CN101032757A - Method of producing vane of nozzle ring - Google Patents
Method of producing vane of nozzle ring Download PDFInfo
- Publication number
- CN101032757A CN101032757A CN 200610024451 CN200610024451A CN101032757A CN 101032757 A CN101032757 A CN 101032757A CN 200610024451 CN200610024451 CN 200610024451 CN 200610024451 A CN200610024451 A CN 200610024451A CN 101032757 A CN101032757 A CN 101032757A
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- CN
- China
- Prior art keywords
- blade
- jet
- pneumatic fixture
- jet blade
- chip type
- 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.)
- Pending
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Abstract
The nozzle blade manufacturing process in high precision general numerically controlled lathe and pneumatic tool set with blade contour locating clamping structure includes the following steps: fixing the shaft with the pneumatic tool set and drawing the nozzle blade backwards until fitting the blade datum face to the pneumatic tool set, clamping the upper part of the blade with the pneumatic tool set via two locating blocks, fitting the lower part of the clamping structure with the lower part of the blade, locating the other section of the blade via fixing with the tailstock center of the lathe, etc. The present invention has reliable locating and fast clamping, and is favorable to control of key sizes and suitable for high efficiency production.
Description
Technical field
The present invention relates to a kind of vehicle turbocharger, relate in particular to the manufacture method of jet blade in a kind of vehicle turbocharger.
Background technology
Core component one jet blade of vehicle turbocharger is one of key technology that improves the turbocharger effect.Vehicular engine is because the characteristics of road operating condition, requirement has higher torque reserve and acceleration, so the design of these parts must be reasonable, and blade processing precision height, it is position-movable, thus enough flow velocity of the best and the high supercharging efficient of in whole engine speed range, providing.The high pressure-charging effect that produces under the slow-speed of revolution becomes gently torque curve, and can improve power output.Removable guide vane is controlled by engine control system, can regulate the air-flow that enters turbocharger, guarantees optimum efficiency, makes engine make rapid reaction to throttle, produces outstanding handling.
The vane end faces flatness 0.005 of jet blade, the both ends of the surface depth of parallelism 0.013, and middle blade-section is for adapting to the air communication mistake is shaped as streamlinedly, and so the clamping difficulty is all quite high to the requirement and the difficulty of the machining accuracy of jet blade; Because the demand of jet blade is quite big, also require to produce to stablize in addition, efficient, large-scale production.
Existing foreign vendor adopts double power head equipment when making this product, the rotating shaft in the middle of the lengthening clamps the blade two ends then, and part is positioned back processing.To the required precision height of foundry goods, there is quality risk like this; The loss of material work in-process is big; Need customization special purpose machine tool equipment, the hardware cost height is not suitable for low-cost production in enormous quantities the in enormous quantities.
Summary of the invention
The technical issues that need to address of the present invention have provided a kind of manufacture method of jet blade, are intended to solve above-mentioned defective.
In order to solve the problems of the technologies described above, the present invention realizes by following steps:
Adopt high-accuracy general numerically controlled lathe and Pneumatic fixture;
Described Pneumatic fixture adopts the blade face locations of contours, and three-chip type closes up clamping structure;
The Pneumatic fixture fixed rotating shaft pulls back jet blade, fits fully until blade datum level and Pneumatic fixture;
The Pneumatic fixture three-chip type clamps the first half with jet blade: the locating piece by two inner chambers coincide with jet blade blade face the first half altogether clamps top, applying blade face profile earlier from the left and right sides;
Second sheet of three-chip type clamping structure coincide with jet blade blade face the latter half from bottom to top;
Another section of jet blade is with the centre bore location, and is top fixing with tail stock for machine tool.
Compared with prior art, the invention has the beneficial effects as follows: owing to realized positioning with blade face profile and datum level, the location is reliable, helps controlling crucial dimensional requirement, simultaneously, also meets the design original intention of drawing; The process that frock clamps is quick, and is reliable, avoided artificial factor to the full extent, very adapts in enormous quantities high efficiency production.
The specific embodiment
Below in conjunction with the specific embodiment the present invention is described in further detail:
In order to solve the problems of the technologies described above, the present invention realizes by following steps:
Adopt high-accuracy general numerically controlled lathe and Pneumatic fixture;
Described Pneumatic fixture adopts the blade face locations of contours, and three-chip type closes up clamping structure;
The Pneumatic fixture fixed rotating shaft pulls back jet blade, fits fully until blade datum level and Pneumatic fixture;
The Pneumatic fixture three-chip type clamps the first half with jet blade: the locating piece by two inner chambers coincide with jet blade blade face the first half altogether clamps top, applying blade face profile earlier from the left and right sides;
Second sheet of three-chip type clamping structure coincide with jet blade blade face the latter half from bottom to top; Reach purpose with the contoured surface location;
Another section of jet blade is with the centre bore location, and is top fixing with tail stock for machine tool.
As long as the allowance on the foundry goods can reach designing requirement, just part can be finished smoothly.Similarly location is all adopted in the processing at two ends, the left and right sides, and the clamping processing scheme has successfully been realized the batch process of part.
The present invention realizes positioning with blade face profile and datum level, and the location is reliable, helps controlling crucial dimensional requirement, simultaneously, also meets the design original intention of drawing; The process that frock clamps is quick, and is reliable, avoided artificial factor to the full extent, very adapts in enormous quantities high efficiency production.The characteristic that more meets its technology itself for the requirement of foundry goods.The more important thing is and realized on common apparatus, producing, reduced the cost that equipment drops into, be fit to scale, in enormous quantities, produce cheaply.
Claims (1)
1. the manufacture method of a jet blade, realize by following steps:
Adopt high-accuracy general numerically controlled lathe and Pneumatic fixture;
Described Pneumatic fixture adopts the blade face locations of contours, and three-chip type closes up clamping structure;
The Pneumatic fixture fixed rotating shaft pulls back jet blade, fits fully until blade datum level and Pneumatic fixture;
The Pneumatic fixture three-chip type clamps the first half with jet blade: the locating piece by two inner chambers coincide with jet blade blade face the first half altogether clamps top, applying blade face profile earlier from the left and right sides;
Second sheet of three-chip type clamping structure coincide with jet blade blade face the latter half from bottom to top;
Another section of jet blade is with the centre bore location, and is top fixing with tail stock for machine tool.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024451 CN101032757A (en) | 2006-03-07 | 2006-03-07 | Method of producing vane of nozzle ring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200610024451 CN101032757A (en) | 2006-03-07 | 2006-03-07 | Method of producing vane of nozzle ring |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101032757A true CN101032757A (en) | 2007-09-12 |
Family
ID=38729609
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200610024451 Pending CN101032757A (en) | 2006-03-07 | 2006-03-07 | Method of producing vane of nozzle ring |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101032757A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454027A (en) * | 2014-10-31 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Machining method of power turbine guider |
| CN107398746A (en) * | 2017-09-22 | 2017-11-28 | 重庆江增船舶重工有限公司 | A kind of cutting tool and processing method of nozzle outer shroud |
| CN110605544A (en) * | 2019-09-23 | 2019-12-24 | 重庆江增船舶重工有限公司 | Method for machining nozzle ring blade |
-
2006
- 2006-03-07 CN CN 200610024451 patent/CN101032757A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454027A (en) * | 2014-10-31 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Machining method of power turbine guider |
| CN104454027B (en) * | 2014-10-31 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | The processing method of power turbine guider |
| CN107398746A (en) * | 2017-09-22 | 2017-11-28 | 重庆江增船舶重工有限公司 | A kind of cutting tool and processing method of nozzle outer shroud |
| CN110605544A (en) * | 2019-09-23 | 2019-12-24 | 重庆江增船舶重工有限公司 | Method for machining nozzle ring blade |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |