CN105728631A - Forging method for maraging steel disc-shaft integrated forged piece - Google Patents
Forging method for maraging steel disc-shaft integrated forged piece Download PDFInfo
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- CN105728631A CN105728631A CN201410752967.5A CN201410752967A CN105728631A CN 105728631 A CN105728631 A CN 105728631A CN 201410752967 A CN201410752967 A CN 201410752967A CN 105728631 A CN105728631 A CN 105728631A
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Abstract
The invention discloses a forging method for a maraging steel disc-shaft integrated forged piece. According to the technical scheme for achieving formation of the disc-shaft integrated forged piece through one heating number, avoiding local idle burning of the forged piece and lowering the production difficulty of the forged piece, the traditional final forging temperature of the maraging steel forged piece is adjusted to 750 DEG C from 820-870 DEG C, the traditional technique that disc upsetting is conducted after rod pulling is changed into the technique that rod pulling is conducted after disc upsetting, then effective protective measures are taken in the deformation process of the forged piece, and the effect that formation of the forged piece is completed through one heating number on the premise that the requirement for the final forging temperature is met is guaranteed. According to the technical scheme, the operability is high, the forging method is suitable for popularization, and the preparation technique for the disc-shaft integrated forged piece and particularly for a large disc-shaft integrated forged piece with the length exceeding 2000 mm is remarkably improved.
Description
Technical field
The invention belongs to technical field of forging, relate to the manufacturing process of a kind of martensite ag(e)ing steel disk axle integration forging.
Background technology
Aviation drive disk assembly material is mainly maraging unimach, Maraging steel is the steel class that in steel, intensity is the highest, toughness is compared higher with other unimach that intensity rank is suitable, it is the steel grade in current material with most high-strength tenacity proportioning, is usually used in the manufacture of the parts such as aerial engine fan axle and low-pressure turbine shaft.
Current aviation drive disk assembly forging is dish axle integral forming, split so can be avoided to shape problems such as welding uneven microstructure, the stress concentration brought again, but add the shaping of forging and metallurgical difficulty.For ensureing the sufficiently conducted of forging recrystallization, traditional martensite ag(e)ing steel disk axle integration forging final forging temperature selects at 820～870 DEG C, it is many fire time and shapes (upsetting dish portion 1 fire, dead man 1-2 fire), for avoiding the long-time empty burning problem in dish portion (little compared to bar portion effective thickness), frequently with the technique thinking in first dead man portion, rear upsetting dish portion.The maximum drawback of traditional handicraft is in that to divide fire to carry out forging upsetting dish and dead man operation, the empty burning problem in forging local has been existed for since so, and empty burning is easier to bring forging coarse grains, the metallurgical problems such as intensity, plasticity index are defective, and forging length greatly increases after dead man, bring very big difficulty in process to sub sequent fire time forging heating and upsetting dish portion operation.
Summary of the invention
The technical problem to be solved in the present invention is: forging upsetting dish and dead man operation are divided fire to carry out by traditional handicraft, there is the empty burning problem in forging local.
The technical scheme is that 1 fire is secondary completes dish axle integration forging forming in order to realize; avoid the empty burning in forging local; and reduce forging producting process difficulty; adopt the technical scheme that: conventional martensitic aged steel forging final forging temperature is adjusted to 750 DEG C by 820～870 DEG C; and upsetting dish technique is dead man after first upsetting dish after changing the first dead man of tradition; effective protection measure is taked again, it is ensured that complete forging forming at next fire of premise meeting final forging temperature in forging deformation process.Concrete forging method comprises the steps:
Step 1: bar heats, and selects the forging heating-up temperature of 1020～1100 DEG C, and final forging temperature is set as 750 DEG C；Bar heating process adopts high temperature cotton carry out jacket, reduce the heat loss shifted after bar is come out of the stove and in forging process；
Step 2: upsetting dish-dead man operation, the shaping thinking in first upsetting dish portion, rear dead man portion selected by blank after coming out of the stove, upsetting dish completes in special loose tool, after completing forging go out loose tool rapidly by heat-preservation cotton by dish portion jacket, and turn forging direction, clamping disk portion carries out dead man；
Step 3: dead man Insulation: in dead man process in step 2, forging covering and heat insulating incessantly is cotton, to reduce conduction of heat between forging and hammer anvil and forging to the heat radiation in space；
Step 4: forge circle soon, utilizes the fast forging function of equipment to carry out the shaping of bar portion after large deformation dead man and beats circle, and the deformation of continuous print Fast Persistence can maintain forging surface temperature substantially.
Step 5: complete forging process.
Can realize completing more than the final forging temperature of 750 DEG C the deformation process of martensite ag(e)ing steel disk axle integration forging through above technical scheme, owing to 1 fire time shaping avoids, forging local is empty burns, not only increase forging structural homogenity, organize also more tiny, it is ensured that the metallurgical quality of forging.
The medicine have the advantages that by adjusting forging terminal temperature, after changing the first dead man of tradition, the technique of upsetting dish is dead man after first upsetting dish, forging process is taked effective Insulation and plays equipment fast forging function, achieve large-scale dish axle integration forging 1 pyrogene shape, not only avoid the local sky of forging to burn, improve forging structural homogenity and performance level, also greatly reduce shaping fire, achieve obvious energy-saving benefit, also avoid after first dead man in upsetting dish process, the long blank heating caused of forging and upsetting dish difficulty simultaneously.The process program of the present invention is workable, is suitable to promote, makes the dish axle integration forging particularly length large-scale dish axle integration forging preparation technology more than 2000mm obtain and significantly improve.
Detailed description of the invention
Below by specific embodiment, the present invention is described in further detail:
Certain type aero-engine low-pressure turbine forging shaft material is C250 unimach, forging length 2115mm, dish portion diameter phi 410mm, bar portion diameter phi 150, forge weight 370Kg, cutting stock weight 413Kg, and φ 250 × 1080 specification selected by bar.
This forging heating-up temperature is 1040 DEG C, forging final forging temperature is set to 750 DEG C, come out of the stove after bar insulation 100min and carry out quick jacket by heat-preservation cotton, melt down after jacket and heat to temperature retention time, upsetting dish is carried out in special loose tool after having heated, take out rapidly forging after completing upsetting dish and by heat-preservation cotton, dish portion carried out jacket, clamping disk portion carries out the pulling of bar portion, the strip heat-preservation cotton got ready in advance is constantly utilized to cover forging during the pulling of bar portion, ensure pressure distortion process is lined with heat-preservation cotton all the time between hammer anvil and forging, reduce the loss of forging surface heat, large deformation utilizes 2500t forcing press fast forging function to carry out the shaping of bar portion and beats circle after completing, the whole forging process used time is about 14min, forging terminal temperature 783 DEG C, meet final forging temperature requirement.
Physicochemical property detection is carried out after the normalized heat treatment of low-pressure turbine forging shaft prepared by above-mentioned 1 fire forming technology, testing result all meets associated specifications, forging even tissue, overall grain size is in 6～7 grades, do not occur that forging local cell granularity prepared by the many fire of tradition time technique exceeds standard (lower than 6 grades) problem, this technique has started the precedent of large-scale dish axle integration forging 1 pyrogene type, production efficiency is improved while achieving lifting forging quality, simultaneously because greatly reduce forging times, achieve obvious energy-saving benefit.
Claims (1)
1. a manufacturing process for martensite ag(e)ing steel disk axle integration forging, comprises the steps:
Step 1: bar heats, and selects the forging heating-up temperature of 1020～1100 DEG C, and final forging temperature is set as 750 DEG C；Bar heating process adopts high temperature cotton carry out jacket, reduce the heat loss shifted after bar is come out of the stove and in forging process；
Step 2: upsetting dish-dead man operation, the shaping thinking in first upsetting dish portion, rear dead man portion selected by blank after coming out of the stove, upsetting dish completes in special loose tool, after completing forging go out loose tool rapidly by heat-preservation cotton by dish portion jacket, and turn forging direction, clamping disk portion carries out dead man；
Step 3: dead man Insulation: in dead man process in step 2, forging covering and heat insulating incessantly is cotton, to reduce conduction of heat between forging and hammer anvil and forging to the heat radiation in space；
Step 4: forge circle soon, utilizes the fast forging function of equipment to carry out the shaping of bar portion after large deformation dead man and beats circle, and the deformation of continuous print Fast Persistence can maintain forging surface temperature substantially；
Step 5: complete forging process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410752967.5A CN105728631A (en) | 2014-12-10 | 2014-12-10 | Forging method for maraging steel disc-shaft integrated forged piece |
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| CN201410752967.5A CN105728631A (en) | 2014-12-10 | 2014-12-10 | Forging method for maraging steel disc-shaft integrated forged piece |
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| CN105728631A true CN105728631A (en) | 2016-07-06 |
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| CN201410752967.5A Pending CN105728631A (en) | 2014-12-10 | 2014-12-10 | Forging method for maraging steel disc-shaft integrated forged piece |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106493281A (en) * | 2016-12-12 | 2017-03-15 | 陕西宏远航空锻造有限责任公司 | A kind of forging method of the hollow Y profile shafts forging of titanium alloy |
| CN111112529A (en) * | 2019-12-11 | 2020-05-08 | 陕西宏远航空锻造有限责任公司 | Method and device for forming step shaft die forging with flange plate in middle |
| CN112719173A (en) * | 2020-12-18 | 2021-04-30 | 陕西宏远航空锻造有限责任公司 | Forging method of 15-5PH disc shaft integrated forging |
| FR3114325A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
| FR3114327A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
| FR3114326A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
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| JP2005131654A (en) * | 2003-10-29 | 2005-05-26 | Sumitomo Heavy Industries Techno-Fort Co Ltd | Method for preforming flanged shaft-like product and forging press |
| CN1736654A (en) * | 2004-08-19 | 2006-02-22 | 中国北车集团大同电力机车有限责任公司 | Integrated forging method of flange type step thin wall long sheath forging |
| CN101412066A (en) * | 2007-10-17 | 2009-04-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Hammer forging technique of GH4169 alloy dish |
| CN103350180A (en) * | 2013-06-21 | 2013-10-16 | 贵州安大航空锻造有限责任公司 | Forging forming method of fan shaft made of C250 maraging steel |
| CN103350179A (en) * | 2013-06-21 | 2013-10-16 | 贵州安大航空锻造有限责任公司 | Forging forming method of low-pressure turbine shaft made of C250 maraging steel |
| CN104108012A (en) * | 2014-07-28 | 2014-10-22 | 中国南方航空工业(集团)有限公司 | Forging method of disc-shaped integrated part and die used for forging method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2005131654A (en) * | 2003-10-29 | 2005-05-26 | Sumitomo Heavy Industries Techno-Fort Co Ltd | Method for preforming flanged shaft-like product and forging press |
| CN1736654A (en) * | 2004-08-19 | 2006-02-22 | 中国北车集团大同电力机车有限责任公司 | Integrated forging method of flange type step thin wall long sheath forging |
| CN101412066A (en) * | 2007-10-17 | 2009-04-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Hammer forging technique of GH4169 alloy dish |
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| CN103350179A (en) * | 2013-06-21 | 2013-10-16 | 贵州安大航空锻造有限责任公司 | Forging forming method of low-pressure turbine shaft made of C250 maraging steel |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106493281A (en) * | 2016-12-12 | 2017-03-15 | 陕西宏远航空锻造有限责任公司 | A kind of forging method of the hollow Y profile shafts forging of titanium alloy |
| CN111112529A (en) * | 2019-12-11 | 2020-05-08 | 陕西宏远航空锻造有限责任公司 | Method and device for forming step shaft die forging with flange plate in middle |
| CN111112529B (en) * | 2019-12-11 | 2021-10-15 | 陕西宏远航空锻造有限责任公司 | Method and device for forming step shaft die forging with flange plate in middle |
| FR3114325A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
| FR3114327A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
| FR3114326A1 (en) * | 2020-09-23 | 2022-03-25 | Safran Aircraft Engines | Process of forging a piece of maraging steel |
| WO2022064124A1 (en) * | 2020-09-23 | 2022-03-31 | Safran Aircraft Engines | Method for forging a part made of maraging steel |
| WO2022064121A1 (en) * | 2020-09-23 | 2022-03-31 | Safran Aircraft Engines | Method for forging a part made of maraging steel |
| WO2022064122A1 (en) * | 2020-09-23 | 2022-03-31 | Safran Aircraft Engines | Method for forging a part made of maraging steel |
| CN112719173A (en) * | 2020-12-18 | 2021-04-30 | 陕西宏远航空锻造有限责任公司 | Forging method of 15-5PH disc shaft integrated forging |
| CN112719173B (en) * | 2020-12-18 | 2023-03-14 | 陕西宏远航空锻造有限责任公司 | Forging method of 15-5PH disc shaft integrated forging |
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Application publication date: 20160706 |