CN107755987A - A kind of processing technology of aero-engine high-pressure compressor rectifier - Google Patents
A kind of processing technology of aero-engine high-pressure compressor rectifier Download PDFInfo
- Publication number
- CN107755987A CN107755987A CN201711187562.1A CN201711187562A CN107755987A CN 107755987 A CN107755987 A CN 107755987A CN 201711187562 A CN201711187562 A CN 201711187562A CN 107755987 A CN107755987 A CN 107755987A
- Authority
- CN
- China
- Prior art keywords
- blade
- processing
- milling
- aero
- 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.)
- Pending
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
Abstract
The present invention discloses a kind of processing technology of aero-engine high-pressure compressor rectifier, and blade stable processing half finishing processing finish-milling blade polishing blade profile vibration finishing finishing processing intermediate survey wire cutting final inspection is rough milled using the rough turn processing of integral ring-shaped forging.The integral processing technique is simple, and for part without deformation, blade profile dispersion is small, adjustable height compressor efficiency, saves processing cost, shortens the process-cycle.
Description
Technical field
The present invention relates to aero-engine technology field, more particularly to a kind of aero-engine high-pressure compressor rectifier
Processing technology.
Background technology
Certain type machine high-pressure compressor rectifier is the part that overall leaf joint new construction is used in aero-engine, and the high temperature closes
The overall leaf joint part of gold is made up of inner ring, outer shroud and blade three parts, and the inner ring and outer rings of part are thin-wall construction, blade position
For typical cavity structure, blade and runner molding surface size and Geometrical Tolerance Principle are strict.Former the type part uses non-integral
Processing method, it is roughly divided into two ways：When the T-shaped plate of single blade+fan-shaped section+fan-shaped section edge-bending plate, using soldering processes
It is welded；Second, the processing of single blade blade is in place, listrium leaves surplus, using vacuum brazing into Combined machining after fan-shaped section
End-state is arrived at listrium.Above-mentioned 2 kinds of processing schemes are related to that technology category is more, technological process is long, brazing deformation is difficult to control, past
It is past to be delivered with overproof.
The content of the invention
In order to solve the above technical problems, it is an object of the invention to provide a kind of aero-engine high-pressure compressor rectifier
Processing technology, concrete technical scheme are as follows：
A kind of processing technology of aero-engine high-pressure compressor rectifier, is added using integral ring-shaped forging-numerical control
Into the processing technology of fan-shaped section, specific processing technology is as follows for work-wire cutting：
Step 1：According to the material requirements of part, the bar of same material is selected to be rolled, at solid solution, timeliness heat
Reason, reaches part performance requirement；Woollen is loop configuration, and each size meets the requirement before part roughing, and is visited through ultrasonic wave
Delivered after wound；
Step 2：Rough turn processing, big surplus is removed, copying is carried out to part, guarantee type face is left uniformly after processing
Surplus, prepared for finishing processing；
Step 3：Blade is rough milled, roughing is carried out to blade, the requirement according to the selection of process equipment and to efficiency, added
Each position of work rear blade retains uniform surplus as far as possible；
Step 4：Stable processing, takes vacuum heat, the inside parts stress after roughing is handled；
Step 5：Half finishing processing, to eliminate caused deformation after stable processing, machining benchmark is repaired, for essence
Milling blade is prepared；
Step 6：Finish-milling blade, blade process without surplus, in addition to roughness, all sizes of processing rear blade and
Technical conditions meet design drawing requirement；
Step 7：Blade profile is polished, ensures that blade roughness tends to meet design drawing requirement；
Step 8：Vibration finishing, ensure that blade roughness meets design drawing requirement, removal amount is not more than 0.005mm；
Step 9：Finishing processing, internal, outer annular surface carry out finishing processing, ensure that all sizes and technical conditions meet
Design drawing requirement；
Step 10：Intermediate survey, check that all sizes of part and technical conditions meet design drawing requirement；
Step 11：Wire cutting, the domain is cut into fan-shaped section, and meet fitted position requirement；
Step 12：Final inspection, detected to cutting into size and technical conditions after fan-shaped section.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, it is characterised in that：It is rough turn to add
After work 1mm surpluses are left to finishing processing；
Finish-milling blade leaves the uneven surpluses of 0.5mm-0.7mm after rough milling blade；
Surface surplus is 0mm after finish-milling blade.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, its preferred scheme are Vehicle Processing
Equipment, select numerical control vertical lathe or numerical control sleeping carriage.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, its preferred scheme are blade milling
Processing need to be selected with 5-axis machining center equipment；
Milling Machining process route is as follows：Rough mill leading edge blade-rough mill exhaust side blade-finish-milling leading edge blade-finish-milling
It is vented side blade.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, its preferred scheme add for finish-milling
Taper ball head milling cutter of the man-hour selection with necking down is processed.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, its preferred scheme are vibration light
Adorn selection center and adorn equipment without island whirling vibration light, by fixture by part in equipment it is fixed, part away from device bottom away from
From for 100mm ± 5mm, abrasive material submergence blade top edges average height is 80mm ± 10mm.
Beneficial effects of the present invention：Technical scheme uses overall leaf joint structure, and the process is that one kind can
Row efficiently solves the process of high temperature alloy entirety leaf joint processing, the process, it is ensured that the part tool after processing
There is small, the blade profile dispersion of deformation small and shorten part process cycle, this technology can also be applied to other materials entirety leaf joint
Processing.
Brief description of the drawings
Fig. 1 is overall leaf joint part schematic diagram；
Fig. 2 is necking down ball cutter schematic diagram；
Fig. 3 is woollen schematic diagram；
Fig. 4 is woollen dimensional drawing；
Fig. 5 is allowance figure；
Embodiment
A kind of processing technology of aero-engine high-pressure compressor rectifier, use are integral ring-shaped as Figure 1-5
Into the processing technology of fan-shaped section, specific processing technology is as follows for forging-digital control processing-wire cutting：
Step 1：According to the material requirements of part, the bar of same material is selected to be rolled, at solid solution, timeliness heat
Reason, reaches part performance requirement；Woollen is loop configuration, and each size meets the requirement before part roughing, and is visited through ultrasonic wave
Delivered after wound；
Step 2：Rough turn processing, big surplus is removed, copying is carried out to part, guarantee type face is left uniformly after processing
Surplus, prepared for finishing processing；
Step 3：Blade is rough milled, roughing is carried out to blade, the requirement according to the selection of process equipment and to efficiency, added
Each position of work rear blade retains uniform surplus as far as possible；
Step 4：Stable processing, takes vacuum heat, the inside parts stress after roughing is handled；
Step 5：Half finishing processing, to eliminate caused deformation after stable processing, machining benchmark is repaired, for essence
Milling blade is prepared；
Step 6：Finish-milling blade, blade process without surplus, in addition to roughness, all sizes of processing rear blade and
Technical conditions meet design drawing requirement；
Step 7：Blade profile is polished, ensures that blade roughness tends to meet design drawing requirement；
Step 8：Vibration finishing, ensure that blade roughness meets design drawing requirement, removal amount is not more than 0.005mm；
Step 9：Finishing processing, internal, outer annular surface carry out finishing processing, ensure that all sizes and technical conditions meet
Design drawing requirement；
Step 10：Intermediate survey, check that all sizes of part and technical conditions meet design drawing requirement；
Step 11：Wire cutting, the domain is cut into fan-shaped section, and meet fitted position requirement；
Step 12：Final inspection, detected to cutting into size and technical conditions after fan-shaped section.
A kind of processing technology of described aero-engine high-pressure compressor rectifier, it is characterised in that：It is rough turn to add
After work 1mm surpluses are left to finishing processing；
Finish-milling blade leaves the uneven surpluses of 0.5mm-0.7mm after rough milling blade；
Surface surplus is 0mm after finish-milling blade.
The equipment of Vehicle Processing, select numerical control vertical lathe or numerical control sleeping carriage.
Blade Milling Machining need to be selected with 5-axis machining center equipment；
Milling Machining process route is as follows：Rough mill leading edge blade-rough mill exhaust side blade-finish-milling leading edge blade-finish-milling
It is vented side blade.
Taper ball head milling cutter of the selection with necking down is processed when finish-milling is processed.
Vibration finishing selects center to adorn equipment without island whirling vibration light, by fixture by part in equipment it is fixed, zero
Part is 100mm ± 5mm away from device bottom distance, and abrasive material submergence blade top edges average height is 80mm ± 10mm.
Claims (6)
- A kind of 1. processing technology of aero-engine high-pressure compressor rectifier, it is characterised in that：Using integral loop die forging Into the processing technology of fan-shaped section, specific processing technology is as follows for part-digital control processing-wire cutting：Step 1：According to the material requirements of part, select the bar of same material to be rolled, by solid solution, aging strengthening model, reach To part performance requirement；Woollen is loop configuration, and each size meets the requirement before part roughing, and is handed over after ultrasonic examination Pay；Step 2：Rough turn processing, big surplus being removed, copying is carried out to part, uniform surplus is left in guarantee type face after processing, Prepared for finishing processing；Step 3：Blade is rough milled, roughing, the requirement according to the selection of process equipment and to efficiency, after processing are carried out to blade Each position of blade retains uniform surplus as far as possible；Step 4：Stable processing, takes vacuum heat, the inside parts stress after roughing is handled；Step 5：Half finishing processing, to eliminate caused deformation after stable processing, machining benchmark is repaired, is finish-milling leaf Piece is prepared；Step 6：Finish-milling blade, blade process without surplus, in addition to roughness, all sizes of processing rear blade and technology Condition meets design drawing requirement；Step 7：Blade profile is polished, ensures that blade roughness tends to meet design drawing requirement；Step 8：Vibration finishing, ensure that blade roughness meets design drawing requirement, removal amount is not more than 0.005mm；Step 9：Finishing processing, internal, outer annular surface carry out finishing processing, ensure that all sizes and technical conditions meet design Figure requires；Step 10：Intermediate survey, check that all sizes of part and technical conditions meet design drawing requirement；Step 11：Wire cutting, the domain is cut into fan-shaped section, and meet fitted position requirement；Step 12：Final inspection, detected to cutting into size and technical conditions after fan-shaped section.
- 2. a kind of processing technology of aero-engine high-pressure compressor rectifier as claimed in claim 1, its feature exist In：After rough turn processing 1mm surpluses are left to finishing processing；Finish-milling blade leaves the uneven surpluses of 0.5mm-0.7mm after rough milling blade；Surface surplus is 0mm after finish-milling blade.
- 3. a kind of processing technology of aero-engine high-pressure compressor rectifier as claimed in claim 1, its feature exist In：The equipment of Vehicle Processing, select numerical control vertical lathe or numerical control sleeping carriage.
- 4. a kind of processing technology of aero-engine high-pressure compressor rectifier as claimed in claim 1, its feature exist In：Blade Milling Machining need to be selected with 5-axis machining center equipment；Milling Machining process route is as follows：Rough mill leading edge blade-rough mill exhaust side blade-finish-milling leading edge blade-finish-milling exhaust Side blade.
- 5. a kind of processing technology of aero-engine high-pressure compressor rectifier as claimed in claim 1, its feature exist In：Taper ball head milling cutter of the selection with necking down is processed when finish-milling is processed.
- 6. a kind of processing technology of aero-engine high-pressure compressor rectifier as claimed in claim 1, its feature exist In：Vibration finishing selects center to adorn equipment without island whirling vibration light, by fixture by part in equipment it is fixed, part is away from setting Standby distance from bottom is 100mm ± 5mm, and abrasive material submergence blade top edges average height is 80mm ± 10mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711187562.1A CN107755987A (en) | 2017-11-24 | 2017-11-24 | A kind of processing technology of aero-engine high-pressure compressor rectifier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711187562.1A CN107755987A (en) | 2017-11-24 | 2017-11-24 | A kind of processing technology of aero-engine high-pressure compressor rectifier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107755987A true CN107755987A (en) | 2018-03-06 |
Family
ID=61276025
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711187562.1A Pending CN107755987A (en) | 2017-11-24 | 2017-11-24 | A kind of processing technology of aero-engine high-pressure compressor rectifier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107755987A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108500574A (en) * | 2018-03-30 | 2018-09-07 | 广汉天空动力机械有限责任公司 | A kind of process preparing aero-engine cyclone using special processing technology |
| CN110860953A (en) * | 2019-11-27 | 2020-03-06 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration finishing processing method for high-temperature alloy disc parts |
| CN110936110A (en) * | 2019-11-29 | 2020-03-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining process method for semi-ring parts |
| CN111774823A (en) * | 2020-07-17 | 2020-10-16 | 四川布蕾德机械制造有限公司 | Method for machining stator blade of aircraft engine |
| CN112548497A (en) * | 2020-11-30 | 2021-03-26 | 重庆市星极齿轮有限责任公司 | Integral machining process for sliding block of mechanical arm |
| CN112872731A (en) * | 2021-01-16 | 2021-06-01 | 江苏赛德力制药机械制造有限公司 | Manufacturing process of annular thin plate with wedge-shaped section |
| CN113915165A (en) * | 2021-11-05 | 2022-01-11 | 湖南南方通用航空发动机有限公司 | Compressor stator blade ring and processing method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101590587A (en) * | 2008-05-29 | 2009-12-02 | 上海电气集团股份有限公司 | A kind of integral impeller processing method |
| CN103317427A (en) * | 2013-05-23 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Protection method for blisk vibration finishing |
| CN105415162A (en) * | 2015-11-19 | 2016-03-23 | 沈阳黎明航空发动机(集团)有限责任公司 | High-accuracy surface fine machining and finish machining method for thin-wall wheel discs |
| CN105904169A (en) * | 2016-05-03 | 2016-08-31 | 上海应用技术学院 | Manufacturing process of ultra-long blade complex curved surface integral impeller made of aluminum alloy material |
| EP3081669A1 (en) * | 2015-04-17 | 2016-10-19 | Hermle Maschinenbau GmbH | Method for the preparation of capped impellers |
| CN106513804A (en) * | 2016-11-29 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Milling method of blade of high-temperature alloy whole blade ring |
| CN106670359A (en) * | 2016-12-01 | 2017-05-17 | 西北工业大学 | GH4169 alloy ring piece and preparation method thereof |
-
2017
- 2017-11-24 CN CN201711187562.1A patent/CN107755987A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101590587A (en) * | 2008-05-29 | 2009-12-02 | 上海电气集团股份有限公司 | A kind of integral impeller processing method |
| CN103317427A (en) * | 2013-05-23 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Protection method for blisk vibration finishing |
| EP3081669A1 (en) * | 2015-04-17 | 2016-10-19 | Hermle Maschinenbau GmbH | Method for the preparation of capped impellers |
| CN105415162A (en) * | 2015-11-19 | 2016-03-23 | 沈阳黎明航空发动机(集团)有限责任公司 | High-accuracy surface fine machining and finish machining method for thin-wall wheel discs |
| CN105904169A (en) * | 2016-05-03 | 2016-08-31 | 上海应用技术学院 | Manufacturing process of ultra-long blade complex curved surface integral impeller made of aluminum alloy material |
| CN106513804A (en) * | 2016-11-29 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Milling method of blade of high-temperature alloy whole blade ring |
| CN106670359A (en) * | 2016-12-01 | 2017-05-17 | 西北工业大学 | GH4169 alloy ring piece and preparation method thereof |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108500574A (en) * | 2018-03-30 | 2018-09-07 | 广汉天空动力机械有限责任公司 | A kind of process preparing aero-engine cyclone using special processing technology |
| CN110860953A (en) * | 2019-11-27 | 2020-03-06 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration finishing processing method for high-temperature alloy disc parts |
| CN110860953B (en) * | 2019-11-27 | 2021-04-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Vibration finishing processing method for high-temperature alloy disc parts |
| CN110936110A (en) * | 2019-11-29 | 2020-03-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining process method for semi-ring parts |
| CN110936110B (en) * | 2019-11-29 | 2022-03-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Machining process method for semi-ring parts |
| CN111774823A (en) * | 2020-07-17 | 2020-10-16 | 四川布蕾德机械制造有限公司 | Method for machining stator blade of aircraft engine |
| CN112548497A (en) * | 2020-11-30 | 2021-03-26 | 重庆市星极齿轮有限责任公司 | Integral machining process for sliding block of mechanical arm |
| CN112548497B (en) * | 2020-11-30 | 2021-11-19 | 重庆市星极齿轮有限责任公司 | Integral machining process for sliding block of mechanical arm |
| CN112872731A (en) * | 2021-01-16 | 2021-06-01 | 江苏赛德力制药机械制造有限公司 | Manufacturing process of annular thin plate with wedge-shaped section |
| CN113915165A (en) * | 2021-11-05 | 2022-01-11 | 湖南南方通用航空发动机有限公司 | Compressor stator blade ring and processing method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107755987A (en) | A kind of processing technology of aero-engine high-pressure compressor rectifier | |
| CN104308481B (en) | Stator blade machining method of aeroengine compressor without mounting plate | |
| CN102717115B (en) | High-speed intermittent ultrasonic vibration cutting method for low-rigidity parts | |
| CN107717030B (en) | A kind of processing method of the long boss of Titanium alloy TA15 thin-walled | |
| CN104148894A (en) | Machining method of thin-walled deep-hole welded workpieces | |
| CN108274202A (en) | A kind of processing technology of deep hole thin-wall part | |
| CN104439452B (en) | A kind of interior grid surface high-efficient milling method of taper revolving body | |
| KR100845873B1 (en) | Method for producing forging die | |
| CN106392491B (en) | A kind of Complex compressor blade is into row's side processing method | |
| CN102999011A (en) | High-temperature alloy thin-wall case numerical-control lathing method | |
| CN110587246B (en) | Manufacturing process of external tooth cylinder type broach finish cutting gear cutter head | |
| CN105562717A (en) | Numerical control turning method for large deep cavity structure of aircraft engine disc part | |
| CN104801935B (en) | Plane aluminium alloy abnormal shape cockpit processing method | |
| CN109926894A (en) | Turbine disc mortise form grinding process equipment and its application method | |
| CN104668901A (en) | Method for machining elastic expansion ring workpiece | |
| CN105081701B (en) | A kind of processing method of Idiotype punching pin | |
| CN105290475B (en) | A kind of titanium alloy fan blade profile milling method | |
| CN105397162A (en) | High-precision complex curved surface processing method for titanium alloy material | |
| CN104014989A (en) | Semi-circular hole machining method | |
| CN108115354B (en) | A kind of process controlling thin-walled semicircular ring machining deformation | |
| CN105252222B (en) | A kind of processing method for small size spout sphere | |
| CN104772604A (en) | Processing method of steam nozzle on steam injection coverplate of steam turbine | |
| CN105364431A (en) | Process flow for machining lower punching die | |
| CN110253233A (en) | A kind of processing technology for casing class part | |
| CN110227969B (en) | Processing method for grinding short hole by using grinding rod with large length-diameter ratio and weak rigidity |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180306 |