CN103341586B - Method for achieving forming of GH4738 nickel-base superalloy turbine discs - Google Patents
Method for achieving forming of GH4738 nickel-base superalloy turbine discs Download PDFInfo
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- CN103341586B CN103341586B CN201310226997.8A CN201310226997A CN103341586B CN 103341586 B CN103341586 B CN 103341586B CN 201310226997 A CN201310226997 A CN 201310226997A CN 103341586 B CN103341586 B CN 103341586B
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 29
- 238000005242 forging Methods 0.000 claims abstract description 47
- 238000010438 heat treatment Methods 0.000 claims abstract description 29
- 238000009413 insulation Methods 0.000 claims abstract description 17
- 229920000742 Cotton Polymers 0.000 claims abstract description 15
- 230000032683 aging Effects 0.000 claims abstract description 8
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 44
- 235000015895 biscuits Nutrition 0.000 claims description 36
- 239000000956 alloy Substances 0.000 claims description 34
- 229910045601 alloy Inorganic materials 0.000 claims description 33
- 229910052759 nickel Inorganic materials 0.000 claims description 20
- 238000001816 cooling Methods 0.000 claims description 19
- 238000004519 manufacturing process Methods 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 14
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- 230000007797 corrosion Effects 0.000 claims description 5
- 238000005260 corrosion Methods 0.000 claims description 5
- 238000005461 lubrication Methods 0.000 claims description 5
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 claims description 4
- 239000003546 flue gas Substances 0.000 claims description 4
- 238000007493 shaping process Methods 0.000 claims description 4
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Abstract
The invention discloses a method for achieving forming of GH4738 nickel-base superalloy turbine discs, and relates to a method for preparing the GH4738 nickel-base superalloy turbine discs. The method aims at solving the problems that an existing technology for preparing the GH4738 nickel-base superalloy turbine discs is complex and low in efficiency, and cannot achieve the purposes that the turbine discs are good in quality, even in grain distribution and free of surface crack. The method for achieving forming of the GH4738 nickel-base superalloy turbine discs comprises the following steps: adopting a compound insulation method with a sheath and insulation cotton, carrying out double-firing-number heating, upsetting and die forging, and carrying out solidifying solution and double aging processing at the subsolid solution temperature. By means of the method, the GH4738 nickel-base superalloy turbine discs with different diameter dimensions and disc thicknesses can be prepared. The method can be applied to preparation of nickel-base superalloy turbine discs in the field of petrochemical engineering and aerospace, and preparation of other disc forge pieces used under the high temperature condition.
Description
Technical field
The present invention relates to the turbine disk molding field of ni-base wrought superalloy, be a kind of for about 720 DEG C Long-Time Service time, it requires higher nickel base superalloy turbine disk manufacturing process under the harsh stress conditions such as elevated temperature strength, durable creeping, fatigue and crack growth rate.
Background technology
The flue gas turbine expander that petrochemical industry utilizes refinery tail-gas heat energy to carry out generating electricity and develops is at home and abroad the product having market prospects, for the national economic development creates enormous benefits; Meanwhile, the turbine diskware that can bear high strength at high temperature needed badly by Aero-Space engine, and is no matter crucial turbine disk parts used on flue gas turbine expander or Aero-Space engine, and its important materials manufacturing this high-temperature hot extremity piece is mainly GH4738 nickel base superalloy.This alloy is domestic precipitation hardenable ni-base wrought superalloy, has another name called GH864 alloy, generally at about 720 DEG C Long-Time Service.This alloy plays invigoration effect mainly through γ ' phase and grain boundary carbide, and it possesses the ability of certain resistance to high temperature oxidation and heat erosion, and one of great advantage is exactly have good high temperature Strengthening and Toughening coupling; Therefore, this alloy is one of the main material manufacturing the turbine disk in aero-engine and dynamic power machine and turbo blade [Semiatin S L always, Fagin P N, Glavicic M G, et al. Deformation behavior of Waspaloy at hot-working temperatures.
scripta Materialia., 2004,50:625; Yao Zhihao, Zhang Maicang, Dong Jianxin. Stress rupture fracture model and microstructure evolution for Waspaloy [J].
metallurgical and Materials Transactions A, DOI:10.1007/s11661-013-1660-8,2013; ];
GH4738 alloy is as the typical male sportsman of one, and its alloying level is high, and resistance of deformation is large, and deformable temperature is narrow, and therefore during hot-working, shaping difficulty is very large; Concerning turbine diskware, often because forging reason causes forging diskware to occur the phenomenon that crackle, serious mixed crystal and crystallite dimension exceed standard, thus cause turbine diskware to scrap, cause huge economic loss, even cause running device to damage and casualties.And the control alloy grain size of hot procedure and the distribution of grain boundary carbide and pattern have important impact, forging temperature is too high, causes coarse grains, even occurs alloy crystal boundary film forming phenomenon; Forging temperature is too low, then cause alloy diskware to produce forge crack.The control of temperature is improper, certainly will affect greatly structure property.Meanwhile, the alloy such as rate of deformation, deflection and Insulation is organized and also can be produced material impact.[Yao Zhihao, Dong Jianxin, Zhang Maicang. GH738 high temperature alloy thermal deformation process microstructures Control and the structure [J] predicting I. microstructure Evolution model.
acta Metallurgica Sinica, 47 (12): 1581-1590,2011; Yao Zhihao, Wang Qiuyu, Zhang Maicang, Dong Jianxin. GH738 high temperature alloy thermal deformation process microstructures Control and prediction II. microstructure Evolution model verification and application [J].
acta Metallurgica Sinica, 47 (12): 1591-1599,2011; Donachie M J, Pinkowish A A, Danesi W P, Radavich J F, Couts W H. Effect of hot work on the properties of Waspaloy [J].
metallurgical Transactions. 1970,1:2623 ~ 2630; ]; Therefore, consider in turbine disk deformation process, relate to the impact of smithing technological parameter and process control, comparatively necessary and important.Choose reasonable forging temperature, rate of deformation accurately control significant to GH4738 alloy structure; In addition, deflection is accurately controlled, turbine diskware will be made to obtain abundant recrystallization; Although the Static Recrystallization of subsequent high temperature solution treatment necessarily can adjust grain size, can not the obvious overall crystallite dimension of reduction dish forging, so be also the basis and the prerequisite that obtain excellent forging for the control of deflection; The forging deviation of parameter and the improper of control procedure, then there will be because precipitated phase is uneven or the back dissolving of carbide is separated out and brought adverse influence to crystal boundary, so that cause the harmful structures such as mixed crystal, Grain-Boundary Phase film forming and abnormal grain! growth phenomenon, thus cause alloy mechanical property to decline and the increase of unstable properties degree.Research show the improvement of subsequent heat treatment system alloy performance also serve important function [Yao Zhihao, Dong Jianxin, Zhang Maicang, etc. the relevance of GH864 alloy microscopic structure and mechanical property.
rare Metals Materials and engineering, 2010,39 (9): 1565; Guimaraes A A, Jonas J J .Recrystallization and aging effects associated with the high temperature deformation of Waspaloy and Inconel 718 [J].
metallurgical Transactions A. 1981, A12:1655-1666; Yao Zhihao, Dong Jianxin, Zhang Maicang, Yu Qiuying, Zheng Lei. solid solubility temperature is on the impact [J] of cigarette machine blade by GH864 alloy structure performance.
material heat treatment journal, 32 (7): 44-50,2011]; At present, in the actual production of GH4738 alloy, because deformation technique controls cause turbine diskware to occur cracking and organize the situation such as defective to happen occasionally, need badly and this alloy turbine dish crucial forming technology that is shaped is studied.
Summary of the invention
The object of the invention is to solve existing preparation GH4738 nickel base superalloy turbine disk complex process, efficiency low and be difficult to obtain that quality is good, Grain size distribution evenly, without the problem of face crack.Thus propose one and realize GH4738 alloy turbine dish forging and molding Controlling Technology, the GH4738 nickel base superalloy turbine disk that can reach the standard-requireds such as mechanical property is obtained to forging.
The present invention relates to GH4738 nickel-base high-temperature alloy material, composition according to mass percent is: C:0.02-0.08; Al:1.2-1.6; Ti:2.75-3.25; Co:12.0-15.0; Cr:18.0-21.0; Mo:3.5-5.0; Fe≤2.0; S≤0.001; P≤0.005; Ni surplus, in this alloy main hardening constituent be spherical gamma ' phase, M
23c
6and MC phase.
Technical scheme of the present invention is: one realizes GH4738 nickel base superalloy turbine disk manufacturing process, specifically comprises step:
Step 1.
1) the cylindrical bar blank of rule is carried out Hard Roll cover:
First, choose the cylindrical alloy bar blank of rule, the initial average grain size of rod blank is less than 170 μm, heat-preservation cotton is adopted to be wrapped up securely by the cylindrical alloy bar blank chosen coating lubricant, be that the corrosion resistant plate of 0.5-1mm carries out Hard Roll cover outside described heat-preservation cotton again with the thickness cut, and junction is welded;
2) bar that jacket is good is heated:
Be placed on by the bar that jacket is good in electric furnace effective coverage, paved below with refractory brick, heating by electric cooker temperature controls at 1060-1120 DEG C, and external armour is even connects K type galvanic couple on request;
3) upsetting cake technique:
A. after blank reaches design temperature completely, be transported to rapidly on press flat anvil after being come out of the stove by the bar of jacket, lower flat anvil paving one layer of heat preservation is cotton, and bar is placed on flat anvil centre position, and transhipment time controling is within 1min, and mold temperature is not less than 350 DEG C;
B. press is suppressed by the compacting pattern pre-set, and first height dimension is suppressed deflection 30-40%, pressurize 30s, finally again by height dimension jumping-up to the 40-50% not being out of shape at first bar height, rate of deformation controls at 5-10mm/s;
C. take off biscuit, remove outside jacket, be placed on sand pit hollow cold, for subsequent use;
Step 2:
Biscuit step 1 obtained carries out following contour forging technique control: a. first as shown in step 1) method by as described in biscuit carry out Hard Roll cover; B. be placed in electric furnace effective coverage by the biscuit that jacket is good, paved with refractory brick below, heating and temperature control is at 1060-1120 DEG C; C. external armour is even connects K type galvanic couple on request,
D. after being adjusted on press by preheated mould, use aqua lubricant lubrication impression, ensure that mold temperature is more than 350 DEG C;
E. after die forging blank reaches design temperature completely, biscuit is transported to rapidly on press die after coming out of the stove, and biscuit is placed on mould centre position, and transhipment time controling is within 1min;
F. press is suppressed by the compacting pattern pre-set, and rate of deformation controls at 5-10mm/s; Finally can suppress deflection should control, at the 55-75% of former biscuit height, after forging, to take off forging immediately, remove outside sheath material, be placed on sand pit hollow cold, for subsequent use;
Step 3:
Die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, heat treatment temperature should control at 1000-1040 DEG C of insulation 4-8 hour, then air cooling or oil cooling, then double aging process is carried out, temperature is that 700-900 DEG C of insulation 1-16h carries out air cooling, is cooled to second stage timeliness with 60 DEG C/min, is 650-800 DEG C of insulation 6-24h in temperature, air cooling carries out, and obtains the shaping GH4738 nickel base superalloy turbine disk.
Obtain GH4738 nickel base superalloy turbine diskware through said method forging, be applicable to manufacture the hot-end components such as Aero-Space engine, flue gas turbine expander GH4738 alloy turbine diskware.
The invention has the advantages that:
(1) the present invention proposes a kind of GH4738 nickel base superalloy turbine disk manufacturing process, the diskware prepared, compared with other diskwares with identical component, ensures without ftractureing and having good grain structure and better mechanical behavior under high temperature.
(2) one that the present invention proposes realizes GH4738 nickel base superalloy turbine disk manufacturing process, in heat treatment optimization, under equal forging condition can be obtained, and more excellent mechanical property.
The invention has the beneficial effects as follows: the GH4738 turbine diskware controlled through this forging forming method, then carry out suitable solid solution and aging strengthening model, and ensure the optimization of temperature and time.The heat treatment state GH4738 alloy structure finally obtained is good, and the comparatively all even grain boundary carbide of grain size intermittently distributes; Tensile property and enduring quality test result show, the turbine diskware performance realizing GH4738 nickel base superalloy turbine disk manufacturing process through this invention has all exceeded the requirement of technical conditions, make the fluctuation of alloy property reduce simultaneously, ensure that the stable operation of hot operation turbine disk parts.
Accompanying drawing explanation
Fig. 1 is original bar initial grain tissue in the embodiment of the present invention 1.
Fig. 2 is forging rear turbine disk R/2 place grain structure in the embodiment of the present invention 1.
Fig. 3 is hardening constituent distribution after turbine disk heat treatment after forging in embodiment 1.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described in detail.
Actual forging checking is carried out, such as: now certain model turbine disk GH4738 alloy bar material is forged according to the above optimal heat control process principle obtained;
Embodiment 1: the present embodiment proposes one and realizes GH4738 nickel base superalloy turbine disk manufacturing process, and obtains better performance, it is characterized in that specifically comprising the following steps:
Step 1:
1) Φ 110mm × 260mm cylindrical bar blank of rule is carried out Hard Roll cover, its Initial Grain Size is 150 μm, and to record this selected GH4738 alloy actual constituent be C:0.06; Al:1.42; Ti:3.15; Co:13.5; Cr:20.0; Mo:4.1; Ni surplus.A. first adopt heat-preservation cotton that bar is wrapped bar securely; B. then outside heat-preservation cotton, carry out Hard Roll cover with the corrosion resistant plate cut (thickness 0.8mm), and junction is welded.
2) bar that jacket is good is heated: bar is placed in electric furnace effective coverage by a., is paved below with refractory brick, and heating and temperature control is at 1080 DEG C; B. external armour is even connects K type galvanic couple on request.
3) upsetting cake technique: after a. blank reaches design temperature completely, be transported to rapidly after the bar of jacket is come out of the stove on press flat anvil, lower flat anvil paving one layer of heat preservation is cotton, and bar is placed on flat anvil centre position, transhipment time controling is within 1min, and mold temperature is not less than 350 DEG C; B. press is suppressed by the compacting pattern pre-set, and first height dimension compacting is not out of shape 30% of bar height, pressurize 30s, then by 50% of initial for height dimension jumping-up non-Deformation Height, rate of deformation controls at 10mm/s.C. take off biscuit, remove outside jacket, be placed on sand pit hollow cold; Biscuit material surface irregularities and oxide skin must be cleaned out;
Step 2:
Biscuit step 1 obtained carries out following contour forging technique control: a. is first as 1) shown in method biscuit is carried out Hard Roll cover; B. be placed in electric furnace effective coverage by the biscuit that jacket is good, paved below with refractory brick, heating and temperature control is at 1080 DEG C; C. external armour is even connects K type galvanic couple on request; D. after being adjusted on press by preheated mould, use aqua lubricant lubrication impression, ensure that temperature is more than 350 DEG C; E. after die forging blank reaches design temperature completely, biscuit is transported to rapidly on press die after coming out of the stove, and biscuit is placed on mould centre position, and transhipment time controling is within 1min; F. press is suppressed by the compacting pattern pre-set, and rate of deformation controls at 10mm/s.Finally can suppress deflection should control at 65% of former biscuit height, to ensure that enough deflections carry out recrystallization, reduces average grain size, improves diskware bulk strength, take off forging immediately after forging, removes outside sheath material, is placed on sand pit hollow cold;
Step 3:
Die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, heat treatment temperature should control at 1020 DEG C of insulations, 4 hours oil coolings, then double aging process is carried out, temperature is that 845 DEG C of insulation 4h carry out air cooling, second stage timeliness is cooled to 60 DEG C/min, be 760 DEG C in temperature and be incubated 16h, air cooling carries out.
Figure 1 shows that bar initial grain tissue, Figure 2 shows that turbine disk R/2 place grain structure after forging, can find out, comparatively evenly, there is not the phenomenon of mixed crystal in forging grain structure, is illustrated in figure 3 hardening constituent distribution after turbine disk heat treatment;
Be the mechanical property of the rear turbine disk of forging shown in table 1-table 3, carry out tangential sampling at turbine disk R/2 position, the alloy property index recorded; Can find, room temperature and high temperature tensile properties and enduring quality all far exceed technical conditions requirement, and room temperature tensile properties intensity comparison with standard value improves about 40%, and plastic elongation rate and the contraction percentage of area then improve more than 1 times; Meanwhile, this wrought alloy enduring quality improves the most obvious, and creep rupture life is more than 5 times of standard value, thus, illustrate that the turbine disk performance through forging of the present invention has larger performance margin;
Table 1 room temperature tensile properties
Table 2 high temperature tensile properties
Table 3 enduring quality
Embodiment 2: the present embodiment proposes one and realizes GH4738 nickel base superalloy turbine disk manufacturing process, and obtains better performance, it is characterized in that specifically comprising the following steps:
Step 1:
1) Φ 102mm × 270mm cylindrical bar blank of rule is carried out Hard Roll cover, its Initial Grain Size is 160 μm, and to record this selected GH4738 alloy actual constituent be C:0.04; Al:1.39; Ti:3.05; Co:13.3; Cr:19.8; Mo:4.05; Ni surplus.A. first adopt heat-preservation cotton that bar is wrapped bar securely; B. then outside heat-preservation cotton, carry out Hard Roll cover with the corrosion resistant plate cut (thickness 0.8mm), and junction is welded.
2) bar that jacket is good is heated: bar is placed in electric furnace effective coverage by a., is paved below with refractory brick, and heating and temperature control is at 1060 DEG C; B. external armour is even connects K type galvanic couple on request.
3) upsetting cake technique: after a. blank reaches design temperature completely, be transported to rapidly after the bar of jacket is come out of the stove on press flat anvil, lower flat anvil paving one layer of heat preservation is cotton, and bar is placed on flat anvil centre position as far as possible, transhipment time controling is within 1min, and mold temperature is not less than 350 DEG C; B. press is suppressed by the compacting pattern pre-set, and first by height dimension compacting 40%, pressurize 30s, then height dimension jumping-up is not out of shape 40% of bar height at first, rate of deformation controls at 5mm/s.C. take off biscuit, remove outside jacket, be placed on sand pit hollow cold; Biscuit material surface irregularities and oxide skin must be cleaned out.
Step 2:
Biscuit step 1 obtained carries out following contour forging technique control: a. is first as 1) shown in method biscuit is carried out Hard Roll cover; B. be placed in electric furnace effective coverage by the biscuit that jacket is good, paved below with refractory brick, heating and temperature control is at 1060 DEG C; C. external armour is even connects K type galvanic couple on request; D. after being adjusted on press by preheated mould, use aqua lubricant lubrication impression, ensure that temperature is more than 350 DEG C; E. after die forging blank reaches design temperature completely, biscuit is transported to rapidly on press die after coming out of the stove, and biscuit is placed on mould centre position, and transhipment time controling is within 1min; F. press is suppressed by the compacting pattern pre-set, and rate of deformation controls at 10mm/s.Finally can suppress deflection should control at 65% of former biscuit height, to ensure that enough deflections carry out recrystallization, reduces average grain size, improves diskware bulk strength, take off forging immediately after forging, removes outside sheath material, is placed on sand pit hollow cold;
Step 3:
Die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, heat treatment temperature should control at 1040 DEG C of insulations, 6 hours oil coolings, then double aging process is carried out, temperature is that 800 DEG C of insulation 8h carry out air cooling, second stage timeliness is cooled to 60 DEG C/min, be 700 DEG C in temperature and be incubated 24h, air cooling carries out.
Obtain room temperature, high temperature tensile properties and enduring quality after tested and all reach technical conditions requirement.
Embodiment 3:
The present embodiment proposes one and realizes GH4738 nickel base superalloy turbine disk manufacturing process, and obtain better performance, the difference of its forming process and embodiment 1 is step (2): biscuit step 1 obtained carries out following contour forging technique control: a. is first as 1) shown in method biscuit is carried out Hard Roll cover; B. be placed in electric furnace effective coverage by the biscuit that jacket is good, paved below with refractory brick, heating and temperature control is at 1080 DEG C; C. external armour is even connects on request, K type galvanic couple; D. after being adjusted on press by preheated mould, use aqua lubricant lubrication impression, ensure that temperature is more than 350 DEG C; E. after die forging blank reaches design temperature completely, biscuit is transported to rapidly on press die after coming out of the stove, and biscuit is placed on mould centre position, and transhipment time controling is within 1min; F. press is suppressed by the compacting pattern pre-set, and rate of deformation controls at 7mm/s.Finally can suppress deflection should control at 65% of former biscuit height, to ensure that enough deflections carry out recrystallization, reduces average grain size, improves diskware bulk strength, take off forging immediately after forging, removes outside sheath material, is placed on sand pit hollow cold; Other each steps are identical with embodiment 1.
Embodiment 4:
The present embodiment proposes one and realizes the crucial manufacturing process of the GH4738 nickel base superalloy turbine disk, and obtain better performance, the difference of its forming process and embodiment 1 is step (3): die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, solution heat treatment temperature should control at 1020 DEG C of insulations, 5 hours oil coolings, then double aging process is carried out, temperature is that 845 DEG C of insulation 4h carry out air cooling, second stage timeliness is cooled to 60 DEG C/min, be 760 DEG C in temperature and be incubated 16h, air cooling carries out, obtain room temperature after tested, high temperature tensile properties and enduring quality all reach technical conditions requirement.Other each steps are identical with embodiment 1.
Embodiment 5:
The present embodiment proposes one and realizes the crucial manufacturing process of the GH4738 nickel base superalloy turbine disk, and obtain better performance, the difference of its forming process and embodiment 1 is step (1): Φ 620mm × 1230mm cylindrical bar blank of rule is carried out Hard Roll cover, its Initial Grain Size is 120 μm, and to record this selected GH4738 alloy actual constituent be C:0.03; Al:1.49; Ti:3.25; Co:13.02; Cr:19.07; Mo:4.44; Ni surplus.A. first adopt heat-preservation cotton that bar is wrapped bar securely; B. then outside heat-preservation cotton, carry out Hard Roll cover with the corrosion resistant plate cut (thickness 0.8mm), and junction is welded;
Step (3): die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, heat treatment temperature should control at 1030 DEG C of insulations, 5 hours air coolings, then double aging process is carried out, temperature is that 845 DEG C of insulation 5h carry out air cooling, being cooled to second stage timeliness with 60 DEG C/min, is that 760 DEG C of laggard line spaces of insulation 16h are cold in temperature.Other each steps are identical with embodiment 1.Obtain room temperature, high temperature tensile properties and enduring quality after tested and all reach technical conditions requirement.
Comprehensive above to analyze, utilize turbine disk shaping critical process of the present invention to control and and appropriate heat treatment is carried out to the turbine disk, satisfied structure and properties data will be obtained, met and exceeded the requirement of technical conditions.
Claims (2)
1. realize a GH4738 nickel base superalloy turbine disk manufacturing process, it is characterized in that, specifically comprise the following steps:
Step 1:
1) the cylindrical bar blank of rule is carried out Hard Roll cover:
First, choose the cylindrical alloy bar blank of rule, the initial average grain size of rod blank is less than 170 μm, heat-preservation cotton is adopted to be wrapped up securely by the cylindrical alloy bar blank chosen coating lubricant, be that the corrosion resistant plate of 0.5-1mm carries out Hard Roll cover outside described heat-preservation cotton again with the thickness cut, and junction is welded;
2) bar that jacket is good is heated:
Be placed on by the bar that jacket is good in electric furnace effective coverage, paved below with refractory brick, heating by electric cooker temperature controls at 1060-1120 DEG C, and external armour is even connects K type galvanic couple on request;
3) upsetting cake technique:
A. after blank reaches design temperature completely, be transported to rapidly on press flat anvil after being come out of the stove by the bar of jacket, lower flat anvil paving one layer of heat preservation is cotton, and bar is placed on flat anvil centre position, and transhipment time controling is within 1min, and mold temperature is not less than 350 DEG C;
B. press is suppressed by the compacting pattern pre-set, and first height dimension is suppressed deflection 30-40%, pressurize 30s, finally again by height dimension jumping-up to the 40-50% not being out of shape at first bar height, rate of deformation controls at 5-10mm/s;
C. take off biscuit, remove outside jacket, be placed on sand pit hollow cold, for subsequent use;
Step 2:
Biscuit step 1 obtained carries out following contour forging technique control: a. first as shown in step 1) method by as described in biscuit carry out Hard Roll cover; B. be placed in electric furnace effective coverage by the biscuit that jacket is good, paved with refractory brick below, heating and temperature control is at 1060-1120 DEG C; C. external armour is even connects K type galvanic couple on request;
D. after being adjusted on press by preheated mould, use aqua lubricant lubrication impression, ensure that mold temperature is more than 350 DEG C;
E. after die forging blank reaches design temperature completely, biscuit is transported to rapidly on press die after coming out of the stove, and biscuit is placed on mould centre position, and transhipment time controling is within 1min;
F. press is suppressed by the compacting pattern pre-set, and rate of deformation controls at 5-10mm/s; Finally can suppress deflection should control, at the 55-75% of former biscuit height, after forging, to take off forging immediately, remove outside sheath material, be placed on sand pit hollow cold, for subsequent use;
Step 3:
Die forging diskware step 2 obtained carries out the Heat Treatment Control under sub-solid solution condition, heat treatment temperature should control within 4-8 hour, to carry out air cooling or oil cooling 1000-1040 DEG C of insulation, then double aging process is carried out, temperature is that 700-900 DEG C of insulation 1-16h carries out air cooling, second stage timeliness is cooled to 60 DEG C/min, be 650-800 DEG C in temperature and be incubated 6-24h, air cooling carries out, and obtains the shaping GH4738 nickel base superalloy turbine disk.
2. a GH4738 nickel base superalloy turbine disk for method process as claimed in claim 1, this GH4738 nickel base superalloy turbine disk is applicable to the turbine diskware manufacturing Aero-Space engine, flue gas turbine expander.
Priority Applications (1)
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| CN104690198B (en) * | 2013-12-10 | 2017-02-01 | 陕西宏远航空锻造有限责任公司 | Forming method of large GH4169 alloy direct aging disc forging |
| CN104368736A (en) * | 2014-11-07 | 2015-02-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Warm forging forming method for high temperature alloy GH3030 |
| CN104815935B (en) * | 2015-05-25 | 2016-09-21 | 无锡派克新材料科技股份有限公司 | A kind of T-shaped high temperature alloy GH3617M forging heating method |
| CN105069207B (en) * | 2015-07-28 | 2019-03-22 | 燕山大学 | Consider the forging process method for numerical simulation of initial uneven grain degree |
| CN105195541B (en) * | 2015-10-13 | 2017-07-18 | 北京科技大学 | Overcritical power station steam turbine blade GH4738 alloy fine grain base preparation methods |
| CN105779742B (en) * | 2016-03-04 | 2018-07-06 | 大连大高阀门股份有限公司 | Core level-one explosive valve shears cap heat treatment process |
| CN106623743B (en) * | 2016-12-01 | 2018-08-14 | 西北工业大学 | A kind of GH4738 alloy die forgings and preparation method thereof |
| CN111360186A (en) * | 2020-03-16 | 2020-07-03 | 江苏集萃先进金属材料研究所有限公司 | High-alloying nickel-based high-temperature alloy forging method |
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| CN113600950B (en) * | 2021-07-14 | 2022-04-08 | 北京科技大学 | Repeated brazing and heat treatment process for improving strength stability of GH4738 alloy |
| CN113604761B (en) * | 2021-07-14 | 2022-04-19 | 北京科技大学 | Nickel-based high-temperature alloy interrupted heat treatment process for turbine disc |
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| CN113560481B (en) * | 2021-07-30 | 2023-07-18 | 内蒙古工业大学 | Thermal processing technology of GH4738 nickel-based superalloy |
| CN113881909A (en) * | 2021-08-26 | 2022-01-04 | 北京钢研高纳科技股份有限公司 | Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging |
| CN114082876B (en) * | 2021-11-24 | 2023-11-21 | 北京钢研高纳科技股份有限公司 | High-temperature-resistant and high-durability alloy turbine disc forging and preparation method thereof |
| CN114574793B (en) * | 2022-01-25 | 2023-03-14 | 东北大学 | Heat treatment process for improving performance of GH4706 alloy |
| CN114799005A (en) * | 2022-05-06 | 2022-07-29 | 任超群 | Forging method of homogeneous fine-grain high-temperature alloy disc |
| CN116875844B (en) * | 2023-07-28 | 2024-02-09 | 北京钢研高纳科技股份有限公司 | Disk-shaft integrated turbine disk and preparation method thereof |
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