CN103028693A - Preforming method for precision forging blades - Google Patents

Preforming method for precision forging blades Download PDF

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Publication number
CN103028693A
CN103028693A CN2011102989005A CN201110298900A CN103028693A CN 103028693 A CN103028693 A CN 103028693A CN 2011102989005 A CN2011102989005 A CN 2011102989005A CN 201110298900 A CN201110298900 A CN 201110298900A CN 103028693 A CN103028693 A CN 103028693A
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CN
China
Prior art keywords
forging
die
blade
extrusion
insert
Prior art date
Application number
CN2011102989005A
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Chinese (zh)
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CN103028693B (en
Inventor
鞠秀义
汪大成
史丽坤
闫进军
刘君
Original Assignee
沈阳黎明航空发动机(集团)有限责任公司
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Priority to CN201110298900.5A priority Critical patent/CN103028693B/en
Publication of CN103028693A publication Critical patent/CN103028693A/en
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Publication of CN103028693B publication Critical patent/CN103028693B/en

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Abstract

Provided is a preforming method for precision forging blades. A precision forging die is utilized and comprises a punch head, a left insert and a right insert, and a bar stock is arranged in the die. A forging piece deforms twice in the extrusion die, through a unique horn-opening-shaped design, materials are gathered at the position of a boss, and the die is mounted on a 160-ton crank press which has an ejector function and can eject the left insert and the right insert from a die seat so that the forging piece can be taken out conveniently. A kerosene blast burner is utilized to heat the die to a temperature between 180 DEG C and 300 DEG C, the bar stock is made of alloy GH4169 and heated to 1,020 DEG C, and the heating parameter is 1 minute per millimeter. In the process of forging, a water-based graphite lubricant is used for lubricating a cavity of the die, and the time from the bar stock is taken out of a furnace to extrusion forming of the bar stock is controlled to be within seven seconds. The preforming method for the precision forging blades has the advantages that the problem that the precision forging blades are pulled to cause damage and scrapped when final forging is carried out to the extrusion piece is solved completely, 10% of materials are saved compared to a traditional extrusion piece, and at the same time, through the preforming method for the precision forging blades, requirements of striking force on equipment when the final forging is carried out to the forging piece are reduced.

Description

A kind of finish forge blade preformation method

 

Technical field

The present invention relates to technical field of forging, a kind of finish forge blade preformation method is provided especially.

Background technology

During traditional design rotor class finish forge blade extrusion prefabricated blank, extrusion bar section shape is according to blade maximum transversal area of section, and the needed deflection design of finish-forging, and bar passes through an extrusion modling in extrusion die.Blade local location metal is too much when so just existing finish-forging, deflection produces greatly and pulls, serious generation is torn, the finish forge blade is scrapped, repair type by the polishing extrusion and just can avoid the generation of pulling, material has too much also strengthened requirement to the hitting power of equipment simultaneously, can only remove excess metal by polishing during production and avoid.

Summary of the invention

The objective of the invention is to rely on the polishing extrusion to remove excess metal in order to solve the traditional design mode, avoid pulling of finish-forging spare blade appearance, and the requirement of reduction equipment hitting power, the spy provides a kind of finish forge blade preformation method.

The invention provides a kind of finish forge blade preformation method, it is characterized in that: described finish forge blade preformation method adopts finish forge mould, and mould comprises drift 1, and a left side inserts 3, and the right side inserts 4, and bar 2 is put into mould.

The first deformed area C of forging, the second deformed area D, design by bell mouth shape, material is gathered the boss place, and heavy line marks the position among Fig. 3, and mould is installed on 160 tons of crank presses, this forcing press has ejecting function, can be inserted in a left side 3 and the right side insert and 4 from mold base, eject, make things convenient for pickup, adopt kerosene blastburne, between mold heated to 180 ℃-300 ℃, bar 2 materials are the GH4169 alloy, are heated to 1020 ℃, and heating parameters is 1 minute/millimeter, it is 20 millimeters such as bar 2 diameters, then be 20 minutes heat time heating time, adopts the lubricated die cavity of colloidal graphite mixed with water during forging, and bar 2 is fetched into the extrusion modling time and is controlled in 7 seconds from stove.

Described forging blade maximum cross-section is the I-I place, and area is 62 square millimeters; The positioning boss II-II place area of section of blade is 86.3 square millimeters.Traditional design is to calculate according to II-II place area of section, causes the waste of material and finish-forging generation to pull.Described finish forge blade preformation method, according to finish-forging spare different cross section the demand of material is redistributed, forge the extrusion that more meets each cross section demand of blade, avoiding producing blade because excess stock is mobile pulls, the projected area of forging when having reduced simultaneously finish-forging reduces the hitting power requirement of equipment.

Advantage of the present invention:

Finish forge blade preformation method of the present invention occurs pulling and scraps at blade when can 100% solving the extrusion finish-forging, saves material 10% according to traditional extrusion, and simultaneously, the method has reduced the requirement to the equipment hitting power.

Description of drawings

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

Fig. 1 is forging longitudinal cross-section calculating location schematic diagram;

Fig. 2 is the method and conventional method extrusion cross section contrast position view;

Fig. 3 is extrusion deformed region design diagram;

Fig. 4 is schematic diagram before the bar extruding;

Fig. 5 is that bar is at extrusion die secondary deformation schematic diagram;

Material Flow schematic diagram when Fig. 6 is secondary deformation;

Fig. 7 is final full state schematic diagram.

The specific embodiment

Embodiment 1

Present embodiment provides a kind of finish forge blade preformation method, it is characterized in that: described finish forge blade preformation method adopts finish forge mould, and mould comprises drift 1, and a left side inserts 3, and the right side inserts 4, and bar 2 is put into mould;

The first deformed area C of forging, the second deformed area D, design by bell mouth shape, material is gathered the boss place, and heavy line marks the position among Fig. 3, and mould is installed on 160 tons of crank presses, this forcing press has ejecting function, can be inserted in a left side 3 and the right side insert and 4 from mold base, eject, make things convenient for pickup, adopt kerosene blastburne, between mold heated to 180 ℃-300 ℃, bar 2 materials are the GH4169 alloy, are heated to 1020 ℃, and heating parameters is 1 minute/millimeter, it is 20 millimeters such as bar 2 diameters, then be 20 minutes heat time heating time, adopts the lubricated die cavity of colloidal graphite mixed with water during forging, and bar 2 is fetched into the extrusion modling time and is controlled in 7 seconds from stove.

Described forging blade maximum cross-section is the I-I place, and area is 62 square millimeters; The positioning boss II-II place sectional area of blade is 86.3 square millimeters.Traditional design is to calculate according to II-II place area of section, causes the waste of material and finish-forging generation to pull.Described finish forge blade preformation method, according to finish-forging spare different cross section the demand of material is redistributed, forge the extrusion that more meets each cross section demand of blade, avoiding producing blade because excess stock is mobile pulls, the projected area of forging when having reduced simultaneously finish-forging reduces the hitting power requirement of equipment.

Claims (2)

1. finish forge blade preformation method is characterized in that: described finish forge blade preformation method adopts finish forge mould, and mould comprises drift (1), inserts (3) in a left side, inserts (4) in the right side, and bar (2) is put into mould;
First deformed area (C) of forging, the second deformed area (D), design by bell mouth shape, material is gathered the boss place, mould is installed on 160 tons of crank presses, this forcing press has ejecting function, can be inserted in a left side (3) and the right side insert (4) from mold base, eject, make things convenient for pickup, adopt kerosene blastburne, between mold heated to 180 ℃-300 ℃, bar (2) material is the GH4169 alloy, is heated to 1020 ℃, and heating parameters is 1 minute/millimeter, adopt the lubricated die cavity of colloidal graphite mixed with water during forging, bar (2) is fetched into the extrusion modling time and is controlled in 7 seconds from stove.
2. according to finish forge blade preformation method claimed in claim 1, it is characterized in that: described forging blade maximum cross-section is the I-I place, and area is 62 square millimeters; The positioning boss II-II place sectional area of blade is 86.3 square millimeters, changes sectional area of one-shot forming of traditional design extrusion, and for long-pending according to forging needs varying cross section, the method more is conducive to the finish forging in later stage.
CN201110298900.5A 2011-09-29 2011-09-29 A kind of finish forge blade preformation method CN103028693B (en)

Priority Applications (1)

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CN201110298900.5A CN103028693B (en) 2011-09-29 2011-09-29 A kind of finish forge blade preformation method

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Application Number Priority Date Filing Date Title
CN201110298900.5A CN103028693B (en) 2011-09-29 2011-09-29 A kind of finish forge blade preformation method

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CN103028693A true CN103028693A (en) 2013-04-10
CN103028693B CN103028693B (en) 2016-01-27

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104308058A (en) * 2014-11-07 2015-01-28 沈阳黎明航空发动机(集团)有限责任公司 Titanium alloy blade forging forming method
CN105290285A (en) * 2015-11-20 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 Manufacturing method for directly forming blade forging piece through extrusion
CN105642809A (en) * 2014-11-10 2016-06-08 沈阳黎明航空发动机(集团)有限责任公司 Design method of abrasion-resistant extrusion die for precisely forged blades
CN106354927A (en) * 2016-08-29 2017-01-25 西北工业大学 Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade
CN106862476A (en) * 2015-12-14 2017-06-20 陕西宏远航空锻造有限责任公司 A kind of aviation forging method of large-scale aluminum matrix composite fan blade fine forge piece
CN107774852A (en) * 2017-11-30 2018-03-09 无锡透平叶片有限公司 A kind of compressor blade forging process for fuel forming method
CN109127888A (en) * 2018-11-05 2019-01-04 中国航发航空科技股份有限公司 A kind of hot extrusion shaping mold of blade

Citations (2)

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Publication number Priority date Publication date Assignee Title
JPS55161542A (en) * 1979-03-11 1980-12-16 Ufimsk Aviatsion Inst Preparation of blade blank and die set for executing said method
US20050086783A1 (en) * 2003-07-23 2005-04-28 Snecma Moteurs Precision-forging parts manufacturingprocess

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55161542A (en) * 1979-03-11 1980-12-16 Ufimsk Aviatsion Inst Preparation of blade blank and die set for executing said method
US20050086783A1 (en) * 2003-07-23 2005-04-28 Snecma Moteurs Precision-forging parts manufacturingprocess

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Title
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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104308058A (en) * 2014-11-07 2015-01-28 沈阳黎明航空发动机(集团)有限责任公司 Titanium alloy blade forging forming method
CN104308058B (en) * 2014-11-07 2016-03-02 沈阳黎明航空发动机(集团)有限责任公司 A kind of method of titanium alloy blade forging and molding
CN105642809A (en) * 2014-11-10 2016-06-08 沈阳黎明航空发动机(集团)有限责任公司 Design method of abrasion-resistant extrusion die for precisely forged blades
CN105642809B (en) * 2014-11-10 2017-10-24 沈阳黎明航空发动机(集团)有限责任公司 A kind of design method of the wear-resisting extrusion die of finish forge blade
CN105290285A (en) * 2015-11-20 2016-02-03 沈阳黎明航空发动机(集团)有限责任公司 Manufacturing method for directly forming blade forging piece through extrusion
CN106862476A (en) * 2015-12-14 2017-06-20 陕西宏远航空锻造有限责任公司 A kind of aviation forging method of large-scale aluminum matrix composite fan blade fine forge piece
CN106862476B (en) * 2015-12-14 2018-07-06 陕西宏远航空锻造有限责任公司 A kind of forging method of the large-scale aluminum matrix composite fan blade fine forge piece of aviation
CN106354927A (en) * 2016-08-29 2017-01-25 西北工业大学 Construction method of optimization model for adaptive processing of front and rear edges of precisely-forged blade
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
CN107774852A (en) * 2017-11-30 2018-03-09 无锡透平叶片有限公司 A kind of compressor blade forging process for fuel forming method
CN109127888A (en) * 2018-11-05 2019-01-04 中国航发航空科技股份有限公司 A kind of hot extrusion shaping mold of blade

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