CN103394629A - Method for forging and sleeve packaging of ultra-large type nickel-base superalloy turbine disc - Google Patents
Method for forging and sleeve packaging of ultra-large type nickel-base superalloy turbine disc Download PDFInfo
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Abstract
The invention discloses a method for forging and sleeve packaging of an ultra-large type nickel-base superalloy turbine disc and relates to a method for heating and sleeve packaging of nickel-base superalloy during the forging process of a turbine disc. The method for forging and sleeve packaging of the ultra-large type nickel-base superalloy turbine disc is realized through the following steps: Step 1, heating and heat preserving an original cylindrical superalloy blank; Step 2, performing heat packaging on the superalloy blank after heating and heat preserving; Step 3, remelting the superalloy blank for heating and heat preserving after heat sleeve packaging. The method, disclosed by the invention, solves the problems that a traditional sleeve packaging method causes the superalloy blank to be heated for an unnecessarily long time in a furnace, a soft sleeve is easy to fall off and the clamp is easy to damage, can effectively solve the problem that the temperature of the superalloy blank is decreased during the delivery and forging processes, avoids cracking of a forge piece during the deformation process, effectively reduces the deformation resistance of the forge piece, and can obtain ideal crystalline grain structures.
Description
Technical field
The present invention relates to a kind of cladding method that the ultra-large type nickel base superalloy turbine disk forges that is applied to, for metallurgical and control insulation machinery industry metal material heat processing process forging temperature, be a kind of special hot-working cladding method, be specially adapted to the situation that the difficult distortion of ultra-large type nickel base superalloy will strictly be controlled the blank deformation temperature.
Background technology
Nickel base superalloy, with its good high-temperature behavior, extensively is selected as the turbine disk material of the industries such as oil, chemical industry, thermoelectricity and nuclear power.In turbine disk use procedure, operating temperature is generally more than 550 ℃, and the quality of its performance is mainly determined by alloy structure.Yet because nickel base superalloy has the high-alloying element, recrystallization temperature is higher, and its first fusing point is lower simultaneously, so cause the outstanding problems such as this alloy forging temperature range is narrower, distortion plasticity is poor, resistance of deformation is large, temperature influence is comparatively responsive.The reduction of deformation temperature, not only cause alloy thermoplasticity sharply to worsen, and alloy deformation temperature and sensitivity of strain rate increase along with the raising of alloying level simultaneously.It is more obvious that microstructure is subject to the technogenic influences such as deformation temperature, rate of deformation, deflection and stress state, and it is harsher than thermoplastic restriction.Thereby, cause be shaped difficulty, lumber recovery of alloy forging low.Particularly for the forging of the higher nickel base superalloy of hardening constituent content and superhuge nickel base superalloy steel ingot, control to temperature has proposed harsh requirement, the thermoplasticity tolerance band is usually in 80 ℃, and microstructure and mechanical property the subject of knowledge and the object of knowledge require temperature range often less, need to take the realization [Yao Zhihao of the special process measure guarantee forging and moldings such as isothermal forging and hot forging and best organizational controls, 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].
At present, because the isothermal forging cost is high, operation is comparatively complicated, is unfavorable for large-scale production.The hot forging production of various Insulations is taked in general employing to blank.Typical heat preserving method is to use asbestos heat insulating material to cover blank surface, the thermal loss that causes because of radiation and convection current to slow down blank.In forging process, owing between mould and blank, having temperature difference, so by asbestos pad between mould and blank and prevent transmission of heat by contact, stop the heat transfer between blank surface and air.In fact, in order to control forging temperature, the heating-up temperature of forging is chosen as the upper limit of license deformation temperature scope, adopt simultaneously jacket parcel blank retarding heat loss, the high insulating efficiency of insulation material is higher, the transfer process of blank and to complete time of distortion shorter, can obtain Deformation structure preferably.Because but the high temperature alloy forging range is very little, blank is come out of the stove and usually will be accurate to second transfer time, therefore in order in blank is come out of the stove process, can effectively to be incubated, need to refill under the cold condition of stokehold the asbestos insulation material is fixed on to blank surface, topmost way is exactly that method by the soldering stainless steel overcoat is fixed on blank surface by insulation material, thereby guarantee that asbestos mat does not come off in blank heating and the transfer process of coming out of the stove, claim in industrial production that the method is the compound jacket of stainless steel alumina silicate or Hard Roll cover.Adopt conventional asbestos sheath material can significantly slow down the heat loss of alloy blank, therefore in the hot procedure of high temperature alloy, be used widely for a long time.
But the method limitation is a lot, can't meet the requirement of Forging Technology to the forging temperature control precision fully, particularly has following several respects outstanding problem:
One, asbestos insulation material and stainless steel outer sleeve at high temperature can not be born larger external force and distortion, in the forging incipient stage, namely break, blank is directly contacted with mould and air, particularly blank sharply descends the blank local temperature with contacting of mould, causes the corresponding cracking destruction of forging and tissue abnormalities.Its two, the stainless steel cladding method is unsuitable for many fire time forging processes such as ingot formation, in hammer forging technique, implements more again, in the hot rolling of bar and tubing, and in rolling large ring process, also can't adopt stainless steel to add the alumina silicate cladding method on machine for rolling ring.Its three, in forging process, use conventional industrial asbestos material can cause serious environmental issue.Its four, the cold conditions jacket causes heat time heating time long, makes easily that stainless steel oxidation is serious, asbestos mat generation embrittlement, causes in clamping process occurring that easily jacket is cracked; Simultaneously, cross long heat tracing energy consumption serious, the waste ample resources.So explore high insulating effect in a kind of sustainable development forging process, cladding method workable, the energy conservation type is the technology that vast forge plant is needed badly.
In order to solve the compound jacket of stainless steel alumina silicate, can only under being in cold conditions, implement blank, can't carry out to the high temperature blank problem of jacket, occurred utilizing glass to have close-burning characteristics at hot mastication, use glass dust the alumina silicate insulation quilt to be sticked on to the method for high temperature blank surface, the method is applied to ingot formation etc. needs many fire to forge, situation about therefore will repeatedly melt down under hot state, can solve the insulation problem that many fire forge-melt down-heat-come out of the stove.But there is the viscosity deficiency in the commercialization glass dust as industrial chemicals, remains the problems such as the viscous state temperature range is little, can not in the desired relevant temperature scope of heat processing technique, remain enough viscosity, when blank, in stove, heat and while being in the higher temperatures temperature, glass can be too low and trickle under Action of Gravity Field due to viscosity, cause the asbestos insulation material to come off from blank surface, the glass melt that runs off simultaneously is difficult to after being retained in stove and solidifying remove, and can cause damage to body of heater and heating system.When blank is come out of the stove the rear surface temperature while occurring descending among a small circle, viscous layer just can be because solidifying embrittlement, thereby come off simultaneously with the asbestos insulation material.Therefore, the method still can not meet the requirement of high temperature alloy hot-working to high insulating efficiency fully.
As can be known according to above analysis, the forging heat preservation technology is the indivisible part of high temperature alloy forging hot-working, forging is shaped smoothly and obtains desirable microstructure property and have important guarantee effect, there is no the support of jacket technology, some material and parts just can't forging and moldings, and heat preservation technology can promote the exploitation of new material and the development of heat processing technique efficiently.
Summary of the invention
The present invention aims to provide a kind of ultra-large type nickel base superalloy turbine disk and forges cladding method, thus can obtain grain size qualified, without the forging of face crack, to forging the nickel base superalloy turbine disk that obtains to reach the standard-requireds such as mechanical property.
The first purpose of the present invention is to propose the cladding method that a kind of ultra-large type nickel base superalloy turbine disk forges, and it is characterized in that, this cladding method specifically comprises the following steps:
Step 1. is carried out heat tracing by initial cylindrical high temperature alloy blank;
Step 2. is carried out hot jacket by the high temperature alloy blank after heat tracing;
High temperature alloy blank after the hot jacket of step 3. melts down and carries out heat tracing.
Preferably, in described step 1, the heating-up temperature scope is 1030-1100 ℃, and the temperature retention time scope is 10-15h.
Preferably, step 2 comprises the following steps:
2.1 the high temperature alloy blank after heat tracing is carried out to the Soft Roll cover;
2.2 the high temperature alloy blank after the Soft Roll cover is carried out to the Hard Roll cover.
Preferably, described Soft Roll cover is specially: utilize heat-preservation cotton to wrap up rear compacting to the high temperature alloy blank, heat-preservation cotton thickness is 5-20mm.
Described Hard Roll cover is specially: by wrap high temperature alloy blank side after Soft Roll cover of stainless steel band; Simultaneously, the high temperature alloy blank up and down both ends of the surface after the Soft Roll cover adopt respectively two stainless steel band right-angled intersections and are fixedly connected with the stainless steel band of described high temperature alloy blank side, and described stainless steel band thickness is 0.5-1.5mm.
Preferably, in described step 3, the high temperature alloy blank heating temperature scope after hot jacket is 1030-1100 ℃, and temperature retention time is 3-6h.
Preferably, the composition of described nickel base superalloy according to mass percent is: C:0.01-0.08%; Al:1.0-4.6%; Ti:1.2-6.25%; Co:10.0-19.0%; Cr:12.0-21.0%; Mo:1.5-6.5%; Fe≤2.0%; S≤0.001%; P≤0.005%; The Ni surplus; Described cylindrical high temperature alloy blank diameter Φ >=500mm, height h >=1000mm.
Another object of the present invention is to provide a kind of ultra-large type nickel base superalloy turbine disk forging method that adopts above-mentioned arbitrary cladding method, described forging method is specially:
Step 4. is depressed into 50% of initial cylindrical high temperature alloy blank height by the high temperature alloy blank height dimension that step 3 obtains, pressurize continues height dimension is deformed into to 20% of initial cylindrical high temperature alloy blank height after stopping 30s again, cooling after the removing jacket, obtain forging;
Step 5: the forging that step 4 is obtained carries out the heat treatment under inferior solid solution condition, carries out afterwards the double aging processing again.
Preferably, the heat treated temperature under described inferior solid solution condition is controlled at 1020 ℃ ± 10 ℃ insulations 4 hours, and after insulation, oil cooling is to room temperature.
Preferably, described double aging is treated to: by the forging after oil cooling at the temperature of 845 ℃ ± 10 ℃ the insulation 4h after air cooling to room temperature; By the forging after air cooling at the temperature of 760 ℃ ± 10 ℃ the insulation 16h after air cooling to room temperature.
The present invention adopts the first heat tracing method of hot jacket again, with traditional cold jacket, compares, and reduces alloy heat time heating time, controls the alloy structure inhomogeneities, prevents that grain structure from growing up and affecting the forging structure refinement; Reduce the risk of jacket damage, can make to be wrapped in heating, transport in clamping process not cracky, difficult drop-off; Effectively alloy blank insulation simultaneously, shorten heat time heating time, save the energy; Through the extraordinary cladding method of the present invention, control the nickel base superalloy turbine disk of forging, can be out of shape the temperature control ability near the isothermal forging process level, significantly improve high temperature alloy forging microstructure and mechanical property, the diskware for preparing is compared with the diskware that other have identical component, assurance has important function without ftractureing and have good grain structure and higher mechanical behavior under high temperature, for raising turbine disk forging production efficiency, control product quality, stablizing and reduce production costs.
The accompanying drawing explanation
Fig. 1 is jacket schematic diagram in embodiment of the present invention 1-5, and wherein, a left side is top view, and the right side is front view.
Fig. 2 is the forging sample ring grain structure-even tissue that obtains in embodiment 5.
Fig. 3 is the forging sample ring grain structure that obtains when in embodiment 5, temperature retention time is long-thick mixed grain structure.
Wherein, 1-high temperature alloy blank; The 2-stainless steel band; The 3-heat-preservation cotton.
The specific embodiment
Below in conjunction with drawings and Examples, the present invention is further described in detail.
In the present invention, blank adopts nickel-base high-temperature alloy material, and composition according to mass percent is: C:0.01-0.08%; Al:1.0-4.6%; Ti:1.2-6.25%; Co:10.0-19.0%; Cr:12.0-21.0%; Mo:1.5-6.5%; Fe≤2.0%; S≤0.001%; P≤0.005%; The Ni surplus.
Adopt the ultra-large type nickel base superalloy turbine disk that above-mentioned alloy material carries out to forge cladding method, specifically comprise the following steps:
Step 1. is carried out heat tracing by initial cylindrical high temperature alloy blank.
The high temperature alloy blank is placed in the electric furnace effective coverage, below with refractory brick, it is paved, to guarantee the high temperature alloy blank, be heated evenly, the heating by electric cooker temperature is controlled at 1030-1100 ℃, and insulation 10-15h, makes the high temperature alloy blank heating complete.Simultaneously can utilize thermocouple to carry out thermometric to the high temperature alloy blank, point for measuring temperature is positioned at the center of bottom surface, i.e. the circle centre position of bottom surface on cylindrical high temperature alloy blank.After the high temperature alloy blank heating reaches design temperature fully, carry out jacket, this design temperature scope is consistent with the heating by electric cooker temperature, is all 1030-1100 ℃ again.The thermocouple that the present invention adopts is external armoured thermocouple, and this external armoured thermocouple is the K type thermocouple wire that the linearity is good, thermo-electromotive force is larger.
After the insulation of step 2. high temperature alloy blank heating, blank is carried out to hot jacket from taking-up heating furnace.
In the present invention, after the insulation of high temperature alloy blank heating, it is carried out to hot jacket processing.Wherein hot jacket comprises two sub-steps: at first carry out the Soft Roll cover, then carry out the Hard Roll cover.
The Soft Roll cover is to utilize heat-preservation cotton to wrap up high temperature alloy blank outer surface, step is: by around the high temperature alloy blank, adopt heat-preservation cotton to wrap up, between its high temperature alloy blank and heat-preservation cotton, adopt high-temperature agglomerant to carry out cementing, after parcel, heat-preservation cotton is compacted at around blank, the heat-preservation cotton layer thickness of parcel is 5-20mm.
And then the Hard Roll cover that carries out is that the part outer surface of the high temperature alloy blank after utilizing stainless steel band to the Soft Roll cover wraps up, it is characterized by: by thickness, be that rectangle stainless steel band that 0.5-1.5mm is thick is wrapped and in, wrapped up the high temperature alloy blank side of heat-preservation cotton, and weld in junction, namely cylindrical sides adopts " cartridge type " parcel mode; Simultaneously, two end faces in high temperature alloy up and down of parcel heat-preservation cotton adopt respectively the stainless steel band of right-angled intersection to weld, be two stainless steel band right-angled intersections on each end face, and the stainless steel band welding of each stainless steel band end and described high temperature alloy blank side parcel, to prevent Soft Roll cover accidental.
Whole hot jacket process time is more short better, should be no more than 10min.
High temperature alloy blank after step 3. jacket melts down and carries out heat tracing.
The high temperature alloy blank that jacket is good is placed in the electric furnace effective coverage, below with refractory brick, it is paved, and the heating by electric cooker temperature is controlled at 1030-1100 ℃, the forging of can coming out of the stove after being incubated 3-6h.Meanwhile, can utilize external armoured thermocouple to carry out thermometric to the high temperature alloy blank, point for measuring temperature directly is contacted with the center of bottom surface on the high temperature alloy blank.
After finishing above-mentioned jacket step, can carry out the follow-up ultra-large type nickel base superalloy turbine disk and forge, be specially:
Step 4. forging and molding.
A. step 3 is obtained high temperature alloy blank rear being transported to rapidly on press die of coming out of the stove, wherein, the transhipment time is controlled in 1min, the press die temperature is not less than 350 ℃; B. press is suppressed by the compacting pattern that sets in advance, first height dimension is depressed into to 50% of the height of wrought superalloy blank (being initial cylindrical high temperature alloy blank) not, pressurize stops 30s, height dimension is deformed into to 20% of initial not wrought superalloy height, rate of deformation is controlled at 10mm/s again; C. take off forging, remove the outside jacket, be placed on the sand pit hollow cold; Forging surface irregularities and oxide skin must be cleaned out; Ultra-large type nickel base superalloy turbine disk forging surface flawless.
Step 5: heat treatment.
The forging that step 4 is obtained carries out the Heat Treatment Control under inferior solid solution condition, it is inferior solution heat treatment, after inferior solution heat treatment temperature should be controlled at 1020 ℃ ± 10 ℃ insulation 4h, oil cooling was to room temperature, then carry out the double aging processing, forging after oil cooling is incubated to 4h at the temperature of 845 ℃ ± 10 ℃ and carries out air cooling to room temperature, then the air cooling after insulation 16h at the temperature of 760 ℃ ± 10 ℃ of the forging after air cooling, to room temperature, is reached to requirement through performance test.
Embodiment 1:
The Φ of rule 600mm * 1260mm cylindrical bar blank is carried out to heat tracing, and its Initial Grain Size is 150 μ m, and to record this selected high temperature 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.
Step 1. is carried out heat tracing by initial cylindrical high temperature alloy blank.
High temperature alloy blank bar is placed in the electric furnace effective coverage, below with refractory brick, it is paved, to guarantee the high temperature alloy blank, be heated evenly, the heating by electric cooker temperature is controlled at 1060 ℃, insulation 15h.
Step 2., after the blank heating insulation, is taken out blank to carry out hot jacket.
After this high temperature alloy blank heating is complete from taking out and carry out rapidly jacket in stove, at first carry out the Soft Roll cover: by around the high temperature alloy blank, adopt heat-preservation cotton to wrap up, between its high temperature alloy blank and heat-preservation cotton, adopt high-temperature agglomerant to carry out cementing, after parcel, heat-preservation cotton is compacted at around the high temperature alloy blank, Soft Roll cover thickness is 20mm.And then carry out the Hard Roll cover, it is characterized by: by thickness, be that rectangle stainless steel band that 1.0mm is thick is wrapped and welded in the ，Bing Zai junction, high temperature alloy blank side of wrapping up heat-preservation cotton, namely cylindrical sides adopts " cartridge type " parcel mode; Simultaneously, two of up and down of the high temperature alloy blank end face of parcel heat-preservation cotton adopts the stainless steel band of right-angled intersection to weld.The about 3min of whole jacket process.Its high temperature alloy blank jacket schematic diagram, as shown in Figure 1.
High temperature alloy blank after step 3. jacket melts down and carries out heat tracing.
High temperature alloy blank after jacket is placed in the electric furnace effective coverage, below with refractory brick, it is paved, the heating by electric cooker temperature is controlled at 1060 ℃, wait being incubated the 5h forging of coming out of the stove after the time.
Step 4. forging and molding.
A. the high temperature alloy blank that obtains of step 3 rear being transported to rapidly on press die of coming out of the stove, the transhipment time is controlled at 1min, and the press die temperature is not less than 350 ℃; B. press is suppressed by the compacting pattern that sets in advance, and first height dimension is depressed into to 50% of wrought superalloy height not, pressurize 30s, then height dimension is deformed into to 20% of initial not Deformation Height, rate of deformation is controlled at 10mm/s; C. take off forging, remove the outside jacket, be placed on the sand pit hollow cold; Forging surface irregularities and oxide skin must be cleaned out; Ultra-large type nickel base superalloy turbine disk forging surface flawless.
Step 5: heat treatment.
The forging that step 4 is obtained carries out the Heat Treatment Control under inferior solid solution condition, it is inferior solution heat treatment, the molten heat treatment temperature of thermosetting should be controlled at 1020 ℃ ± 10 ℃ the insulation 4 hours after oil cooling to room temperature, then carry out the double aging processing, forging after oil cooling is incubated to 4h at the temperature of 845 ℃ ± 10 ℃ and carries out air cooling to room temperature, then the air cooling after insulation 16h at the temperature of 760 ℃ ± 10 ℃ of the forging after air cooling, to room temperature, is reached to requirement through performance test.
Embodiment 2:
The present embodiment adopts Φ 508mm * 1200mm cylindrical bar blank to carry out heat tracing, and its Initial Grain Size is 150 μ m, and to record this selected high temperature alloy actual constituent be C:0.06%; Al:1.45%; Ti:3.10%; Co:13.2%; Cr:19.3%; Mo:4.4%; The Ni surplus.
The difference of its jacket and forging process and embodiment 1 is:
Heating by electric cooker temperature in step 1 is controlled at 1030 ℃, and temperature retention time is 10h;
Heating by electric cooker temperature in step 3 is controlled at 1030 ℃, and temperature retention time is 3h;
Other each steps and embodiment 1 are identical.Obtain after tested room temperature, high temperature tensile properties and enduring quality and all reach the technical conditions requirement.
Embodiment 3:
The present embodiment adopts Φ 600mm * 1240mm cylindrical bar blank to carry out heat tracing, and its Initial Grain Size is 135 μ m, and to record this selected high temperature alloy actual constituent be C:0.07%; Al:1.38%; Ti:3.5%; Co:13.0%; Cr:19.5%; Mo:4.3%; The Ni surplus.
The difference of its jacket and forging process and embodiment 1 is: in step 2, Soft Roll cover thickness is 5mm, and the stainless steel belt thickness of Hard Roll cover is 1.5mm.
Other each steps and embodiment 1 are identical.Obtain after tested room temperature, high temperature tensile properties and enduring quality and all reach the technical conditions requirement.
Embodiment 4:
The present embodiment adopts Φ 580mm * 1200mm cylindrical bar blank to carry out heat tracing, and its Initial Grain Size is 120 μ m, and to record this selected high temperature alloy actual constituent be C:0.05%; Al:1.47%; Ti:3.85%; Co:13.9%; Cr:21.0%; Mo:4.0%; The Ni surplus.
The difference of its jacket and forging process and embodiment 1 is: in step 2, Soft Roll cover thickness is 20mm, and the stainless steel belt thickness of Hard Roll cover is 1.5mm.
Other each steps and embodiment 1 are identical.Obtain after tested room temperature, high temperature tensile properties and enduring quality and all reach the technical conditions requirement.
Embodiment 5:
The present embodiment adopts Φ 600mm * 1160mm cylindrical bar blank to carry out heat tracing, and its Initial Grain Size is 143 μ m, and to record this selected high temperature alloy actual constituent be C:0.04%; Al:1.40%; Ti:3.25%; Co:13.9%; Cr:19.8%; Mo:4.2%; The Ni surplus.
The difference of its jacket and forging process and embodiment 1 is:
Heating by electric cooker temperature in step 3 is controlled at 1080 ℃, and temperature retention time is 6h; Other each steps and embodiment 1 are identical.Obtain after tested room temperature, high temperature tensile properties and enduring quality and all reach the technical conditions requirement, its forging sample ring is organized as shown in Figure 2.
By comparison, if when step 3 temperature retention time is 25h, sample ring is organized as the mixed crystal state after tested, and tissue odds is even, and to be that after the later stage jacket, temperature retention time is long cause main cause.Its forging sample ring is organized as shown in Figure 3.
Comprehensive above the analysis, utilize the ultra-large type nickel base superalloy turbine disk of the present invention to forge cladding method the turbine disk suitably be out of shape and heat treatment, will obtain satisfied tissue and performance data, met and exceeded the requirement of technical conditions.
Through above-mentioned cladding method, forge the ultra-large type nickel base superalloy turbine disk forging that obtains, microscopic structure and mechanical property can alignment requests up to standard, for improving forging production efficiency, control constant product quality and reducing costs significant.The present invention can be used for preparing ultra-large type (initial column type high temperature alloy billet size: diameter of phi >=500mm, the nickel base superalloy turbine disk of height h >=1000mm).Be applicable to manufacture the hot-end components such as the ultra-large type nickel base superalloy turbine disk such as oil, chemical industry, thermoelectricity and nuclear power.
Although illustrated and described embodiments of the invention, for the ordinary skill in the art, be appreciated that without departing from the principles and spirit of the present invention and can carry out multiple variation, modification, replacement and modification to these embodiment, scope of the present invention is by claims and be equal to and limit.
Claims (9)
1. one kind is applied to the cladding method that the ultra-large type nickel base superalloy turbine disk forges, and it is characterized in that, this cladding method specifically comprises the following steps:
Step 1. is carried out heat tracing by initial cylindrical high temperature alloy blank;
Step 2. is carried out hot jacket by the high temperature alloy blank after heat tracing;
High temperature alloy blank after the hot jacket of step 3. melts down and carries out heat tracing.
2. a cladding method as claimed in claim 1, is characterized in that, in described step 1, the heating-up temperature scope is 1030-1100 ℃, and the temperature retention time scope is 10-15h.
3. a cladding method as claimed in claim 1, is characterized in that, step 2 comprises the following steps:
2.1 the high temperature alloy blank after heat tracing is carried out to the Soft Roll cover;
2.2 the high temperature alloy blank after the Soft Roll cover is carried out to the Hard Roll cover.
4. cladding method as claimed in claim 1 is characterized in that:
Described Soft Roll cover is specially: utilize heat-preservation cotton to wrap up rear compacting to the high temperature alloy blank, heat-preservation cotton thickness is 5-20mm;
Described Hard Roll cover is specially: by wrap high temperature alloy blank side after Soft Roll cover of stainless steel band; Simultaneously, the high temperature alloy blank up and down both ends of the surface after the Soft Roll cover adopt respectively two stainless steel band right-angled intersections and are fixedly connected with the stainless steel band of described high temperature alloy blank side, and described stainless steel band thickness is 0.5-1.5mm.
5. a cladding method as claimed in claim 1, is characterized in that, in described step 3, the high temperature alloy blank heating temperature scope after hot jacket is 1030-1100 ℃, and temperature retention time is 3-6h.
6. a cladding method as claimed in claim 1, is characterized in that, the composition of described nickel base superalloy according to mass percent is: C:0.01-0.08%; Al:1.0-4.6%; Ti:1.2-6.25%; Co:10.0-19.0%; Cr:12.0-21.0%; Mo:1.5-6.5%; Fe≤2.0%; S≤0.001%; P≤0.005%; The Ni surplus; Described cylindrical high temperature alloy blank diameter Φ >=500mm, height h >=1000mm.
7. an employing is as the ultra-large type nickel base superalloy turbine disk forging method of arbitrary cladding method as described in claim 1-6, and described forging method is specially:
Step 4. is depressed into 50% of initial cylindrical high temperature alloy blank height by the high temperature alloy blank height dimension that step 3 obtains, pressurize continues height dimension is deformed into to 20% of initial cylindrical high temperature alloy blank height after stopping 30s again, cooling after the removing jacket, obtain forging;
Step 5: the forging that step 4 is obtained carries out the heat treatment under inferior solid solution condition, carries out afterwards the double aging processing again.
8. a ultra-large type nickel base superalloy turbine disk forging method as claimed in claim 7, is characterized in that, the heat treated temperature under described inferior solid solution condition is controlled at 1020 ℃ ± 10 ℃ insulations 4 hours, and after insulation, oil cooling is to room temperature.
9. a ultra-large type nickel base superalloy turbine disk forging method as claimed in claim 8, is characterized in that, described double aging is treated to: by the forging after oil cooling at the temperature of 845 ℃ ± 10 ℃ the insulation 4h after air cooling to room temperature; By the forging after air cooling at the temperature of 760 ℃ ± 10 ℃ the insulation 16h after air cooling to room temperature.
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| CN106040928A (en) * | 2016-05-30 | 2016-10-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal-covering process for thermal forming of super-large titanium alloy whole frame die forging |
| CN106607529A (en) * | 2015-10-27 | 2017-05-03 | 陕西宏远航空锻造有限责任公司 | Forging method for high-temperature alloy biscuits |
| CN108515132A (en) * | 2018-04-09 | 2018-09-11 | 宁波工程学院 | A kind of hot-die forging process of ni-base wrought superalloy double-properties turbine disk |
| CN109773096A (en) * | 2018-12-11 | 2019-05-21 | 陕西宏远航空锻造有限责任公司 | It is a kind of to improve flaw detection horizontal forging method and device |
| CN111496160A (en) * | 2020-04-28 | 2020-08-07 | 北京钢研高纳科技股份有限公司 | Forging method for improving end surface structure of high-temperature alloy ingot blank, application of forging method and high-temperature alloy forging blank |
| CN111790866A (en) * | 2019-04-08 | 2020-10-20 | 中国科学院金属研究所 | Forging method and application of large-size cake blank of non-sheathed TiAl alloy |
| CN112496217A (en) * | 2020-11-16 | 2021-03-16 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Integral forming method for high-temperature titanium alloy frame die forging |
| CN112808911A (en) * | 2020-12-18 | 2021-05-18 | 贵阳安大宇航材料工程有限公司 | Machining method of GH4169 disc shaft integrated forging |
| CN112828219A (en) * | 2020-12-31 | 2021-05-25 | 无锡派克新材料科技股份有限公司 | GH738 high-temperature alloy grain homogenization forging technology |
| CN113458308A (en) * | 2021-06-28 | 2021-10-01 | 北京科技大学 | Limit forming method for realizing ultra-large turbine disc forging |
| CN113564504A (en) * | 2021-07-14 | 2021-10-29 | 北京科技大学 | Heat treatment process for carrying out rapid aging on large-size GH4738 alloy forging |
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| CN104878174A (en) * | 2014-02-28 | 2015-09-02 | 钢铁研究总院 | Method for controlling heat treatment cooling speed of high temperature alloy product |
| CN104878174B (en) * | 2014-02-28 | 2018-09-07 | 钢铁研究总院 | Control the process of high temperature alloy product heat treatment cooling velocity |
| CN106607529A (en) * | 2015-10-27 | 2017-05-03 | 陕西宏远航空锻造有限责任公司 | Forging method for high-temperature alloy biscuits |
| CN105479107A (en) * | 2015-12-18 | 2016-04-13 | 贵州航宇科技发展股份有限公司 | Shaping method of annular forging of Rene41 alloy |
| CN105478643A (en) * | 2015-12-24 | 2016-04-13 | 中国第二重型机械集团德阳万航模锻有限责任公司 | GH864 high-temperature alloy die forging method |
| CN106040928A (en) * | 2016-05-30 | 2016-10-26 | 中国航空工业集团公司北京航空材料研究院 | Thermal-covering process for thermal forming of super-large titanium alloy whole frame die forging |
| CN108515132A (en) * | 2018-04-09 | 2018-09-11 | 宁波工程学院 | A kind of hot-die forging process of ni-base wrought superalloy double-properties turbine disk |
| CN108515132B (en) * | 2018-04-09 | 2019-04-16 | 宁波工程学院 | A kind of hot-die forging process of ni-base wrought superalloy double-properties turbine disk |
| CN109773096A (en) * | 2018-12-11 | 2019-05-21 | 陕西宏远航空锻造有限责任公司 | It is a kind of to improve flaw detection horizontal forging method and device |
| CN111790866A (en) * | 2019-04-08 | 2020-10-20 | 中国科学院金属研究所 | Forging method and application of large-size cake blank of non-sheathed TiAl alloy |
| CN111496160A (en) * | 2020-04-28 | 2020-08-07 | 北京钢研高纳科技股份有限公司 | Forging method for improving end surface structure of high-temperature alloy ingot blank, application of forging method and high-temperature alloy forging blank |
| CN111496160B (en) * | 2020-04-28 | 2021-12-21 | 北京钢研高纳科技股份有限公司 | Forging method for improving end surface structure of high-temperature alloy ingot blank, application of forging method and high-temperature alloy forging blank |
| CN112496217A (en) * | 2020-11-16 | 2021-03-16 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Integral forming method for high-temperature titanium alloy frame die forging |
| CN112808911A (en) * | 2020-12-18 | 2021-05-18 | 贵阳安大宇航材料工程有限公司 | Machining method of GH4169 disc shaft integrated forging |
| CN112828219A (en) * | 2020-12-31 | 2021-05-25 | 无锡派克新材料科技股份有限公司 | GH738 high-temperature alloy grain homogenization forging technology |
| CN113458308A (en) * | 2021-06-28 | 2021-10-01 | 北京科技大学 | Limit forming method for realizing ultra-large turbine disc forging |
| CN113458308B (en) * | 2021-06-28 | 2022-04-05 | 北京科技大学 | Limit forming method for realizing ultra-large turbine disc forging |
| CN113564504A (en) * | 2021-07-14 | 2021-10-29 | 北京科技大学 | Heat treatment process for carrying out rapid aging on large-size GH4738 alloy forging |
| CN113564504B (en) * | 2021-07-14 | 2022-02-11 | 北京科技大学 | Heat treatment process for carrying out rapid aging on large-size GH4738 alloy forging |
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