CN104476112B - A kind of processing method of high temperature alloy large diameter thin wall cone integral casing - Google Patents
A kind of processing method of high temperature alloy large diameter thin wall cone integral casing Download PDFInfo
- Publication number
- CN104476112B CN104476112B CN201410589370.3A CN201410589370A CN104476112B CN 104476112 B CN104476112 B CN 104476112B CN 201410589370 A CN201410589370 A CN 201410589370A CN 104476112 B CN104476112 B CN 104476112B
- Authority
- CN
- China
- Prior art keywords
- casing
- annular groove
- profile
- processing
- finish
- 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.)
- Expired - Fee Related
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- 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
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Forging (AREA)
Abstract
The processing method of the present invention a kind of high temperature alloy large diameter thin wall cone integral casing, belong to mechanical manufacturing field, this processing method changes conventional inside and outside profile and divides different operation processing, allowance distribution is uneven, the processing mode that size is difficult to ensure that, i.e. ensure that part is good for delivery, in turn ensure that and connect cutter requirement between list, assembly, ultimately formed with single-piece three road Vehicle Processing, one Vehicle Processing of assembly, the Boring technological process as trunk；Taking into full account the yielding factor of Thin-Wall Outer Casing in part process of the present invention, in finish turning processing and Boring, aiding support mode the most in different ways is to prevent part from trembleing；The selection of finish turning process tool, cutting line, parameter aspect are all optimized；It addition, use thread milling machine process technology to instead of high temperature alloy minor diameter screwed hole hand tapping；Using this processing method to ensure that the dimensional accuracy of part, and realize high-quality, high efficiency, low cost, market application foreground is wide.
Description
Technical field
The invention belongs to mechanical manufacturing field, the processing method being specifically related to a kind of high temperature alloy large diameter thin wall cone integral casing.
Background technology
Along with developing by leaps and bounds of China's Aviation Industry, bulk transport aircraft technology is the most perfect, and bulk transport engine technology also exists
Persistently improving, the requirement to part is more and more higher therewith；Major diameter casing part is widely applied on bulk transport engine,
As typical case casing part thin-walled cone integral casing, the feature of this type of casing be structure complexity, dimensional accuracy height, thin-walled,
Material difficulty processing etc.；
Low-pressure turbine casing cell cube is by low-pressure turbine shaft assembly, low-pressure turbine stator part sub-assembly and low-pressure turbine casing list
Unit's body three part composition；Most important part i.e. low-pressure turbine casing welding group in low-pressure turbine stator part sub-assembly
Component, ring sub-assembly of obturaging outside its mounted inside guide vane and rotor blade (is commonly called as " honeycomb "), outside equipped with 6 heat
Galvanic couple, has 3 pressure taps and 3 peepholes outside casing；
Low-pressure turbine casing welding sub-assembly belongs to large thin-wall casing (maximum gauge is 1065mm, wall thickness 1.45mm), and structure is relatively
For complexity, having 6 road grooves inside casing, there is U-type groove cell body side, and 3 kinds of totally 12 boss, forward and backward installation limits are welded in outside
It is drilled with hole.The sixty-four dollar question that large-scale casing and Thin-Wall Outer Casing work in-process are faced process exactly in sidewall and forward and backward installation
Limit easily causes deformation；Part the most also can cause deformation.Therefore, overcome in casing deformation processing and face
Significant problem.The inside of casing is furnished with multiple tracks abnormal shape annular groove, and size is less, precision is higher；Casing material is GH4169 hardness
Relatively big, processing difficulties；Due to the increase of casing diameter, its deflection is more difficult to control；
Low-pressure turbine casing welding sub-assembly is made up of after welding boss low-pressure turbine wheel chamber casing；At present, processing scheme
Being to process the boss after casing is welded by all of casing size again to be processed, the inside and outside profile of casing divides different operation processing,
Allowance distribution is uneven, and size is difficult to ensure that, it is impossible to ensures that part is good for delivery and connects cutter requirement between list, assembly, existing adds
Part after the processing of work scheme deforms greatly after welding, and diameter dimension maximum distortion reaches more than 2mm, and internal annular groove the most seriously becomes
Shape, part also have impact on, while not meeting design requirement, ring sub-assembly of obturaging outside guide vane and rotor blade and fills normally
Join；
In order to avoid part deformation, meet bulk transport reseach of engine, need a kind of stable processing method to realize part
Processing request.
Summary of the invention
For the shortcoming of prior art, the present invention proposes the processing method of a kind of high temperature alloy large diameter thin wall cone integral casing,
To reach to solve high temperature alloy large diameter thin wall cone integral casing part deformation problem, while meeting Project R&D, improve
Quality, working (machining) efficiency and the purpose of reduction cost.
The processing method of a kind of high temperature alloy large diameter thin wall cone integral casing, comprises the following steps:
Step 1, high temperature alloy large diameter thin wall cone integral casing blank material is installed on lathe, it is carried out roughing；
Step 2, the casing after roughing is positioned in heat-treatment furnace to its be removed stress process；
Step 3, go de-stress after, more again casing is installed on Digit Control Machine Tool, it is carried out semifinishing；
Step 4, by casing by outer mold surface auxiliary support fixture be fixed on Digit Control Machine Tool；
Step 5, casing small end is finished；
Step 6, end big to casing finish；
Step 7, interior profile to casing carry out roughing；
Step 8, outer mold surface to casing carry out roughing, finish；
Step 9, interior profile to casing finish；
Step 10, on casing, radial hole is beaten in certain position according to the actual requirements；
Step 11, mounting seat is fixed with casing by radial hole, form assembly；
Step 12, repetition step 4 and step 5, finish casing small end face again；
Step 13, U-type groove and outer wall bottom to the second level in profile in casing to penultimate stage annular groove finish；
Step 14, complete the processing to high temperature alloy large diameter thin wall cone integral casing.
The interior profile to casing described in step 9 finishes, and process is as follows:
Step 9-1, from casing seam, internal profile finishes；
Step 9-2, when first order annular groove in profile in arriving, according to the width of U-type groove, the degree of depth and the end of first order annular groove
Portion's radius, chooses ball cutter, uses selected ball cutter to finish the U-type groove of first order annular groove；
Step 9-3, complete the finishing of U-type groove to first order annular groove after, switching cutter continues profile in casing is carried out essence
Processing；
Step 9-4, when second level annular groove in profile in arriving, first use the U-type groove surplus of groove cutter removal second level annular groove,
Use ball cutter that the U-type groove of second level annular groove is finished again；
Step 9-5, the process identical with step 9-4 internal remaining annular groove of profile successively is used to finish；
Step 9-6 is until completing the finishing of internal profile afterbody annular groove.
The invention have the advantages that
The processing method of the present invention a kind of high temperature alloy large diameter thin wall cone integral casing, this processing method change with inside,
Outer mold surface divides different operation processing, and allowance distribution is uneven, and the processing mode that size is difficult to ensure that i.e. ensure that part is good for delivery,
In turn ensure that and connect cutter requirement between list, assembly, ultimately formed with single-piece three road Vehicle Processing, one Vehicle Processing of assembly, bore hole
It is processed as the technological process of trunk；Part process of the present invention takes into full account the yielding factor of Thin-Wall Outer Casing, finish turning processing and
In Boring, aiding support mode the most in different ways is to prevent part from trembleing；Selection, feed to finish turning process tool
Route, parameter aspect are all optimized；It addition, use thread milling machine process technology to instead of high temperature alloy minor diameter screwed hole hand
Dynamic tapping；Use this processing method to ensure that the dimensional accuracy of part, and realize high-quality, high efficiency, low cost, market
Have a extensive future.
Accompanying drawing explanation
Fig. 1 is the high temperature alloy large diameter thin wall cone integral casing structural representation of an embodiment of the present invention；
Fig. 2 is the processing method flow chart of the high temperature alloy large diameter thin wall cone integral casing of an embodiment of the present invention；
Fig. 3 is the low-pressure turbine casing welding sub-assembly inner loop tank car process operation figure of an embodiment of the present invention, wherein, 1
For cutter, 2 is cutter rail, and 3 is casing annular groove；
Fig. 4 is the casing small end face machining area schematic diagram of an embodiment of the present invention；
Fig. 5 is the casing annular groove machining area schematic diagram of an embodiment of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawings an embodiment of the present invention is described further.
In the embodiment of the present invention, according to the experience of existing processing technology, after solving part welding, deform excessive effective method
It is that the surplus to single-piece and sub-assembly is adjusted, will all leave the sub-assembly after welding for except all final sizes outside casing
Processing, the deformation that thus can welding be brought is removed in the processing of sub-assembly, it is ensured that dimensional requirement.
In the embodiment of the present invention, low-pressure turbine casing is processed, to low-pressure turbine casing as it is shown in figure 1, processing method stream
Journey figure is as in figure 2 it is shown, comprise the following steps:
Step 1, high temperature alloy large diameter thin wall cone integral casing woollen is installed on lathe, it is carried out roughing；
In the embodiment of the present invention, low-pressure turbine casing, as single-piece, leaves 1mm to 1.5mm on its forward and backward installation limit and internal annular groove
Surplus, similar to conventional casing processing route, point rough turn, half finish turning and finish turning processing；
In the embodiment of the present invention, CAM (computer-aided manufacturing) function of UG NX7.5 software is used to carry out aided programming,
Numerical control program is generated, as it is shown on figure 3, utilize VERICUT software after Program Generating after the processes such as modeling, foundation operation and post processing
Analog simulation, whether inspection program exists residual and crosses unreasonable parts such as cutting, and program carries out trickle adjustment, utilizing VERICUT
The accuracy of software check procedure, pick out those can part of damages, frock clamp and the mistake of process tool, including: 1)
Drawing or interpreting blueprints mistake；2) programming inaccuracy；3) contact material when quickly moving；4) feed path of mistake；5) with
The collision that frock clamp occurs；6) CAD/CAM and preprocessor mistake；7) stress produced in processing is analyzed.
Step 2, the casing after roughing is positioned in heat-treatment furnace to its be removed stress process；
Step 3, go de-stress after, more again casing is installed on Digit Control Machine Tool, it is carried out semifinishing；
Step 4, by casing by outer mold surface auxiliary support fixture be fixed on Digit Control Machine Tool；
Step 5, casing small end is finished, specifically comprise the following steps that
Step 5-1, lower surface and arc surface to casing small end outer mold surface finish；
As shown in Figure 4, in the embodiment of the present invention, use ball cutter to the 1. region finish, rotating speed is 8-12r/min,
Feeding rate is 0.1-0.16mm/r；
Step 5-2, sidewall to the outer mold surface of casing small end finish；
As shown in Figure 4, in the embodiment of the present invention, use offset tool to the 2. region finish；
Step 5-3, sidewall to the interior profile of casing small end finish；
As shown in Figure 4, in the embodiment of the present invention, use offset tool to the 3. region finish；
Step 5-4, inner headed face to casing small end finish；
As shown in Figure 4, in the embodiment of the present invention, use offset tool to the 4. region finish；
Step 6, casing large end face is finished；
Step 7, interior profile to casing carry out roughing；
Step 8, outer mold surface to casing carry out roughing, finish；
In the embodiment of the present invention, it is 0.2-0.3mm that surplus is removed in roughing to finishing；
Step 9, interior profile to casing finish, and process is as follows:
Step 9-1, from casing seam, internal profile finishes；
Step 9-2, when first order annular groove in profile in arriving, according to the width of U-type groove, the degree of depth and the end of first order annular groove
Portion's radius, chooses ball cutter, uses selected ball cutter to finish the U-type groove of first order annular groove；
Step 9-3, complete the finishing of U-type groove to first order annular groove after, switching cutter continues profile in casing is carried out essence
Processing；
Step 9-4, when second level annular groove in profile in arriving, first use the U-type groove surplus of groove cutter removal second level annular groove,
Use ball cutter that the U-type groove of second level annular groove is finished again；
Step 9-5, the process identical with step 9-4 internal remaining annular groove of profile successively is used to finish；
Step 9-6 is until completing the finishing of internal profile afterbody annular groove.
Step 10, according to the actual requirements certain position brill boring radial hole on casing；
In the embodiment of the present invention, thread milling machine process technology is used to be drilled with 12 radial holes in casing outer mold surface, during for welded and installed seat
Use；
Step 11, mounting seat is carried out electron beam by radial hole with casing weld formation assembly；
In the embodiment of the present invention, after the main processing purpose of sub-assembly after welding seeks to remove housing institute's made allowance and welding
Deformation；
Step 12, repetition step 4 and step 5, finish casing small end face again；
Step 13, U-type groove and outer wall bottom to the second level in profile in casing to penultimate stage annular groove finish
1-1.5mm；
5. and 6. as it is shown in figure 5, machining area is；
Step 14, complete the processing to high temperature alloy large diameter thin wall cone integral casing.
In the embodiment of the present invention, under virtual environment, carry out the processing of part, after process finishing, part is analyzed, design
Entity automatically compares with the entity after cutting thus found to cut or remaining balance, can entirety compare in comparison procedure,
Can also compare subregion, the precision according to comparing resets tolerance.
The experiment proved that, the present invention is effectively controlled part deformation, meets design drawing and matching requirements；Process-cycle improves
More than 30%；Processing cost reduces more than 30%.
Claims (2)
1. the processing method of a high temperature alloy large diameter thin wall cone integral casing, it is characterised in that: comprise the following steps:
Step 1, high temperature alloy large diameter thin wall cone integral casing blank material is installed on lathe, it is carried out roughing；
Step 2, the casing after roughing is positioned in heat-treatment furnace to its be removed stress process；
Step 3, go de-stress after, more again casing is installed on Digit Control Machine Tool, it is carried out semifinishing；
Step 4, by casing by outer mold surface auxiliary support fixture be fixed on Digit Control Machine Tool；
Step 5, casing small end is finished；
Step 6, end big to casing finish；
Step 7, interior profile to casing carry out roughing；
Step 8, outer mold surface to casing carry out roughing, finish；
Step 9, interior profile to casing finish；
Step 10, on casing, radial hole is beaten in certain position according to the actual requirements；
Step 11, mounting seat is fixed with casing by radial hole, form assembly；
Step 12, repetition step 4 and step 5, finish casing small end face again；
Step 13, U-type groove and outer wall bottom to the second level in profile in casing to penultimate stage annular groove carry out finishing
Work；
Step 14, complete the processing to high temperature alloy large diameter thin wall cone integral casing.
The processing method of high temperature alloy large diameter thin wall cone integral casing the most according to claim 1, it is characterised in that: step
The interior profile to casing described in rapid 9 finishes, and process is as follows:
Step 9-1, from casing seam, internal profile finishes；
Step 9-2, when first order annular groove in profile in arriving, according to the width of U-type groove, the degree of depth and the end of first order annular groove
Portion's radius, chooses ball cutter, uses selected ball cutter to finish the U-type groove of first order annular groove；
Step 9-3, complete the finishing of U-type groove to first order annular groove after, switching cutter continues profile in casing is carried out essence
Processing；
Step 9-4, when second level annular groove in profile in arriving, first use the U-type groove surplus of groove cutter removal second level annular groove,
Use ball cutter that the U-type groove of second level annular groove is finished again；
Step 9-5, the process identical with step 9-4 internal remaining annular groove of profile successively is used to finish；
Step 9-6 is until completing the finishing of internal profile afterbody annular groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589370.3A CN104476112B (en) | 2014-10-28 | 2014-10-28 | A kind of processing method of high temperature alloy large diameter thin wall cone integral casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589370.3A CN104476112B (en) | 2014-10-28 | 2014-10-28 | A kind of processing method of high temperature alloy large diameter thin wall cone integral casing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104476112A CN104476112A (en) | 2015-04-01 |
| CN104476112B true CN104476112B (en) | 2016-08-17 |
Family
ID=52750786
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589370.3A Expired - Fee Related CN104476112B (en) | 2014-10-28 | 2014-10-28 | A kind of processing method of high temperature alloy large diameter thin wall cone integral casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104476112B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107931972A (en) * | 2017-11-09 | 2018-04-20 | 中国航发航空动力股份有限公司 | A kind of aero-engine front housing component machining benchmark conversion method |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105345402B (en) * | 2015-11-19 | 2017-12-01 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of distortion-free processing method of casing part Milling Machining circular hole and lace |
| CN105328209B (en) * | 2015-12-04 | 2017-09-12 | 无锡易通精密机械股份有限公司 | A kind of Vehicle Processing technique of aircraft air intake casing |
| CN105643213B (en) * | 2016-03-08 | 2020-10-02 | 哈尔滨东安发动机（集团）有限公司 | Machining method for out-of-tolerance bottom hole of casing blank |
| CN105690041B (en) * | 2016-04-11 | 2018-02-16 | 贵州遵义驰宇精密机电制造有限公司 | A kind of processing method of aircraft engine front housing |
| CN106514152B (en) * | 2016-12-07 | 2018-11-27 | 贵州黎阳航空动力有限公司 | A kind of processing method of the more rib titanium alloy components of thin-walled |
| CN106514160A (en) * | 2017-01-04 | 2017-03-22 | 成都四威高科技产业园有限公司 | High-precision microwave assembly bottom face machining process |
| CN107479503B (en) * | 2017-07-31 | 2020-04-03 | 成都飞机工业（集团）有限责任公司 | Simulation comparison inspection method for size of numerical control machining threaded hole |
| CN107695634A (en) * | 2017-11-23 | 2018-02-16 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of Thin-Wall Outer Casing T-slot processing method |
| CN108044316B (en) * | 2017-12-18 | 2019-05-14 | 中国航发贵州黎阳航空动力有限公司 | A kind of processing method of turbine casing housing unit |
| CN109352120A (en) * | 2018-11-27 | 2019-02-19 | 中国航发贵州黎阳航空动力有限公司 | One kind obturaging ring parts vacuum brazing clamp |
| CN110064897B (en) * | 2019-04-30 | 2021-01-01 | 中国航发南方工业有限公司 | Machining method for blank of spinning part of aviation part |
| CN110936108B (en) * | 2019-11-19 | 2022-05-10 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining method for improving assembly precision of thin-wall annular casing type parts |
| CN111037226B (en) * | 2019-12-19 | 2021-07-13 | 北京精密机电控制设备研究所 | Processing method of titanium alloy thin-wall part |
| CN111805186B (en) * | 2020-07-29 | 2024-07-09 | 山西航天清华装备有限责任公司 | Tensioning and positioning tool assembly for superhard material special-shaped component and milling method |
| CN112091544B (en) * | 2020-09-15 | 2022-06-28 | 中国航发贵州黎阳航空动力有限公司 | Processing method of thin-wall bearing ring with inclination |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5201115A (en) * | 1990-09-17 | 1993-04-13 | Mazda Motor Corporation | Method of manufacturing cylinder block of an engine |
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103551816A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for controlling processing deformation of titanium-aluminum alloy thin-wall case |
-
2014
- 2014-10-28 CN CN201410589370.3A patent/CN104476112B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5201115A (en) * | 1990-09-17 | 1993-04-13 | Mazda Motor Corporation | Method of manufacturing cylinder block of an engine |
| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103551816A (en) * | 2013-11-18 | 2014-02-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method for controlling processing deformation of titanium-aluminum alloy thin-wall case |
Non-Patent Citations (2)
| Title |
|---|
| 双环薄壁铸铝机匣的机械加工;张辉等;《航天工艺》;20011028(第05期);第7-10页 * |
| 精密铸造铝合金机匣的机械加工;王晓伟;《航天制造技术》;20020428(第02期);第34-36页 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107931972A (en) * | 2017-11-09 | 2018-04-20 | 中国航发航空动力股份有限公司 | A kind of aero-engine front housing component machining benchmark conversion method |
| CN107931972B (en) * | 2017-11-09 | 2019-05-21 | 中国航发航空动力股份有限公司 | A kind of aero-engine front housing component machining benchmark conversion method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104476112A (en) | 2015-04-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104476112B (en) | A kind of processing method of high temperature alloy large diameter thin wall cone integral casing | |
| CN105382313A (en) | Machining method for numerical control milling of thin-wall curved-surface irregular parts | |
| CN104384825A (en) | Machining deformation control method of bushing thin-wall part | |
| CN104015016A (en) | Method for processing high precision thin-wall deep-cavity part | |
| CN104148894A (en) | Machining method of thin-walled deep-hole welded workpieces | |
| CN105269277A (en) | Method for machining arc-tooth tenon blade of aircraft engine gas compressor | |
| CN103111814A (en) | Numerical control machining method of aero-engine disc-shaft integrated structure part | |
| CN104822489B (en) | Method and device for manufacturing turbine blades | |
| CN105773073A (en) | Method for manufacturing complex metal part by combining additive manufacturing with milling | |
| CN104972281B (en) | A kind of processing technology of unenclosed construction part | |
| CN108723715A (en) | A method of with bar working nozzle shell | |
| CN109570907B (en) | Groove cavity and machining method | |
| Klink et al. | Technology-based assessment of subtractive machining processes for mold manufacture | |
| CN106312152A (en) | Method for machining thin-walled components | |
| CN103372759A (en) | Insert integration type processing process | |
| US20110255976A1 (en) | Manufacturing method for closed vane wheels | |
| CN105750844A (en) | Processing method for hollow spindle of compressor | |
| CN106736292A (en) | A kind of advanced pressurized water reactor fuel element base machining process | |
| US8020296B2 (en) | Method for the production of secondary fluid ducts | |
| Pasko et al. | High speed machining (HSM)–the effective way of modern cutting | |
| EP3366884B1 (en) | Method for manufacturing blisk | |
| Xin et al. | Compound efficient and powerful milling machine tool of blisk | |
| CN104439468A (en) | Milling cutter suitable for layered milling forming process of integral leaf disk structural profile | |
| CN104772604A (en) | Processing method of steam nozzle on steam injection coverplate of steam turbine | |
| EP3685956B1 (en) | Method for processing workpiece with laser, and use thereof in cutter manufacturing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
|
| CP01 | Change in the name or title of a patent holder | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 Termination date: 20201028 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |