CN103341586A - 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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- CN103341586A CN103341586A CN2013102269978A CN201310226997A CN103341586A CN 103341586 A CN103341586 A CN 103341586A CN 2013102269978 A CN2013102269978 A CN 2013102269978A CN 201310226997 A CN201310226997 A CN 201310226997A CN 103341586 A CN103341586 A CN 103341586A
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- 229910000601 superalloy Inorganic materials 0.000 title claims abstract description 29
- 238000005242 forging Methods 0.000 claims abstract description 42
- 238000010438 heat treatment Methods 0.000 claims abstract description 30
- 238000009413 insulation Methods 0.000 claims abstract description 17
- 229920000742 Cotton Polymers 0.000 claims abstract description 15
- 238000005516 engineering process Methods 0.000 claims abstract description 9
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 42
- 235000015895 biscuits Nutrition 0.000 claims description 36
- 239000000956 alloy Substances 0.000 claims description 33
- 229910045601 alloy Inorganic materials 0.000 claims description 32
- 238000001816 cooling Methods 0.000 claims description 28
- 229910052759 nickel Inorganic materials 0.000 claims description 19
- 238000004519 manufacturing process Methods 0.000 claims description 15
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- 238000005260 corrosion 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
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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 shaping field of ni-base wrought superalloy, be a kind of when using for about 720 ℃ long-term, the nickel base superalloy turbine disk manufacturing process that it is had relatively high expectations under harsh stress conditions such as elevated temperature strength, durable creeping, fatigue and crack growth rate.
Background technology
Petrochemical industry utilizes refinery tail-gas heat energy to generate electricity and the flue gas turbine expander developed, at home and abroad is the product that has market prospects, for enormous benefits has been created in the national economic development; Simultaneously, the Aero-Space engine is needed the turbine diskware that can bear high strength at high temperature badly, and no matter is crucial turbine disk parts used on flue gas turbine expander or the Aero-Space engine, and its important materials of making this elevated temperature heat extremity piece is mainly the GH4738 nickel base superalloy.This alloy is homemade precipitation hardenable ni-base wrought superalloy, has another name called the GH864 alloy, generally uses for a long time about 720 ℃.This alloy mainly reaches grain boundary carbide mutually by γ ' and plays invigoration effect, and it possesses the ability of certain resistance to high temperature oxidation and heat erosion, and one of great advantage is exactly to have good high-temperature Strengthening and Toughening coupling; Therefore, this alloy is to make one of the turbine disk in aero-engine and the dynamic power machine and the main material of 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; ];
The GH4738 alloy is as a kind of typical difficult wrought superalloy, its alloying level height, and resistance of deformation is big, and the deformable temperature is narrow, so the shaping difficulty is very big during hot-working; Concerning the turbine diskware, often cause the forging diskware phenomenon that crackle, serious mixed crystal and crystallite dimension exceed standard to occur because forge reason, thereby cause the turbine diskware to scrap, cause enormous economic loss, even cause running device to damage and casualties.And distribution and the pattern important influence of the involutory Jin Jing's granularity of the control of hot procedure and grain boundary carbide, the too high crystal grain that then causes of forging temperature is thick, even alloy crystal boundary film forming phenomenon occurs; Forging temperature is low excessively, then causes the alloy diskware to produce forge crack.Temperature controlling is improper, certainly will affect greatly structure property.Meanwhile, rate of deformation, deflection and insulation measure etc. also can produce material impact to alloy structure.[Yao Zhihao, Dong Jianxin, Zhang Maicang. GH738 high temperature alloy thermal deformation process microstructures Control and the structure [J] of 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 modelling 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, take all factors into consideration in the turbine disk deformation process, relate to the influence of smithing technological parameter and process control, comparatively necessary and important.Accurately control is significant to the GH4738 alloy structure for choose reasonable forging temperature, rate of deformation; In addition, deflection is accurately controlled, will be made the turbine diskware obtain abundant recrystallization; Though the static recrystallization that follow-up high temperature solid solution is handled can necessarily be adjusted grain size, the obvious whole crystallite dimension of reduction dish forging not is so also be basis and the prerequisite of the good forging of acquisition for the control of deflection; Forge the improper of the deviation of parameter and control procedure, then can occur because precipitated phase Hui Rong inhomogeneous or carbide separates out and crystal boundary is brought adverse influence, so that cause mixed crystal, crystal boundary phase film forming and the abnormal grain harmful structures such as phenomenon of growing up, thereby cause alloy mechanical property to descend and the unstable properties degree increases.Studies show that the subsequent heat treatment system to the improvement of alloy property also played important function [Zhang Maicang is etc. the relevance of GH864 alloy microscopic structure and mechanical property for Yao Zhihao, Dong Jianxin.
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 to cigarette machine blade GH864 alloy structure Effect on Performance [J].
The material heat treatment journal, 32 (7): 44-50,2011]; At present, in the actual production of GH4738 alloy, because deformation technique control causes the turbine diskware cracking to occur and organize situation such as defective to happen occasionally, need badly this alloy turbine dish crucial forming technology that is shaped is studied.
Summary of the invention
The objective of the invention is to solve existing preparation GH4738 nickel base superalloy turbine disk complex process, efficient is low and be difficult to obtain that quality is good, grain size is evenly distributed, do not have the problem of face crack.Thereby a kind of realization GH4738 alloy turbine dish forging and molding control technology has been proposed, in the hope of forging the GH4738 nickel base superalloy turbine disk that obtains to reach standard-requireds such as mechanical property.
The present invention relates to the 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; The Ni surplus, in this alloy main hardening constituent be spherical gamma ' phase, M
23C
6And MC phase.
Technical scheme of the present invention is: a kind of realization GH4738 nickel base superalloy turbine disk manufacturing process specifically comprises step:
Step 1.
1) the cylindrical bar blank with rule carries out the Hard Roll cover:
At first, choose the cylindrical alloy bar blank of rule, the initial average grain size of rod blank is less than 170 μ m, the cylindrical alloy bar blank of choosing that adopts heat-preservation cotton will coat lubricant wraps up securely, be that the corrosion resistant plate of 0.5-1mm carries out the Hard Roll cover in the described heat-preservation cotton outside with the thickness that cuts again, and the junction is welded;
2) jacket is good bar heats:
The bar that jacket is good is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and the electric furnace heating and temperature control is at 1060-1120 ℃, and external armour idol connects K type galvanic couple on request;
3) rammer cake technology:
A. after blank reaches design temperature fully, be transported to rapidly on the press flat anvil after the bar of jacket come out of the stove, following flat anvil shop one deck heat-preservation cotton, bar is placed on the flat anvil centre position, and the transhipment time is controlled in 1min, and mold temperature is not less than 350 ℃;
B. press is suppressed by the compacting pattern that sets in advance, and earlier height dimension is suppressed deflection 30-40%, pressurize 30s, final again with the height dimension jumping-up to the initial 40-50% that is not out of shape the bar height, rate of deformation is controlled at 5-10mm/s;
C. take off biscuit, remove the outside jacket, be placed on air cooling in the sand pit, standby;
Step 2:
The biscuit that step 1 is obtained carry out following contour forging technique control: a. at first shown in step 1) method with as described in biscuit carry out the Hard Roll cover; B. jacket is good biscuit is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1060-1120 ℃; C. external armour idol connects K type galvanic couple on request,
D. preheating is good mould uses the lubricated impression of aqua lubricant after press is adjusted, guarantee that mold temperature is more than 350 ℃;
E. after the die forging blank reaches design temperature fully, be transported to rapidly after biscuit is come out of the stove on the press die, biscuit is placed on the mould centre position, the transhipment time is controlled in 1min;
F. press is suppressed by the compacting pattern that sets in advance, and rate of deformation is controlled at 5-10mm/s; Finally can suppress deflection and should control 55-75% at former biscuit height, take off forging after the forging immediately, remove the outside sheath material, be placed on air cooling in the sand pit, standby;
Step 3:
The die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, heat treatment temperature should be controlled 1000-1040 ℃ of insulation 4-8 hour, air cooling or oil cooling then, carrying out double aging then handles, temperature is that 700-900 ℃ of insulation 1-16h carries out air cooling, is cooled to the second stage timeliness with 60 ℃/min, is 650-800 ℃ of insulation 6-24h in temperature, air cooling carries out, and the GH4738 nickel base superalloy turbine disk obtains being shaped.
Forge acquisition GH4738 nickel base superalloy turbine diskware through said method, be applicable to and make Aero-Space engine, flue gas turbine expander hot-end components such as 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 for preparing is compared with the diskware that other have identical component, guarantees not have cracking and has good grain structure and better mechanical behavior under high temperature.
(2) a kind of realization GH4738 nickel base superalloy turbine disk manufacturing process of the present invention's proposition aspect heat treatment optimization, can obtain under the equal forging condition more excellent mechanical property.
The invention has the beneficial effects as follows: the GH4738 turbine diskware through the control of this forging and molding method, then carry out suitable solid solution and timeliness heat treatment, and guarantee the optimization of temperature and time.The heat treatment state GH4738 alloy structure that obtains at last is good, and grain size comparatively all even grain boundary carbide intermittently distributes; Tensile property and enduring quality test result show, all surpassed the requirement of technical conditions through the turbine diskware performance of the realization GH4738 of this invention nickel base superalloy turbine disk manufacturing process, the fluctuation of alloy property is reduced, guaranteed the stable operation of hot operation turbine disk parts.
Description of drawings
Fig. 1 is the initial grain structure of original bar in the embodiment of the invention 1.
Fig. 2 forges turbine disk R/2 place, back grain structure in the embodiment of the invention 1.
Fig. 3 forges hardening constituent distribution after the turbine disk heat treatment of back among the embodiment 1.
The specific embodiment
Below in conjunction with drawings and Examples the present invention is further described in detail.
Carry out actual forging according to the optimal heat processing technology control principle of above acquisition and produce checking, for example: now certain model turbine disk is forged with the GH4738 alloy bar material;
Embodiment 1: present embodiment proposes a kind of realization GH4738 nickel base superalloy turbine disk manufacturing process, and obtains better performance, it is characterized in that specifically may further comprise the steps:
Step 1:
1) the Φ 110mm * 260mm cylindrical bar blank with rule carries out the Hard Roll cover, and its initial crystallite dimension is 150 μ m, 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; The Ni surplus.A. at first adopt heat-preservation cotton that bar is wrapped bar securely; B. carry out the Hard Roll cover with the corrosion resistant plate (thickness 0.8mm) that cuts in the heat-preservation cotton outside then, and the junction is welded.
2) jacket is good bar heats: a. is placed on bar in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1080 ℃; B. external armour idol connects K type galvanic couple on request.
3) rammer cake technology: after a. blank reaches design temperature fully, after coming out of the stove, the bar of jacket is transported to rapidly on the press flat anvil, following flat anvil shop one deck heat-preservation cotton, and bar is placed on the flat anvil centre position, the control of transhipment time is in 1min, and mold temperature is not less than 350 ℃; B. press is suppressed by the compacting pattern that sets in advance, and earlier 30% of bar height is not out of shape in the height dimension compacting, pressurize 30s, and with 50% of the initial not Deformation Height of height dimension jumping-up, rate of deformation is controlled at 10mm/s again.C. take off biscuit, remove the outside jacket, be placed on air cooling in the sand pit; Biscuit material surface irregularities and oxide skin must be cleaned out;
Step 2:
The biscuit that step 1 is obtained carries out following contour forging technique control: a. is at first as 1) shown in method biscuit is carried out the Hard Roll cover; B. jacket is good biscuit is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1080 ℃; C. external armour idol connects K type galvanic couple on request; D. preheating is good mould uses the lubricated impression of aqua lubricant after press is adjusted, guarantee that temperature is more than 350 ℃; E. after the die forging blank reaches design temperature fully, be transported to rapidly after biscuit is come out of the stove on the press die, biscuit is placed on the mould centre position, the transhipment time is controlled in 1min; F. press is suppressed by the compacting pattern that sets in advance, and rate of deformation is controlled at 10mm/s.Finally can suppress deflection and should control at 65% of former biscuit height, carry out recrystallization to guarantee enough deflections, reduce average grain size, improve the diskware bulk strength, take off forging after the forging immediately, remove the outside sheath material, be placed on air cooling in the sand pit;
Step 3:
The die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, heat treatment temperature should be controlled at 4 hours oil coolings of 1020 ℃ of insulations, carrying out double aging then handles, temperature is that 845 ℃ of insulation 4h carry out air cooling, be cooled to the second stage timeliness with 60 ℃/min, be 760 ℃ in temperature and be incubated 16h, air cooling carries out.
Figure 1 shows that the initial grain structure of bar, Figure 2 shows that and forge turbine disk R/2 place, back grain structure that as can be seen, the forging grain structure is comparatively even, the phenomenon of mixed crystal do not occur, be illustrated in figure 3 as hardening constituent distribution after the turbine disk heat treatment;
Be the mechanical property of forging the back turbine disk shown in the table 1-table 3, carry out tangential sampling at turbine disk R/2 position, the alloy property index that records; Can find that room temperature and high temperature tensile properties and enduring quality all far surpass the technical conditions requirement, it is about 40% that room temperature tensile performance intensity comparison with standard value has improved, and plastic elongation rate and the contraction percentage of area have then improved more than 1 times; Simultaneously, this wrought alloy enduring quality improves the most obvious, and be more than 5 times of standard value creep rupture life, thereby, illustrate that the turbine disk performance of forging production through the present invention has bigger performance margin;
Table 1 room temperature tensile performance
Table 2 high temperature tensile properties
Table 3 enduring quality
Embodiment 2: present embodiment proposes a kind of realization GH4738 nickel base superalloy turbine disk manufacturing process, and obtains better performance, it is characterized in that specifically may further comprise the steps:
Step 1:
1) the Φ 102mm * 270mm cylindrical bar blank with rule carries out the Hard Roll cover, and its initial crystallite dimension is 160 μ m, 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; The Ni surplus.A. at first adopt heat-preservation cotton that bar is wrapped bar securely; B. carry out the Hard Roll cover with the corrosion resistant plate (thickness 0.8mm) that cuts in the heat-preservation cotton outside then, and the junction is welded.
2) jacket is good bar heats: a. is placed on bar in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1060 ℃; B. external armour idol connects K type galvanic couple on request.
3) rammer cake technology: after a. blank reaches design temperature fully, after coming out of the stove, the bar of jacket is transported to rapidly on the press flat anvil, following flat anvil shop one deck heat-preservation cotton, and bar is placed on the flat anvil centre position as far as possible, the control of transhipment time is in 1min, and mold temperature is not less than 350 ℃; B. press is suppressed by the compacting pattern that sets in advance, and with height dimension compacting 40%, pressurize 30s is not out of shape 40% of bar height at first with the height dimension jumping-up more earlier, and rate of deformation is controlled at 5mm/s.C. take off biscuit, remove the outside jacket, be placed on air cooling in the sand pit; Biscuit material surface irregularities and oxide skin must be cleaned out.
Step 2:
The biscuit that step 1 is obtained carries out following contour forging technique control: a. is at first as 1) shown in method biscuit is carried out the Hard Roll cover; B. jacket is good biscuit is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1060 ℃; C. external armour idol connects K type galvanic couple on request; D. preheating is good mould uses the lubricated impression of aqua lubricant after press is adjusted, guarantee that temperature is more than 350 ℃; E. after the die forging blank reaches design temperature fully, be transported to rapidly after biscuit is come out of the stove on the press die, biscuit is placed on the mould centre position, the transhipment time is controlled in 1min; F. press is suppressed by the compacting pattern that sets in advance, and rate of deformation is controlled at 10mm/s.Finally can suppress deflection and should control at 65% of former biscuit height, carry out recrystallization to guarantee enough deflections, reduce average grain size, improve the diskware bulk strength, take off forging after the forging immediately, remove the outside sheath material, be placed on air cooling in the sand pit;
Step 3:
The die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, heat treatment temperature should be controlled at 6 hours oil coolings of 1040 ℃ of insulations, carrying out double aging then handles, temperature is that 800 ℃ of insulation 8h carry out air cooling, be cooled to the second stage timeliness with 60 ℃/min, be 700 ℃ 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 the technical conditions requirement.
Embodiment 3:
Present embodiment proposes a kind of realization GH4738 nickel base superalloy turbine disk manufacturing process, and the acquisition better performance, the difference of its forming process and embodiment 1 is step (2): the biscuit that step 1 is obtained carries out following contour forging technique control: a. is at first as 1) shown in method biscuit is carried out the Hard Roll cover; B. jacket is good biscuit is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1080 ℃; C. external armour idol connects K type galvanic couple on request; D. preheating is good mould uses the lubricated impression of aqua lubricant after press is adjusted, guarantee that temperature is more than 350 ℃; E. after the die forging blank reaches design temperature fully, be transported to rapidly after biscuit is come out of the stove on the press die, biscuit is placed on the mould centre position, the transhipment time is controlled in 1min; F. press is suppressed by the compacting pattern that sets in advance, and rate of deformation is controlled at 7mm/s.Finally can suppress deflection and should control at 65% of former biscuit height, carry out recrystallization to guarantee enough deflections, reduce average grain size, improve the diskware bulk strength, take off forging after the forging immediately, remove the outside sheath material, be placed on air cooling in the sand pit; Other each steps and embodiment 1 are identical.
Embodiment 4:
Present embodiment proposes the crucial manufacturing process of a kind of realization GH4738 nickel base superalloy turbine disk, and acquisition better performance, the difference of its forming process and embodiment 1 is step (3): the die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, solution heat treatment temperature should be controlled at 5 hours oil coolings of 1020 ℃ of insulations, carrying out double aging then handles, temperature is that 845 ℃ of insulation 4h carry out air cooling, be cooled to the second stage timeliness with 60 ℃/min, be 760 ℃ in temperature and be incubated 16h, air cooling carries out, and obtains room temperature after tested, high temperature tensile properties and enduring quality all reach the technical conditions requirement.Other each steps and embodiment 1 are identical.
Embodiment 5:
Present embodiment proposes the crucial manufacturing process of a kind of realization GH4738 nickel base superalloy turbine disk, and acquisition better performance, the difference of its forming process and embodiment 1 is step (1): the Φ 620mm * 1230mm cylindrical bar blank of rule is carried out the Hard Roll cover, its initial crystallite dimension is 120 μ m, 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; The Ni surplus.A. at first adopt heat-preservation cotton that bar is wrapped bar securely; B. carry out the Hard Roll cover with the corrosion resistant plate (thickness 0.8mm) that cuts in the heat-preservation cotton outside then, and the junction is welded;
Step (3): the die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, heat treatment temperature should be controlled at 5 hours air coolings of 1030 ℃ of insulations, carrying out double aging then handles, temperature is that 845 ℃ of insulation 5h carry out air cooling, being cooled to the second stage timeliness with 60 ℃/min, is that 760 ℃ of laggard line spaces of insulation 16h are cold in temperature.Other each steps and embodiment 1 are identical.Obtain room temperature, high temperature tensile properties and enduring quality after tested and all reach the technical conditions requirement.
Comprehensive above the analysis, utilize turbine disk shaping critical process control of the present invention and and the turbine disk carried out appropriate heat treatment, will obtain satisfied tissue and performance data, met and exceeded the requirement of technical conditions.
Claims (2)
1. realize GH4738 nickel base superalloy turbine disk manufacturing process for one kind, it is characterized in that, specifically may further comprise the steps:
Step 1.
1) the cylindrical bar blank with rule carries out the Hard Roll cover:
At first, choose the cylindrical alloy bar blank of rule, the initial average grain size of rod blank is less than 170 μ m, the cylindrical alloy bar blank of choosing that adopts heat-preservation cotton will coat lubricant wraps up securely, be that the corrosion resistant plate of 0.5-1mm carries out the Hard Roll cover in the described heat-preservation cotton outside with the thickness that cuts again, and the junction is welded;
2) jacket is good bar heats:
The bar that jacket is good is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and the electric furnace heating and temperature control is at 1060-1120 ℃, and external armour idol connects K type galvanic couple on request;
3) rammer cake technology:
A. after blank reaches design temperature fully, be transported to rapidly on the press flat anvil after the bar of jacket come out of the stove, following flat anvil shop one deck heat-preservation cotton, bar is placed on the flat anvil centre position, and the transhipment time is controlled in 1min, and mold temperature is not less than 350 ℃;
B. press is suppressed by the compacting pattern that sets in advance, and earlier height dimension is suppressed deflection 30-40%, pressurize 30s, final again with the height dimension jumping-up to the initial 40-50% that is not out of shape the bar height, rate of deformation is controlled at 5-10mm/s;
C. take off biscuit, remove the outside jacket, be placed on air cooling in the sand pit, standby;
Step 2:
The biscuit that step 1 is obtained carry out following contour forging technique control: a. at first shown in step 1) method with as described in biscuit carry out the Hard Roll cover; B. jacket is good biscuit is placed in the electric furnace effective coverage, with refractory brick it is filled up below, and heating and temperature control is at 1060-1120 ℃; C. external armour idol connects K type galvanic couple on request;
D. preheating is good mould uses the lubricated impression of aqua lubricant after press is adjusted, guarantee that mold temperature is more than 350 ℃;
E. after the die forging blank reaches design temperature fully, be transported to rapidly after biscuit is come out of the stove on the press die, biscuit is placed on the mould centre position, the transhipment time is controlled in 1min;
F. press is suppressed by the compacting pattern that sets in advance, and rate of deformation is controlled at 5-10mm/s; Finally can suppress deflection and should control 55-75% at former biscuit height, take off forging after the forging immediately, remove the outside sheath material, be placed on air cooling in the sand pit, standby;
Step 3:
The die forging diskware that step 2 is obtained carries out the Heat Treatment Control under the inferior solid solution condition, heat treatment temperature should be controlled 1000-1040 ℃ of insulation and carry out air cooling or oil cooling in 4-8 hour, carrying out double aging then handles, temperature is that 700-900 ℃ of insulation 1-16h carries out air cooling, be cooled to the second stage timeliness with 60 ℃/min, be 650-800 ℃ in temperature and be incubated 6-24h, air cooling carries out, and the GH4738 nickel base superalloy turbine disk obtains being shaped.
One kind according to claim 1 the GH4738 nickel base superalloy turbine disk handled of method be applicable to and make Aero-Space engine, flue gas turbine expander with the forging production of turbine diskware.
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