CN106224013A - A kind of nozzle ring for turbocharger - Google Patents
A kind of nozzle ring for turbocharger Download PDFInfo
- Publication number
- CN106224013A CN106224013A CN201610741226.6A CN201610741226A CN106224013A CN 106224013 A CN106224013 A CN 106224013A CN 201610741226 A CN201610741226 A CN 201610741226A CN 106224013 A CN106224013 A CN 106224013A
- Authority
- CN
- China
- Prior art keywords
- disc
- mounting
- shifting
- mounting disc
- nozzle ring
- 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.)
- Granted
Links
Classifications
-
- 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
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a kind of nozzle ring for turbocharger, it includes a mounting disc, a shifting disc and multiple shift fork, and shifting disc is spindle rotationally arranged on the end face of mounting disc；Deviating from of shifting disc is provided with multiple mounting groove on the end face of mounting disc, multiple mounting grooves are spaced setting along the circumferential direction of shifting disc, and shift fork is arranged with mounting groove one_to_one corresponding, and one end of each shift fork is all spindle rotationally arranged in corresponding mounting groove；Being provided with a convex annular edge on the end face of the close mounting disc of shifting disc, convex annular is nested with on the perisporium of mounting disc along rotating.The present invention need not arrange roller and roller pin so that nozzle ring simple in construction, and shifting disc is fixing firm.
Description
Technical field
The present invention relates to a kind of nozzle ring for turbocharger.
Background technology
Nozzle ring is arranged in turbocharger, increases to control turbine for the exhausted air quantity controlling to enter in turbine wheel
The rotating speed of depressor.Nozzle ring generally comprises a mounting disc, a shifting disc, multiple shift fork and multiple blade, and shifting disc is rotating
Being arranged on the end face of mounting disc, multiple shift forks are provided at circumferentially spaced on the end face of mounting disc, between multiple blade circumferences
On the other end being arranged on mounting disc, shift fork and blade one_to_one corresponding are arranged, one end of multiple shift forks the most mobilizable with
Shifting disc is connected, and the other end of multiple shift forks is all connected with corresponding blade by a bearing pin, and mounting disc is provided with use
In the installing hole through bearing pin, when shifting disc rotates, shifting disc drives shift fork to rotate, by bearing pin band movable vane when shift fork rotates
Sheet rotates, and can change blade angle, regulation flow area by the rotation of blade, thus regulate air inflow.
And as described in the patent document of the patent No. 200920064784.9, in current nozzle ring, in addition it is also necessary in peace
Arranging multiple roller on the end face of sabot, roller is rotating to be nested with on roller pin, and roller pin is fixed in mounting disc, rolling
Wheel is for carrying out location axially and radially to shifting disc, owing to needs arrange roller and roller pin so that nozzle ring structure is relatively
For complexity, and roller is nested with and is fixed on roller pin, when nozzle ring is given a shock, and fixing shakiness between roller and roller pin
Gu, roller shakes easily with respect to roller pin, so that position shifting disc built on the sand.
Summary of the invention
The technical problem to be solved is to provide a kind of nozzle ring for turbocharger, and it need not set
Put roller and roller pin so that nozzle ring simple in construction, and shifting disc is fixing firm.
For solve above-mentioned technical problem, the present invention provide the nozzle ring for turbocharger, it include a mounting disc,
One shifting disc and multiple shift fork, shifting disc is spindle rotationally arranged on the end face of mounting disc；
Deviating from of shifting disc is provided with multiple mounting groove on the end face of mounting disc, multiple mounting grooves are along the circumferential direction of shifting disc
Interval is arranged, and shift fork is arranged with mounting groove one_to_one corresponding, and one end of each shift fork is all spindle rotationally arranged in corresponding installation
In groove；
Being provided with a convex annular edge on the end face of the close mounting disc of shifting disc, convex annular is nested with in mounting disc along rotating
Perisporium on.
As preferably, the end face of the close shifting disc of described mounting disc is provided with an annular convex rib, annular convex rib
The end face of the close mounting disc with shifting disc offsets.
As preferably, described nozzle ring also includes a turbine lining and a bonnet, and turbine lining and bonnet may be contained within
The side deviating from shifting disc of mounting disc, bonnet is connected with mounting disc and leaves gap between bonnet and mounting disc, and turbine serves as a contrast
Set and the one-body molded setting of bonnet.
As preferably, the periphery wall of described turbine lining is provided with an annular groove, in annular groove, is provided with one
Piston ring.
After using above structure, the present invention compared with prior art, has the advantage that
The nozzle ring of the present invention, mounting disc is positioned along shifting disc carries out radial direction by convex annular, and shifting disc is pressed in by shift fork
In mounting disc, shifting disc is axially positioned by shift fork so that shifting disc is axially and radially located, it is not necessary to again by peace
Shifting disc is positioned by dress roller, compared to arranging roller on nozzle ring in prior art and shifting disc is entered by roller pin
Row location, structure is simplified, and when nozzle ring is given a shock, produces impact substantially without on mounting disc and shift fork, make
Obtain shifting disc location firm.
Accompanying drawing explanation
Fig. 1 is the structural representation of nozzle ring of the present invention；
Fig. 2 is the sectional exploded view of nozzle ring of the present invention.
Detailed description of the invention
With detailed description of the invention, the present invention is described in more detail below in conjunction with the accompanying drawings.
Shown in Fig. 1, Fig. 2, the present invention includes mounting disc 1, shifting disc 2, many for the nozzle ring of turbocharger
Individual shift fork 3, bonnet 402, turbine lining 401, multiple blade 501, multiple blade bearing pin 502, bolt 6 and a spacer sleeve
7, a piston ring 8, shifting disc 2 is annular, and shifting disc 2 is spindle rotationally arranged on the end face of mounting disc 1, shifting disc 2 and peace
Sabot 1 is coaxially set, and shifting disc 2 can be around own axis.
Being provided with multiple mounting groove 201 on the end face deviating from mounting disc 1 of shifting disc 2, multiple mounting grooves 201 are along stirring
The circumferential direction interval of dish 2 is arranged, and shift fork 3 is arranged with mounting groove 201 one_to_one corresponding, and shift fork 3 sets with blade 501 one_to_one corresponding
Putting, one end of each shift fork 3 is all spindle rotationally arranged in corresponding mounting groove 201, and the other end of each shift fork 3 all passes through
One blade bearing pin 502 is connected with corresponding blade 501, and mounting disc 1 is provided with for the installation through blade bearing pin 502
Hole, when shifting disc 2 rotates, shifting disc 2 drives shift fork 3 to rotate, by blade bearing pin 502 band moving vane 501 when shift fork 3 rotates
Rotate, blade angle, regulation flow area can be changed by the rotation of blade 501, thus regulate air inflow.
Being provided with a convex annular on the end face of the close mounting disc 1 of shifting disc 2 along 202, convex annular is rotating along 202
It is nested with on the perisporium of mounting disc 1, say, that mounting disc 1 carries out radially positioning along 202 pairs of shifting discs 2 by convex annular, and
Shifting disc 2 is pressed in mounting disc 1 by shift fork 3, and shifting disc 2 is axially positioned by shift fork 3 so that shifting disc 2 can around it certainly
Body axis rotates, and shifting disc 2 is positioned.
Be provided with an annular convex rib 101 on the end face of the close shifting disc 2 of described mounting disc 1, annular convex rib 101 with
The end face of the close mounting disc 1 of shifting disc 2 offsets, so, shifting disc 2 rotate time, shifting disc 2 and annular convex rib 101 phase
Contact, shifting disc 2 is less with annular convex rib 101 contact area so that when shifting disc 2 rotates, frictional force is less, it is simple to shifting disc
Rotation.
Described nozzle ring also includes that a turbine lining 401 and a bonnet 402, turbine lining 401 and bonnet 402 are respectively provided with
In the side deviating from shifting disc 2 of mounting disc 1, bonnet 402 is connected with mounting disc 1 and leaves between bonnet 402 and mounting disc 1
Gap, bonnet 402 is tabular, and bonnet 402 is paralleled with the end face deviating from shifting disc 2 of mounting disc 1, turbine lining 401
Setting one-body molded with bonnet 402, the two ends of bolt 6 are connected in bonnet 402 and mounting disc 1, and spacer sleeve 7 is fixing to be nested with
On bolt 6, spacer sleeve 7 between bonnet 402 and the end face deviating from shifting disc 2 of mounting disc 1, the two ends of spacer sleeve 7
Offseting with bonnet 402 and mounting disc 1 respectively, spacer sleeve 7 makes to have between bonnet 402 and mounting disc 1 gap, and blade 501 sets
Putting in the gap, turbine lining 401 is sleeve-shaped, and the periphery wall of turbine lining 401 is provided with an annular groove 403, ring
It is provided with a piston ring 8 in connected in star 403, so, when this nozzle ring is installed, turbine lining 401 is assembled turbocharger snail
On shell, turbocharger volute being provided with pilot hole, be provided with piston groove in pilot hole, turbine lining 401 is assembled to this
After in pilot hole, piston ring 8 is embedded into piston channel so that this nozzle ring firmly installs.
Below only apply preferably example to be made that explanation with regard to the present invention, but be not to be construed as the limit to claim
System, the structure of the present invention can have other to change, be not limited to said structure.In a word, all independent claims in the present invention
Protection domain in the various changes made the most within the scope of the present invention.
Claims (4)
1., for a nozzle ring for turbocharger, it includes a mounting disc (1), a shifting disc (2) and multiple shift fork (3),
Shifting disc (2) is spindle rotationally arranged on the end face of mounting disc (1), it is characterised in that:
Multiple mounting groove (201), multiple mounting grooves (201) edge it is provided with on the end face deviating from mounting disc (1) of shifting disc (2)
The circumferential direction interval of shifting disc (2) is arranged, and shift fork (3) is arranged with mounting groove (201) one_to_one corresponding, the one of each shift fork (3)
End is all spindle rotationally arranged in corresponding mounting groove (201)；
It is provided with a convex annular on the end face of the close mounting disc (1) of shifting disc (2) can turn along (202), convex annular along (202)
Dynamic is nested with on the perisporium of mounting disc (1).
A kind of nozzle ring for turbocharger the most according to claim 1, it is characterised in that: described mounting disc
(1) annular convex rib (101), annular convex rib (101) and shifting disc (2) it are provided with on the end face of close shifting disc (2)
End face near mounting disc (1) offsets.
A kind of nozzle ring for turbocharger the most according to claim 1, it is characterised in that: described nozzle ring is also
Mounting disc (1) is may be contained within including a turbine lining (401) and a bonnet (402), turbine lining (401) and bonnet (402)
Deviating from the side of shifting disc (2), bonnet (402) is connected with mounting disc (1) and leaves between bonnet (402) and mounting disc (1)
Gap, turbine lining (401) and bonnet (402) one-body molded setting.
A kind of nozzle ring for turbocharger the most according to claim 3, it is characterised in that: described turbine lining
(401) it is provided with an annular groove (403) on periphery wall, in annular groove (403), is provided with a piston ring (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610741226.6A CN106224013B (en) | 2016-08-29 | 2016-08-29 | A kind of nozzle ring for turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610741226.6A CN106224013B (en) | 2016-08-29 | 2016-08-29 | A kind of nozzle ring for turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106224013A true CN106224013A (en) | 2016-12-14 |
| CN106224013B CN106224013B (en) | 2018-08-10 |
Family
ID=57555837
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610741226.6A Active CN106224013B (en) | 2016-08-29 | 2016-08-29 | A kind of nozzle ring for turbocharger |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106224013B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020135709A1 (en) * | 2018-12-29 | 2020-07-02 | Nissens Automotive A/S | A nozzle ring structure |
| CN112324523A (en) * | 2020-11-04 | 2021-02-05 | 萍乡德博科技股份有限公司 | Assembly structure of variable-section nozzle ring of gasoline engine |
| CN114251134A (en) * | 2021-12-07 | 2022-03-29 | 萍乡德博科技股份有限公司 | Turbocharging variable-section nozzle ring of gasoline engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050252210A1 (en) * | 2002-10-18 | 2005-11-17 | Takashi Shiraishi | Variable-nozzle mechanism, exhaust turbocharger equipped therewith, and method of manufacturing exhaust turbocharger with the variable-nozzle mechanism |
| EP1840386A1 (en) * | 2006-03-31 | 2007-10-03 | ABB Turbo Systems AG | Pre-swirl device |
| CN203067041U (en) * | 2012-12-14 | 2013-07-17 | 湖南天雁机械有限责任公司 | Variable nozzle ring of ball type structure |
| CN104295330A (en) * | 2014-09-16 | 2015-01-21 | 萍乡市德博科技发展有限公司 | Section-variable nozzle ring for turbocharger |
| CN205908317U (en) * | 2016-08-29 | 2017-01-25 | 萍乡德博科技股份有限公司 | A nozzle cascade for turbo charger |
-
2016
- 2016-08-29 CN CN201610741226.6A patent/CN106224013B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050252210A1 (en) * | 2002-10-18 | 2005-11-17 | Takashi Shiraishi | Variable-nozzle mechanism, exhaust turbocharger equipped therewith, and method of manufacturing exhaust turbocharger with the variable-nozzle mechanism |
| EP1840386A1 (en) * | 2006-03-31 | 2007-10-03 | ABB Turbo Systems AG | Pre-swirl device |
| CN203067041U (en) * | 2012-12-14 | 2013-07-17 | 湖南天雁机械有限责任公司 | Variable nozzle ring of ball type structure |
| CN104295330A (en) * | 2014-09-16 | 2015-01-21 | 萍乡市德博科技发展有限公司 | Section-variable nozzle ring for turbocharger |
| CN205908317U (en) * | 2016-08-29 | 2017-01-25 | 萍乡德博科技股份有限公司 | A nozzle cascade for turbo charger |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020135709A1 (en) * | 2018-12-29 | 2020-07-02 | Nissens Automotive A/S | A nozzle ring structure |
| CN112324523A (en) * | 2020-11-04 | 2021-02-05 | 萍乡德博科技股份有限公司 | Assembly structure of variable-section nozzle ring of gasoline engine |
| CN112324523B (en) * | 2020-11-04 | 2023-04-25 | 萍乡德博科技股份有限公司 | Assembly structure of variable-section nozzle ring of gasoline engine |
| CN114251134A (en) * | 2021-12-07 | 2022-03-29 | 萍乡德博科技股份有限公司 | Turbocharging variable-section nozzle ring of gasoline engine |
| CN114251134B (en) * | 2021-12-07 | 2024-01-26 | 萍乡德博科技股份有限公司 | Turbocharging variable section nozzle ring of petrol engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106224013B (en) | 2018-08-10 |
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| GR01 | Patent grant |