CN101949305B - Turbocharger composite nozzle device - Google Patents

Turbocharger composite nozzle device Download PDF

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Publication number
CN101949305B
CN101949305B CN2010102735860A CN201010273586A CN101949305B CN 101949305 B CN101949305 B CN 101949305B CN 2010102735860 A CN2010102735860 A CN 2010102735860A CN 201010273586 A CN201010273586 A CN 201010273586A CN 101949305 B CN101949305 B CN 101949305B
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China
Prior art keywords
blade
nozzle
moving blade
ring supporting
shift fork
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CN2010102735860A
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Chinese (zh)
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CN101949305A (en
Inventor
王航
刘莹
王聪聪
朱智富
李永泰
宋丽华
信效芬
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Kangyue Technology (Shandong) Co.,Ltd.
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Kangyue Technology Co Ltd
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/141Shape, i.e. outer, aerodynamic form
    • F01D5/146Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12Control of the pumps
    • F02B37/24Control of the pumps by using pumps or turbines with adjustable guide vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/40Application in turbochargers
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/12Improving ICE efficiencies

Abstract

The invention discloses a turbocharger composite nozzle device, comprising a turbine wheel and a nozzle ring supporting disc mounted coaxially therewith. The nozzle ring supporting disc is provided with a plurality of groups of composite nozzle blades each comprising a movable blade and a fixed blade, the fixed blade is fixedly connected with the nozzle ring supporting disc and the movable blade is in transmission connection with a power transmission device; in case of other working conditions of an engine, a transmission mechanism adjusts the position of the movable blade continuously according to the change of the working conditions of the engine, and the control for waste gas energy is realized by changing the area of volute nozzle outlet, in order to improve aerodynamic performance of the turbocharger, especially aerodynamic performance of the engine under the working condition of small flow, thus better matching with the engine is reached.

Description

Composite spraying nozzle device of turbocharger
Technical field
The present invention relates to a kind of variable-area turbocharger, relate to specifically a kind of composite spraying nozzle device of turbocharger, can effectively take into account the high low speed supercharging requirement of motor, especially improve the low speed torque performance, belong to field of internal combustion engine.
Background technique
Progressively raising along with emission standard, pressurized machine has become the indispensable component of Modern Engine, thereby pressurized machine not only will be born the function that traditional raising engine charge density improves engine power density and improves burning, but also must be able to realize the regulatory function of boost pressure and engine back pressure.Along with the enforcement of state's four dischargings, variable-area turbocharger has become the emphasis of pressurized machine industry research and development.
Generally adopt at present and increase the requirement that the swivel nozzle blade satisfies variable cross section in turbine.It can effectively improve the efficient of turbosupercharger and widen matching range with motor.
Rotary vane type variable geometry turbocharger 1 structural representation as shown in Figure 1, the turbine portion of rotary vane type turbosupercharger is divided and is comprised turbine volute 5, spiral case nozzle 7, turbine wheel 9 three parts.The high-temp waste gas that turbine volute 5 is collected arrives spiral case nozzle 7 through volute air-inlet runner 11, under driving mechanism 4 effects, regulate the outlet circulation area of spiral case nozzle 7 by the angle of swing of Control Nozzle blade 8, make waste gas arrive the periphery of turbine wheel 9 by the angular distribution of design, promote turbine wheel 9 High Rotation Speeds.Under the support of middle case 3 internal float dynamic bearings 12, drive compressor impeller 14 High Rotation Speeds by turbine rotor shaft 13, the air that axially enters gas compressor is compressed, be admitted to the combustion process that cylinder participates in motor after the collection of air by compressor casing 2 of compression, realize the purpose of supercharging.The high-temp waste gas of motor is discharged in the waste pipe road by spiral case relief opening 10 after turbine wheel 9 is finished merit.
Nozzle vane 8 on nozzle ring supporting disk 6 satisfies coupling with Under Different Work Condition of Engine by different opening.A1 shown in Figure 2 is large aperture.Nozzle vane trailing edge 23 is nearest from turbine blade leading edge 24, and aerodynamic loss is minimum.At this moment, the operating mode of pressurized machine and Engine Matching is large flow rate working conditions.A2 shown in Figure 3 is little aperture.Nozzle vane trailing edge 23 from the distance of turbine blade leading edge 24 farthest, exit area of nozzle is minimum.At this moment, the operating mode of pressurized machine and Engine Matching is low flow rate condition.
Find that by the application of reality this rotary vane type variable geometry turbocharger also exists some shortcomings in the Performance Match process.
Under large flow rate working conditions, the aperture of nozzle vane 8 is maximum when motor, and nozzle vane trailing edge 23 is in the most close turbine blade leading edge 24 in the radial direction, and air-flow can be blown into smoothly according to the guiding of blade turbine wheel 9 actings, so aerodynamic loss is very little.But nozzle vane 8 is nearer apart from turbine blade leading edge 24, and the particle in waste gas can cause larger wearing and tearing to nozzle vane 8.Under the operating mode of motor at small flow, nozzle vane 8 apertures reduce, thereby have reduced exit area of nozzle, have increased the suction pressure of turbine, and turbine output increases, thereby satisfy the requirement of engine boost pressure.But because rotating speed is relatively low, in the situation that the little aperture of nozzle vane 8, nozzle vane trailing edge 23 apart from turbine blade leading edge 24 farthest, the air current flow path is the longest, and aerodynamic loss is the most serious, and turbine air inlet circumferential speed strengthens in little aperture situation, turbine becomes action turbine, be unfavorable for taking full advantage of of exhaust energy, make turbine efficiency on the low side, and cause engine exhaust back pressure too high.
Therefore wish a kind of nozzle of design, can be applicable to variable-area turbocharger and solve the aerodynamic loss of slow speed jet blade with emphasis, and improve the efficient of pressurized machine.Regulate to obtain than common swivel nozzle blade gas flow paths more suitably by the cooperation of nozzle, improve the efficient of turbosupercharger and realize better mating with the low speed of motor.
Summary of the invention
The problem to be solved in the present invention is for the rotary vane type variable geometry turbocharger problem that aerodynamic loss is serious under low flow rate condition, efficiency of turbocharger is on the low side, design a kind of composite spraying nozzle device of turbocharger, can effectively solve the matching effect of operating mode under gas flow loss problem and improvement and motor small flow, satisfy the supercharging requirement of motor.
In order to address the above problem, the present invention by the following technical solutions:
A kind of composite spraying nozzle device of turbocharger, comprise turbine wheel and nozzle ring supporting disk coaxial mounted with it, be provided with some groups of combining nozzle blades on the nozzle ring supporting disk, described combining nozzle blade comprises moving blade and stator blade, described stator blade is fixedly connected with the nozzle ring supporting disk, and described moving blade and actuating unit are in transmission connection.
Below further improvement of these options of the present invention:
Position corresponding with moving blade on the nozzle ring supporting disk is provided with skewed slot, and the leading edge end of described moving blade is provided with the moving blade axle, and described moving blade axle passes skewed slot and actuating unit is in transmission connection.
Further improve: described moving blade, described stator blade and skewed slot are arcuate structure.
Described skewed slot has been considered the pneumatic blade profile of stator blade when design, make described moving blade in carry out circumferential and radial motion process along described skewed slot as far as possible, the cambered surface transition position of the cambered surface of moving blade and described stator blade can not produce too large curve form sudden change, can reduce like this energy loss in the gas flow process.
Further improve:
Described skewed slot is arranged on the position of close stator blade leading edge on the nozzle ring supporting disk, moving blade is moved along skewed slot with respect to stator blade, move to the footpath when upwards nearest apart from the turbine blade leading edge, form the exit area of nozzle of minimum between moving blade and contiguous stator blade; Move to the footpath upwards apart from the turbine blade leading edge farthest the time, the exit area of nozzle of the formation maximum between moving blade and the stator blade that is close to.
In described combining nozzle blade cooperating process, no matter engine operation is when large flow or small flow, the distance of described stator blade trailing edge and turbine blade leading edge remains unchanged, and is realized the variation of turbine nozzle flow area by the movement of described moving blade.Along with moving blade moves by the direction away from turbine wheel along skewed slot, it is large that the turbine nozzle discharge area becomes; When moving blade moves by opposite direction along skewed slot, exit area of nozzle diminishes, and controls the energy of waste gas by changing the turbine nozzle discharge area, and then controls the rotational speed of turbine wheel, satisfy the supercharging requirement of motor, to adapt to the coupling requirement of Under Different Work Condition of Engine.
Further improve:
Be provided with some shift forks on the nozzle ring supporting disk of a side opposite to the combining nozzle blade, described shift fork is corresponding one by one with moving blade, and described moving blade axle passes skewed slot and is connected with shift fork.
Be provided with shifting fork disc on the excircle of nozzle ring supporting disk, described shift fork is comprised of two shift fork arms, the common terminal of described two shift fork arms is rotationally connected by driven shift fork running shaft and nozzle ring supporting disk, the other end and the shifting fork disc of one of them shift fork arm are rotationally connected, and the other end of another shift fork arm is connected with the moving blade axle.
The shift fork arm that shifting fork disc rotate to drive described shift fork rotate around driven declutch shift shaft, and then another shift fork arm that drive is connected with described moving blade axle rotates around driven declutch shift shaft, realizes that moving blade carries out carrying out circumferential and radial motion along skewed slot.
Further improve: be provided with the active rotation axle on the nozzle ring supporting disk, initiatively shift fork is installed on described active rotation axle, described active shift fork and shifting fork disc are rotationally connected.
The another kind of improvement: the end of described stator blade is provided with stator blade welding axle, and described stator blade welding axle is fixedly connected with the nozzle ring supporting disk.
The present invention regulates by the cooperation of moving blade and stator blade, can make air-flow move to turbine wheel according to rational route, and it can according to the requirement of Under Different Work Condition of Engine, under the effect of driving mechanism, realize different fit angle.In whole process, the position of stator blade remains unchanged, and under the driving of actuating unit, moving blade carries out circumferentially and radial motion along skewed slot.
Can effectively reduce so common single blade too far away apart from the turbine blade leading edge at small flow lower blade trailing edge, cause serious aerodynamic loss, and improve the acting ability of turbine.The wearing and tearing of the nozzle vane that single blade too closely causes apart from the turbine blade leading edge because of blade trailing edge have been reduced under large flow.
When moving blade moves to the footpath when upwards nearest apart from the turbine blade leading edge along skewed slot, at this moment moving blade is minimum with the exit area of nozzle that contiguous stator blade forms.At this moment turbine inlet pressure raises, and makes flowing gas have more energy.When the combining nozzle blade can reduce small flow simultaneously, the air inlet circumferential speed is too high, has avoided turbine wheel to become the impact type impeller fully, the turbine efficiency in the time of improving small flow.When flowing gas impulse turbine impeller, have the output work that more energy changes into turbine, thereby improve the boost pressure of motor under small flow, better realize and the coupling of motor under low flow rate condition.
When moving blade moves to the footpath upwards apart from the turbine blade leading edge farthest the time along skewed slot, at this moment the exit area of nozzle maximum that forms of two adjacent combining nozzle blades is to guarantee negotiability.With realize with the large flow rate working conditions of motor under with the coupling of motor,
Under other working conditions of motor, driving mechanism can constantly be regulated according to the variation of engine operating condition the position of moving blade, realizes control to exhaust energy by changing the spiral case exit area of nozzle, thereby realizes the coupling with each operating mode of motor.
To sum up, the combining nozzle turbosupercharger of employing Tape movement blade can effectively be improved the aeroperformance of pressurized machine, especially improves the aeroperformance of motor under low flow rate condition, better realizes the coupling with motor.
Below in conjunction with drawings and Examples, this outbreak is further illustrated:
Description of drawings:
Fig. 1 is rotary vane type variable geometry turbocharger structural representation in background technique;
Fig. 2 is the structural representation of rotary vane type nozzle mechanism under the large flow rate working conditions of motor in background technique;
Fig. 3 is the structural representation of rotary vane type nozzle mechanism under the motor low flow rate condition in background technique;
Fig. 4 is the assembly structure schematic diagram of the combining nozzle of Tape movement blade in the embodiment of the present invention;
Fig. 5 is the combining nozzle blade structure schematic diagram of Tape movement blade in the embodiment of the present invention;
Fig. 6 is the schematic diagram of moving blade motion in the embodiment of the present invention;
Fig. 7 is the assembling schematic diagram of moving blade in the embodiment of the present invention;
Fig. 8 is the structural representation of motor combining nozzle of Tape movement blade under low flow rate condition in the embodiment of the present invention;
Fig. 9 is the structural representation of motor combining nozzle of Tape movement blade under large flow rate working conditions in the embodiment of the present invention.
In figure: 1-rotary vane type variable geometry turbocharger The 2-compressor casing; The 3-middle case; The 4-driving mechanism; The 5-turbine volute; 6-nozzle ring supporting disk; 7-spiral case nozzle; The 8-nozzle vane; The 9-turbine wheel; 10-spiral case relief opening; 11-volute air-inlet runner; The 12-floating bearing; The 13-turbine rotor shaft; The 14-compressor impeller; The 15-shift fork; The 16-shifting fork disc; The 17-moving blade; The 18-stator blade; The 19-skewed slot; 20-moving blade axle; 21-stator blade welding axle; 22-stator blade trailing edge; 23-nozzle vane trailing edge; 24-turbine blade leading edge; 25-active rotation axle; 26-is shift fork initiatively; The driven shift fork running shaft of 27-; 28-combining nozzle blade.
Embodiment
Embodiment, as shown in Figure 4, a kind of composite spraying nozzle device of turbocharger, it comprises turbine wheel 9 and nozzle ring supporting disk 6 coaxial mounted with it, evenly be provided with ringwise some groups of combining nozzle blades 28 on nozzle ring supporting disk 6, every group of combining nozzle blade 28 comprises a moving blade 17 and a stator blade 18.Have some skewed slots 19 on the nozzle ring supporting disk, described skewed slot 19 is corresponding one by one with moving blade 17,
Described moving blade 17, described stator blade 18 are arcuate structure with skewed slot 19, when design skewed slot 19, make described moving blade 17 along in described skewed slot 19 movement processes as far as possible, the cambered surface transition position of the cambered surface of moving blade 17 and described stator blade 18 can not produce too large curve form sudden change, can reduce like this energy loss in the gas flow process, improve the utilization of waste gas energy strength.
As shown in Figure 5, moving blade 17 can carry out radially and circumferential movement along the skewed slot on the nozzle ring supporting disk, comes together to coordinate with stator blade 18 work of realization.Stator blade 18 welds axle 21 by stator blade and is fixedly installed on the nozzle ring supporting disk.Moving blade 17 is provided with moving blade axle 20, and described moving blade axle 20 passes skewed slot 19 and is in transmission connection with actuating unit.
as shown in Figure 6, described actuating unit comprises the some shift forks 15 on the nozzle ring supporting disk 6 that is arranged on a side opposite to the combining nozzle blade, described shift fork 15 is corresponding one by one with moving blade 17, described moving blade axle 20 passes skewed slot 19 and is connected with shift fork 15, be provided with shifting fork disc 16 on the excircle of nozzle ring supporting disk 6, described shift fork 15 is comprised of two shift fork arms, the common terminal of described two shift fork arms is rotationally connected with nozzle ring supporting disk 6 by driven declutch shift shaft 27, the other end of one of them shift fork arm and shifting fork disc 16 are rotationally connected, the other end of another shift fork arm is connected with moving blade axle 20.
Be provided with active rotation axle 25 on nozzle ring supporting disk 6, initiatively shift fork 26 is installed on described active rotation axle 25, and described active shift fork 26 is rotationally connected with shifting fork disc 16, under the effect of driving mechanism, active rotation axle 25 drives initiatively shift fork 26 rotations, and then drives shifting fork disc 16 rotations.Shifting fork disc 16 rotates a shift fork arm that drives again shift fork 15 and rotates around driven shift fork running shaft 27, and then another shift fork arm that drive is connected with moving blade axle 20 rotates around driven declutch shift shaft 27.
The track that actuating unit driving moving blade 17 is set along skewed slot 19 carries out radially and circumferential movement, realizes changing the effect of turbine nozzle discharge area.
As shown in Figure 7, shift fork 15 is arranged on the nozzle ring supporting disk 16 of a side opposite to moving blade 17, and moving blade 17 is connected with shift fork 15 by moving blade axle 20.Shift fork 15 drives 20 motions of moving blade axle, and moving blade 17 is carried out circumferentially and radial motion along skewed slot.
As shown in Figure 8, described skewed slot 19 is arranged on the position of close stator blade 18 leading edges on nozzle ring supporting disk 6, moving blade 17 is moved along skewed slot 19 with respect to stator blade 18, when moving to the leading edge locus of skewed slot 19, namely move to the footpath upwards apart from turbine blade leading edge 24 recently the time, form minimum exit area of nozzle between the stator blade 18 of moving blade 17 and vicinity, moving blade 17 interacts with adjacent stator blade 18 and completes the guiding work of air-flow, and aerodynamic loss greatly reduces.
As shown in Figure 9, moving blade 17 is moved along skewed slot 19 with respect to stator blade 18, when moving to the posterior border position of skewed slot 19, namely move to the footpath upwards apart from turbine blade leading edge 24 farthest the time, the exit area of nozzle of the formation maximum between moving blade 17 and the stator blade 18 that is close to.
Stator blade trailing edge 22 is still constant apart from the distance of turbine blade leading edge 24.At this moment two contiguous combining nozzle blades 28 are completed the leading role of air-flow jointly, and aerodynamic loss is little.At this moment, the coupling operating mode of pressurized machine and motor is large flow rate working conditions.
Under other working conditions of motor, driving mechanism can constantly be regulated according to the variation of engine operating condition the position of moving blade, realizes control to exhaust energy by changing the spiral case exit area of nozzle, thereby realizes the coupling with each operating mode of motor.
Patent of the present invention has been completed the exploitation of the composite spraying nozzle device of turbocharger that is comprised of moving blade and stator blade for the demand of variable nozzle turbocharger, effectively controls and utilized exhaust energy.This combining nozzle blade can be completed by same type of material and existing casting and processing technique.Movement in combining nozzle, stator blade adopt solid construction mostly, and function mobile, stator blade can be replaced mutually according to the structure needs.

Claims (2)

1. composite spraying nozzle device of turbocharger, comprise turbine wheel (9) and nozzle ring supporting disk coaxial mounted with it (6), be provided with some groups of combining nozzle blades (28) on nozzle ring supporting disk (6), it is characterized in that: described combining nozzle blade (28) comprises moving blade (17) and stator blade (18), described stator blade (18) is fixedly connected with nozzle ring supporting disk (6), and moving blade (17) is in transmission connection with actuating unit;
The upper position corresponding with moving blade (17) of nozzle ring supporting disk (6) is provided with skewed slot (19), the leading edge end of described moving blade (17) is provided with moving blade axle (20), and described moving blade axle (20) passes skewed slot (19) and is in transmission connection with actuating unit;
Described moving blade (17), described stator blade (18) are arcuate structure with skewed slot (19);
Described skewed slot (19) is arranged on the position of upper close stator blade (18) leading edge of nozzle ring supporting disk (6), moving blade (17) is mobile along skewed slot (19) with respect to stator blade (18), when described moving blade (17) moves to the leading edge locus of skewed slot (19), form minimum exit area of nozzle between the stator blade (18) of moving blade (17) and vicinity; When described moving blade (17) moves to the posterior border position of skewed slot (19), form maximum exit area of nozzle between the stator blade (18) of moving blade (17) and vicinity;
Described actuating unit comprises the some shift forks (15) on the nozzle ring supporting disk (6) that is arranged on a side opposite to the combining nozzle blade, described shift fork (15) is corresponding one by one with moving blade (17), and described moving blade axle (20) passes skewed slot (19) and is connected with shift fork (15);
Be provided with shifting fork disc (16) on the excircle of nozzle ring supporting disk (6), described shift fork (15) is comprised of two shift fork arms, the common terminal of described two shift fork arms is rotationally connected by driven shift fork running shaft (27) and nozzle ring supporting disk (6), the other end of one of them shift fork arm and shifting fork disc (16) are rotationally connected, and the other end of another shift fork arm is connected with moving blade axle (20);
Be provided with active rotation axle (25) on nozzle ring supporting disk (6), initiatively shift fork (26) is installed on described active rotation axle (25), described active shift fork (26) is rotationally connected with shifting fork disc (16).
2. composite spraying nozzle device of turbocharger according to claim 1, it is characterized in that: the end of described stator blade (18) is provided with stator blade welding axle (21), and described stator blade welding axle (21) is fixedly connected with nozzle ring supporting disk (6).
CN2010102735860A 2010-09-07 2010-09-07 Turbocharger composite nozzle device Active CN101949305B (en)

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CN2010102735860A CN101949305B (en) 2010-09-07 2010-09-07 Turbocharger composite nozzle device
PCT/CN2010/001790 WO2012031381A1 (en) 2010-09-07 2010-11-08 Composite nozzle device for turbocharger

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CN101949305B true CN101949305B (en) 2013-06-05

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CN102777214B (en) * 2012-07-27 2014-12-03 萍乡市慧成精密机电有限公司 Nozzle blade of ceramic powder turbocharger and manufacturing method thereof
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CN110761847A (en) * 2019-10-30 2020-02-07 辽宁工程技术大学 Split sliding type adjustable nozzle ring of turbocharger
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CN201794621U (en) * 2010-09-07 2011-04-13 康跃科技股份有限公司 Composite spraying nozzle device of turbocharger

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