray
It is provided with mouth outer shroud 3 (as shown in Figure 4) with the hole 32 that the external diameter of the 3rd spacer sleeve section 63 is matched for the 3rd spacer sleeve section 63
Insertion.Blade 21 is arranged in the space that the second spacer sleeve section 62 is surrounded with insert 1, nozzle outer shroud 3.Blade 21 is not stuck
In the space, but can be in the spatial movement.
Fig. 2 and 3 shows a specific embodiment of blade assembly 2.Rotating shaft 22 is divided into first paragraph 24, interlude
25 and the 3rd section 26.External diameter and three section 26 of external diameter of the external diameter of interlude 25 less than first paragraph 24.The external diameter of first paragraph 24
External diameter with the 3rd section 26 is equal.External diameter of the external diameter of rocking arm and the 3rd section 26 of joining part 27 less than the 3rd section 26.First
Section 24 is connected with blade 21.The integrated formed structure that blade assembly 2 generally casts or other modes are made.
Figure 4 and 5 basically illustrate structure of the nozzle outer shroud 3 toward and away from the side of blade respectively.The difference of Fig. 6 and 7
Basically illustrate structure of the nozzle inner ring 4 toward and away from the side of blade.As shown in figs. 4-7, on the inwall of nozzle outer shroud 3
Outer shroud boss 33 is provided with, is matched in the axial direction with the inner ring boss 43 set on the outer wall of nozzle inner ring 4 and connected so that nozzle
Inner ring 4 provides the support force on axial direction to nozzle outer shroud 3.Outer shroud boss 33 be arranged on nozzle outer shroud 3 towards rocking arm one side (i.e.
The dorsad side of blade), it is annular.The internal diameter of outer shroud boss 33 is identical with the internal diameter of nozzle outer shroud 3, outside outer shroud boss 33
Footpath is larger than the maximum radial dimension of the semi-circular recesses 31 of nozzle outer shroud 3, i.e. outer shroud boss 33 and to completely include outside nozzle
The semi-circular recesses 31 of ring 3；The Main Function of outer shroud boss 33 is positioned for rocking arm provides axially support, and is contacted by reducing
Friction loss between area reduction rocking arm and nozzle outer shroud 3.Inner ring boss 43 is arranged on one side of the nozzle inner ring 4 towards rocking arm
(i.e. the dorsad side of blade), is annular, and its external diameter is the maximum outside diameter of nozzle inner ring 4.Nozzle inner ring 4 towards blade one
Heat shield positioning boss 42 is provided with the inwall in face, is annular.Heat shield positioning boss 42 is used to be assembled to when nozzle inner ring
During turbocharger, by heat shield 106 by heat shield positioning boss 42 for nozzle inner ring 4 provides axial support, such as Figure 14 institutes
Show.
Fig. 8 shows the partial enlargement structure of nozzle inner ring 4 and the assembling of nozzle outer shroud 3.Inner ring boss 43 and outer shroud boss
One side of 33 planes for connecting to nozzle inner ring 4 towards blade 21 apart from H1, be less than outer shroud boss 33 and inner ring boss 43
One side of the plane for connecting to nozzle outer shroud 3 towards blade 21 apart from H2.This be conducive to preventing blade in rotation process with
Nozzle inner ring produces interference, and can reduce influence of the nozzle inner ring to air-flow.As shown in figure 12, blade 21 is towards rocking arm 23
End face and rocking arm 23 towards the spacing H3 between the end face of blade 21, be larger than that outer shroud boss connects with inner ring boss is flat
One side of the face to nozzle outer shroud towards blade apart from H2.In this way, can just ensure that blade assembly 2 is successfully installed to nozzle outer shroud
On 3, and in rotation process will not because of high-temperature expansion clamping stagnation.
Assembling process as shown in figs9-12, is comprised the following steps：
Step one, blade assembly 2 is assembled on the semicircle groove on nozzle outer shroud 3 so that rocking arm 23 towards outside, such as
Shown in Figure 10.
Step 2, by nozzle inner ring 4 by nozzle outer shroud 3 the abutting end of rocking arm 23 insert, until the interior ring convex of nozzle inner ring 4
Platform is in contact with the outer shroud boss of nozzle outer shroud 3, and causes the semicircle groove of nozzle inner ring 4 and the semicircle groove of nozzle outer shroud 3
Alignment composition manhole, as shown in figure 11.
Step 3, clipping room spacer 6 and insert 1.The 3rd spacer sleeve section of spacer sleeve 6 is inserted on nozzle outer shroud 3
In the hole matched with the external diameter of the 3rd spacer sleeve section, the first spacer sleeve section of spacer sleeve 6 is inserted on insert 1 again then
In the hole matched with the external diameter of the first spacer sleeve section.
Step 4, synchronous ring 5 is installed, so as to the turbocharger variable nozzle ring for being assembled, as shown in figure 12.
Step 3 and step 4 do not exist sequencing.
Figure 13 and 14 shows position of the turbocharger variable nozzle ring in turbocharger, and a-quadrant is irised out in figure
The general location of turbocharger variable nozzle ring of the invention.As can be seen from the figure turbocharger includes turbocharging
Device variable nozzle ring, turbine 100, volute 101, middle case 102, pressure shell 104, pinch roller 103, heat shield 106 and press-fit spring
105.The annular channel of volute 100 receives the waste gas from engine, and the turbocharger variable nozzle ring of annular is arranged on whirlpool
Between wheel booster runner and turbine 100, the waste gas guiding in volute flow passage is blowed into turbine 100, and air-flow can be adjusted
The angle of turbine 100 is blowed to, so as to adjust the mechanical efficiency of turbine 100.Turbine 100 drives coaxial pinch roller 103 to engine
Air inlet compressed action.
The specific embodiment of the present invention described in detail above, only for illustrating technology design of the invention and spy
Point, its object is to allowing those skilled in the art to will appreciate that present disclosure and implementing according to this, can not limit this with this
The protection domain of invention.It should be appreciated that one of ordinary skill in the art just can be with of the invention without creative work
Many modifications and variations are made in design.Therefore, all technical staff in the art are under this invention's idea in prior art
On the basis of by the available technical scheme of logical analysis, reasoning, or a limited experiment, all should be by claims institute
In the protection domain of determination.
Claims (10)
1. a kind of turbocharger variable nozzle ring, it is characterised in that including integrally formed blade assembly, nozzle inner ring and spray
Mouth outer shroud；One end of the blade assembly is blade, and centre is rotating shaft, and the other end is rocking arm, and the rocking arm is by the rotating shaft
Drive the blade movement；The nozzle outer shroud is set in outside the nozzle inner ring so that on the inwall of the nozzle outer shroud
Semi-circular recesses are combined into manhole with the semi-circular recesses on the outer wall of the nozzle inner ring；The rotating shaft matching is arranged on
In the manhole, the blade and the rocking arm stretch out the two ends of the manhole respectively.
2. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that the rotating shaft is divided into first
Section, interlude and the 3rd section；External diameter and described three section of external diameter of the external diameter of the interlude less than the first paragraph.
3. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that also including synchronous ring；The rocking arm
Inwardly, the other end of the rocking arm is outwardly for that one end being connected with the rotating shaft；The rocking arm is arranged on the interior of the synchronous ring
In the groove of wall so that the rocking arm can be rotated and moved with the synchronous ring, so as to drive the blade movement.
4. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that also including insert and spacer sleeve；
The insert is connected by the spacer sleeve with the nozzle outer shroud；The spacer sleeve is divided into the first spacer sleeve section, the
Two spacer sleeves section and the 3rd spacer sleeve section；The external diameter of the external diameter more than first spacer sleeve section of the second spacer sleeve section and institute
State the external diameter of the 3rd spacer sleeve section；The hole matched with the external diameter of first spacer sleeve section is provided with the insert and supplies institute
State the section insertion of the first spacer sleeve；The hole matched with the external diameter of the 3rd spacer sleeve section is provided with the nozzle outer shroud and supplies institute
State the section insertion of the 3rd spacer sleeve；The blade is arranged on the second spacer sleeve section with the insert, the outer collar of the nozzle
Into space in, and the blade can be in the spatial movement.
5. turbocharger variable nozzle ring as claimed in claim 4, it is characterised in that be provided with piston on the insert
Ring.
6. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that the nozzle inner ring is towards blade
Heat shield positioning boss is provided with inwall simultaneously, the heat shield positioning boss is annular.
7. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that set on the inwall of the nozzle outer shroud
Outer shroud boss is equipped with, is matched in the axial direction with the inner ring boss set on the outer wall of the nozzle inner ring and connected so that the spray
Mouth inner ring provides the support force on axial direction by the inner ring boss and the outer shroud boss to the nozzle outer shroud.
8. turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that the quantity of the blade assembly is 8-
16；The quantity of the semi-circular recesses on the inwall of the nozzle outer shroud and the semi-circular recesses on the outer wall of the nozzle inner ring
Quantity with the blade assembly is identical.
9. a kind of assembly method of turbocharger variable nozzle ring as claimed in claim 1, it is characterised in that including following
Step：
Step one, the blade assembly is assembled on the semicircle groove on the nozzle outer shroud so that the rocking arm is towards outer
Side；
Step 2, by the nozzle inner ring by the nozzle outer shroud rocking arm abutting end insert, until in the nozzle inner ring
Ring convex platform is in contact with the outer shroud boss of the nozzle outer shroud, and causes outside semicircle groove and the nozzle of the nozzle inner ring
The semicircle groove alignment composition manhole of ring；
Step 3, the installation spacer sleeve and the insert；
Step 4, the installation synchronous ring；
The step 3 and the step 4 do not exist sequencing.
10. assembly method as claimed in claim 9, it is characterised in that the step 3 is specially the of the spacer sleeve
Three spacer sleeves section is inserted on the nozzle outer shroud in the hole matched with the external diameter of the 3rd spacer sleeve section, then again by institute
The the first spacer sleeve section for stating spacer sleeve is inserted on the insert in the hole matched with the external diameter of first spacer sleeve section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710231445.4A CN106870018A (en) | 2017-04-11 | 2017-04-11 | A kind of turbocharger variable nozzle ring and its assembly method |
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Cited By (3)
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| CN108775261A (en) * | 2018-03-26 | 2018-11-09 | 北京理工大学 | A kind of turbocharger with radial-flow turbine nozzle ring adjustable vane structure |
| CN109834443A (en) * | 2017-11-24 | 2019-06-04 | 江苏毅合捷汽车科技股份有限公司 | A kind of VNT nozzle ring assembly method |
| CN115142946A (en) * | 2021-03-31 | 2022-10-04 | 盖瑞特交通一公司 | Turbocharger having vaned turbine nozzle and method of assembling same |
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| CN109834443A (en) * | 2017-11-24 | 2019-06-04 | 江苏毅合捷汽车科技股份有限公司 | A kind of VNT nozzle ring assembly method |
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| CN115142946A (en) * | 2021-03-31 | 2022-10-04 | 盖瑞特交通一公司 | Turbocharger having vaned turbine nozzle and method of assembling same |
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