CN106939828A - It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation - Google Patents
It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation Download PDFInfo
- Publication number
- CN106939828A CN106939828A CN201710331338.9A CN201710331338A CN106939828A CN 106939828 A CN106939828 A CN 106939828A CN 201710331338 A CN201710331338 A CN 201710331338A CN 106939828 A CN106939828 A CN 106939828A
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- China
- Prior art keywords
- blade
- variable
- nozzle ring
- clamping stagnation
- ring assemblies
- Prior art date
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- 238000000429 assembly Methods 0.000 title claims abstract description 31
- 230000000712 assembly Effects 0.000 title claims abstract description 31
- 239000011435 rock Substances 0.000 claims abstract description 29
- 230000001360 synchronised effect Effects 0.000 claims abstract description 28
- 238000012856 packing Methods 0.000 claims description 20
- 238000003466 welding Methods 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 4
- 230000013011 mating Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 20
- 239000002912 waste gas Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 238000010276 construction Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
- F02B37/12—Control of the pumps
- F02B37/24—Control of the pumps by using pumps or turbines with adjustable guide vanes
-
- 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
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
-
- 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
- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation, it is a kind of turbocharger accessory, the whirlpool end of turbocharger includes volute, turbine and variable-nozzle ring assemblies, and variable-nozzle ring assemblies include blade backplate, spacing pin, blade, mounting disc, rigging pilotage, synchronous ring and adjusting rock arm.Blade backplate is located between volute and blade, and spacing pin, blade and rigging pilotage are assemblied in mounting disc, and synchronous ring is fixed in mounting disc by rigging pilotage, and adjusting rock arm is connected with synchronous ring, and the shaft end of adjusting rock arm and blade is assembled；Variable-nozzle ring assemblies can reduce the risk of nozzle vane high temperature clamping stagnation by adjusting the design structure of spacing pin and blade backplate, while impeller clearance design load can also be reduced, improve low-speed performance.
Description
Technical field
It is particularly a kind of effectively to prevent the variable-nozzle ring group of blade clamping stagnation the present invention relates to a kind of turbocharger accessory
Part.
Background technology
Turbocharger is a kind of device being used in combination with internal combustion engine, for being transported to engine by compression
The air of air inlet, to mix and to burn within the engine with fuel, so as to increase the power output of engine.Turbine increases
Depressor includes the compressor impeller and the turbine in turbine cylinder being arranged in compressor housing, and also another
The individual middle casing being connected between turbine cylinder and compressor housing, the middle casing be used for bearing installation, cooling and
Lubrication.Wherein, turbine cylinder is formed separately with compressor housing, and turbine cylinder limits the substantially ring for surrounding turbine
Shape runner, the nozzle that turbine assembly is led in turbine including runner.Air flows to turbine from runner by the nozzle, and drives
Turbine rotation, turbine are so as to drive coaxially connected compressor to rotate.Finally, air is compressed by compressor impeller, then
Engine intake is flowed to from housing outlets.
When using turbocharger come booster, a challenge of its aspect of performance is the whole work in engine
The power output of the engine of desired size is realized in the range of work.Those skilled in the art have found, utilize fixed nozzle size
Turbocharger is generally not readily reachable by the purpose, therefore carries out more great Cheng to the boosting amount that turbocharger is produced to realize
The control of degree ground, has had been developed for the turbocharger of variable-nozzle size.Wherein, a type of variable-sized turbocharging
Device is variable-nozzle turbocharger (VNT), and it includes one group of variable-vane in turbomachine injection nozzle.These blades are rotationally
In nozzle ring and it is connected to the drive mechanism that blade angle is changed.Change the set angle of blade to changing
Effective flowing area in turbomachine injection nozzle has influence, therefore, it is possible to flow to whirlpool by controlling the relative position of blade to adjust
The exhaust flowing of wheel.In this way, the power output of turbine can be adjusted, this causes and the whirlpool using fixed nozzle size
Wheel booster is usual achieved to be compared, and the output of engine power can be controlled to a greater extent.
Usually, variable blade component includes nozzle ring, and the nozzle ring is rotatably supported one with nozzle ring
It is individual to face near blade.Blade has the rotary 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 by rotation axis limit, so as to change the set angle of blade.
In order to ensure low-speed performance, it is necessary to control the gap of blade upper and lower ends, the gap mainly passes through spacing pin at present
It is controlled, spacing pin plays axial supporting role simultaneously.But, current spacing pin design is two ends welding/riveted type and set
Meter, the major defect that the design is present is that gap design must be sufficiently large, larger to prevent that clamping stagnation from occurring at high temperature in blade
Impeller clearance can cause exhaust gas leakage amount larger again so that can reduce turbine mechanical efficiency reduction, the influence in low speed by
It is more particularly evident than relatively low meeting in total tolerance.If gap design is unreasonable, high-temperature expansion, which just has, causes the risk of blade clamping stagnation,
And because the spacing pin two ends of existing design are fixed assembling, so blade clamping stagnation can not be eliminated automatically, so as to can enter one
Step causes booster to fail.
The nozzle ring modular construction of prior art, as shown in Figure of description Fig. 1, typically in nozzle ring X3 and insert X1
Between there is 3 spacing pin X2, spacing pin X2 to be distributed on around blade, spacing pin X2 structures are as shown in Figure of description Fig. 2, spacing
Respectively there is a step surface X4 at pin two ends, are engaged respectively with the hole on nozzle ring X3 and insert X1, and two ends are fixed,
Typically by the way of welding or riveting, support nozzle ring X3 and insert X1.The distance between two step surface X4 are subtracted
The height of blade is exactly impeller clearance, and the structure design major defect is：When clamping stagnation occurs in blade, because two ends are using solid
Fixed assembling, it is impossible to eliminate clamping stagnation automatically, so as to cause booster failure generation；If using two ends fixing assembling structure, in order to
Blade is avoided to occur clamping stagnation in use, the ratio that the first meeting of design designs impeller clearance is larger, larger gap can be with
Clamping stagnation risk is reduced, but can also increase air leakage simultaneously, so that the mechanical efficiency of turbine is reduced, it is particularly evident in low speed.
The content of the invention
In view of problem above, present invention offer is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation, by spacing
Pin is designed as one end and fixed, and the other end is coordinated with the hole on blade backplate using gap, and increases between blade backplate and volute
Plus two Packing springs.Under the design structure, when clamping stagnation occurs for blade, because blade backplate and spacing pin are freely to fill
Match somebody with somebody, so blade can carry out blade backplate jack-up, so as to eliminate blade clamping stagnation automatically.Further, since the design possesses automatically
Eliminate clamping stagnation structure, so the gap between blade and two end plates can design it is smaller, so the nozzle ring group of the structure
Part operating efficiency is higher, and low-speed performance is more preferable.
The whirlpool end of turbocharger with variable-nozzle ring assemblies includes volute and turbine, and the turbine is arranged on described
In volute, the annular channel of the volute receives the waste gas from engine, and annular variable-nozzle ring assemblies are arranged on turbine
Between the annular channel and the turbine of the volute of booster, the waste gas guiding in the annular channel of the volute is blowed to
The turbine；And air-flow can be adjusted and blow to the angle of the turbine, so as to adjust the mechanical efficiency of the turbine.Wheel press
Including pressure shell and pinch roller, the pinch roller is arranged in the pressure shell.The turbine drives coaxial wheel press to engine charge
Compressed action, improves engine charge density, so as to improve the power per liter and torque per liter of engine.
Effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation the invention provides a kind of, including blade backplate, spacing pin,
Blade, mounting disc, rigging pilotage, synchronous ring and adjusting rock arm.Blade backplate, spacing pin, blade, mounting disc, rigging pilotage, synchronization
Ring, adjusting rock arm are set gradually, and are used in conjunction with each other.The blade backplate is located between the volute and the blade, institute
State spacing pin, the blade and the rigging pilotage to be assemblied in the mounting disc, the synchronous ring is fixed on by the rigging pilotage
In the mounting disc, the adjusting rock arm is connected with the synchronous ring, and the shaft end of the adjusting rock arm and the blade is carried out
Assembling.
Further, the blade backplate is designed with three blind holes towards vane end faces, the blind hole and the spacing
Gap is sold to coordinate.
Further, one end of the spacing pin is designed with assembled shaft, and the assembled shaft is using welding or the shape riveted
Assembling is fixed in spacing pin pilot hole in formula and the mounting disc, and the other end is free end, and on the blade backplate
The blind hole carries out gap cooperation.
Further, the distance of end face of the step surface that the spacing pin and the mounting disc coordinate to the free end is big
In the height and the depth sum of the blind hole of the guide face of the blade.
Further, the blade is mainly made up of guide face and rotary shaft, and the rotary shaft is arranged on the mounting disc
Rotated in upper default mounting hole, the path part for rotating shaft end is used to weld or rivet with the adjusting rock arm to fill
Match somebody with somebody.
Further, the turbine mating holes for being provided centrally with circle of the mounting disc, in the circumference of the mounting disc
The different hole of some diameters is configured with, the spacing pin, the blade and the assembling of the rigging pilotage is respectively used to.
Further, the synchronous ring is fixed in the mounting disc by the rigging pilotage, is had on the synchronous ring and institute
The equal groove of adjusting rock arm quantity is stated, and is connected with external drive rocking arm.
Further, the through hole of described adjusting rock arm one end is coordinated with the blade shaft end, and mainly using weldering
Constraint is fixed in the assembly method for connecing or riveting；The other end of the adjusting rock arm is carried out with the groove on the synchronous ring
Assembling.
Further, Packing spring fitting recess, the sealing are designed with the volute corresponding with the blade backplate
Assembling Packing spring in spring fitting recess, the axial maximum height of the Packing spring is greater than the Packing spring fitting recess
Bottom is the distance between to the blade backplate, so as to ensure the Packing spring under any shape all in compressive state.
Present invention offer is a kind of effectively to prevent the variable-nozzle ring assemblies design organization of blade clamping stagnation, relative to prior art
Scheme, with advantages below：
1st, when clamping stagnation occurs for blade, blade can carry out blade backplate jack-up, so that the problem of eliminating high temperature clamping stagnation；
2nd, because clamping stagnation Hazard ratio is relatively low, so low-speed performance can be improved by reducing the design load of impeller clearance；
3rd, the spring between volute and blade backplate, not only facilitates elimination clamping stagnation problem, and waste gas can be prevented from leaf
Revealed between piece backplate and volute.
Brief description of the drawings
Fig. 1 is the component assembling schematic diagram of prior art；
Fig. 2 is the structural representation of the spacing pin of prior art；
Fig. 3 is a kind of turbo-charger complement profile of preferred embodiment of the invention；
Fig. 4 is a kind of variable nozzle ring modular construction schematic diagram of preferred embodiment of the invention；
Fig. 5 is a kind of blade guard board structure schematic diagram of preferred embodiment of the invention；
Fig. 6 is a kind of spacing latch structure schematic diagram of preferred embodiment of the invention；
Fig. 7 is a kind of blade construction schematic diagram of preferred embodiment of the invention；
Fig. 8 is a kind of mounting disc structural representation of preferred embodiment of the invention；
Fig. 9 is that a kind of variable-nozzle ring assemblies of preferred embodiment of the invention and volute assemble partial enlarged drawing.
Embodiment
The present invention is described in more detail hereinafter with reference to accompanying drawing, which show some of the present invention rather than institute
Some embodiments.In fact, the present invention can be specially many different forms, it is impossible to think to shall be limited only to following implementations
Example, on the contrary, these embodiments are provided to enable the open legal provisions for meeting and being applicable.
As shown in figure 3, the whirlpool end of the turbocharger with variable-nozzle ring assemblies includes volute 13 and turbine 14, turbine
14 are arranged in volute 13, and the annular channel of volute 13 receives the waste gas from engine, and annular variable-nozzle ring assemblies are set
Put between the annular channel and turbine 14 of the volute 13 of turbocharger, the waste gas guiding in the annular channel of volute 13 is blown
To turbine 14；And air-flow can be adjusted and blow to the angle of turbine 14, so as to adjust the mechanical efficiency of turbine 14.Wheel press includes
Pressure shell 11 and pinch roller 12, pinch roller 12 are arranged in pressure shell 11.Turbine 14 drives coaxial wheel press to do engine charge compression
Work(, improves engine charge density, so as to improve the power per liter and torque per liter of engine.
As shown in figure 4, a kind of effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation, including blade backplate 21, spacing pin
22nd, blade 23, mounting disc 24, rigging pilotage 25, synchronous ring 26 and adjusting rock arm 27.Blade backplate 21, spacing pin 22, blade 23,
Mounting disc 24, rigging pilotage 25, synchronous ring 26, adjusting rock arm 27 are set gradually, and are used in conjunction with each other.Blade backplate 21 is located at volute
Between 13 and blade 23, spacing pin 22, blade 23 and rigging pilotage 25 are assemblied in mounting disc 24, and synchronous ring 26 is consolidated in rigging pilotage 25
It is scheduled in mounting disc 24, adjusting rock arm 27 is connected with synchronous ring 26, and the shaft end of adjusting rock arm 27 and blade 23 is assembled.
As shown in figure 5, blade backplate 21 towards vane end faces 211 is designed with three blind holes 212, the diameter of blind hole 212
More than the diameter that spacing pin 22 and blind hole 212 coordinate section, that is, ensure that spacing pin 22 coordinates with blind hole 212 for gap, the gap is needed
Ensure that spacing pin 22 expands clamping stagnation with blade backplate 21 all without generation under any operating mode.
Fig. 6 shows a kind of design structure of spacing pin 22, and its one end is designed with assembled shaft 221, for mounting disc 24
On spacing pin pilot hole assembled, and using welding or riveting in the form of assembling is fixed；The other end is free end
Blind hole 212 on 222, with blade backplate 21 carries out gap cooperation, support blade backplate.
The assembled shaft 221 of spacing pin 22 is assembled in the spacing pin pilot hole in mounting disc 24, then by blade backplate
Three blind holes 212 correspondence on 21 is assembled to the free end 222 of three spacing pins 22；Blind hole 212 with diameter greater than spacing pin 22
Free end 222 diameter, blind hole 212 and spacing pin 22 are that gap coordinates.
As shown in fig. 7, blade 23 is mainly made up of guide face 231 and rotary shaft 232, wherein guide face 231 is mainly used in
The aperture size of nozzle ring assemblies is adjusted, and adjusts the angle that waste gas blows to turbine 14, the shape of guide face 231 is to nozzle ring
Component and the influence of booster overall performance need to carry out the analysis of joint aerodynamics simu1ation with turbine 14 than larger at the beginning of design, from
And determine the size and shape of guide face 231；Rotary shaft 232 is arranged in mounting disc and rotated in default mounting hole, rotary shaft
The path part of 232 ends is used to welding or riveting assembling with adjusting rock arm 27.The geomery of all blades 23 is consistent, leaf
The quantity of piece 23 needs to be determined according to specific products application, can be 6,8,11 etc..
In order to ensure that blade axially has gap after the completion of assembling, the step surface that spacing pin 22 coordinates with mounting disc 24 is to certainly
It is more than the height and the depth sum of blind hole 212 of the guide face 231 of blade 23 by the distance of the end face at end 222, so as to prevent leaf
Piece clamping stagnation.
Mounting disc 24 is that nozzle ring assemblies assemble fixed main supporting with booster, and it is basic loop configuration,
As shown in figure 8, there is circular through hole at the center of mounting disc 24, the hole is turbine mating holes 241, is matched somebody with somebody in the circumference of mounting disc 24
The different hole of some diameters is equipped with, the assembling of spacing pin 22, blade 23 and rigging pilotage 25 is respectively used to.
The axle of blade 23 is assembled with adjusting rock arm 27 and completed through the blade mounting hole in mounting disc 24, all blades 23
Afterwards, corresponding assembling groove is engaged adjusting rock arm 27 above with synchronous ring 26, and rigging pilotage 25 then is arranged on into mounting disc 24
It is upper to provide spacing for synchronous ring 26.
Rigging pilotage 25 is used to provide axial constraint to synchronous ring 26, will synchronous ring 26 be fixed in mounting disc 24, still
The circumferential movement of synchronous ring 26 is not influenceed simultaneously.Have the groove equal with the quantity of adjusting rock arm 27 on synchronous ring 26, and with it is outer
Portion's driving rocking arm is connected, and outside driving force is converted into being synchronized with the movement for all adjusting rock arms 27, it is ensured that all adjustable
The aperture of blade 23 is identical.
The through hole of the one end of adjusting rock arm 27 is coordinated with the shaft end of blade 23, and carries out fixed constraint, main using weldering
The assembly method for connecing or riveting；The other end of adjusting rock arm 27 is assembled with the groove on synchronous ring 26, and both are gaps
Coordinate, it is ensured that without clamping stagnation under any aperture.The main function of adjusting rock arm 27 is by the external motivating force transmission of synchronous ring 26
To the rotary shaft of blade 23, so as to adjust the aperture of blade.
If there is rigid contact in variable-nozzle ring assemblies, then volute 13 is produced at high temperature in the axial direction with volute 13
Thermal deformation can extrude blade backplate 21, cause blade backplate 21 to produce the deflection to the direction of blade 23, so that leaf can be caused
The clamping stagnation of piece 23, so the two can not produce rigid contact in the axial direction.But if exist between blade backplate 21 and volute 13
Gap, can cause exhaust leak first, reduce the functioning efficiency of turbine 14, particularly evident in low speed；Secondly as blade is protected
Plate 21 and spacing pin 22 without the fixed constraint on axial direction, if so gap is larger, also result in blade backplate 21 produce compared with
Big rocks.Therefore, as shown in figure 9, being designed with Packing spring fitting recess 31 on volute 13 corresponding with blade backplate 21, the groove
Interior assembling Packing spring 32, the axial maximum height of Packing spring 32 is greater than installed in trench bottom between blade backplate 21
Distance, so as to ensure Packing spring 32 under any shape all in compressive state.Packing spring 32 has two effects, is first
Axial constraint is provided for blade backplate 21, it is ensured that the tight fit between blade 23 and spacing pin 22, next to that playing sealing
Effect, prevents that waste gas from revealing between blade backplate 21 and volute 13.The rigidity of Packing spring 32 can not be too big, if sealing bullet
Spring 32 is too big to the pressure of blade backplate 21, then when blade 23 produces clamping stagnation, and blade 23 is just not enough to the power of blade backplate 21
So that blade backplate jack-up to be come, so that clamping stagnation problem can not be eliminated；The rigidity of Packing spring 32 can not be too small, if too small deficiency
If pushing down blade backplate 21, the axial movement that blade backplate 21 is produced can also increase the gap of blade 23, so as to cause effect
Rate declines.The rigidity and decrement of Packing spring 32 need to be calculated in detail according to specific design, but this calculating is for this
For art personnel and in the absence of hell and high water, so the shape and quantity in the present invention not to Packing spring are carried out in detail
Description, of the invention is mainly characterized by structure design, so changing the size of each parts still in the protection model of the present invention
Within enclosing.
Preferred embodiment of the invention described in detail above.It should be appreciated that one of ordinary skill in the art without
Need creative work just can make many modifications and variations according to the design of the present invention.Therefore, all technologies in the art
Personnel are available by logical analysis, reasoning, or a limited experiment on the basis of existing technology under this invention's idea
Technical scheme, all should be in the protection domain being defined in the patent claims.
Claims (10)
1. a kind of effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation, the variable-nozzle ring assemblies are arranged on turbocharging
In device, the whirlpool end of the turbocharger includes volute, turbine and variable-nozzle ring assemblies, it is characterised in that the variable spray
Mouth ring assemblies include blade backplate, spacing pin, blade, mounting disc, rigging pilotage, synchronous ring and adjusting rock arm, the blade backplate
Between the volute and the blade, the spacing pin, the blade and the rigging pilotage are assemblied in the mounting disc,
The synchronous ring is fixed in the mounting disc by the rigging pilotage, and the adjusting rock arm is connected with the synchronous ring, described to adjust
The shaft end of section rocking arm and the blade is assembled.
2. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the blade shield
Plate is designed with three blind holes towards vane end faces, and the blind hole coordinates with the spacing pin gap.
3. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the spacing pin
One end be designed with assembled shaft, the assembled shaft is assembled using the form of welding or riveting with the spacing pin in the mounting disc
Assembling is fixed in hole, and the other end is free end, and gap cooperation is carried out with the blind hole on the blade backplate.
4. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 3, it is characterised in that the spacing pin
With the mounting disc coordinate step surface to the end face of the free end distance more than the blade guide face height and
The depth sum of the blind hole.
5. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the blade master
To be made up of guide face and rotary shaft, the rotary shaft is arranged in the mounting disc and rotated in default mounting hole, described turn
The path part of moving axis end is used to weld or rivet with the adjusting rock arm to assemble.
6. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the mounting disc
Be provided centrally with circle turbine mating holes, the different hole of some diameters is configured with the circumference of the mounting disc, respectively
For the spacing pin, the blade and the assembling of the rigging pilotage.
7. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the rigging pilotage
The synchronous ring is fixed in the mounting disc, there is the groove equal with the adjusting rock arm quantity on the synchronous ring, and
And be connected with external drive rocking arm.
8. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that the regulation is shaken
The through hole of arm one end is coordinated with the blade shaft end, and the main assembly method using welding or riveting is fixed about
Beam, the other end of the adjusting rock arm is assembled with the groove on the synchronous ring.
9. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 1, it is characterised in that with the blade
Assembling Packing spring in Packing spring fitting recess, the Packing spring fitting recess is designed with the corresponding volute of backplate.
10. effectively prevent the variable-nozzle ring assemblies of blade clamping stagnation as claimed in claim 9, it is characterised in that the sealing
The axial maximum height of spring is greater than the bottom of the Packing spring fitting recess the distance between to blade backplate, so as to ensure
The Packing spring is under any shape all in compressive state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710331338.9A CN106939828A (en) | 2017-05-11 | 2017-05-11 | It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710331338.9A CN106939828A (en) | 2017-05-11 | 2017-05-11 | It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation |
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| Publication Number | Publication Date |
|---|---|
| CN106939828A true CN106939828A (en) | 2017-07-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710331338.9A Pending CN106939828A (en) | 2017-05-11 | 2017-05-11 | It is a kind of effectively to prevent the variable-nozzle ring assemblies of blade clamping stagnation |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108252744A (en) * | 2018-04-24 | 2018-07-06 | 长兴永能动力科技有限公司 | A kind of two-sided adjusting centripetal turbine wheel |
| CN113309607A (en) * | 2021-06-24 | 2021-08-27 | 蜂巢蔚领动力科技(江苏)有限公司 | VGT structure of adjustable blade and turbo charger of using thereof |
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| CN101668933A (en) * | 2007-12-21 | 2010-03-10 | 三菱重工业株式会社 | Variable capacity-type exhaust turbo supercharger equipped with variable nozzle mechanism |
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| CN108252744A (en) * | 2018-04-24 | 2018-07-06 | 长兴永能动力科技有限公司 | A kind of two-sided adjusting centripetal turbine wheel |
| CN108252744B (en) * | 2018-04-24 | 2023-04-21 | 长兴永能动力科技有限公司 | Double-sided adjusting centripetal turbine blade |
| CN113309607A (en) * | 2021-06-24 | 2021-08-27 | 蜂巢蔚领动力科技(江苏)有限公司 | VGT structure of adjustable blade and turbo charger of using thereof |
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