CN117248992A - Turbocharger with improved nozzle ring positioning structure - Google Patents
Turbocharger with improved nozzle ring positioning structure Download PDFInfo
- Publication number
- CN117248992A CN117248992A CN202311539134.6A CN202311539134A CN117248992A CN 117248992 A CN117248992 A CN 117248992A CN 202311539134 A CN202311539134 A CN 202311539134A CN 117248992 A CN117248992 A CN 117248992A
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- Prior art keywords
- nozzle ring
- positioning
- ring
- section
- turbocharger
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- 238000003756 stirring Methods 0.000 claims abstract description 3
- 238000006073 displacement reaction Methods 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims description 3
- 238000004939 coking Methods 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
Classifications
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- 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
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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
- 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
- F01D17/165—Final 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The turbocharger with the improved nozzle ring positioning structure comprises a bearing body, wherein a shafting component is arranged in the bearing body, a compressor component and a turbine component are respectively arranged on two sides of the bearing body, a nozzle ring component is arranged between the turbine component and the bearing body, the nozzle ring component comprises a nozzle ring, a blade unit is arranged on the nozzle ring, and the blade unit is driven to rotate through a stirring piece and a corresponding driving structure; the inner surface of the nozzle ring is not contacted with the bearing body and is provided with a gap; the turbine assembly comprises a shell, an assembling table extends out of the position, facing the nozzle ring, of the shell, the outer surface of the nozzle ring is assembled on the assembling table through a positioning ring, the positioning ring is assembled on the assembling table through a step structure, and an elastic hook-shaped part is arranged on the positioning ring. In the application, the axial positioning and the radial positioning of the nozzle ring can be completed through one structure, and the structure is simple; meanwhile, the heat transfer path is cut off, and the efficient and stable operation of the supercharger is ensured.
Description
Technical Field
The invention belongs to the technical field of turbochargers, and particularly relates to a turbocharger with an improved nozzle ring positioning structure.
Background
The turbocharger is a mechanical device for driving an impeller to rotate through exhaust gas discharged by an automobile, so that the air inflow of an engine is increased, the air inflow of the automobile engine can be obviously increased, and the turbocharger is widely applied to middle-high-end automobiles at present.
An adjustable vane turbocharger is one of the superchargers, wherein a nozzle ring is arranged, and a vane structure is arranged on the nozzle ring. In conventional assembly arrangements, radial positioning of the nozzle ring is typically accomplished by direct contact of the inner surface thereof with the bearing body, or by addition of a U-ring or similar structure between the nozzle ring and the bearing body; the axial positioning of the nozzle ring is typically achieved by axially mounting a belleville spring between the bearing body and the nozzle ring, with the other side positioned by the nozzle ring being placed on the volute or the rear cover and distance pin being mounted directly on the volute outlet end face.
Both the above radial positioning and axial positioning have the disadvantage of contacting the bearing body, which makes the turbine end heat transfer paths numerous, easily resulting in: (1) The risk of coking of the lubricating oil of the bearing body is high, and the rotating shaft system is easy to fail; (2) After heat is transferred to the compressor end, the performance of the compressor is seriously affected.
Therefore, if the positioning structure of the nozzle ring can be further improved, and the heat transfer path is reduced, the risk of rotor failure can be effectively reduced, and the influence on the performance of the compressor can be reduced. The present application has been further studied and improved in this direction.
Disclosure of Invention
In order to solve the defects existing in the prior art, the application provides the turbocharger with the improved nozzle ring positioning structure, and the axial positioning and the radial positioning of the nozzle ring can be completed through only one structure, so that the structure is simple; meanwhile, the contact with the bearing body is eliminated, the heat transfer path is effectively cut off, and the efficient and stable operation of the supercharger is ensured.
The technical scheme of the invention is as follows.
The turbocharger with the improved nozzle ring positioning structure comprises a bearing body, wherein a shafting component is arranged in the bearing body, a gas compressor component and a turbine component are respectively arranged on two sides of the bearing body, a nozzle ring component is arranged between the turbine component and the bearing body, the nozzle ring component comprises a nozzle ring, a blade unit is arranged on the nozzle ring, and the blade unit is driven to rotate through a stirring piece and a corresponding driving structure; the inner surface of the nozzle ring is not contacted with the bearing body and is provided with a gap; the turbine assembly comprises a shell, an assembling table is extended from the position of the shell, which faces the nozzle ring, the outer surface of the nozzle ring is assembled on the assembling table through a positioning ring, the positioning ring is assembled on the assembling table through a step structure, and an elastic hook-shaped part is arranged on the positioning ring and abuts against the nozzle ring and applies elastic pretightening force on the nozzle ring in the axial direction.
At present, in the traditional turbocharger in the prior art, the positioning of the nozzle ring is realized through two structures, namely, the radial positioning is performed by propping the inner surface of the nozzle ring on the bearing body, and the axial positioning is realized through the structures such as the belleville springs, the distance pins and the like. The two positioning structures are matched to jointly realize radial and axial positioning of the nozzle ring, so that the positioning structure is complex, and the accumulated error of the positioning precision is large; moreover, the positioning structure enables the nozzle ring to be in contact with the bearing body, heat can be transferred to the bearing body, the risk of lubricating oil coking is high, the rotating shaft system is easy to fail, and the service life of the supercharger main body is influenced.
In this application, changed the traditional locate mode that has long been used always in the trade for a long time, adopted a new location structure, through a locating ring of setting on the nozzle ring surface, assemble through the stable assembly of step structure between the assembly stand with the turbine casing, can realize the location of nozzle ring well, through the elasticity of hook portion applys on the nozzle ring on it, can counter the high-pressure air pressure of turbine end, have fine elastic support power. The positioning mode is simple in structure, and the way of heat transfer from the nozzle ring to the bearing body is directly cut off without depending on contact with the bearing body, so that the risk of failure of a rotating shaft system is obviously reduced, and the service life of the supercharger is prolonged.
In a preferred embodiment, the retaining ring has at least one radially inner surface thereon which directly or indirectly abuts a radially outer surface or part of a radially outer surface of the nozzle ring for limiting radial displacement of the nozzle ring.
In a preferred embodiment, the retaining ring has a hook thereon which abuts an axial surface of the nozzle ring for limiting axial displacement of the nozzle ring in one direction.
In a preferred embodiment, the positioning ring has a stepped structure, the stepped structure comprises a first positioning ring section, a second positioning ring section and a third positioning ring section which are sequentially connected, the first positioning ring section and the third positioning ring section have surfaces in the axial direction, and the second positioning ring section has surfaces in the radial direction; the outer side of the first section of the positioning ring is provided with an inclined section and forms a hook-shaped part; the inner surface of the first section of the positioning ring is propped against the nozzle ring and positioned in the radial direction; the end of the inclined section is propped against the nozzle ring and axially positioned. In the structure, the first section of the positioning ring is propped against the radial outer surface of the nozzle ring to play a radial positioning function, the end part of the inclined section is propped against the axial end surface of one side of the outer edge of the nozzle ring, and meanwhile, the axial end surface of the other side of the outer edge of the nozzle ring can be propped against the assembly table directly or indirectly, so that the axial positioning of the nozzle ring is realized, the structure is simple, and the assembly is compact.
In a preferred embodiment, the outer surface of the nozzle ring has a stepped shape including a first stepped surface, a second stepped surface, a third stepped surface, a fourth stepped surface, and a fifth stepped surface connected in sequence; the first step surface, the third step surface and the fifth step surface are in axial directions, and the second step surface and the fourth step surface are in radial directions; the inner surface of the first section of the positioning ring is propped against the third step surface; the end part of the inclined section is propped against the second step surface. In the structure, the outer side surface structure of the nozzle ring is matched with the stepped structure of the positioning ring, so that the nozzle ring can be assembled better, and the strength is high after assembly.
In a preferred embodiment, an arc transition section is arranged between the first step surface and the second step surface, so that the end part of the inclined section can slide in a small range conveniently, and the clamping is avoided.
In a preferred embodiment, the inner surface of the assembly table is provided with a concave structure, and the concave structure comprises a first concave surface, a second concave surface, a third concave surface, a fourth concave surface and a fifth concave surface which are sequentially connected; the first inner concave surface, the third inner concave surface and the fifth inner concave surface are in axial directions, and the second inner concave surface and the fourth inner concave surface are in radial directions; the first inner concave surface is propped against the outer surface of the first section of the positioning ring; the second inner concave surface is propped against the outer surface of the second section of the positioning ring; the second inner concave surface, the third inner concave surface and the fourth inner concave surface jointly form a concave cavity, and the third section of the positioning ring is arranged in the concave cavity; the fourth concave surface is propped against the fourth step surface. In the structure, the inner surface of the assembly table is matched with the outer surface structure of the nozzle ring and the stepped structure of the positioning ring, when the assembly is carried out, the positioning ring is clamped on the inner surface of the assembly table, the pre-positioning is realized by means of the second inner concave surface and the second section of the positioning ring, then the nozzle ring is clamped into the positioning ring, the inclined section is pressed and deformed firstly, and then the inclined section is sprung and spread after being assembled in place, so that the assembly of the whole structure is realized.
In a preferred embodiment, the fifth concave surface is disposed opposite to the fifth step surface with a gap therebetween, so as to reduce heat transfer.
In a preferred embodiment, the third segment of the retaining ring is disposed within the cavity and does not contact the inner wall of the cavity, reducing heat transfer.
In a preferred embodiment, the third section of the retaining ring further has an extension at its end that abuts between the fourth concave surface and the fourth step surface to form a more stable assembly while spacing the turbine housing from the nozzle ring to reduce heat transfer.
Compared with the prior art, the invention has the following beneficial effects: the turbocharger with the improved nozzle ring positioning structure is simple in structure, and the axial positioning and the radial positioning of the nozzle ring can be completed through one structure; meanwhile, the contact with the bearing body is eliminated, the heat transfer path is effectively cut off, and the efficient and stable operation of the supercharger is ensured.
Drawings
Fig. 1 is a perspective view of a turbocharger of the present application.
Fig. 2 is a cross-sectional view of a turbocharger of the present application.
Fig. 3 is an enlarged view of area a in fig. 2.
Fig. 4 is an enlarged view of the area A1 in fig. 3.
Fig. 5 is a perspective view of a retaining ring in one embodiment of the present application.
Fig. 6 is a cross-sectional view of a retaining ring in one embodiment of the present application.
Fig. 7 is a perspective view of a nozzle ring in the present application.
Fig. 8 is a partial structural sectional view of the nozzle ring in the present application.
Fig. 9 is a cross-sectional view of a retaining ring in another embodiment of the present application.
The following is a description of the marks in the drawings of the specification.
1-compressor assembly.
2-a turbine assembly; 21-an assembly station; 21 a-a first concave surface; 21 b-a second concave surface; 21 c-a third concave surface; 21 d-a fourth concave surface; 21 e-a fifth concave inner surface.
3-a bearing body; 33-turbine wheel.
4-a nozzle ring; 41 a-a first step surface; 41 b-a second step surface; 41 c-a third step surface; 41 d-a fourth step surface; 41 e-fifth step surface; 42-toggle; 45-void; 48-blade unit.
6-positioning rings; 61-oblique section; 61 a-positioning the first segment of the ring; 61 b-a second segment of the retaining ring; 61 c-a third segment of the retaining ring; 61 d-extension.
Detailed Description
The invention is described in further detail below with reference to the drawings and the detailed description.
In the following embodiments, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout, and the embodiments described below by referring to the drawings are exemplary only for explaining the present invention and are not to be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms: the directions of the center, the longitudinal, the lateral, the length, the width, the thickness, the upper, the lower, the front, the rear, the left, the right, the vertical, the horizontal, the top, the bottom, the inner, the outer, the clockwise, the counterclockwise, etc. indicate the directions or the positional relationship based on the directions or the positional relationship shown in the drawings, are merely for convenience of description and simplification of the description, and therefore, should not be construed as limiting the present invention. Furthermore, the term: first, second, etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of features shown. In the description of the present invention, unless explicitly specified and defined otherwise, the terms: mounting, connecting, etc. are to be construed broadly and the specific meaning of the terms herein described will be understood by those skilled in the art in view of the specific circumstances.
In the prior art, the positioning of the nozzle ring in the turbocharger has long been achieved by two structures: the first structure is to support the inner surface of the nozzle ring to the bearing body for radial positioning, and the second structure is to realize axial positioning through disc springs, distance pins and other structures. The positioning structure is complex, and the positioning precision accumulated error is large; and in the positioning structure, heat can be easily transferred to the bearing body, so that the risk of coking of lubricating oil is high, a rotating shaft system is easy to fail, and the service life of the supercharger main body is influenced.
Therefore, in the application, the traditional positioning mode which is used for a long time in the industry is changed, and a new positioning structure is adopted, and the specific technical scheme is as follows.
Referring to fig. 1, a turbocharger with an improved nozzle ring positioning structure in the present application includes a bearing body 3, a shafting assembly is disposed in the bearing body 3, and two sides of the bearing body 3 are respectively provided with a compressor assembly 1 and a turbine assembly 2.
Specifically, as can be seen from fig. 2 to fig. 4, a nozzle ring assembly is disposed between the turbine assembly 2 and the bearing body 3, the nozzle ring assembly includes a nozzle ring 4, a vane unit 48 is disposed on the nozzle ring 4, and the vane unit 48 is driven to rotate by a toggle member 42 and a corresponding driving structure; the inner surface of the nozzle ring 4 is not contacted with the bearing body 3 and is provided with a gap 45; the turbine assembly 2 comprises a shell, a mounting table 21 extends out of the shell towards the position of the nozzle ring 4, the outer surface of the nozzle ring 4 is mounted on the mounting table 21 through a positioning ring 6, the positioning ring 6 is mounted on the mounting table 21 through a step structure, and the positioning ring 6 is provided with an elastic hook part, and the hook part abuts against the nozzle ring 4 and exerts elastic pretightening force on the nozzle ring 4 in the axial direction.
In the above structure, the positioning ring has at least one radially inner surface thereon, which directly or indirectly abuts against a radially outer surface or a part of a radially outer surface of the nozzle ring for limiting radial displacement of the nozzle ring. The positioning ring is provided with a hook part which is propped against the axial surface of the nozzle ring to limit the axial displacement of the nozzle ring in one direction, and can resist the high-pressure air pressure of the turbine end, and has good elastic supporting force, wherein the limit of the axial displacement of the nozzle ring 4 in the other direction can be realized through the structure of propping against the volute, or other propped structures.
Specifically, as can be seen from fig. 5 and 6, in the present application, the positioning ring 6 has a stepped structure having a first positioning ring section 61a, a second positioning ring section 61b, and a third positioning ring section 61c connected in this order, the first positioning ring section 61a and the third positioning ring section 61c having surfaces in the axial direction, and the second positioning ring section 61b having surfaces in the radial direction; the outer side of the first section 61a of the positioning ring is provided with an inclined section 61 and forms a hook-shaped part; the inner surface of the first positioning ring section 61a is propped against the nozzle ring 4 and positioned in the radial direction; the end of the inclined segment 61 is abutted against the nozzle ring 4 and axially positioned. In this structure, the first segment 61a of the positioning ring is abutted against the radial outer surface of the nozzle ring 4 to perform a radial positioning function, the end of the inclined segment 61 is abutted against the axial end surface of one side of the outer edge of the nozzle ring 4, and at the same time, the axial end surface of the other side of the outer edge of the nozzle ring 4 can be directly or indirectly abutted against the assembly table 21 to perform axial positioning of the nozzle ring 4, and the structure is simple and the assembly is compact.
As can be seen from fig. 7 and 8, in the present application, the outer surface of the nozzle ring 4 has a stepped shape including a first stepped surface 41a, a second stepped surface 41b, a third stepped surface 41c, a fourth stepped surface 41d, and a fifth stepped surface 41e, which are sequentially connected; the first step surface 41a, the third step surface 41c, and the fifth step surface 41e are axial directions, and the second step surface 41b and the fourth step surface 41d are radial directions; the inner surface of the first section 61a of the positioning ring abuts against the third step surface 41 c; the end of the inclined section 61 abuts against the second step surface 41 b. In this structure, the outer surface structure of the nozzle ring 4 is matched with the stepped structure of the positioning ring 6, so that the assembly can be better performed, and the strength after the assembly is high.
In a further scheme, an arc transition section is arranged between the first step surface 41a and the second step surface 41b, so that the end part of the inclined section 61 can slide in a small range conveniently, and the locking is avoided.
In addition, as can be seen from fig. 4, the inner surface of the assembly table 21 has a concave structure, and the concave structure includes a first concave surface 21a, a second concave surface 21b, a third concave surface 21c, a fourth concave surface 21d, and a fifth concave surface 21e, which are sequentially connected; the first inner concave surface 21a, the third inner concave surface 21c and the fifth inner concave surface 21e are in axial direction, and the second inner concave surface 21b and the fourth inner concave surface 21d are in radial direction; the first concave inner surface 21a is abutted against the outer surface of the first section 61a of the positioning ring; the second concave surface 21b abuts against the outer surface of the second segment 61b of the retaining ring; the second inner concave surface 21b, the third inner concave surface 21c and the fourth inner concave surface 21d together form a concave cavity, and the third section 61c of the positioning ring is arranged in the concave cavity; the fourth concave surface 21d abuts against the fourth step surface 41 d. In this structure, the inner surface of the mounting table 21 is matched with the outer surface structure of the nozzle ring 4 and the stepped structure of the positioning ring 6.
In the above-described structure according to the first embodiment, in a preferred further structure, the fifth concave surface 21e is disposed opposite to the fifth step surface 41e, and a gap is formed between the two surfaces, so as to reduce heat transfer. The third segment 61c of the retaining ring is disposed within the cavity and does not contact the inner wall of the cavity, reducing heat transfer.
Fig. 9 shows the structure of the positioning ring in the second embodiment of the present application, as can be seen in fig. 9, the end of the third section 61c of the positioning ring further has an extension section 61d, and the extension section 61d abuts between the fourth concave surface 21d and the fourth step surface 41d, so as to form a more stable assembly structure, and space the turbine housing and the nozzle ring, thereby reducing heat transfer.
The turbocharger with the innovative positioning structure is described above, when the turbocharger is assembled, the positioning ring 6 is clamped on the inner surface of the assembly table 21, the pre-positioning is realized by means of the second inner concave surface 21b and the second section 61b of the positioning ring, then the nozzle ring 4 is clamped into the positioning ring 6, the inclined section 61 is pressed and deformed firstly, and then the inclined section 61 is sprung and spread after being assembled in place, so that the assembly of the integral structure is realized, and the axial and radial dual positioning of the nozzle ring is realized.
As can be seen from the above description, in the present application, the axial positioning and radial positioning of the nozzle ring 4 can be well achieved by means of a positioning ring 6 provided on the outer surface of the nozzle ring 4, cooperating with the mounting table 21 of the turbine housing. The positioning mode is simple in structure, and the way of heat transfer from the nozzle ring 4 to the bearing body 3 is directly cut off without depending on contact with the bearing body 3, so that the risk of failure of a rotating shaft system is obviously reduced, the service life of the supercharger is prolonged, and the efficient and stable operation of the supercharger is ensured.
The scope of the present invention includes, but is not limited to, the above embodiments, and any alterations, modifications, and improvements made by those skilled in the art are intended to fall within the scope of the invention.
Claims (10)
1. The utility model provides a turbocharger with improved generation nozzle ring location structure, includes bearing body (3), be equipped with shafting subassembly in bearing body (3), the both sides of bearing body (3) are equipped with compressor subassembly (1) and turbine subassembly (2) respectively, turbine subassembly (2) with be equipped with nozzle ring subassembly between bearing body (3), its characterized in that:
the nozzle ring assembly comprises a nozzle ring (4), wherein a blade unit (48) is arranged on the nozzle ring (4), and the blade unit (48) is driven to rotate through a stirring piece (42) and a corresponding driving structure;
the inner surface of the nozzle ring (4) is not contacted with the bearing body (3) and is provided with a gap (45);
the turbine assembly (2) comprises a shell, an assembling table (21) extends out of the shell towards the position of the nozzle ring (4), a positioning ring (6) is assembled on the assembling table (21) through a step structure, and a hook-shaped part with elasticity is arranged on the positioning ring (6), and the hook-shaped part abuts against the nozzle ring (4) and exerts elastic pretightening force on the nozzle ring (4) in the axial direction.
2. A turbocharger with improved nozzle ring positioning according to claim 1, wherein the positioning ring (6) has at least one radially inner surface directly or indirectly abutting against a radially outer surface or part of a radially outer surface of the nozzle ring (4) for defining the radial displacement of the nozzle ring (4).
3. A turbocharger with improved nozzle ring positioning structure according to claim 1, wherein the hook portion abuts on an axial surface of the nozzle ring (4) for limiting axial displacement of the nozzle ring (4) in one direction.
4. A turbocharger with improved nozzle ring positioning structure according to claim 3, characterized in that the stepped structure of the positioning ring (6) is part of the stepped structure with a positioning ring first section (61 a), a positioning ring second section (61 b), a positioning ring third section (61 c) connected in sequence, the positioning ring first section (61 a) and the positioning ring third section (61 c) having axially directed surfaces, the positioning ring second section (61 b) having radially directed surfaces;
the outer side of the first section (61 a) of the positioning ring is provided with an inclined section (61) and forms a hook-shaped part;
the inner surface of the first section (61 a) of the positioning ring is propped against the nozzle ring (4) and positioned in the radial direction;
the end of the inclined section (61) is propped against the nozzle ring (4) and axially positioned.
5. The turbocharger with the improved nozzle ring positioning structure according to claim 4, wherein the step shape of the outer surface of the nozzle ring (4) is a part of the step structure, and the step shape comprises a first step surface (41 a), a second step surface (41 b), a third step surface (41 c), a fourth step surface (41 d) and a fifth step surface (41 e) which are sequentially connected;
the first step surface (41 a), the third step surface (41 c) and the fifth step surface (41 e) are in the axial direction, and the second step surface (41 b) and the fourth step surface (41 d) are in the radial direction;
the inner surface of the first section (61 a) of the positioning ring is propped against the third step surface (41 c);
the end of the inclined section (61) is abutted against the second step surface (41 b).
6. A turbocharger with improved nozzle ring positioning structure according to claim 5, wherein the first step surface (41 a) and the second step surface (41 b) have a circular arc transition therebetween.
7. The turbocharger with the improved nozzle ring positioning structure according to claim 6, wherein the concave structure of the inner surface of the assembly table (21) is a part of the step structure, and the concave structure comprises a first concave surface (21 a), a second concave surface (21 b), a third concave surface (21 c), a fourth concave surface (21 d) and a fifth concave surface (21 e) which are sequentially connected;
the first inner concave surface (21 a), the third inner concave surface (21 c) and the fifth inner concave surface (21 e) are in axial directions, and the second inner concave surface (21 b) and the fourth inner concave surface (21 d) are in radial directions;
the first concave surface (21 a) is abutted against the outer surface of the first section (61 a) of the positioning ring;
the second concave surface (21 b) is abutted against the outer surface of the second section (61 b) of the positioning ring;
the second inner concave surface (21 b), the third inner concave surface (21 c) and the fourth inner concave surface (21 d) jointly form a concave cavity, and the third section (61 c) of the positioning ring is arranged in the concave cavity;
the fourth concave surface (21 d) is abutted against the fourth step surface (41 d).
8. A turbocharger with improved nozzle ring positioning structure according to claim 7, wherein the fifth concave inner surface (21 e) is disposed opposite the fifth step surface (41 e) with a gap therebetween.
9. A turbocharger with improved nozzle ring positioning according to claim 8, wherein the third segment (61 c) of the positioning ring is disposed in the cavity and is not in contact with the inner wall of the cavity.
10. The turbocharger with improved nozzle ring positioning structure of claim 8, wherein the end of the third segment (61 c) of the positioning ring further has an extension (61 d), the extension (61 d) abutting between the fourth concave inner surface (21 d) and the fourth step surface (41 d).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311539134.6A CN117248992B (en) | 2023-11-17 | 2023-11-17 | Turbocharger with improved nozzle ring positioning structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311539134.6A CN117248992B (en) | 2023-11-17 | 2023-11-17 | Turbocharger with improved nozzle ring positioning structure |
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| Publication Number | Publication Date |
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| CN117248992A true CN117248992A (en) | 2023-12-19 |
| CN117248992B CN117248992B (en) | 2024-01-26 |
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| CN202311539134.6A Active CN117248992B (en) | 2023-11-17 | 2023-11-17 | Turbocharger with improved nozzle ring positioning structure |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013194546A (en) * | 2012-03-16 | 2013-09-30 | Ihi Corp | Variable nozzle unit and variable capacity type supercharger |
| CN106715863A (en) * | 2014-10-02 | 2017-05-24 | 株式会社Ihi | Variable nozzle unit and variable-capacity supercharger |
| WO2018037970A1 (en) * | 2016-08-24 | 2018-03-01 | 株式会社Ihi | Variable displacement supercharger |
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| CN112867852A (en) * | 2018-12-04 | 2021-05-28 | 株式会社Ihi | Variable capacity supercharger |
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| US20220220864A1 (en) * | 2019-10-30 | 2022-07-14 | Ihi Corporation | Cooling structure and turbocharger |
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| JP2013194546A (en) * | 2012-03-16 | 2013-09-30 | Ihi Corp | Variable nozzle unit and variable capacity type supercharger |
| CN106715863A (en) * | 2014-10-02 | 2017-05-24 | 株式会社Ihi | Variable nozzle unit and variable-capacity supercharger |
| WO2018037970A1 (en) * | 2016-08-24 | 2018-03-01 | 株式会社Ihi | Variable displacement supercharger |
| CN208763696U (en) * | 2018-08-27 | 2019-04-19 | 永能动力（北京）科技有限公司 | A kind of constructional element with spring of Gas Turbine first order nozzle |
| CN112867852A (en) * | 2018-12-04 | 2021-05-28 | 株式会社Ihi | Variable capacity supercharger |
| US20220220864A1 (en) * | 2019-10-30 | 2022-07-14 | Ihi Corporation | Cooling structure and turbocharger |
| JP2021165545A (en) * | 2020-04-08 | 2021-10-14 | 株式会社豊田自動織機 | Variable capacity type supercharger |
| CN215057604U (en) * | 2021-01-11 | 2021-12-07 | 蜂巢蔚领动力科技(江苏)有限公司 | Variable cross-section turbocharger without distance sleeve structure in nozzle ring |
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| CN117248992B (en) | 2024-01-26 |
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