CN103464989A - Processing technique of precision turbine parts - Google Patents

Processing technique of precision turbine parts Download PDF

Info

Publication number
CN103464989A
CN103464989A CN2013104192769A CN201310419276A CN103464989A CN 103464989 A CN103464989 A CN 103464989A CN 2013104192769 A CN2013104192769 A CN 2013104192769A CN 201310419276 A CN201310419276 A CN 201310419276A CN 103464989 A CN103464989 A CN 103464989A
Authority
CN
China
Prior art keywords
processing
grinding
milling
outlet
diameter phi
Prior art date
Application number
CN2013104192769A
Other languages
Chinese (zh)
Inventor
徐汇音
Original Assignee
苏州大学
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 苏州大学 filed Critical 苏州大学
Priority to CN2013104192769A priority Critical patent/CN103464989A/en
Publication of CN103464989A publication Critical patent/CN103464989A/en

Links

Abstract

The invention discloses a processing technique of precision turbine parts. The processing technique includes following steps: milling and rough machining, large balance removing, hexahedron grinding, milling of various holes, heat treating of the parts, molding and grinding of an upper large face and a lower large face, wire cut electrical discharge machining, internal and external grinding machine processing, molding and grinding, molding and milling, numerical control turning, text carving, electrical spark molding and product testing. After heat treatment, a material adopted by the processing technique is remarkable in abrasion resistance and durability, can reach a higher mirror face degree, is outstanding in processing of decoration flowers, small in scale change of the heat treatment and fine in ductility, and processing quality is guaranteed and production efficiency is improved.

Description

A kind of processing technology of accurate turbine components
Technical field
The present invention relates to the fine finishining field of machine components, what be specifically related to is a kind of processing technology of accurate turbine components.
Background technology
Turbine is a kind of rotary power machinery that is mechanical energy by the power conversion of flow working medium, be widely used in the fields such as aero-engine, gas turbine, steam turbine, processing raw material hardness number after high temperature commonly used is lower, cause the quality of processing to can not get ensureing, the used time is also very long.
Summary of the invention
The object of the invention is to overcome the above problem that prior art exists, a kind of processing technology of accurate turbine components is provided, be applicable to the high microsize part of baroque required precision.
For realizing above-mentioned technical purpose, reach above-mentioned technique effect, the present invention is achieved through the following technical solutions:
A kind of processing technology of accurate turbine components comprises the following steps:
Step 1) milling roughing, remove large surplus
According to the dimensional drawing of part, the hexahedron that mills out part is of a size of 55.05 * 55.05 * 49.25(mm);
Step 2) grinding hexahedron
After grinding rear surface roughness is Ra0.8~0.2 μ m, two interplanar dimensional tolerance grades can reach IT6~IT5, and flatness can reach 0.01~0.03mm/m, and fine grinding is removed surplus 0.05mm, the size 55 * 55 * 49.2 after fine grinding;
Each hole system of step 3) Milling Process
1, bottom outlet φ 1.500 mm sizes are drilled into to diameter phi 1.2 mm, and φ 2.0 mm holes are bored in processing;
2, respectively 2 bottom outlet φ, 2.500 mm sizes are drilled into to diameter phi 2.2 mm, and the φ dark 35mm of 3.0 mm hole is bored in processing;
3, bottom outlet φ 5.600 mm sizes are drilled into to diameter phi 5.0 mm, and chamfering C0.5 mm;
The heat treatment of step 4) part
Lonneal again after adopt quenching, hardness number reaches HRC58;
The step 5) form grinding
Upper and lower two the large faces of grinding, be ground to 49.1mm by gauge, and surface roughness is Ra0.8~0.2 μ m;
Step 6) line cutting processing
1, bottom outlet φ 1.2 mm size electricity cremate lines are cut to φ 1.500 mm holes;
2, respectively 2 bottom outlet φ, 2. 2 mm size electricity cremate lines are cut to φ 2.500 mm holes;
3, bottom outlet φ 5.0 mm size electricity cremate lines are cut to φ 5.600 mm holes;
4, electric cremate line cutting φ 24.400 mm cylindrical shapes, cutting openings groove, once success simultaneously;
The processing of step 7) internal and external grinding machine
1, mill diameter phi 24.400 mm cylindricals;
2, grinding diameter phi 5.6 mm endoporus sections;
3, cylindricalo grinding 5um exhaust, size is to 40.27-0.3 mm;
The step 8) form grinding
The wide 3mm groove of grinding
The step 9) moulding
Milling annular row air drain, utilize the disk forming milling tool; The dark 0.3mm air discharge duct of milling 2.0mm;
The processing of step 10) numerical control turning
1, numerical control turning processing φ 23.16 mm conical external circles, will highly be machined to 48.46 mm;
2, spark discharge is processed diameter phi 7.150 mm, is about the 11mm circular hole, the end fillet;
The processing of step 11) numerical control milling
Text engraving
The step 12) Electric Discharge Machining
Spark discharge processing top groove;
The step 13) dimensional gaughing.
Further, described step 3 adopts the processing method of boring a line cutting.
Further, described step 6 adopts the cutting of slow wire feeding electricity cremate line.
The invention has the beneficial effects as follows:
After the material heat treatment that the present invention adopts, wearability and durability are outstanding, can reach higher mirror face degree, and erosion flower processability is outstanding, and the heat treatment change in size is less, and good toughness has guaranteed the quality of processing, and has improved production efficiency.
The accompanying drawing explanation
Fig. 1 is part drawing of the present invention;
The key dimension that Fig. 2 is part.
The specific embodiment
Below with reference to the accompanying drawings and in conjunction with the embodiments, describe the present invention in detail.
Shown in Fig. 1, a kind of processing technology of accurate turbine components comprises the following steps:
Step 1) milling roughing, remove large surplus
According to the dimensional drawing of part, the hexahedron that mills out part is of a size of 55.05 * 55.05 * 49.25(mm);
Step 2) grinding hexahedron
After grinding rear surface roughness is Ra0.8~0.2 μ m, two interplanar dimensional tolerance grades can reach IT6~IT5, and flatness can reach 0.01~0.03mm/m, and fine grinding is removed surplus 0.05mm, the size 55 * 55 * 49.2 after fine grinding;
Each hole system of step 3) Milling Process, as shown in Figure 2,
1, bottom outlet φ 1.500 mm sizes are drilled into to diameter phi 1.2 mm, and φ 2.0 mm holes are bored in processing;
2, respectively 2 bottom outlet φ, 2.500 mm sizes are drilled into to diameter phi 2.2 mm, and the φ dark 35mm of 3.0 mm hole is bored in processing;
3, bottom outlet φ 5.600 mm sizes are drilled into to diameter phi 5.0 mm, and chamfering C0.5 mm;
The heat treatment of step 4) part
Lonneal again after adopt quenching, hardness number reaches HRC58;
The step 5) form grinding
Upper and lower two the large faces of grinding, be ground to 49.1mm by gauge, and surface roughness is Ra0.8~0.2 μ m;
Step 6) line cutting processing
1, bottom outlet φ 1.2 mm size electricity cremate lines are cut to φ 1.500 mm holes;
2, respectively 2 bottom outlet φ, 2. 2 mm size electricity cremate lines are cut to φ 2.500 mm holes;
3, bottom outlet φ 5.0 mm size electricity cremate lines are cut to φ 5.600 mm holes;
4, electric cremate line cutting φ 24.400 mm cylindrical shapes, cutting openings groove, once success simultaneously;
The processing of step 7) internal and external grinding machine
1, mill diameter phi 24.400 mm cylindricals;
2, grinding diameter phi 5.6 mm endoporus sections;
3, cylindricalo grinding 5um exhaust, size is to 40.27-0.3 mm;
The step 8) form grinding
The wide 3mm groove of grinding
The step 9) moulding
Milling annular row air drain, utilize the disk forming milling tool; The dark 0.3mm air discharge duct of milling 2.0mm;
The processing of step 10) numerical control turning
1, numerical control turning processing φ 23.16 mm conical external circles, will highly be machined to 48.46 mm;
2, spark discharge is processed diameter phi 7.150 mm, is about the 11mm circular hole, the end fillet;
The processing of step 11) numerical control milling
Text engraving
The step 12) Electric Discharge Machining
Spark discharge processing top groove;
The step 13) dimensional gaughing.
Further, described step 3 adopts the processing method of boring a line cutting.
Further, described step 6 adopts the cutting of slow wire feeding electricity cremate line.

Claims (3)

1. the processing technology of an accurate turbine components, is characterized in that, comprises the following steps:
Step 1) milling roughing, remove large surplus
According to the dimensional drawing of part, the hexahedron that mills out part is of a size of 55.05 * 55.05 * 49.25(mm);
Step 2) grinding hexahedron
After grinding rear surface roughness is Ra0.8~0.2 μ m, two interplanar dimensional tolerance grades can reach IT6~IT5, and flatness can reach 0.01~0.03mm/m, and fine grinding is removed surplus 0.05mm, the size 55 * 55 * 49.2 after fine grinding;
Each hole system of step 3) Milling Process
1, bottom outlet φ 1.500 mm sizes are drilled into to diameter phi 1.2 mm, and φ 2.0 mm holes are bored in processing;
2, respectively 2 bottom outlet φ, 2.500 mm sizes are drilled into to diameter phi 2.2 mm, and the φ dark 35mm of 3.0 mm hole is bored in processing;
3, bottom outlet φ 5.600 mm sizes are drilled into to diameter phi 5.0 mm, and chamfering C0.5 mm;
The heat treatment of step 4) part
Lonneal again after adopt quenching, hardness number reaches HRC58;
The step 5) form grinding
Upper and lower two the large faces of grinding, be ground to 49.1mm by gauge, and surface roughness is Ra0.8~0.2 μ m;
Step 6) line cutting processing
1, bottom outlet φ 1.2 mm size electricity cremate lines are cut to φ 1.500 mm holes;
2, respectively 2 bottom outlet φ, 2. 2 mm size electricity cremate lines are cut to φ 2.500 mm holes;
3, bottom outlet φ 5.0 mm size electricity cremate lines are cut to φ 5.600 mm holes;
4, electric cremate line cutting φ 24.400 mm cylindrical shapes, cutting openings groove, once success simultaneously;
The processing of step 7) internal and external grinding machine
1, mill diameter phi 24.400 mm cylindricals;
2, grinding diameter phi 5.6 mm endoporus sections;
3, cylindricalo grinding 5um exhaust, size is to 40.27-0.3 mm;
The step 8) form grinding
The wide 3mm groove of grinding
The step 9) moulding
Milling annular row air drain, utilize the disk forming milling tool; The dark 0.3mm air discharge duct of milling 2.0mm;
The processing of step 10) numerical control turning
1, numerical control turning processing φ 23.16 mm conical external circles, will highly be machined to 48.46 mm;
2, spark discharge is processed diameter phi 7.150 mm, is about the 11mm circular hole, the end fillet;
The processing of step 11) numerical control milling
Text engraving
The step 12) Electric Discharge Machining
Spark discharge processing top groove;
The step 13) dimensional gaughing.
2. the processing technology of accurate turbine components according to claim 1, is characterized in that: the processing method that described step 3 adopts brill one line to cut.
3. the processing technology of accurate turbine components according to claim 1, is characterized in that: the cutting of described step 6 employing slow wire feeding electricity cremate line.
CN2013104192769A 2013-09-16 2013-09-16 Processing technique of precision turbine parts CN103464989A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN2013104192769A CN103464989A (en) 2013-09-16 2013-09-16 Processing technique of precision turbine parts

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2013104192769A CN103464989A (en) 2013-09-16 2013-09-16 Processing technique of precision turbine parts

Publications (1)

Publication Number Publication Date
CN103464989A true CN103464989A (en) 2013-12-25

Family

ID=49790153

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2013104192769A CN103464989A (en) 2013-09-16 2013-09-16 Processing technique of precision turbine parts

Country Status (1)

Country Link
CN (1) CN103464989A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104588984A (en) * 2014-11-28 2015-05-06 江西洪都航空工业集团有限责任公司 Processing technology for stop dog cover
CN104827147A (en) * 2015-05-29 2015-08-12 东莞豪顺家具有限公司 Machining technology for punching display screen backboard
CN105583581A (en) * 2015-12-17 2016-05-18 沈阳鼓风机集团齿轮压缩机有限公司 Machining method and device for bearing standard block

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4576770A (en) * 1982-04-01 1986-03-18 General Electric Co. Method of manufacturing a turbomachinery rotor
DE19544817A1 (en) * 1995-12-01 1997-06-05 Asea Brown Boveri Manufacturing method for guide vane segments for gas-turbine
CN1810427A (en) * 2005-01-28 2006-08-02 三星Techwin株式会社 Method and apparatus for electric-discharge machining of a turbine blade
CN101774114A (en) * 2009-12-23 2010-07-14 煤炭科学研究总院太原研究院 Manufacturing method of turbine of copper alloy coupler
CN102861956A (en) * 2012-09-20 2013-01-09 清华大学 Machining method of gravity-free smelting layer air membrane hole of aviation engine turbine blade

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4576770A (en) * 1982-04-01 1986-03-18 General Electric Co. Method of manufacturing a turbomachinery rotor
DE19544817A1 (en) * 1995-12-01 1997-06-05 Asea Brown Boveri Manufacturing method for guide vane segments for gas-turbine
CN1810427A (en) * 2005-01-28 2006-08-02 三星Techwin株式会社 Method and apparatus for electric-discharge machining of a turbine blade
CN101774114A (en) * 2009-12-23 2010-07-14 煤炭科学研究总院太原研究院 Manufacturing method of turbine of copper alloy coupler
CN102861956A (en) * 2012-09-20 2013-01-09 清华大学 Machining method of gravity-free smelting layer air membrane hole of aviation engine turbine blade

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
徐汇音: "精密涡轮零件的加工工艺分析", 《机床与液压》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104588984A (en) * 2014-11-28 2015-05-06 江西洪都航空工业集团有限责任公司 Processing technology for stop dog cover
CN104588984B (en) * 2014-11-28 2017-07-21 江西洪都航空工业集团有限责任公司 A kind of cover of retainer processing technology
CN104827147A (en) * 2015-05-29 2015-08-12 东莞豪顺家具有限公司 Machining technology for punching display screen backboard
CN105583581A (en) * 2015-12-17 2016-05-18 沈阳鼓风机集团齿轮压缩机有限公司 Machining method and device for bearing standard block

Similar Documents

Publication Publication Date Title
CN102806443B (en) Numerically-controlled processing method of nozzle housing piece
KR100845873B1 (en) Method for producing forging die
CN101856784B (en) Machining process of train body profile mold
CN104015016B (en) The processing method of thin-walled deep-recessed part in high precision
CN102091919B (en) Machining method of three-dimensional closed impeller
CN104084773A (en) Machining process of axial-flow type turbine blade
CN105458626A (en) Machining control method for aero-engine fuel nozzle part
CN102922244A (en) Processing method for realizing integrity of surface of titanium alloy impeller
CN101284294B (en) Silicon steel sheet punching die blade blocks processing technique
CN100431774C (en) Making process of gear box casing for centrifugal compressor
CN103464996A (en) Die production process
CN200963702Y (en) Composite cutter for processing hole
CN103433711A (en) Processing process of shell
CN101767218A (en) Five-axis plunge milling method of aeroengine crankcase
CN204524307U (en) Tool-rest of Numerical Control Lathe water injector structure
CN103111812A (en) Processing method of turbine axial blade
CN106425286A (en) Machining method for deformation control of high-precision thin-wall cylinder shaft
CN104148902A (en) Machining method benefiting to hole boring quality and bearing base mechanical property
CN104191185B (en) A kind of processing technology without through hole miniature turbine
CN102357773A (en) Processing method for preventing bar-shaped thin-wall part from deforming
CN104028782A (en) Lathe machining method for end face deep narrow groove in aerial engine crankcase
CN102303221B (en) Method for processing female die with large square hole
CN101745673A (en) Processing method of turbo machine rotor wheel groove and milling cutter
CN103447833A (en) PTFE (polytetrafluoroethylene) plastic rotating sleeve machining method
CN106695248B (en) The manufacturing method of cylinder cover for diesel engine

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20131225

C02 Deemed withdrawal of patent application after publication (patent law 2001)