CN103394629B - A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk - Google Patents
A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk Download PDFInfo
- Publication number
- CN103394629B CN103394629B CN201310359168.7A CN201310359168A CN103394629B CN 103394629 B CN103394629 B CN 103394629B CN 201310359168 A CN201310359168 A CN 201310359168A CN 103394629 B CN103394629 B CN 103394629B
- Authority
- CN
- China
- Prior art keywords
- high temperature
- forging
- temperature alloy
- alloy blank
- blank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Forging (AREA)
Abstract
The invention discloses one and be applied to ultra-large type nickel base superalloy turbine disk forging cladding method, it relates to nickel base superalloy and heat cladding method in turbine disk forging process, and the present invention realizes as follows: initial cylindrical high temperature alloy blank is carried out heating and thermal insulation by step 1.; High temperature alloy blank after heating and thermal insulation is carried out hot jacket by step 2.; High temperature alloy blank after the hot jacket of step 3. melts down and carries out heating and thermal insulation.The present invention avoids traditional cladding method to cause high temperature alloy blank heat time in stove long, Soft Roll cover easily to come off, clamp the problems such as cracky, effectively can reduce temperature in high temperature alloy blank transhipment forging process and reduce problem, avoid ftractureing in forging deformation process, effectively reducing forging resistance of deformation, desirable grain structure can be obtained.
Description
Technical field
The present invention relates to a kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk, be incubated with the control of forging temperature in machinery industry metal material heat processing process for metallurgical, be a kind of special hot-working cladding method, be specially adapted to the situation that ultra-large type difficulty distortion nickel base superalloy strictly will control blank deformation temperature.
Background technology
Nickel base superalloy, with its excellent high-temperature behavior, is extensively 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 DEG C, and the quality of its performance determines primarily of alloy structure.But because nickel base superalloy has high-alloying element, recrystallization temperature is higher, 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 causes 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 comparatively 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.Thus, cause alloy forging forming difficulty, lumber recovery low.Particularly for the forging of the higher nickel base superalloy of hardening constituent content and superhuge nickel base superalloy steel ingot, harsh requirement is proposed to the control of temperature, thermoplasticity tolerance band is usually within 80 DEG C, and temperature range is often less required by microstructure and mechanical property, need the realization [Yao Zhihao taking the special process such as isothermal forging and hot forging measure guarantee forging and molding and best organizational controls, 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 builds new .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].
At present, because isothermal forging cost is high, operation is comparatively complicated, is unfavorable for large-scale production.General employing takes the hot forging of various Insulation to produce to blank.Typical heat preserving method uses asbestos heat insulating material to cover blank surface, to slow down the thermal loss that blank causes because of radiation and convection current.In forging process, owing to there is temperature difference between mould and blank, so asbestos pad is prevented transmission of heat by contact between mould and blank, stop the heat transfer between blank surface and air.In fact, in order to controlled forge process temperature, the heating-up temperature of forging is chosen as the upper limit of license deformation temperature range, adopt jacket parcel blank retarding heat loss simultaneously, the high insulating efficiency of insulation material is higher, the transfer process of blank and to complete time of distortion shorter, then can obtain good Deformation structure.Due to high temperature alloy can forging range very little, blank is come out of the stove and usually will be accurate to second transfer time, therefore can effectively be incubated in coming out of the stove process at blank, under needing to refill the cold condition of stokehold, asbestos insulation material is fixed on blank surface, topmost way is exactly, by the method for soldering stainless steel overcoat, insulation material is fixed on blank surface, thus ensure that asbestos mat does not come off in blank heating and transfer process of coming out of the stove, claim the method to be stainless steel alumina silicate compound jacket or Hard Roll cover in industrial production.Adopt conventional rock wool sheath material significantly can slow down the heat loss of alloy blank, be therefore used widely in the hot procedure of high temperature alloy for a long time.
But the method limitation is a lot, cannot meet the requirement of Forging Technology to forging temperature control precision completely, particularly there is following several respects outstanding problem:
One, asbestos insulation material and stainless steel outer sleeve at high temperature can not bear larger external force and distortion, namely break in the forging incipient stage, blank is directly contacted with mould and air, particularly the contact of blank and mould makes blank local temperature sharply decline, and causes the corresponding cracking destruction of forging and tissue abnormalities.Its two, stainless steel cladding method is unsuitable for many fire time forging processes such as ingot formation, more cannot implement in hammer forging technique again, in the hot rolling of bar and tubing, and on machine for rolling ring in rolling large ring process, stainless steel also cannot be adopted to add alumina silicate cladding method.Its three, in forging process, use conventional industrial asbestos material can cause serious environmental issue.Its four, cold conditions jacket causes the heat time long, easily makes that stainless steel oxidation is serious, asbestos mat occurs brittle, causes easily occurring in clamping process that jacket is cracked; Meanwhile, cross long heating and thermal insulation energy consumption serious, waste ample resources.So explore high insulating effect in a kind of sustainable development forging process, cladding method that is workable, energy conservation type be the technology that vast forge plant is needed badly.
Can only implement under blank is in cold conditions to solve stainless steel alumina silicate compound jacket, the problem of jacket cannot be carried out to high temperature blank, occur utilizing glass to have close-burning feature at hot mastication, glass dust is used alumina silicate insulation quilt to be pasted onto the method for high temperature blank surface, the method is applied to ingot formation etc. needs time forging of many fire, situation about therefore will repeatedly melt down in hot state, can solve the insulation problem that many fire forge-melt down-heat-come out of the stove.But there is viscosity deficiency, maintain the problems such as viscous state temperature range is little in the commercialization glass dust as industrial chemicals, enough viscosity can not be maintained within the scope of the relevant temperature required by heat processing technique, when blank heats and is in higher temperatures temperature in stove, glass can be too low and trickle under gravity due to viscosity, asbestos insulation material is caused to come off from blank surface, the glass melt simultaneously run off is difficult to after being retained in and solidifying in stove remove, and can cause damage to body of heater and heating system.When blank come out of the stove rear surface temperature occur declining among a small circle time, viscous layer just can be brittle because solidifying, thus come off with asbestos insulation material simultaneously.Therefore, the method still can not meet the requirement of high temperature alloy hot-working to high insulating efficiency completely.
Known according to above analysis, 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 there is important guarantee effect, there is no the support of jacket technology, some material and parts just cannot 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 forging cladding method, thus can obtain grain size qualified, without the forging of face crack, the nickel base superalloy turbine disk of the standard-requireds such as mechanical property can be reached to forging acquisition.
The first object of the present invention is the cladding method proposing the forging of a kind of ultra-large type nickel base superalloy turbine disk, and it is characterized in that, this cladding method specifically comprises the following steps:
Initial cylindrical high temperature alloy blank is carried out heating and thermal insulation by step 1.;
High temperature alloy blank after heating and thermal insulation is carried out hot jacket by step 2.;
High temperature alloy blank after the hot jacket of step 3. melts down and carries out heating and thermal insulation.
Preferably, in described step 1, heating temperature range is 1030-1100 DEG C, and temperature retention time scope is 10-15h.
Preferably, step 2 comprises the following steps:
High temperature alloy blank after heating and thermal insulation is carried out Soft Roll cover by 2.1;
High temperature alloy blank after 2.2 pairs of Soft Roll covers carries out Hard Roll cover.
Preferably, described Soft Roll cover is specially: utilize heat-preservation cotton to wrap up rear compacting to high temperature alloy blank, and heat-preservation cotton thickness is 5-20mm.
Described Hard Roll cover is specially: the high temperature alloy stock side of being wrapped by stainless steel band after Soft Roll cover; Meanwhile, the upper and lower both ends of the surface of high temperature alloy blank after Soft Roll cover adopt two stainless steel band right-angled intersections respectively and are fixedly connected with the stainless steel band of described high temperature alloy stock 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 DEG C, 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%; 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 adopting above-mentioned arbitrary cladding method, described forging method is specially:
The high temperature alloy blank height dimension that step 3 obtains by step 4. is depressed into 50% of initial cylindrical high temperature alloy blank height, pressurize continues height dimension to be deformed into 20% of initial cylindrical high temperature alloy blank height after stopping 30s again, cool after removing jacket, obtain forging;
Step 5: forging step 4 obtained carries out the heat treatment under sub-solid solution condition, carries out double aging process more afterwards.
Preferably, the heat treated temperature under described sub-solid solution condition controls 1020 DEG C ± 10 DEG C insulations 4 hours, and after insulation, oil cooling is to room temperature.
Preferably, described double aging is treated to: after the forging after oil cooling is incubated 4h at the temperature of 845 DEG C ± 10 DEG C, air cooling is to room temperature; After forging after air cooling is incubated 16h at the temperature of 760 DEG C ± 10 DEG C, air cooling is to room temperature.
The present invention adopts the method for first heating and thermal insulation reheating jacket, compared with traditional cold jacket, reduces the alloy heat time, controls alloy structure inhomogeneities, prevent grain structure from growing up and affect forging structure refinement; Reduce the risk of jacket damage, can make to be wrapped in heating, to transport in clamping process not cracky, difficult drop-off; Effectively alloy blank insulation, shortens heat time, economize energy simultaneously; The nickel base superalloy turbine disk of controlled forge process is carried out through the extraordinary cladding method of the present invention, temperature control ability can be out of shape close to isothermal forging process level, significantly improve high temperature alloy forging microstructure and mechanical property, the diskware prepared is compared with other diskwares with identical component, ensure without ftractureing and there is good grain structure and higher mechanical behavior under high temperature, raising turbine disk forging production efficiency, control product quality are stablized and reduced production cost and have important function.
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 obtained in embodiment 5.
Fig. 3 is the mixed grain structure of the forging sample ring grain structure-thick obtained when temperature retention time is long in embodiment 5.
Wherein, 1-high temperature alloy blank; 2-stainless steel band; 3-heat-preservation cotton.
Detailed description of the invention
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%; Ni surplus.
The ultra-large type nickel base superalloy turbine disk forging cladding method adopting above-mentioned alloy material to carry out, specifically comprises the following steps:
Initial cylindrical high temperature alloy blank is carried out heating and thermal insulation by step 1..
Be placed on by high temperature alloy blank in electric furnace effective coverage, paved below with refractory brick, to ensure that high temperature alloy blank is heated evenly, heating by electric cooker temperature controls at 1030-1100 DEG C, and is incubated 10-15h, makes high temperature alloy blank heating complete.Simultaneously thermocouple can be utilized to carry out thermometric to 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 high temperature alloy blank heating reaches design temperature completely, carry out jacket again, this design temperature scope is consistent with heating by electric cooker temperature, is all 1030-1100 DEG C.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 taken out from heating furnace and carries out hot jacket.
In the present invention after the insulation of high temperature alloy blank heating, hot jacket process is carried out to it.Wherein hot jacket comprises two sub-steps: first carry out Soft Roll cover, then carries out Hard Roll cover.
Soft Roll cover utilizes heat-preservation cotton to wrap up high temperature alloy blank outer surface, step is: adopt heat-preservation cotton to wrap up by around high temperature alloy blank, high-temperature agglomerant is adopted to carry out between its high temperature alloy blank and heat-preservation cotton cementing, be compacted at around blank by heat-preservation cotton after parcel, the heat-preservation cotton layer thickness of parcel is 5-20mm.
And then the Hard Roll cover carried out utilizes the partial outer face of stainless steel band to the high temperature alloy blank after Soft Roll cover to wrap up, it is characterized by: be that rectangle stainless steel band that 0.5-1.5mm is thick is wrapped in the high temperature alloy stock side wrapping up heat-preservation cotton by thickness, and weld in junction, namely cylindrical sides adopts " cartridge type " to wrap up mode; Simultaneously, upper and lower two end faces of high temperature alloy of parcel heat-preservation cotton adopt the stainless steel band of right-angled intersection to weld respectively, namely two stainless steel band right-angled intersections on each end face, and the stainless steel band that each bar stainless steel band end and described high temperature alloy stock side wrap up welds, overlap accidental to prevent Soft Roll.
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 heating and thermal insulation.
Be placed in electric furnace effective coverage by high temperature alloy blank good for jacket, paved below with refractory brick, heating by electric cooker temperature controls at 1030-1100 DEG C, can carry out forging of coming out of the stove after insulation 3-6h.Meanwhile, external armoured thermocouple can be utilized to carry out thermometric to high temperature alloy blank, and point for measuring temperature is directly contacted with the center of bottom surface on high temperature alloy blank.
After terminating above-mentioned jacket step, follow-up ultra-large type nickel base superalloy turbine disk forging can be carried out, be specially:
Step 4. forging and molding.
A. step 3 is obtained high temperature alloy blank come out of the stove after be transported to rapidly on press die, wherein, transhipment time controling within 1min, press die temperature is not less than 350 DEG C; B. press is suppressed by the compacting pattern pre-set, first height dimension is depressed into 50% of non-wrought superalloy blank (i.e. initial cylindrical high temperature alloy blank) height, pressurize stops 30s, height dimension is deformed into 20% of initial non-wrought superalloy height, rate of deformation controls at 10mm/s again; C. take off forging, remove outside jacket, be placed on 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.
Forging step 4 obtained carries out the Heat Treatment Control under sub-solid solution condition, i.e. sub-solution heat treatment, after sub-solution heat treatment temperature should control to be incubated 4h at 1020 DEG C ± 10 DEG C, oil cooling is to room temperature, then double aging process is carried out, forging after oil cooling is incubated at the temperature of 845 DEG C ± 10 DEG C 4h and carries out air cooling to room temperature, then after the forging after air cooling being incubated 16h at the temperature of 760 DEG C ± 10 DEG C, air cooling is to room temperature, reaches requirement through performance test.
embodiment 1:
Φ 600mm × 1260mm cylindrical bar blank of rule is carried out heating and thermal insulation, and its Initial Grain Size is 150 μm, 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%; Ni surplus.
Initial cylindrical high temperature alloy blank is carried out heating and thermal insulation by step 1..
Be placed in electric furnace effective coverage by high temperature alloy blank bar, paved below with refractory brick, to ensure that high temperature alloy blank is heated evenly, heating by electric cooker temperature controls at 1060 DEG C, insulation 15h.
Blank, when after blank heating insulation, takes out and carries out hot jacket by step 2..
Jacket is carried out rapidly by taking out in stove after this high temperature alloy blank heating, first Soft Roll cover is carried out: adopt heat-preservation cotton to wrap up by around high temperature alloy blank, high-temperature agglomerant is adopted to carry out between its high temperature alloy blank and heat-preservation cotton cementing, heat-preservation cotton be compacted at around high temperature alloy blank after parcel, Soft Roll cover thickness is 20mm.And then carry out Hard Roll cover, it is characterized by: be that rectangle stainless steel band that 1.0mm is thick is wrapped in the high temperature alloy stock side wrapping up heat-preservation cotton by thickness, and weld in junction, namely cylindrical sides adopts " cartridge type " to wrap up mode; Meanwhile, upper and lower two end faces of high temperature alloy blank wrapping up heat-preservation cotton adopt the stainless steel band of right-angled intersection to weld.Whole jacket process is about 3min.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 heating and thermal insulation.
Be placed in electric furnace effective coverage by the high temperature alloy blank after jacket, paved below with refractory brick, heating by electric cooker temperature controls at 1060 DEG C, forging of coming out of the stove after the insulation 5h time.
Step 4. forging and molding.
A. the high temperature alloy blank that step 3 obtains is transported to rapidly on press die after coming out of the stove, and transhipment time controling is at 1min, and press die temperature is not less than 350 DEG C; B. press is suppressed by the compacting pattern pre-set, and first height dimension is depressed into 50%, pressurize 30s of non-wrought superalloy height, then height dimension is deformed into 20% of initial non-Deformation Height, and rate of deformation controls at 10mm/s; C. take off forging, remove outside jacket, be placed on 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.
Forging step 4 obtained carries out the Heat Treatment Control under sub-solid solution condition, i.e. sub-solution heat treatment, after hot solution heat treatment temperature should control to be incubated 4 hours at 1020 DEG C ± 10 DEG C, oil cooling is to room temperature, then double aging process is carried out, forging after oil cooling is incubated at the temperature of 845 DEG C ± 10 DEG C 4h and carries out air cooling to room temperature, then after the forging after air cooling being incubated 16h at the temperature of 760 DEG C ± 10 DEG C, air cooling is to room temperature, reaches requirement through performance test.
embodiment 2:
The present embodiment adopts Φ 508mm × 1200mm cylindrical bar blank to carry out heating and thermal insulation, and its Initial Grain Size is 150 μm, 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%; Ni surplus.
The difference of its jacket and forging process and embodiment 1 is:
Heating by electric cooker temperature in step 1 controls at 1030 DEG C, and temperature retention time is 10h;
Heating by electric cooker temperature in step 3 controls at 1030 DEG C, and temperature retention time is 3h;
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.
embodiment 3:
The present embodiment adopts Φ 600mm × 1240mm cylindrical bar blank to carry out heating and thermal insulation, and its Initial Grain Size is 135 μm, 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%; Ni surplus.
The difference of its jacket and forging process and embodiment 1 is: in step 2, Soft Roll overlaps thickness is 5mm, and the stainless steel belt thickness of Hard Roll cover is 1.5mm.
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.
embodiment 4:
The present embodiment adopts Φ 580mm × 1200mm cylindrical bar blank to carry out heating and thermal insulation, and its Initial Grain Size is 120 μm, 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%; Ni surplus.
The difference of its jacket and forging process and embodiment 1 is: in step 2, Soft Roll overlaps thickness is 20mm, and the stainless steel belt thickness of Hard Roll cover is 1.5mm.
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.
embodiment 5:
The present embodiment adopts Φ 600mm × 1160mm cylindrical bar blank to carry out heating and thermal insulation, and its Initial Grain Size is 143 μm, 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%; Ni surplus.
The difference of its jacket and forging process and embodiment 1 is:
Heating by electric cooker temperature in step 3 controls at 1080 DEG C, and temperature retention time is 6h; 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, 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 mixed crystal state after tested, uneven microstructure, and to be that after later stage jacket, temperature retention time is long cause main cause.Its forging sample ring is organized as shown in Figure 3.
Comprehensive above analysis, utilizes the ultra-large type nickel base superalloy turbine disk of the present invention to forge cladding method and is suitably out of shape and heat treatment the turbine disk, will obtain satisfied structure and properties data, meet and exceed the requirement of technical conditions.
Through the ultra-large type nickel base superalloy turbine disk forging that the forging of above-mentioned cladding method obtains, microscopic structure and mechanical property can alignment requests up to standard, for raising forging production efficiency, control constant product quality with reduce costs significant.The present invention can be used for preparation ultra-large type (initial column type high temperature alloy billet size: diameter of phi >=500mm, height h >=1000mm) the nickel base superalloy turbine disk.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 illustrate and describe embodiments of the invention, for the ordinary skill in the art, be appreciated that and can carry out multiple change, amendment, replacement and modification to these embodiments without departing from the principles and spirit of the present invention, scope of the present invention is by claims and equivalency thereof.
Claims (6)
1. a cladding method for ultra-large type nickel base superalloy turbine disk forging, it is characterized in that, the method comprises the following steps:
Initial cylindrical high temperature alloy blank is carried out heating and thermal insulation by step 1.;
High temperature alloy blank after heating and thermal insulation is carried out hot jacket by step 2.;
Step 2 comprises the following steps:
High temperature alloy blank after heating and thermal insulation is carried out Soft Roll cover by 2.1; Described Soft Roll cover is specially: utilize heat-preservation cotton to wrap up rear compacting to high temperature alloy blank, and heat-preservation cotton thickness is 5-20mm;
High temperature alloy blank after 2.2 pairs of Soft Roll covers carries out Hard Roll cover; Described Hard Roll cover is specially: the high temperature alloy stock side of being wrapped by stainless steel band after Soft Roll cover; Meanwhile, the upper and lower both ends of the surface of high temperature alloy blank after Soft Roll cover adopt two stainless steel band right-angled intersections respectively and are fixedly connected with the stainless steel band of described high temperature alloy stock side, and described stainless steel band thickness is 0.5-1.5mm;
High temperature alloy blank after the hot jacket of step 3. melts down and carries out heating and thermal insulation;
The high temperature alloy blank height dimension that step 3 obtains by step 4. is depressed into 50% of initial cylindrical high temperature alloy blank height, pressurize continues height dimension to be deformed into 20% of initial cylindrical high temperature alloy blank height after stopping 30s again, cool after removing jacket, obtain forging;
The forging that step 4 obtains by step 5. carries out the heat treatment under sub-solid solution condition, carries out double aging process more afterwards.
2. a cladding method for ultra-large type nickel base superalloy turbine disk forging as claimed in claim 1, it is characterized in that, in described step 1, blank heating temperature scope is 1030-1100 DEG C, and temperature retention time scope is 10-15h.
3. a cladding method for ultra-large type nickel base superalloy turbine disk forging as claimed in claim 1, it is characterized in that, in described step 3, the high temperature alloy blank heating temperature scope after hot jacket is 1030-1100 DEG C, and temperature retention time is 3-6h.
4. a cladding method for ultra-large type nickel base superalloy turbine disk forging as claimed in claim 1, it 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%; Ni surplus; Described cylindrical high temperature alloy blank diameter Φ >=500mm, height h >=1000mm.
5. a cladding method for ultra-large type nickel base superalloy turbine disk forging as claimed in claim 1, is characterized in that, the heat treated temperature under described sub-solid solution condition controls 1020 DEG C ± 10 DEG C insulations 4 hours, and after insulation, oil cooling is to room temperature.
6. a cladding method for ultra-large type nickel base superalloy turbine disk forging as claimed in claim 1, it is characterized in that, described double aging is treated to: after the forging after oil cooling is incubated 4h at the temperature of 845 DEG C ± 10 DEG C, air cooling is to room temperature; After forging after air cooling is incubated 16h at the temperature of 760 DEG C ± 10 DEG C, air cooling is to room temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310359168.7A CN103394629B (en) | 2013-08-16 | 2013-08-16 | A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310359168.7A CN103394629B (en) | 2013-08-16 | 2013-08-16 | A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103394629A CN103394629A (en) | 2013-11-20 |
| CN103394629B true CN103394629B (en) | 2015-11-18 |
Family
ID=49558456
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310359168.7A Expired - Fee Related CN103394629B (en) | 2013-08-16 | 2013-08-16 | A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103394629B (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105479107B (en) * | 2015-12-18 | 2017-08-08 | 贵州航宇科技发展股份有限公司 | The annular forging piece manufacturing process of Rene41 alloys |
| 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 |
| CN106040928B (en) * | 2016-05-30 | 2017-10-31 | 中国航空工业集团公司北京航空材料研究院 | The especially big whole frame forging part hot forming thermal sheathing process of Type Titanium Alloy |
| 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 |
| CN111790866B (en) * | 2019-04-08 | 2022-04-05 | 中国科学院金属研究所 | Forging method and application of large-size cake blank of non-sheathed TiAl alloy |
| 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 |
| CN113458308B (en) * | 2021-06-28 | 2022-04-05 | 北京科技大学 | Limit forming method for realizing ultra-large turbine disc 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1654140A (en) * | 2005-03-04 | 2005-08-17 | 宝钢集团上海五钢有限公司 | Hot-forming and forging method for large-sized high-temperature alloy turbine disc |
| CN101070223A (en) * | 2007-06-29 | 2007-11-14 | 钢铁研究总院 | Heat-processing temperature-cntrolled heat-insulation material, its preparing method and use |
| CN100424193C (en) * | 2006-02-09 | 2008-10-08 | 沈阳黎明航空发动机(集团)有限责任公司 | GH696 alloy vane ausform forming process |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6447828A (en) * | 1987-08-12 | 1989-02-22 | Agency Ind Science Techn | Turbin disk by super plastic forging of different alloys |
| US20090000706A1 (en) * | 2007-06-28 | 2009-01-01 | General Electric Company | Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys |
-
2013
- 2013-08-16 CN CN201310359168.7A patent/CN103394629B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1654140A (en) * | 2005-03-04 | 2005-08-17 | 宝钢集团上海五钢有限公司 | Hot-forming and forging method for large-sized high-temperature alloy turbine disc |
| CN100424193C (en) * | 2006-02-09 | 2008-10-08 | 沈阳黎明航空发动机(集团)有限责任公司 | GH696 alloy vane ausform forming process |
| CN101070223A (en) * | 2007-06-29 | 2007-11-14 | 钢铁研究总院 | Heat-processing temperature-cntrolled heat-insulation material, its preparing method and use |
Non-Patent Citations (1)
| Title |
|---|
| 《GH378合金大截面钢锭偏析问题研究》;羡梦芝;《沪昌科技》;19960229;第49、50页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103394629A (en) | 2013-11-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103394629B (en) | A kind of cladding method being applied to the forging of the ultra-large type nickel base superalloy turbine disk | |
| CN103341586B (en) | Method for achieving forming of GH4738 nickel-base superalloy turbine discs | |
| CN109365728A (en) | A kind of cladding method applied to the forging of the ultra-large type nickel base superalloy turbine disk | |
| CN105200224B (en) | A kind of local post weld heat treatment method of quenched material very large vessels | |
| CN112725572B (en) | Main and auxiliary induction heating local heat treatment method | |
| CN112247478A (en) | Copper alloy casting roller sleeve assembling method | |
| CN106929653B (en) | A kind of 25Cr2Ni2MoV rotor made of steel forging heat treatment method after forging | |
| CN104646419A (en) | TiAl alloy-improved sheath and method for performing large-deformation-amount plate rolling by applying TiAl alloy-improved sheath | |
| CN103128256A (en) | Preparation method for GH 4133 nickel-base superalloy semisolid blank | |
| CN102399972B (en) | Temperature on-line measuring device for roller type quenching process of medium and heavy plate | |
| CN113857283A (en) | Forming method of high-speed tool steel bar | |
| JP2020534441A (en) | Mobile hot coil heat insulation heat treatment equipment | |
| CN106903248A (en) | Forging method | |
| CN104668316B (en) | The method and apparatus of aligning outside sintering blank stove | |
| CN100537790C (en) | The heat treating method of marine diesel oil machine bolt | |
| JP2017131939A (en) | Alloy lump manufacturing method | |
| CN111974924B (en) | Auxiliary heating method for isothermal forging die | |
| CN201381358Y (en) | System of TD process equipment | |
| CN210928038U (en) | Induction heater convenient to developments temperature measurement | |
| CN102814347A (en) | Medium carbon alloy steel electrical contact heating warm drawing process | |
| CN103586378B (en) | High temperature alloy dual-property dish forming process of roll milling | |
| CN108620452B (en) | Thermal shape correcting method for titanium alloy special-shaped tubular casting | |
| CN216095628U (en) | High-speed tool steel bar forming production system | |
| CN204509390U (en) | A kind of heat treatment device of online band pressure | |
| CN205241495U (en) | Forming die device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| CB03 | Change of inventor or designer information |
Inventor after: Yao Zhihao Inventor after: Dong Jianxin Inventor after: Liu Zhiyuan Inventor after: Li Pengchuan Inventor before: Yao Zhihao Inventor before: Dong Jianxin Inventor before: Zhang Maicang Inventor before: Li Pengchuan |
|
| COR | Change of bibliographic data | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20151013 Address after: 100007 Beijing, Dongzhimen, North Street, No. 9, No. Applicant after: China National Petroleum Corporation Applicant after: CNPC Bohai Equipment Manufacturing Co., Ltd. Applicant after: University of Science and Technology Beijing Address before: 100083 Haidian District, Xueyuan Road, No. 30, Applicant before: University of Science and Technology Beijing |
|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151118 Termination date: 20160816 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |