CN103111814A - Numerical control machining method of aero-engine disc-shaft integrated structure part - Google Patents

Numerical control machining method of aero-engine disc-shaft integrated structure part Download PDF

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Publication number
CN103111814A
CN103111814A CN2013100022877A CN201310002287A CN103111814A CN 103111814 A CN103111814 A CN 103111814A CN 2013100022877 A CN2013100022877 A CN 2013100022877A CN 201310002287 A CN201310002287 A CN 201310002287A CN 103111814 A CN103111814 A CN 103111814A
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China
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machining
lathe
processing
numerical control
turn
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CN2013100022877A
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Chinese (zh)
Inventor
韩德印
潘玉良
赵明
沈志云
张旭
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沈阳黎明航空发动机(集团)有限责任公司
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Priority to CN2013100022877A priority Critical patent/CN103111814A/en
Publication of CN103111814A publication Critical patent/CN103111814A/en

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Abstract

Disclosed is a numerical control machining method of an aero-engine disc-shaft integrated structure part. Main machining processes of the part are four procedures of die forging, rough machining of a big end, rough machining of a small end, vacuum stress relief heat treatment, finish machining of a molded surface of the big end, and finish machining of a molded surface of the small end, and two sets of special clamps are needed. A turn-milling composite machining center with double main shafts is adopted to replace an original ordinary lathe, a numerical control lathe, a five-coordinate machining center and other devices to machine the part, when finish turning machining is carried out, an online measuring function of the turn-milling composite machining center is adopted to carry out part size measurement and automatic compensation of cutter compensation of a cutter, a cutter compensation deviation value is automatically calculated by the numerical control lathe and input into a lathe cutter wear value, the automatic compensation is carried out, and finished size machining of the part is finished. The numerical control machining method of the aero-engine disc-shaft integrated structure part has the advantages that a machining process is stable, quality is improved, once submit qualified rate of the part is obviously improved, single-set machining cycle is reduced by more than 100 hours, production efficiency is improved by 35%, and a solid foundation is laid for machining a part with a homogeneous structure on the turn-milling composite machining center.

Description

A kind of aero-engine dish axle integrative-structure part by numerical control processing method

Technical field

The present invention relates to the Computerized Numerical Control processing technology field, particularly a kind of aero-engine dish axle integrative-structure part by numerical control processing method.

Background technology

Aero-engine dish axle integrative-structure part is the parts with complex structures that comprises disk-like accessory and axle journal class part dual structure feature, blank is forging part, the difficult machining titanium alloy material of material, owing to having the strict dark chamber of thin-wall construction wall thickness and thin web pattern engine disk body on this part, more than 30 with reference position and the strict PRECISION HOLE of geometric accuracy, therefore, difficulty of processing is very big.Disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating, originally adopt common equipment and numerical control device combination processing, be subjected to design of part restriction to take car, the process equipment such as to mill more, machining process route is long, production cycle is long, be difficult to guarantee the schedule requirement produced in batches, at car and mill that between process equipment, frequent transitions parts size precision and positional precision are difficult to guarantee.

Summary of the invention

The objective of the invention is in the clamped one time process, complete the processing at dark chamber, plate convergence plate endoporus, dish end face and a plurality of positions such as cylindrical profile and PRECISION HOLE between part axle journal and disk body, to solve part process-cycle length, to use the technical problems such as frock is many, the part qualification rate is low, the spy provides a kind of aero-engine dish axle integrative-structure part by numerical control processing method.

The invention provides a kind of aero-engine dish axle integrative-structure part by numerical control processing method, it is characterized in that: described aero-engine dish axle integrative-structure part by numerical control processing method is as follows:

Part disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating; The main manufacturing procedure of part: the large end of the forging part → roughing → roughing small end → vacuum large end profile of heat treatment → fine finishining → fine finishining small end totally 4 procedures of escaping by luck that eliminate stress need 2 cover special fixtures; The turn-milling complex machining center that employing has two main shafts replaces the equipment processing parts such as original engine lathe, numerically controlled lathe and five-axis machining center; The pressure that uses turnning and milling complex centre lathe to have for the dark cavity configuration of part during part roughing is processed as the interior cold lathe tool of the high-pressure cooling water of 300bar, smear metal can be interrupted in process and become chip, can improve working (machining) efficiency, improve tool life, reduce the cost of charp tool and guarantee surface quality;

The turn-milling complex machining center machine tooling is all adopted in roughing and fine finishining, and during fine finishining, clamped one time is completed the profile Vehicle Processing, part end face hole, axle journal end inclined hole and limit, hole chamfering mill processing; The dark chamber of part finish turning adds and utilizes turn-milling complex machining center B axle swing bicycle machining functions man-hour, sidecar is cut B axle pivot limit, lathe tool edge and is rotated, utilize a lathe tool to complete profile processing, compare by 2 lathe tools with traditional numerical control lathe processing and be reduced to a lathe tool, reduce by a machined trace, improve surface quality of workpieces and working (machining) efficiency; Finish turning adds and adopts man-hour turn-milling complex machining center on-line measurement function to carry out part dimension measurement and cutter cutter to mend auto-compensation, be divided into every layer of 0.3~0.6mm according to allowance, at first Vehicle Processing 0.3~0.6mm layer of material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement according to programmed values, automatically calculating cutter by Digit Control Machine Tool remedies defects and carries out auto-compensation in difference input machine tool wearing valve, carry out 0.3~0.6mm materials processing of lower one deck according to program, complete the processing of part final size.

Advantage of the present invention:

Aero-engine dish axle integrative-structure part by numerical control processing method of the present invention, process is stable, quality improvement, part by one-step submits to qualification rate obviously to improve, the separate unit process-cycle, reduction was more than 100 hours, production efficiency has improved 35%, and special fixture is by reducing to 3 covers, for processing homogeneous structure part on turn-milling complex machining center is laid a good foundation.

Description of drawings

The present invention is further detailed explanation below in conjunction with drawings and the embodiments:

Fig. 1 is the design of part schematic diagram.

The specific embodiment

Embodiment 1

The present embodiment provides a kind of aero-engine dish axle integrative-structure part by numerical control processing method, it is characterized in that: described aero-engine dish axle integrative-structure part by numerical control processing method is as follows:

Part disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating; The main manufacturing procedure of part: the large end of the forging part → roughing → roughing small end → vacuum large end profile of heat treatment → fine finishining → fine finishining small end totally 4 procedures of escaping by luck that eliminate stress need 2 cover special fixtures; The turn-milling complex machining center that employing has two main shafts replaces the equipment processing parts such as original engine lathe, numerically controlled lathe and five-axis machining center; The pressure that uses turnning and milling complex centre lathe to have for the dark cavity configuration of part during part roughing is processed as the interior cold lathe tool of the high-pressure cooling water of 300bar, smear metal can be interrupted in process and become chip, can improve working (machining) efficiency, improve tool life, reduce the cost of charp tool and guarantee surface quality;

The turn-milling complex machining center machine tooling is all adopted in roughing and fine finishining, and during fine finishining, clamped one time is completed the profile Vehicle Processing, part end face hole, axle journal end inclined hole and limit, hole chamfering mill processing; The dark chamber of part finish turning adds and utilizes turn-milling complex machining center B axle swing bicycle machining functions man-hour, sidecar is cut B axle pivot limit, lathe tool edge and is rotated, utilize a lathe tool to complete profile processing, compare by 2 lathe tools with traditional numerical control lathe processing and be reduced to a lathe tool, reduce by a machined trace, improve surface quality of workpieces and working (machining) efficiency; Finish turning adds and adopts man-hour turn-milling complex machining center on-line measurement function to carry out part dimension measurement and cutter cutter to mend auto-compensation, be divided into every layer of 0.3mm according to allowance, at first Vehicle Processing 0.3mm layer of material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement according to programmed values, automatically calculating cutter by Digit Control Machine Tool remedies defects and carries out auto-compensation in difference input machine tool wearing valve, carry out the 0.3mm materials processing of lower one deck according to program, complete the processing of part final size.

Embodiment 2

The present embodiment provides a kind of aero-engine dish axle integrative-structure part by numerical control processing method, it is characterized in that: described aero-engine dish axle integrative-structure part by numerical control processing method is as follows:

Part disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating; The main manufacturing procedure of part: the large end of the forging part → roughing → roughing small end → vacuum large end profile of heat treatment → fine finishining → fine finishining small end totally 4 procedures of escaping by luck that eliminate stress need 2 cover special fixtures; The turn-milling complex machining center that employing has two main shafts replaces the equipment processing parts such as original engine lathe, numerically controlled lathe and five-axis machining center; The pressure that uses turnning and milling complex centre lathe to have for the dark cavity configuration of part during part roughing is processed as the interior cold lathe tool of the high-pressure cooling water of 300bar, smear metal can be interrupted in process and become chip, can improve working (machining) efficiency, improve tool life, reduce the cost of charp tool and guarantee surface quality;

The turn-milling complex machining center machine tooling is all adopted in roughing and fine finishining, and during fine finishining, clamped one time is completed the profile Vehicle Processing, part end face hole, axle journal end inclined hole and limit, hole chamfering mill processing; The dark chamber of part finish turning adds and utilizes turn-milling complex machining center B axle swing bicycle machining functions man-hour, sidecar is cut B axle pivot limit, lathe tool edge and is rotated, utilize a lathe tool to complete profile processing, compare by 2 lathe tools with traditional numerical control lathe processing and be reduced to a lathe tool, reduce by a machined trace, improve surface quality of workpieces and working (machining) efficiency; Finish turning adds and adopts man-hour turn-milling complex machining center on-line measurement function to carry out part dimension measurement and cutter cutter to mend auto-compensation, be divided into every layer of 0.4mm according to allowance, at first Vehicle Processing 0.4mm layer of material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement according to programmed values, automatically calculating cutter by Digit Control Machine Tool remedies defects and carries out auto-compensation in difference input machine tool wearing valve, carry out the 0.4mm materials processing of lower one deck according to program, complete the processing of part final size.

Embodiment 3

The present embodiment provides a kind of aero-engine dish axle integrative-structure part by numerical control processing method, it is characterized in that: described aero-engine dish axle integrative-structure part by numerical control processing method is as follows:

Part disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating; The main manufacturing procedure of part: the large end of the forging part → roughing → roughing small end → vacuum large end profile of heat treatment → fine finishining → fine finishining small end totally 4 procedures of escaping by luck that eliminate stress need 2 cover special fixtures; The turn-milling complex machining center that employing has two main shafts replaces the equipment processing parts such as original engine lathe, numerically controlled lathe and five-axis machining center; The pressure that uses turnning and milling complex centre lathe to have for the dark cavity configuration of part during part roughing is processed as the interior cold lathe tool of the high-pressure cooling water of 300bar, smear metal can be interrupted in process and become chip, can improve working (machining) efficiency, improve tool life, reduce the cost of charp tool and guarantee surface quality;

The turn-milling complex machining center machine tooling is all adopted in roughing and fine finishining, and during fine finishining, clamped one time is completed the profile Vehicle Processing, part end face hole, axle journal end inclined hole and limit, hole chamfering mill processing; The dark chamber of part finish turning adds and utilizes turn-milling complex machining center B axle swing bicycle machining functions man-hour, sidecar is cut B axle pivot limit, lathe tool edge and is rotated, utilize a lathe tool to complete profile processing, compare by 2 lathe tools with traditional numerical control lathe processing and be reduced to a lathe tool, reduce by a machined trace, improve surface quality of workpieces and working (machining) efficiency; Finish turning adds and adopts man-hour turn-milling complex machining center on-line measurement function to carry out part dimension measurement and cutter cutter to mend auto-compensation, be divided into every layer of 0.6mm according to allowance, at first Vehicle Processing 0.6mm layer of material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement according to programmed values, automatically calculating cutter by Digit Control Machine Tool remedies defects and carries out auto-compensation in difference input machine tool wearing valve, carry out the 0.6mm materials processing of lower one deck according to program, complete the processing of part final size.

Claims (1)

1. aero-engine dish axle integrative-structure part by numerical control processing method, it is characterized in that: described aero-engine dish axle integrative-structure part by numerical control processing method is as follows:
Part disc and axle journal and disk body connecting portion wall thickness tolerance 0.05mm, PRECISION HOLE diameter tolerance 0.015mm, relative datum position degree Φ 0.05mm, disc end face and endoporus relative datum perpendicularity are 0.01mm with beating;
The main manufacturing procedure of part: the large end of the forging part → roughing → roughing small end → vacuum large end profile of heat treatment → fine finishining → fine finishining small end totally 4 procedures of escaping by luck that eliminate stress need 2 cover special fixtures; The turn-milling complex machining center that employing has two main shafts replaces the equipment processing parts such as original engine lathe, numerically controlled lathe and five-axis machining center; The pressure that uses turnning and milling complex centre lathe to have for the dark cavity configuration of part during part roughing is processed as the interior cold lathe tool of the high-pressure cooling water of 300bar, smear metal can be interrupted in process and become chip, can improve working (machining) efficiency, improve tool life, reduce the cost of charp tool and guarantee surface quality;
The turn-milling complex machining center machine tooling is all adopted in roughing and fine finishining, and during fine finishining, clamped one time is completed the profile Vehicle Processing, part end face hole, axle journal end inclined hole and limit, hole chamfering mill processing; The dark chamber of part finish turning adds and utilizes turn-milling complex machining center B axle swing bicycle machining functions man-hour, sidecar is cut B axle pivot limit, lathe tool edge and is rotated, utilize a lathe tool to complete profile processing, compare by 2 lathe tools with traditional numerical control lathe processing and be reduced to a lathe tool, reduce by a machined trace, improve surface quality of workpieces and working (machining) efficiency; Finish turning adds and adopts man-hour turn-milling complex machining center on-line measurement function to carry out part dimension measurement and cutter cutter to mend auto-compensation, be divided into every layer of 0.3~0.6mm according to allowance, at first Vehicle Processing 0.3~0.6mm layer of material when programming, utilize the actual value processing of machine tool on-line measurement functional measurement according to programmed values, automatically calculating cutter by Digit Control Machine Tool remedies defects and carries out auto-compensation in difference input machine tool wearing valve, carry out 0.3~0.6mm materials processing of lower one deck according to program, complete the processing of part final size.
CN2013100022877A 2013-01-05 2013-01-05 Numerical control machining method of aero-engine disc-shaft integrated structure part CN103111814A (en)

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Cited By (15)

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Publication number Priority date Publication date Assignee Title
CN103273282A (en) * 2013-06-20 2013-09-04 贵州红林机械有限公司 Method for machining high-accuracy special profile of elongated rod
CN103586495A (en) * 2013-09-30 2014-02-19 沈阳黎明航空发动机(集团)有限责任公司 Cutting tool of ultra-high-pressure inner-cooling structure and using method for cutting tool
CN103737266A (en) * 2013-12-31 2014-04-23 贵州遵义驰宇精密机电制造有限公司 Machining method for rear shaft neck of aerial turbofan engine
CN104308661A (en) * 2014-10-08 2015-01-28 烟台拓伟机械有限公司 Disc type part numerical control turning processing dimension on-line measurement device
CN104400008A (en) * 2014-11-24 2015-03-11 沈阳黎明航空发动机(集团)有限责任公司 Numerical-control processing method of sealed ring-shaped deep cavity
CN104439945A (en) * 2014-11-11 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 Numerical control machining method for aero-engine main nozzle parts
CN104481699A (en) * 2014-11-10 2015-04-01 沈阳黎明航空发动机(集团)有限责任公司 Processing method of oversized drum precision connecting holes
CN105562717A (en) * 2014-10-13 2016-05-11 沈阳黎明航空发动机(集团)有限责任公司 Numerical control turning method for large deep cavity structure of aircraft engine disc part
CN107649845A (en) * 2017-11-09 2018-02-02 东方电气集团东方汽轮机有限公司 A kind of large scale combustion engine turbine blade essence casting blank positioning and processing method
CN107991994A (en) * 2017-11-24 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 processing method for clamping of not feeling relieved
CN108044325A (en) * 2017-12-25 2018-05-18 芜湖锐进医疗设备有限公司 Hexagonal axis manufacturing process in a kind of medical instrument
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
CN109366103A (en) * 2018-11-26 2019-02-22 中国航发沈阳黎明航空发动机有限责任公司 A method of for improving aeroengine rotor wheel disc machining accuracy
CN109500639A (en) * 2018-11-20 2019-03-22 中国航发贵州黎阳航空动力有限公司 A kind of device and clamping method of the aero-engine with heat screen bushing class Vehicle Processing
CN109787063A (en) * 2018-12-10 2019-05-21 上海航天设备制造总厂有限公司 Conducting slip ring dissimilar material pressure pouring part CNC lathe work

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103273282B (en) * 2013-06-20 2015-09-09 贵州红林机械有限公司 The processing method of the special profile of elongate rod high accuracy
CN103273282A (en) * 2013-06-20 2013-09-04 贵州红林机械有限公司 Method for machining high-accuracy special profile of elongated rod
CN103586495A (en) * 2013-09-30 2014-02-19 沈阳黎明航空发动机(集团)有限责任公司 Cutting tool of ultra-high-pressure inner-cooling structure and using method for cutting tool
CN103737266A (en) * 2013-12-31 2014-04-23 贵州遵义驰宇精密机电制造有限公司 Machining method for rear shaft neck of aerial turbofan engine
CN103737266B (en) * 2013-12-31 2016-08-31 贵州遵义驰宇精密机电制造有限公司 A kind of processing method of aviation turbofan engine rear shaft neck
CN104308661A (en) * 2014-10-08 2015-01-28 烟台拓伟机械有限公司 Disc type part numerical control turning processing dimension on-line measurement device
CN104308661B (en) * 2014-10-08 2015-08-05 烟台拓伟机械有限公司 Disk-like accessory numerical control lathe pin processing dimension on-line measurement device
CN105562717A (en) * 2014-10-13 2016-05-11 沈阳黎明航空发动机(集团)有限责任公司 Numerical control turning method for large deep cavity structure of aircraft engine disc part
CN104481699A (en) * 2014-11-10 2015-04-01 沈阳黎明航空发动机(集团)有限责任公司 Processing method of oversized drum precision connecting holes
CN104439945A (en) * 2014-11-11 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 Numerical control machining method for aero-engine main nozzle parts
CN104400008A (en) * 2014-11-24 2015-03-11 沈阳黎明航空发动机(集团)有限责任公司 Numerical-control processing method of sealed ring-shaped deep cavity
CN107649845A (en) * 2017-11-09 2018-02-02 东方电气集团东方汽轮机有限公司 A kind of large scale combustion engine turbine blade essence casting blank positioning and processing method
CN107991994A (en) * 2017-11-24 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 processing method for clamping of not feeling relieved
CN108044325A (en) * 2017-12-25 2018-05-18 芜湖锐进医疗设备有限公司 Hexagonal axis manufacturing process in a kind of medical instrument
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
CN109500639A (en) * 2018-11-20 2019-03-22 中国航发贵州黎阳航空动力有限公司 A kind of device and clamping method of the aero-engine with heat screen bushing class Vehicle Processing
CN109366103A (en) * 2018-11-26 2019-02-22 中国航发沈阳黎明航空发动机有限责任公司 A method of for improving aeroengine rotor wheel disc machining accuracy
CN109787063A (en) * 2018-12-10 2019-05-21 上海航天设备制造总厂有限公司 Conducting slip ring dissimilar material pressure pouring part CNC lathe work

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Application publication date: 20130522