CN104308481B - Stator blade machining method of aeroengine compressor without mounting plate - Google Patents
Stator blade machining method of aeroengine compressor without mounting plate Download PDFInfo
- Publication number
- CN104308481B CN104308481B CN201410583311.5A CN201410583311A CN104308481B CN 104308481 B CN104308481 B CN 104308481B CN 201410583311 A CN201410583311 A CN 201410583311A CN 104308481 B CN104308481 B CN 104308481B
- Authority
- CN
- China
- Prior art keywords
- blade
- false boss
- boss
- limit
- root
- 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.)
- Active
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
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
Abstract
Disclosed is a stator blade machining method of aeroengine compressor with a mounting plate. The stator blade machining method includes adopting a stator blade blank without a mounting plate of a finish forge workpiece, positioning, clamping and machining an air inlet side and an exhaust side on a numerical-control milling machine by a first technical boss, a second technical boss, the end face of the second technical boss and a basin side of a blade body; polishing the air inlet side and the exhaust side, and ensuring that the size and the shape of the air inlet side and the exhaust side conform to the design requirements; positioning, clamping and machining a blade tip and a blade root on a numerical wire-cut machine by the basin side of the blade, the first technical boss, the second technical boss and the end face of the second technical boss, and removing the first technical boss and the second technical boss; finishing the blade tip and the blade root by clamps and removing wire-cut remelting layers on the blade tip and the blade root. By adopting the finish-forging blank, profile tolerance and surface quality of the molded profile of the blade are guaranteed, and the machined blade conforms to the design requirement and is high in yield. The stator blade machining method is simple in machining process, machining efficiency is effectively improved and machining period is shortened.
Description
Technical field
The invention belongs to aero-engine compressor blade processing technology, relate to aero-engine
The improvement of the processing method of compressor stator blade without installing plate, is specifically related to a kind of aero-engine
The processing method of compressor stator blade without installing plate.
Background technology
Certain h type engine h compressor one sees Fig. 1 without installing plate stator blade structure, blade by
Blade tip 1, blade 2, aerofluxus limit 3, blade root 4 and leading edge 5 form.Blade tip 1 is by three sections
Curved surface forms, and blade root 4 is with step, and leading edge 5 and aerofluxus limit 3 are the molded line of change.Mesh
Before, processing the main method without installing plate stator blade is: 1) use die forging blank or plate,
First numerical control milling blade profile, re-polishing blade profile, final cutting blade tip and blade root.The party
Method need to process blade profile, complex process, and working (machining) efficiency is low, blade profile profile tolerance qualification rate
Low；2) plate is used, first rolling blade profile, it is then cut off blade tip and blade root.The method
Complex process, working (machining) efficiency is low.
Summary of the invention
It is an object of the invention to provide a kind of aero-engine compressor without installing plate stator blade
Processing method, to ensure blade profile profile tolerance, improve working (machining) efficiency, shorten the process-cycle.
For achieving the above object, the present invention adopts the following technical scheme that:
1) milling inlet and outlet limit: use fine forge piece as without installing plate stator blade blank, hair
Base includes blade, the aerofluxus limit being positioned at blade side, is positioned at the leading edge of blade opposite side, position
The first false boss in blade one end and the second false boss being positioned at the blade other end, wherein
Blade includes blade tip and blade root, and blade tip connects the first false boss, and blade root fastenings the second technique is convex
Platform, the second false boss end face is the axial benchmark of blade；
With the first false boss, the second false boss, the second false boss end in CNC milling machine
The positioning and clamping processing gas inlet limit, basin side of face and blade and aerofluxus limit, leading edge stays with aerofluxus limit
0.05mm～0.15mm surplus；
2) polishing inlet and outlet limit: polishing leading edge and aerofluxus limit, makes leading edge and aerofluxus limit
Size and dimension meet design requirement；
3) line cutting blade tip and blade root: on numerically controlled wire cutting machine with the basin side of blade, the
One false boss, the second false boss and the second false boss end face positioning and clamping, process blade tip
And blade root, remove the first false boss and the second false boss；
4) pincers repair: pincers repair blade tip and blade root, removal step 3) in be retained in blade tip and blade root
On line cutting remelted layer, and make the surface roughness of blade tip and blade root meet design requirement.
There is 2mm～3mm allowance on the leading edge of described blank and aerofluxus limit.
Described step 2) in polishing use bob and nylon wheel to carry out on buffing machine.
Described step 4) employing file repaiied by middle pincers and sand paper is carried out.
Compared with prior art, the invention have the benefit that the invention proposes one
Plant the aero-engine improvement processing method without installing plate stator blade, by finish forge blank is entered
Row milling intake and exhaust limit, polishing intake and exhaust limit, line cutting blade tip blade root and pincers are repaiied, and processing is navigated
Empty electromotor is without installing plate compressor stator blade.The invention have the advantages that 1) the party
Method uses finish forge blank, it is ensured that blade type profile tolerance of a surface and surface quality, makes the leaf prepared
Sheet meets design requirement；Owing to blank uses fine forge piece, so that prepare the qualification rate of blade
Height, overcome the working (machining) efficiency caused owing to using die forging blank or plate in prior art and
The problem that qualification rate is low；2) the method work flow that the present invention provides is simple, is effectively increased
Working (machining) efficiency, shortens the process-cycle.
Accompanying drawing explanation
Fig. 1 is that certain h type engine h compressor one is without installing plate stator blade structural representation；
Fig. 2 is that certain h type engine h compressor one is without installing plate stator blade blank schematic diagram；
Fig. 3 be the second false boss along Fig. 2 A-A to sectional view.
In figure, 1 is blade tip, and 2 is blade, and 3 is aerofluxus limit, and 4 is blade root, and 5 is air inlet
Limit, 6 is the first false boss, and 7 is the second false boss, and 8 is the second false boss end face.
Detailed description of the invention
The present invention is described in detail below in conjunction with the accompanying drawings.
The aero-engine of the present invention is fine forge piece without the blank of installing plate stator blade, and blank is tied
Structure sees Fig. 2 and Fig. 3, blank include blade 2, the aerofluxus limit 3 being positioned at blade 2 side,
The leading edge 5 being positioned at blade 2 opposite side, the first false boss 6 and being positioned at blade 2 one end
Being positioned at the second false boss 7 of blade 2 other end, wherein blade 2 includes blade tip 1 and blade root
4, blade tip 1 connects the first false boss 6, and blade root 4 connects the second false boss 7, blade 2
Not having surplus, leading edge 5 and aerofluxus limit 3 to have 2mm～3mm allowance, the second technique is convex
You face 8 is the axial benchmark of blade, and its procedure of processing is:
1) milling inlet and outlet limit: with first false boss the 6, second technique in CNC milling machine
The positioning and clamping processing gas inlet limit, basin side 5 of boss the 7, second false boss end face 8 and blade 2
With aerofluxus limit 3,0.05mm～0.15mm surplus is stayed on leading edge 5 and aerofluxus limit 3.
2) polishing inlet and outlet limit: with bob and nylon wheel polishing leading edge 5 on buffing machine
With aerofluxus limit 3, it is ensured that the size and dimension on leading edge 5 and aerofluxus limit 3 meets design requirement.
3) line cutting blade tip and blade root: on numerically controlled wire cutting machine with the basin side of blade 2,
First false boss the 6, second false boss 7 and the second false boss end face 8 positioning and clamping,
Processing blade tip 1 and blade root 4, remove the first false boss 6 and the second false boss 7.
4) pincers are repaiied: clamp with file and sand paper and repair blade tip 1 and blade root 4, removal step 3) middle something lost
Stay the line cutting remelted layer on blade tip 1 and blade root 4, and ensure blade tip 1 and the table of blade root 4
Surface roughness meets design requirement.
Claims (4)
1. aero-engine exists without an installing plate compressor stator blade processing method, its feature
In, comprise the following steps:
1) milling inlet and outlet limit: use fine forge piece as without installing plate stator blade blank, hair
Base includes blade (2), the aerofluxus limit (3) being positioned at blade (2) side, is positioned at blade (2)
The leading edge (5) of opposite side, the first false boss (6) being positioned at blade (2) one end and position
In second false boss (7) of blade (2) other end, wherein blade (2) includes blade tip (1)
With blade root (4), blade tip (1) connects the first false boss (6), and blade root (4) connects second
False boss (7), the second false boss end face (8) is the axial benchmark of blade；
With the first false boss (6), the second false boss (7), the second work in CNC milling machine
Positioning and clamping processing gas inlet limit, the basin side (5) of skill raised head face (8) and blade (2) and row
Gas limit (3), 0.05mm～0.15mm surplus is stayed on leading edge (5) and aerofluxus limit (3)；
2) polishing inlet and outlet limit: polishing leading edge (5) and aerofluxus limit (3), makes leading edge
And the size and dimension of aerofluxus limit (3) meets design requirement (5)；
3) line cutting blade tip and blade root: on numerically controlled wire cutting machine with the basin side of blade (2),
First false boss (6), the second false boss (7) and the second false boss end face (8) are fixed
Position clamping, processing blade tip (1) and blade root (4), remove the first false boss (6) and second
False boss (7)；
4) pincers repair: pincers repair blade tip (1) and blade root (4), removal step 3) in be retained in leaf
Line cutting remelted layer on point (1) and blade root (4), and make blade tip (1) and blade root (4)
Surface roughness meet design requirement.
A kind of aero-engine the most according to claim 1 is without installing plate Profile For Compressor Stator
Blade machining process, it is characterised in that the leading edge (5) of described blank and aerofluxus limit (3)
There is 2mm～3mm allowance.
A kind of aero-engine the most according to claim 1 is without installing plate Profile For Compressor Stator
Blade machining process, it is characterised in that described step 2) in polishing be on buffing machine use
Bob and nylon wheel are carried out.
A kind of aero-engine the most according to claim 1 is without installing plate Profile For Compressor Stator
Blade machining process, it is characterised in that described step 4) in pincers to repair be to use file and sand paper
Carry out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410583311.5A CN104308481B (en) | 2014-10-27 | 2014-10-27 | Stator blade machining method of aeroengine compressor without mounting plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410583311.5A CN104308481B (en) | 2014-10-27 | 2014-10-27 | Stator blade machining method of aeroengine compressor without mounting plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104308481A CN104308481A (en) | 2015-01-28 |
| CN104308481B true CN104308481B (en) | 2017-01-11 |
Family
ID=52363864
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410583311.5A Active CN104308481B (en) | 2014-10-27 | 2014-10-27 | Stator blade machining method of aeroengine compressor without mounting plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104308481B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108714771A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of aero-engine compressor stator blade processing method and products thereof |
Families Citing this family (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105252224B (en) * | 2015-11-19 | 2017-09-22 | 华中科技大学无锡研究院 | A kind of aero-engine outer duct outlet guide vanes processing method |
| CN105252233B (en) * | 2015-11-19 | 2017-09-05 | 华中科技大学无锡研究院 | A kind of aero-engine high temperature alloy counterweight blade machining process |
| CN106354927B (en) * | 2016-08-29 | 2019-05-10 | 西北工业大学 | A kind of construction method of precision forged blade front and rear edge adaptive machining Optimized model |
| CN106271469B (en) * | 2016-08-29 | 2018-03-30 | 中航动力股份有限公司 | A kind of processing method of the more cavity thin-wall compressor blades of elongated hollow |
| CN107520673A (en) * | 2017-08-02 | 2017-12-29 | 安吉圆磨机械科技有限公司 | A kind of centrifugal wheel technique for grinding |
| CN107520674A (en) * | 2017-08-02 | 2017-12-29 | 安吉圆磨机械科技有限公司 | A kind of centrifugal wheel polishing process |
| CN107520716A (en) * | 2017-08-02 | 2017-12-29 | 安吉圆磨机械科技有限公司 | A kind of technique for grinding of centrifugal automobile wheel |
| CN107520672A (en) * | 2017-08-02 | 2017-12-29 | 安吉圆磨机械科技有限公司 | A kind of polishing process of centrifugal automobile wheel |
| CN107984179A (en) * | 2017-11-22 | 2018-05-04 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of quick method for preparing double installing plate blades |
| CN108145393B (en) * | 2017-11-29 | 2019-10-11 | 株洲丰发精工实业有限公司 | A kind of aero-engine compressor blade and its processing method |
| CN108500574B (en) * | 2018-03-30 | 2020-02-18 | 广汉天空动力机械有限责任公司 | Process method for preparing aero-engine swirler by adopting special machining technology |
| CN108714770A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of method of engine rectification guide vane processing |
| CN108747232B (en) * | 2018-05-30 | 2020-02-11 | 中国航发动力股份有限公司 | Automatic machining method for precisely forged stator blade |
| CN109531198B (en) * | 2018-11-27 | 2020-09-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for improving machining precision of large-scale complex-structure blade and fine trimming clamp of process table |
| CN109365884A (en) * | 2018-12-17 | 2019-02-22 | 中国航发动力股份有限公司 | A kind of rotor blade tip cutting off processing method and its application |
| CN111890078A (en) * | 2020-07-24 | 2020-11-06 | 都江堰川相铝业有限公司 | Manufacturing process of machine oil pump shell |
| CN112809059B (en) * | 2020-12-22 | 2022-06-24 | 成都和鸿科技股份有限公司 | Processing method of journal type compressor blade |
| CN113369830A (en) * | 2021-06-30 | 2021-09-10 | 中国航发动力股份有限公司 | Machining method for forging low-pressure turbine blade |
| CN113977209B (en) * | 2021-12-15 | 2023-03-24 | 中国航发动力股份有限公司 | Aviation blade processing technology based on hard clamping |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102152071A (en) * | 2011-02-18 | 2011-08-17 | 常州市风机制造有限公司 | Processing technique of Roots blower impeller component |
| CN103586647A (en) * | 2013-10-14 | 2014-02-19 | 西安航空动力股份有限公司 | Forming method of aeroengine hollow guide vane |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101363327B (en) * | 2008-09-26 | 2011-08-24 | 无锡透平叶片有限公司 | Method for processing TC11 material blade |
| FR2965496B1 (en) * | 2010-09-30 | 2013-07-12 | Snecma | "MULTI-EFFECT" FORM TOOLING FOR HIGH TEMPERATURE FORMING. |
| CN102773733B (en) * | 2012-07-18 | 2014-06-11 | 西安航空动力股份有限公司 | Method and clamp for moulding surface positioning clamping of finish forge blade |
| CN102825436B (en) * | 2012-10-08 | 2015-04-22 | 南通中能机械制造有限公司 | Method for machining small moving blade of turbine |
| CN103286532B (en) * | 2013-05-13 | 2017-01-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Technique for processing stator blades |
-
2014
- 2014-10-27 CN CN201410583311.5A patent/CN104308481B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102152071A (en) * | 2011-02-18 | 2011-08-17 | 常州市风机制造有限公司 | Processing technique of Roots blower impeller component |
| CN103586647A (en) * | 2013-10-14 | 2014-02-19 | 西安航空动力股份有限公司 | Forming method of aeroengine hollow guide vane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108714771A (en) * | 2018-05-30 | 2018-10-30 | 中国航发动力股份有限公司 | A kind of aero-engine compressor stator blade processing method and products thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104308481A (en) | 2015-01-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104308481B (en) | Stator blade machining method of aeroengine compressor without mounting plate | |
| CN104028983B (en) | A kind of fir-tree root class turbine blade manufacturing process | |
| CN105269277A (en) | Method for machining arc-tooth tenon blade of aircraft engine gas compressor | |
| CN101733461A (en) | Sectional rigid milling process for integrated impeller blade | |
| CN101363327B (en) | Method for processing TC11 material blade | |
| CN107755987A (en) | A kind of processing technology of aero-engine high-pressure compressor rectifier | |
| US8826784B2 (en) | Airfoil machining method and cutting tools | |
| CN104475841A (en) | Long-cantilever large-scale integral blade-disc blade one-step milling method | |
| CN101670465B (en) | Method for machining round head blade of wind guide wheel of supercharger | |
| CN108714771A (en) | A kind of aero-engine compressor stator blade processing method and products thereof | |
| EP2050927A3 (en) | Method for restoring airfoil tip contour | |
| CN103921068A (en) | Single-curvature cover machining method | |
| CN105562717A (en) | Numerical control turning method for large deep cavity structure of aircraft engine disc part | |
| CN104475835A (en) | Blade tenon rounding mechanical processing method | |
| CN105436843A (en) | Machining process for sealing ring mold | |
| CN103203490A (en) | Processing method of five-fork blade-root moving blades with own shrouds | |
| CN205184290U (en) | Thin wall sheet metal component numerical control milling anchor clamps | |
| CN104439468B (en) | It is applicable to the milling cutter of Blisk profile layered milling moulding process | |
| CN102922397A (en) | Accessory lathe-grinding integration device for lathe machining center and use method thereof | |
| CN108115559A (en) | A kind of grinding processing method of titanium alloy component | |
| CN102528411B (en) | Method for processing cutter blades of gear hob with inserted blades | |
| CN104227103A (en) | Method for stepped symmetrical milling of thin-wall part | |
| CN102528138A (en) | Processing method of complex curved surface by adopting drum-like cutter | |
| EP1955812A1 (en) | Blade feature machining | |
| CN104772604A (en) | Processing method of steam nozzle on steam injection coverplate of steam turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC |
|
| CP01 | Change in the name or title of a patent holder | ||
| CP03 | Change of name, title or address |
Address after: Weiyang Xu Jia Wan 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |
|
| CP03 | Change of name, title or address |