CN102950316A - Processing method of sub-last stage blade with good blade profile stability of large turbine - Google Patents
Processing method of sub-last stage blade with good blade profile stability of large turbine Download PDFInfo
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- CN102950316A CN102950316A CN2012104869290A CN201210486929A CN102950316A CN 102950316 A CN102950316 A CN 102950316A CN 2012104869290 A CN2012104869290 A CN 2012104869290A CN 201210486929 A CN201210486929 A CN 201210486929A CN 102950316 A CN102950316 A CN 102950316A
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Abstract
The invention relates to a processing method of a large blade of a turbine, in particular to a processing method of a sub-last stage blade with good blade profile stability of a large turbine, which aims to solve the defect that in the prior art, the manufactured sub-last stage blade of the large turbine is easy to deform. The method comprises the following steps of: firstly clamping a casting to be milled on a Ferrari machine tool at one step, then adopting a three-cutter milling method for processing, so as to complete the processing on the sub-last stage blade with the good blade profile stability of the large turbine. The processing method disclosed by the invention has the advantages that 1, the profile is kept good, and the blade is not easily deformed; 2, the errors can be eliminated, so that the whole consistency of an assembling part of the blade can be ensured, and further, the ultrothin shroud molded lines of a blade shroud skeleton pattern is uniform and consistent in deformation; 3, the three-cutter milling method is adopted for processing, so that forging stress of a blank can be released, the mechanical processing stress can be eliminated, and the polishing amount of a blade steam passage can be ensured; and 4, the gap uniformity and linearity in the whole circle of assembling of the blade can be ensured. The processing method is mainly used for processing the sub-last stage blade of the large turbine.
Description
Technical field
The present invention relates to the large blade machining process of a kind of steam turbine.
Background technology
At present, second last stage blade on the steam turbine else has and reaches the above large blade of 1000mm, this large-size steam turbine second last stage blade molded line in process keeps good, but machining, after pulling down from lathe soon deformable blade can occur, at this moment blade steam passage molded line and shroud all do not satisfy product requirement, need school type operation to process.And the compacting that school type operation just is similar to vane type line at the gear place is qualified, and blade still requires not in full conformity with product technology on the whole.Therefore the large-size steam turbine second last stage blade of existing invention preparation exists and holds yielding defective.
Summary of the invention
There is the yielding defective of appearance in the large-size steam turbine second last stage blade that purpose of the present invention will solve existing invention preparation, and a kind of large-size steam turbine second last stage blade processing method of blade profile good stability is provided.
A kind of large-size steam turbine second last stage blade processing method of blade profile good stability, specifically finish according to the following steps: will treat that at first milling foundry goods clamped one time is on the lathe of Ferrari, then adopt three cutter method for milling to process, namely finish the large-size steam turbine second last stage blade processing of blade profile good stability.
Advantage of the present invention: one, large-size steam turbine second last stage blade of the present invention molded line in process keeps good, and is machining, and pulls down rear blade from lathe and also is difficult for occuring deformable blade; Two, the present invention adopts clamped one time, namely when processing steam passage molded line, the ultra-thin shroud molded line of integral shroud bone type is also processed; Utilize the Ferrari lathe with pneumatic pinch, the clamping force of each blade is even, and optional cutter is various in the machine cutter holder, this processing mode, having eliminated blade adds the error of bringing in the transformation of criterion process of folder for twice on the one hand, and on the other hand, clamped one time is processed the mode of steam passage and the ultra-thin shroud molded line of integral shroud bone type simultaneously, guaranteed the global consistency of blade assembled portion, made the ultra-thin shroud molded line distortion of integral shroud bone type of blade even and unified; Three, the present invention adopts three cutter method for milling to process, and the first cutter is removed the blank hardened layer, and the cutter that can be lower order uses condition is provided, and can discharge for the first time blank forging stress; The second cutter is that finish-milling goes surplus, and can remove for the second time mechanical machining stress; The 3rd cutter is finish-milling, guarantees blade steam passage polished amount; Four, blade steam passage molded line and the shroud of the large-size steam turbine second last stage blade of the present invention processing all satisfy product requirement, and reasonable gap when having guaranteed the whole circle assembling of blade is even, linear.
Description of drawings
Fig. 1 is test one described three cutter method for milling milling schematic diagrames, A represents the blank hardened layer that the first cutter is removed among the figure, B represents the second cutter finish-milling removal layer among the figure, and C represents the 3rd cutter polishing removal layer, the large-size steam turbine second last stage blade after D represents to process among the figure among the figure.
The specific embodiment
The specific embodiment one: the large-size steam turbine second last stage blade processing method of the described a kind of blade profile good stability of present embodiment, specifically finish according to the following steps: will treat that at first milling foundry goods clamped one time is on the lathe of Ferrari, then adopt three cutter method for milling to process, namely finish the large-size steam turbine second last stage blade processing of blade profile good stability.
Present embodiment large-size steam turbine second last stage blade molded line in process keeps good, and is machining, and pulls down rear blade from lathe and also is difficult for occuring deformable blade.
Present embodiment adopts clamped one time, namely when processing steam passage molded line, the ultra-thin shroud molded line of integral shroud bone type is also processed; Utilize the Ferrari lathe with pneumatic pinch, the clamping force of each blade is even, and optional cutter is various in the machine cutter holder, this processing mode, having eliminated blade adds the error of bringing in the transformation of criterion process of folder for twice on the one hand, and on the other hand, clamped one time is processed the mode of steam passage and the ultra-thin shroud molded line of integral shroud bone type simultaneously, guaranteed the global consistency of blade assembled portion, made the ultra-thin shroud molded line distortion of integral shroud bone type of blade even and unified.
Blade steam passage molded line and the shroud of the large-size steam turbine second last stage blade of present embodiment processing all satisfy product requirement, and reasonable gap when having guaranteed the whole circle assembling of blade is even, linear.
The specific embodiment two: the difference of present embodiment and the specific embodiment one is: described three cutter method for milling concrete operations are as follows: the first cutter roughing is removed and is treated milling cast(ing) surface blank hardened layer, it is that 0.5mm carries out finish-milling that the second cutter adopts surplus, and it is that 0.1mm polishes that the 3rd cutter adopts surplus.Other are identical with the specific embodiment one.
Present embodiment adopts three cutter method for milling to process, and the first cutter is removed the blank hardened layer, and the cutter that can be lower order uses condition is provided, and can discharge for the first time blank forging stress; The second cutter is that finish-milling goes surplus, and can remove for the second time mechanical machining stress; The 3rd cutter is finish-milling, guarantees blade steam passage polished amount.
Adopt following verification experimental verification effect of the present invention:
Test one: in conjunction with Fig. 1, a kind of large-size steam turbine second last stage blade processing method of blade profile good stability, specifically finish according to the following steps: will treat that at first milling foundry goods clamped one time is on the lathe of Ferrari, then adopt three cutter method for milling to process, namely finish the large-size steam turbine second last stage blade processing of blade profile good stability.
Test described three cutter method for milling concrete operations as follows: the first cutter roughing is removed and is treated milling cast(ing) surface blank hardened layer (shown in A among the figure), it is that 0.5mm carries out finish-milling (shown in B among the figure) that the second cutter adopts surplus, and it is that 0.1mm polishes (shown in C among the figure) that the 3rd cutter adopts surplus.
Test described three cutter method for milling milling schematic diagrames as shown in Figure 1, A represents the blank hardened layer that the first cutter is removed among the figure, B represents the second cutter finish-milling removal layer among the figure, and C represents the 3rd cutter polishing removal layer, the large-size steam turbine second last stage blade after D represents to process among the figure among the figure.
Claims (2)
1. the large-size steam turbine second last stage blade processing method of a blade profile good stability, the large-size steam turbine second last stage blade processing method that it is characterized in that a kind of blade profile good stability is finished according to the following steps: will treat that at first milling foundry goods clamped one time is on the lathe of Ferrari, then adopt three cutter method for milling to process, namely finish the large-size steam turbine second last stage blade processing of blade profile good stability.
2. the large-size steam turbine second last stage blade processing method of a kind of blade profile good stability according to claim 1, it is characterized in that described three cutter method for milling concrete operations are as follows: the first cutter roughing is removed and is treated milling cast(ing) surface blank hardened layer, it is that 0.5mm carries out finish-milling that the second cutter adopts surplus, and it is that 0.1mm polishes that the 3rd cutter adopts surplus.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012104869290A CN102950316A (en) | 2012-11-26 | 2012-11-26 | Processing method of sub-last stage blade with good blade profile stability of large turbine |
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| CN2012104869290A CN102950316A (en) | 2012-11-26 | 2012-11-26 | Processing method of sub-last stage blade with good blade profile stability of large turbine |
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| CN102950316A true CN102950316A (en) | 2013-03-06 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105312647A (en) * | 2015-12-02 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Processing method of thin vanes of engines |
| CN105358277A (en) * | 2013-05-09 | 2016-02-24 | 株式会社Ihi | Wing surface finishing method and wing component |
| EP3015218A1 (en) * | 2014-10-15 | 2016-05-04 | United Technologies Corporation | Airfoil material removal |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1827271A (en) * | 2006-04-03 | 2006-09-06 | 潘毅 | Method for processing rivet head of moving blade of turbine |
| CN201109035Y (en) * | 2007-09-24 | 2008-09-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Special-purpose fixture |
| CN101363327A (en) * | 2008-09-26 | 2009-02-11 | 无锡透平叶片有限公司 | Method for processing TC11 material blade |
| CN101518835A (en) * | 2009-03-19 | 2009-09-02 | 无锡透平叶片有限公司 | Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft |
| CN101980823A (en) * | 2008-03-31 | 2011-02-23 | 斯奈克玛公司 | Method for producing a one-piece bladed disc by abrasive water-jet cutting |
| CN102528138A (en) * | 2010-12-24 | 2012-07-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method of complex curved surface by adopting drum-like cutter |
-
2012
- 2012-11-26 CN CN2012104869290A patent/CN102950316A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1827271A (en) * | 2006-04-03 | 2006-09-06 | 潘毅 | Method for processing rivet head of moving blade of turbine |
| CN201109035Y (en) * | 2007-09-24 | 2008-09-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Special-purpose fixture |
| CN101980823A (en) * | 2008-03-31 | 2011-02-23 | 斯奈克玛公司 | Method for producing a one-piece bladed disc by abrasive water-jet cutting |
| CN101363327A (en) * | 2008-09-26 | 2009-02-11 | 无锡透平叶片有限公司 | Method for processing TC11 material blade |
| CN101518835A (en) * | 2009-03-19 | 2009-09-02 | 无锡透平叶片有限公司 | Method for controlling machining distortion of titanium alloy large-size fan blade of large aircraft |
| CN102528138A (en) * | 2010-12-24 | 2012-07-04 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method of complex curved surface by adopting drum-like cutter |
Non-Patent Citations (2)
| Title |
|---|
| 吴汉夫: "弯扭小带冠导叶片的加工工艺分析", 《中国新技术新产品》, no. 17, 15 September 2011 (2011-09-15) * |
| 唐清春 等: "弯扭小带冠导叶片D600B112的加工工艺分析", 《汽轮机技术》, vol. 53, no. 6, 31 December 2011 (2011-12-31) * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105358277A (en) * | 2013-05-09 | 2016-02-24 | 株式会社Ihi | Wing surface finishing method and wing component |
| US9694430B2 (en) | 2013-05-09 | 2017-07-04 | Ihi Corporation | Wing surface finishing method and wing component |
| EP3015218A1 (en) * | 2014-10-15 | 2016-05-04 | United Technologies Corporation | Airfoil material removal |
| US10105804B2 (en) | 2014-10-15 | 2018-10-23 | United Technologies Corporation | Fixture system and method for securing an airfoil during material removal operations |
| CN105312647A (en) * | 2015-12-02 | 2016-02-10 | 中国南方航空工业(集团)有限公司 | Processing method of thin vanes of engines |
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Application publication date: 20130306 |