CN204371429U - Integrated type turbocharger variable nozzle ring member - Google Patents
Integrated type turbocharger variable nozzle ring member Download PDFInfo
- Publication number
- CN204371429U CN204371429U CN201420785554.2U CN201420785554U CN204371429U CN 204371429 U CN204371429 U CN 204371429U CN 201420785554 U CN201420785554 U CN 201420785554U CN 204371429 U CN204371429 U CN 204371429U
- Authority
- CN
- China
- Prior art keywords
- ring
- blade
- seat
- turborotor
- supporting base
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model belongs to field of turbochargers, specifically a kind of integrated type turbocharger variable nozzle ring member.It comprises whirlpool end seal ring, turborotor seat, 12 impeller assemblys, the main supporting base of blade, intermediate gland, driving ring, orbit ring, blade locating stud and four screws, turborotor seat, the main supporting base of blade, intermediate gland, driving ring and orbit ring are fixed as one by four screws respectively, and blade locating stud is connected between driving ring and main supporting base fixing.The utility model has the advantages that on the nozzle ring basis of digesting and assimilating conventional model, in structure, many places are separated and make riveted joint into by many places change, location is reliable, component assembly relation simplifies, improve assembly precision, decrease component and reduce cost of production, assembling easily operates, efficiency is high, adapts to promote.
Description
Technical field
The utility model belongs to field of turbochargers, specifically a kind of integrated type turbocharger variable nozzle ring member.
Background technique
Supercharging technology is one of the major measure improving engine power performance, and most widely used be adopt turbocharging technology.Turbosupercharger is the energy utilizing motor combustion gas, mechanical work is become by turbine, drive turbine wheel transmission, the compressor impeller coaxial with turbine wheel also runs up with same speed, after compresses fresh air, send into cylinder, improve air density and the aeration quantity of cylinder, thus improve the power of motor, improve the combustion condition of fuel oil, make fuel oil Thorough combustion, thus fuel consume is reduced, decrease the ratio of Toxic in the waste gas entering air, and then finally realize environmental protection and energy saving, improve the effect of engine power.
But vehicle turbocharger should have broader operating range, because when time of engine low speed, the energy provided due to waste gas is little, and the rotating speed of turbosupercharger is too low, be difficult to provide applicable boost pressure and sufficient air inflow, be also just difficult to produce larger torque; Be again motor when running up, because delivery temperature and pressure are very high, pressurized machine may be caused to exceed the speed limit.In addition, delayed due to pressurized machine response, makes the response of the response ratio air inflow supply of in transient process oil mass supply fast, and therefore causes the transient response performance of motor difference and acceleration of smoldering.In order to address these problems, people have employed all multi-methods such as reducing pressurized machine rotary inertia, installation exhaust vent valve, auxiliary air injection, adjustment nozzle ring aperture.The method of nozzle ring aperture is regulated to have been widely recognized because of improve with the obvious advantage of its engine performance.Adopt variable nozzle ring turbosupercharger compared with the common pressurized machine of employing, the low speed torque of motor, smoke intensity and oil consumption are obtained for improvement.
As shown in Figures 1 and 2, it comprises a driving ring, three supporting wheels, three support wheel shafts, 11 driven rocking arms, 11 blades, blade seat, three step pins and a nozzle carrier to existing variable nozzle ring.Supporting wheel is arranged on blade seat by supporting wheel shaft, adopts Spielpassung between supporting wheel and support wheel shaft, supports between wheel shaft and blade seat and adopts Spielpassung.Blade and driven rocking arm are arranged on blade seat by being welded and fixed, and adopt Spielpassung between blade and blade seat.Driving ring is assemblied in the draw-in groove of a supporting wheel.Step pin is arranged in the pin hole on blade seat, and the pin hole on step pin and blade seat adopts Spielpassung.Nozzle carrier is provided with three be used for nozzle carrier 8 being arranged in the screw hole on turbocharger middle body.
Accompanying drawing 3 is the schematic diagram that existing variable nozzle ring is arranged in turbosupercharger, and blade seat is arranged on turbocharger middle body by step pin, and the pin hole on step pin and turbocharger middle body adopts Spielpassung.Nozzle carrier is arranged on turbocharger middle body by screw.
Existing variable nozzle ring has the following disadvantages: one be most of component is all separation member, and component assembling is loaded down with trivial details, and efficiency is low; Two is when installing variable nozzle ring in turbosupercharger, not only nozzle carrier 8 will be arranged on turbocharger middle body by screw, and to position limit pin be assembled on turbocharger middle body, which adds bearing support manufacturing procedure and assembly process, add number of spare parts simultaneously.
Honeywell Inc. discloses the variable nozzle component of turbocharger with blade seal ring in Chinese patent CN 102828785A, blade seal ring pushes the near-end of blade to by discarding pressure reduction, and therefore blade is pushed to relative nozzle wall, thus the far-end of described blade is close to described wall, cause reducing at the near-end of blade and the gap of far-end or closing.
Known complete closable spray nozzle device in Japanese patent publication JP-A-2002-038964.Build variable nozzle device by pivotable blade, make the geometrical construction of runner be adjustable.The blade that pivotable vane tip is adjacent adjacent respectively, makes almost to be closed completely by the runner of nozzle.
Summary of the invention
It is that in prior art, split type jet element complexity, component assemble loaded down with trivial details problem that the present invention will solve, and provides one integrated type turbocharger variable nozzle ring member.
Present invention employs following technological scheme:
It comprises whirlpool end seal ring, turborotor seat, 12 impeller assemblys, the main supporting base of blade, intermediate gland, driving ring, orbit ring, blade locating stud and four screws, turbine end seal ring is located at turborotor seat end, impeller assembly comprises blade assembly, sharf, blade assembly is fixed on sharf, sharf and blade assembly are distributed on the both sides of the main supporting base of blade and turborotor seat, driving ring is provided with 13 flutings, 12 blades are located in fluting respectively, remain a fluting to be connected with the initiatively rocking arm of intermediate, four screws are respectively by turborotor seat, the main supporting base of blade, intermediate gland, driving ring and orbit ring riveted joint are fixed as one, blade locating stud is connected between driving ring and main supporting base fixing.
Described whirlpool end seal ring comprises two, is located at respectively in two seal grooves on the external cylindrical surface of turborotor seat front end.
Described driving ring is also provided with the opening slot of 12 V-shapeds
The utility model has the advantages that on the nozzle ring basis of digesting and assimilating conventional model, in structure, many places are separated and make riveted joint into by many places change, location is reliable, component assembly relation simplifies, improve assembly precision. decrease component and reduce cost of production, assembling easily operates, efficiency is high, adapts to promote.
Accompanying drawing explanation
Fig. 1 is existing variable nozzle ring structural representation;
Fig. 2 is existing variable nozzle ring structural representation;
Fig. 3 is the schematic diagram that existing variable nozzle ring is arranged in turbosupercharger;
The variable nozzle ring detonation configuration schematic diagram that Fig. 4 provides for the utility model;
The variable nozzle ring structural representation that Fig. 5 provides for the utility model
Fig. 6 is that the A-A of Fig. 5 is to sectional view;
Fig. 7 is arranged on the schematic diagram in turbosupercharger for variable nozzle ring that the utility model provides.
Embodiment
As Fig. 4, Fig. 5, shown in Fig. 6, a kind of push-in double-sealing water conservancy diversion integrated type variable nozzle component of turbocharger, by two whirlpool end seal rings 2, a turborotor seat 1, 12 impeller assemblys, a main supporting base 3 of blade, an intermediate gland 4, a driving ring 5, an orbit ring 8, a blade locating stud 10, four screws 9 form, impeller assembly comprises blade assembly 6 and sharf 7, driving ring 5 end face has two kinds of opening slots, driving ring 5 outer ring has the opening slot of 12 wide V-types, opening slot driving ring 5 circumferencial direction spacing in intermediate gland 4 time reduce between mismatch error, driving ring 5 inner ring has 13 opening slots, wherein 12 impeller assemblys kept a grip on by 12 opening slots, the initiatively rocking arm on intermediate kept a grip on by a remaining opening slot, 12 impeller assemblys realize the folding change of nozzle under the drive of driving ring 5, orbit ring 8 is riveted with remaining parts in nozzle ring, and the single-way moving of the step surface restriction driving ring 5 of rule distribution on it, intermediate gland 4 has equally 11 press the rightabout movements of wrapping and limiting driving rings 5,
Intermediate gland 4 is except completing the unidirectional restriction in driving ring 5 movement process, and large cylindrical flange is used for being fixed in turbosupercharger, external cylindrical surface has an aperture, is fixed in turbosupercharger again by driving ring 5;
Turborotor seat 1, front end external cylindrical surface has two seal grooves, each groove is built with a whirlpool end seal ring 2, this structure reaches sealing effect with after the combination of volute endoporus, the inner arc surface of turborotor seat 1 is identical with the steel wheel molded line curved surface curvature matched, complete the derivation of high-temp waste gas, in 12 holes that 12 impeller assemblys assist fulcrum to be arranged on turborotor seat 1 end face, its end face also has the hole that four are not uniform, assist fulcrum hole point-blank with adjacent impeller assembly and the center of circle of face, go side circle; Turborotor seat 1, the main supporting base 3 of blade, intermediate gland 4. driving ring 5 and orbit ring 8 are riveted into one by four screws 9;
Impeller assembly comprises blade assembly 6 and sharf 7, sharf 7 and blade assembly 6 are distributed on the both sides of the main supporting base 3 of blade and turborotor seat 1, a corresponding blade 6 of sharf 7, is fixedly mounted on the main supporting base 3 of blade and turborotor seat 1 by riveted joint between sharf 7 and blade 6;
Blade locating stud 10 has two effects, one is the assembling and positioning of driving ring 5 in turbosupercharger, two is break points of the maximum opening of impeller assembly, blade locating stud 10 is in driving ring 5 and blade main supporting base 3 interference fit joint, through remaining adjacent parts, the minimum aperture of impeller assembly holds realization constrained each other by the whole story of adjacent two blade assemblies 6;
Claims (3)
1. integrated type turbocharger variable nozzle ring member, it comprises whirlpool end seal ring, turborotor seat, 12 impeller assemblys, the main supporting base of blade, intermediate gland, driving ring, orbit ring, blade locating stud and four screws, it is characterized in that: turbine end seal ring is located at turborotor seat end, impeller assembly comprises blade assembly, sharf, blade assembly is fixed on sharf, sharf and blade assembly are distributed on the both sides of the main supporting base of blade and turborotor seat, driving ring is provided with 13 flutings, 12 blades are located in fluting respectively, remain a fluting to be connected with the initiatively rocking arm of intermediate, four screws are respectively by turborotor seat, the main supporting base of blade, intermediate gland, driving ring and orbit ring riveted joint are fixed as one, blade locating stud is connected between driving ring and main supporting base fixing.
2. integrated type turbocharger variable nozzle ring member according to claim 1, is characterized in that: described whirlpool end seal ring comprises two, is located at respectively in two seal grooves on the external cylindrical surface of turborotor seat front end.
3. integrated type turbocharger variable nozzle ring member according to claim 1, is characterized in that: described driving ring is also provided with the opening slot of 12 V-shapeds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420785554.2U CN204371429U (en) | 2014-12-12 | 2014-12-12 | Integrated type turbocharger variable nozzle ring member |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420785554.2U CN204371429U (en) | 2014-12-12 | 2014-12-12 | Integrated type turbocharger variable nozzle ring member |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204371429U true CN204371429U (en) | 2015-06-03 |
Family
ID=53327658
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420785554.2U Expired - Fee Related CN204371429U (en) | 2014-12-12 | 2014-12-12 | Integrated type turbocharger variable nozzle ring member |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204371429U (en) |
-
2014
- 2014-12-12 CN CN201420785554.2U patent/CN204371429U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2822965C (en) | Gas turbine engine and variable camber vane system | |
| CN104454034A (en) | Fast-inserting type double-sealed variable nozzle turbocharger | |
| CN102900479B (en) | Variable nozzle turbocharger regulating mechanism integrated on turbine shell | |
| CN202065055U (en) | Turbocharger | |
| CN201474729U (en) | Compact disk shaped driving variable cross section nozzle ring component | |
| CN102619616A (en) | Turbine supercharger | |
| CN201884075U (en) | Plate-driven nozzle ring component with variable cross section | |
| CN105736072A (en) | Variable nozzle ring assembly of integral turbosupercharger | |
| CN104819014B (en) | The adjustable nozzle ring structure of combined flow turbine supercharger peculiar to vessel | |
| CN203867702U (en) | Turbine air intake supercharger of axial-flow type aerodynamic internal combustion engine | |
| CN204371429U (en) | Integrated type turbocharger variable nozzle ring member | |
| CN204371427U (en) | Push-in double-sealing variable nozzle turbocharger | |
| CN102606229A (en) | Variable nozzle component of turbocharger | |
| CN102242645B (en) | Integral variable nozzle ring of turbocharger | |
| CN205117414U (en) | Nozzle cascade subassembly of circular structure | |
| CN202176378U (en) | Integrated variable nozzle ring of turbocharger | |
| CN105189935A (en) | Integrated vane stops for variable-geometry turbocharger mechanism | |
| CN100470011C (en) | Radial-flow waste gas turbocharger adjustable nozzle ring mechanism for ship | |
| CN203321669U (en) | Turbocharger intermediate | |
| CN204041221U (en) | Exhaust-gas turbocharger VGT supporting structure | |
| CN203441545U (en) | Bolt shaft tightening impeller and connection structure of impeller and turbine shaft | |
| CN205714417U (en) | A kind of turbocharger, electromotor and automobile | |
| CN202417694U (en) | Turbocharger middle body | |
| CN103727071A (en) | Variable pressure expander of pressurizer gas compressor | |
| CN104718361B (en) | Turbocharger, turbine nozzle and boats and ships |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150603 Termination date: 20181212 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |