CN108487941B - Turbocharger conical variable nozzle assembly - Google Patents
Turbocharger conical variable nozzle assembly Download PDFInfo
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- CN108487941B CN108487941B CN201810509263.3A CN201810509263A CN108487941B CN 108487941 B CN108487941 B CN 108487941B CN 201810509263 A CN201810509263 A CN 201810509263A CN 108487941 B CN108487941 B CN 108487941B
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- Prior art keywords
- nozzle
- ring
- opening
- turbocharger
- vanes
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/148—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of rotatable members, e.g. butterfly valves
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a conical variable nozzle assembly of a turbocharger, which relates to the field of turbochargers and comprises a positioning pin, a cover plate, an opening ring and a nozzle ring, wherein the nozzle ring comprises a base plate, nozzle blades and an air inlet groove, the cover plate is connected with the nozzle blades through the positioning pin, and the circumferential side surfaces of the nozzle blades are designed to be conical. The invention has the advantages of less number of parts, simple structure, and greatly reduced part cost and assembly cost; the pneumatic performance can be further improved, and the efficiency is improved.
Description
Technical Field
The invention relates to the field of turbochargers, in particular to a conical variable nozzle assembly of a turbocharger.
Background
Turbochargers are devices used in conjunction with internal combustion engines to increase the power output of the engine by compressing air delivered to the engine intake for mixing with fuel and combustion in the engine. The turbocharger includes a compressor wheel mounted in a compressor housing and a turbine wheel mounted in a turbine housing. Wherein the turbine housing is formed separately from the compressor housing and yet another intermediate housing is connected between the turbine housing and the compressor housing for mounting of the bearings and cooling lubrication. The turbine housing defines a generally annular flow passage surrounding the turbine, and exhaust gas enters the flow passage from the engine and blows toward the turbine and drives the turbine in rotation, which drives the coaxially coupled compressor in rotation. Air is compressed through the compressor wheel and then from the housing outlet to the engine air intake.
One challenge in boosting engine performance with a turbocharger is achieving a desired amount of engine power output over the entire operating range of the engine. It has been found that this is not generally readily achieved with a turbocharger of fixed nozzle size; by adjusting the intake air flow to the turbine of the turbocharger, well known operational advantages are provided in terms of improved ability to control the amount of boost delivered by the turbocharger to the associated internal combustion engine. By incorporating a variable geometry in the nozzle leading into the turbine wheel, regulation of the impingement of the exhaust gases on the turbine wheel is achieved. By varying the size of the nozzle flow area, the flow into the turbine wheel, and thus the overall boost provided by the compressor of the turbocharger, can be adjusted.
Variable geometry nozzles for turbochargers are currently generally divided into two main types: variable vane nozzles and sliding piston nozzles. Vanes are typically included in the turbine nozzle for directing exhaust gas into the turbine in a beneficial direction. For a variable vane nozzle, a row of circumferentially spaced vanes extend axially through the nozzle and may be driven in synchronous rotation by a drive means. The exhaust gas from the volute flow passage flows radially inward through the passages between the blades, and the blades may redirect the flow of the gas stream to direct the flow of the exhaust gas into the turbine wheel in a desired direction. In most variable vane nozzles, the vanes are rotatable about their axes to vary the angle at which the vanes are disposed, thereby varying the flow area of the inter-vane passages. The variable vane nozzle is flexible to adjust, but the complex structure limits the application range of the variable vane nozzle, and the application temperature range of the variable vane nozzle is limited because the variable vane nozzle has more moving parts and is extremely easy to have the risk of clamping failure at high temperature; meanwhile, the variable vane nozzle has a complex structure and high cost, and the application range of the variable vane nozzle is limited.
In a sliding piston nozzle, the nozzle may also include vanes, but the vanes are fixed in place. The change in nozzle flow area is achieved by an axially sliding piston that slides in a bore in the turbine housing. The piston is tubular and is located just radially inward of the nozzle. The axial movement of the piston effectively changes the axial extent of the nozzle introduced into the turbine wheel, thereby changing the "throat area" at the inlet of the turbine wheel. When the vane is included in the nozzle, the piston may slide adjacent a radially inner edge (i.e., trailing edge) of the vane; alternatively, the piston and vane may overlap in a radial direction, and the piston may include a slot for receiving at least a portion of the vane as the piston slides axially to adjust the nozzle. The sliding piston type nozzle has not been widely used, mainly because the control structure is difficult to be arranged, because the piston is required to slide in the axial direction, the control mechanism is also required to be controlled in the axial direction, and because the scroll is connected to the intermediate housing on one side and the exhaust gas treatment line on the other side, the control mechanism is difficult to be arranged in the axial direction.
Variable vane-type and sliding piston-type variable nozzles, both of which have advantages and disadvantages. For example, variable vane nozzles with rotatable vanes typically have good aerodynamic performance, but are mechanically complex due to the large number of moving parts. Sliding piston type variable nozzles are much simpler mechanically, have few moving parts, but are generally less aerodynamically than variable vane nozzles.
The company has filed patent application (patent number 201810373619.5, patent name is variable nozzle for turbocharger and control method thereof, and turbocharger), integrates the advantages of vane type nozzle and sliding piston type nozzle with feasible design structure, simple structure, low production cost, and easy control. To further improve aerodynamic performance and efficiency, those skilled in the art have devised a turbocharger cone-shaped variable nozzle assembly for the product of this patent.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, the present invention aims to further improve pneumatic performance and pneumatic efficiency.
In order to achieve the above object, the present invention provides a turbocharger cone-shaped variable nozzle assembly comprising a positioning pin, a cover plate, an opening ring and a nozzle ring, wherein the nozzle ring comprises a base plate, nozzle vanes and an air inlet groove, and the circumferential side surfaces of the nozzle vanes are designed to be cone-shaped. The nozzle ring is in a basic annular structure, a plurality of nozzle blades are arranged on one side surface of the nozzle ring in a circumferential array, the nozzle blades are part of the nozzle ring, and the nozzle blades and the nozzle ring are integrated into a whole; the opening ring is annular, is positioned at the outer side of the nozzle ring, and controls the opening of the nozzle.
Further, the angle of the nozzle vanes is fixed and not adjustable, and the opening portion between adjacent vanes, i.e., the air intake groove, is used for guiding the exhaust gas to blow toward the turbine, and the nozzle vane angle is fixed to the optimum efficiency incident angle.
Further, the opening ring is designed in the shape of a ring with the same or approximately the same taper as the circumferential side of the nozzle vane.
Further, the diameter size of the opening ring is slightly larger than that of the nozzle ring, a plurality of opening grooves are uniformly formed in the circumferential direction of the opening ring, the number of the opening grooves is equal to that of the nozzle blades, the circumferential width of the opening grooves is equal to that of air inlet grooves between the nozzle blades, the height of the opening grooves is equal to that of the nozzle blades, and the overlapping area of the opening grooves on the opening ring and the air inlet grooves between the nozzle blades determines the opening size of the nozzle assembly.
Further, a gap is designed between the conical surface of the opening ring and the circumferential side surface of the nozzle vane, and the preferable gap range is 0.2-1 mm.
Further, a shifting fork is arranged on one axial side of the opening ring, the shifting fork shifts the opening ring to rotate at the position, and the opening of the nozzle assembly is adjusted.
Further, the shifting fork can be driven by an electric actuator or a pneumatic actuator in various driving modes.
Further, the preferred angle of inclination of the circumferential side taper of the nozzle vanes ranges from a = 10 ° to 40 °.
Further, the cover plate and the blades are fixed through the locating pins or assembled together in other non-fixed connection modes.
The invention can obtain the following technical effects:
1. the number of parts is small, the structure is simple, and the cost of parts and assembly is greatly reduced;
2. the pneumatic performance can be further improved, and the efficiency is improved.
The conception, specific structure, and technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, features, and effects of the present invention.
Drawings
FIG. 1 is a schematic view of a nozzle ring with a cylindrical circumferential side of nozzle vanes;
FIG. 2 is an exploded view of a tapered variable nozzle assembly according to a preferred embodiment of the present invention;
FIG. 3 is a schematic view of a nozzle ring with a tapered circumferential side of nozzle vanes in accordance with a preferred embodiment of the present invention;
FIG. 4 is a schematic view of a preferred embodiment of the invention in which the opening ring is tapered;
FIG. 5 is a schematic view of a conical variable nozzle assembly installation of a preferred embodiment of the present invention;
FIG. 6 is an enlarged partial view of a tapered variable nozzle assembly in accordance with a preferred embodiment of the present invention.
Detailed Description
The following description of the preferred embodiments of the present invention refers to the accompanying drawings, which make the technical contents thereof more clear and easy to understand. The present invention may be embodied in many different forms of embodiments and the scope of the present invention is not limited to only the embodiments described herein.
In the drawings, like structural elements are referred to by like reference numerals and components having similar structure or function are referred to by like reference numerals. The dimensions and thickness of each component shown in the drawings are arbitrarily shown, and the present invention is not limited to the dimensions and thickness of each component. The thickness of the components is exaggerated in some places in the drawings for clarity of illustration.
As shown in fig. 1, the circumferential side of the nozzle vanes of the nozzle ring of the prior art is cylindrical.
As shown in fig. 2, the first embodiment of the present invention includes a positioning pin 1, a cover plate 2, an opening ring 3, and a nozzle ring 4, and as shown in fig. 3, the nozzle ring 4 includes a base plate 41, an air intake groove 42, and nozzle vanes 43, and the circumferential side surfaces of the nozzle vanes 43 are designed to be tapered. The nozzle ring 4 is of a substantially circular ring-shaped structure, a plurality of nozzle vanes 43 are located in a circumferential array on one side of the nozzle ring 4, and the nozzle vanes 43 are part of the nozzle ring 4, the nozzle vanes 43 being integral with the nozzle ring 4. The angle of the nozzle vanes 43 is fixed and not adjustable, and the opening portion between adjacent vanes, i.e., the air intake groove, is used to guide the exhaust gas to the turbine, and the angle of the nozzle vanes 43 is approximately equal to the optimum efficiency incident angle.
As shown in fig. 4, the opening ring 3 is in a ring structure, the diameter size is slightly larger than that of the nozzle and 4, and a gap is reserved between the opening ring 3 and the nozzle ring 4 so as to prevent the clamping stagnation of the opening ring and the nozzle ring caused by high temperature. The opening ring 3 is circumferentially provided with a plurality of opening grooves called opening grooves 32, the number of which is identical to that of the nozzle vanes 43, the circumferential width of the opening grooves 32 is approximately equal to that of the air inlet grooves 42 between the nozzle vanes, and the height of the opening grooves 32 is equal to that of the nozzle vanes 43. The area of overlap of the opening slots 32 on the opening ring 3 with the inlet slots 42 between the nozzle vanes 43 determines the opening size of the nozzle assembly. A shifting fork 33 is designed on one axial side of the opening ring 3, and the shifting fork 33 shifts the opening ring 3 to rotate at the position, namely, the opening size is adjusted; the shifting fork is driven by an electric control actuator.
As shown in fig. 6, the inclination angle α=10° of the circumferential side taper of the nozzle vane 43. The cover plate 2 is connected with the nozzle ring 4 through the positioning pins 1.
FIG. 5 is a tapered variable nozzle assembly with components of a first embodiment of the invention mounted together.
The second embodiment of the present invention differs from the first embodiment in that the inclination angle of the circumferential side taper of the nozzle vanes 43 is different. In particular as described below.
As shown in fig. 2, the second embodiment of the present invention includes a positioning pin 1, a cover plate 2, an opening ring 3, and a nozzle ring 4, and as shown in fig. 3, the nozzle ring 4 includes a base plate 41, an air intake groove 42, and nozzle vanes 43, and the circumferential side surfaces of the nozzle vanes 43 are designed to be tapered. The nozzle ring 4 is of a substantially circular ring-shaped structure, a plurality of nozzle vanes 43 are located in a circumferential array on one side of the nozzle ring 4, and the nozzle vanes 43 are part of the nozzle ring 4, the nozzle vanes 43 being integral with the nozzle ring 4. The angle of the nozzle vanes 43 is fixed and not adjustable, and the opening portion between adjacent vanes, i.e., the air intake groove, is used to guide the exhaust gas to the turbine, and the angle of the nozzle vanes 43 is approximately equal to the optimum efficiency incident angle.
As shown in fig. 4, the opening ring 3 is in a ring structure, the diameter size is slightly larger than that of the nozzle and 4, and a gap is reserved between the opening ring 3 and the nozzle ring 4 so as to prevent the clamping stagnation of the opening ring and the nozzle ring caused by high temperature. The opening ring 3 is circumferentially provided with a plurality of opening grooves called opening grooves 32, the number of which is identical to that of the nozzle vanes 43, the circumferential width of the opening grooves 32 is approximately equal to that of the air inlet grooves 42 between the nozzle vanes, and the height of the opening grooves 32 is equal to that of the nozzle vanes 43. The area of overlap of the opening slots 32 on the opening ring 3 with the inlet slots 42 between the nozzle vanes 43 determines the opening size of the nozzle assembly. A shifting fork 33 is designed on one axial side of the opening ring 3, and the shifting fork 33 shifts the opening ring 3 to rotate at the position, namely, the opening size is adjusted; the shifting fork is driven by an electric control actuator.
As shown in fig. 6, the inclination angle α=40° of the circumferential side taper of the nozzle vane 43. The cover plate 2 is connected with the nozzle ring 4 through the positioning pins 1.
The foregoing describes in detail preferred embodiments of the present invention. It should be understood that numerous modifications and variations can be made in accordance with the concepts of the invention without requiring creative effort by one of ordinary skill in the art. Therefore, all technical solutions which can be obtained by logic analysis, reasoning or limited experiments based on the prior art by the person skilled in the art according to the inventive concept shall be within the scope of protection defined by the claims.
Claims (7)
1. The conical variable nozzle assembly of the turbocharger is characterized by comprising a positioning pin, a cover plate, an opening ring and a nozzle ring, wherein the nozzle ring comprises a base plate, nozzle blades and an air inlet groove, the cover plate and the nozzle blades are fixedly connected through the positioning pin, the nozzle ring is in a circular ring shape, a plurality of nozzle blades are arranged on one side surface of the nozzle ring in a circumferential uniform array, and the circumferential side surface of the nozzle blades is designed to be conical; the opening ring is annular, is positioned at the outer side of the nozzle ring and controls the opening of the nozzle;
the nozzle vanes are part of the nozzle ring, the nozzle vanes are integrated with the nozzle ring, and the angle of the nozzle vanes is not adjustable;
the nozzle vane angle is fixed to an optimal efficiency incident angle;
the opening ring is designed into an annular shape with the same taper as the circumferential side surface of the nozzle vane.
2. The turbocharger cone-shaped variable nozzle assembly according to claim 1, wherein the aperture ring diameter is slightly larger than the nozzle ring vanes, the aperture ring is circumferentially and uniformly provided with a plurality of aperture grooves, the number of aperture grooves is equal to the number of nozzle vanes, the circumferential width of the aperture grooves is equal to the width of the air inlet grooves between the nozzle vanes, and the height of the aperture grooves is equal to the height of the nozzle vanes.
3. The turbocharger cone variable nozzle assembly according to claim 1, wherein a gap is designed between the opening ring conical surface and the circumferential side surface of the nozzle vane, and the gap ranges from 0.2 mm to 1mm.
4. The turbocharger cone-shaped variable nozzle assembly according to claim 1, wherein a shifting fork is arranged on one axial side of the opening ring, and the shifting fork shifts the opening ring to rotate at a position on one axial side of the opening ring, so that the opening degree of the nozzle assembly is adjusted.
5. The turbocharger cone variable nozzle assembly according to claim 4, wherein said fork is driven by an electrically controlled actuator.
6. The turbocharger cone variable nozzle assembly according to claim 4, wherein said fork is driven by a pneumatic actuator.
7. The turbocharger cone variable nozzle assembly according to claim 1, wherein the nozzle vane circumferential side taper angle ranges from α = 10 ° to 40 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509263.3A CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509263.3A CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
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| Publication Number | Publication Date |
|---|---|
| CN108487941A CN108487941A (en) | 2018-09-04 |
| CN108487941B true CN108487941B (en) | 2024-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810509263.3A Active CN108487941B (en) | 2018-05-24 | 2018-05-24 | Turbocharger conical variable nozzle assembly |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111156052B (en) * | 2020-01-03 | 2021-07-09 | 清华大学 | Rotary Variable Nozzle Partially Intake Radial Turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3127909A (en) * | 1962-07-18 | 1964-04-07 | Honeywell Regulator Co | Rotary gate valve |
| CN103958837A (en) * | 2011-12-01 | 2014-07-30 | Ihi供应系统国际有限责任公司 | Fluid energy machine, in particular for exhaust-gas turbocharger, with obliquely arranged rotatable guide element |
| CN105927290A (en) * | 2016-06-29 | 2016-09-07 | 江苏毅合捷汽车科技股份有限公司 | Variable-section nozzle assembly for turbocharger |
| CN208416620U (en) * | 2018-05-24 | 2019-01-22 | 奕森科技（上海）有限公司 | A kind of turbocharger taper variable-nozzle assembly |
-
2018
- 2018-05-24 CN CN201810509263.3A patent/CN108487941B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3127909A (en) * | 1962-07-18 | 1964-04-07 | Honeywell Regulator Co | Rotary gate valve |
| CN103958837A (en) * | 2011-12-01 | 2014-07-30 | Ihi供应系统国际有限责任公司 | Fluid energy machine, in particular for exhaust-gas turbocharger, with obliquely arranged rotatable guide element |
| CN105927290A (en) * | 2016-06-29 | 2016-09-07 | 江苏毅合捷汽车科技股份有限公司 | Variable-section nozzle assembly for turbocharger |
| CN208416620U (en) * | 2018-05-24 | 2019-01-22 | 奕森科技（上海）有限公司 | A kind of turbocharger taper variable-nozzle assembly |
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| Publication number | Publication date |
|---|---|
| CN108487941A (en) | 2018-09-04 |
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Effective date of registration: 20210330 Address after: 215506 no.1150, Southeast Avenue, Southeast street, Changshu City, Suzhou City, Jiangsu Province Applicant after: Eason Technology (Jiangsu) Co.,Ltd. Address before: 201703 1st floor, building 1, 518 Songhui Road, Qingpu District, Shanghai Applicant before: ISEM TECHNOLOGIES (SHANGHAI) Co. |
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