CN110551955B - Method for reducing internal residual stress of GH4169 alloy large-size disc forging - Google Patents
Method for reducing internal residual stress of GH4169 alloy large-size disc forging Download PDFInfo
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- CN110551955B CN110551955B CN201910789217.8A CN201910789217A CN110551955B CN 110551955 B CN110551955 B CN 110551955B CN 201910789217 A CN201910789217 A CN 201910789217A CN 110551955 B CN110551955 B CN 110551955B
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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Abstract
The invention belongs to the technical field of preparation of deformation high-temperature alloy GH4169 disc forgings for advanced aeroengines, and relates to a method for reducing internal residual stress of GH4169 alloy large-size disc forgings. The method comprises the following steps: preparing GH4169 alloy pure smelting ingot; homogenizing GH4169 cast ingot; casting ingot cogging; preparing a cake blank; compounding and sheathing; gradient speed control isothermal die forging; carrying out heat treatment on the disc forging; rough machining; and (5) stress relief annealing. The prepared low-stress GH4169 alloy disc forging piece not only ensures that the internal stress of the deformed high-temperature alloy cast ingot is released slowly, but also improves the metallurgical quality inside the alloy ingot. The method can be used for preparing parts such as a high-pressure compressor disk, a high-pressure turbine disk, a low-pressure turbine disk and the like of an advanced aero-engine.
Description
The technical field is as follows:
the method belongs to the field of advanced deformation high-temperature alloy disc forging preparation processes. Relates to a process method for reducing the residual stress of a GH4169 alloy disc forging, reducing the machining and use deformation and accurately controlling the size of the disc.
Background art:
the advanced preparation technology of the deformed high-temperature alloy disk piece (turbine disk and high-pressure compressor disk) for the aircraft engine. The residual stress refers to the elastic stress of an object keeping balance under the action of no external force or external moment, and is an important research content of the surface integrity of the metal parts. The fatigue resistance of the disc of the aircraft engine is greatly influenced, so that the disc is valued at home and abroad.
Metallic parts, including GH4169 alloy turbine disks, whether hot or cold worked, develop residual stresses internally. The residual stress in the GH4169 disc cannot be completely eliminated due to various reasons such as a preparation process, a working environment and the like, and 3 natural aging, artificial aging and vibration aging are commonly used for reducing the adverse effect of the residual stress on metal parts. And (1) naturally aging. The forgings are stored for a long time of half a year or more, so that the residual stress is slowly relaxed. The method needs too long time, the internal stress is not completely eliminated, and the production is less; (2) and (5) artificial aging. Also called stress relief annealing, heating a workpiece to a certain temperature, preserving heat for a long time, and then slowly cooling. Because the yield limit of the metal after being heated is greatly reduced, local plastic deformation occurs when the residual stress exceeds the yield limit, and therefore the metal is fully relaxed in the slow cooling process. The stress-relief annealing effect is related to the heating temperature and the holding time. The higher the heating temperature is, the more thorough the stress removal is, and the less the required heat preservation time is; (3) and (5) vibration aging. A method for mechanically removing stress. When stress is removed, a vibration exciter is used to make the workpiece vibrate with a certain intensity (additional dynamic stress) near its resonant frequency, and the local plastic deformation after the dynamic stress and residual stress are superimposed is used to relax and homogenize the internal stress. Among the three methods, the low-temperature aging heat treatment of the GH4169 disc prepared by the direct aging process without the solid solution treatment cannot completely eliminate the residual stress in the forged piece by the artificial aging stress reduction method. The application of the method for relieving the residual stress by vibration aging on the turbine disk is not researched, and whether the performance of the GH4169 alloy turbine disk is damaged or not in the high-frequency vibration process needs to be proved by research.
At present, GH4169 disc parts produced in China generally have abnormal deformation caused by residual stress after parts are machined, so that the size of the disc parts is out of tolerance, and great hidden danger is brought to the reliability of an engine and the safety of an airplane. According to statistics, the size of a GH4169 disc of a certain type of mass-produced engine after finish machining is almost 100% out of tolerance, and the requirement can be met only by adding more than 2 times of rework correction.
Because the testing methods of different residual stresses are limited by the detection depth and the detection area, the research on the detection of the residual stress of the IN718 disk and the established detection standard are different. At present, the foreign method for detecting the residual stress of the high-temperature alloy disc part of the aeroengine mainly comprises an X-ray diffraction method (XRD method), a computational simulation method, an electrochemical polishing method, a neutron diffraction method and the like. The comparison of the detection depth and the detection area of various residual stress measurement methods shows that the detection depth of the X-ray diffraction method is about 10 mu m, and the method belongs to the material surface layer detection technology. The detection depth of the neutron diffraction technology can reach 10cm, and the internal stress of the material can be measured.
And a lot of research work is carried out on the residual stress of the high-temperature alloy forging in China. The american Air Force Materials Laboratory (AFML) has conducted systematic research on the surface integrity of superalloys for more than twenty years, and the contents relate to the surface morphology, residual stress and fatigue properties formed by various processing procedures of the superalloys, forming a surface integrity processing and manufacturing system, and the residual stress becomes a core means and key parameters for controlling the technology. IN terms of the residual stress detection standard, the related specifications of the XRD method for determining the residual stress are established IN the United states, research and research of various testing methods are also carried out IN engineering, a corresponding standard system is formed, and the corresponding standard system comprises a damaged drilling strain method and a nondestructive X-ray diffraction method, but the specific specifications of the residual stress test of the IN718 alloy disk part are not established. In recent years, NASA, siemens, germany, and roclo, uk, have also continually optimized the manufacturing processes and adopted new materials to make engine components, all of which have required critical and core residual stress testing and process parameter control to limit residual stresses to a certain range. There are various methods for detecting residual stress of metal material forgings (including deformed high-temperature alloy disc forgings). The technology for measuring the residual stress of the metal parts by the X-ray diffraction method is mature, high in efficiency, accurate and reliable in result, and is widely applied to the measurement of the residual stress of the high-temperature alloy turbine disc. The XRD technology is adopted by a certain famous airline company abroad for measuring the residual stress of the low-pressure turbine disk of the aero-engine, namely, the residual stress value of the surface of the disk is measured by adopting an X-ray diffraction method, and the maximum value requirement of the residual stress of the surface layer (more than about 0.025 mm) of the disk shaft type rotating part is not higher than a certain critical value. The neutron diffraction method is a nondestructive testing analysis method which can be used for measuring the three-dimensional residual stress distribution in the material. The neutron diffraction technology is an effective method for nondestructively measuring the internal residual stress of the material at present. In the eighties of the last century, neutron diffraction methods were first adopted in the united states, germany and uk to measure the internal stress of materials. Currently, the united states has the most advanced neutron diffraction residual stress measurement instrument worldwide, wherein the BT8 residual stress diffractometer of the national institute of technology (NIST) can perform three-dimensional stress measurement and the like. Compared with X-ray and synchrotron radiation, neutrons have stronger penetrating power and are more favorable for measuring the stress state in materials or engineering components. For most materials, the neutron penetration capacity is several orders of magnitude higher than that of conventional X-rays, for engineering applications it can extend to depths of several centimeters in structural components to obtain residual strain information, and in principle the neutron penetration capacity allows free choice of the direction of measurement of the strain inside the material, but it has the disadvantages of high cost, long time and the presence of trace radiation of the metal parts after measurement. Neutron diffraction measurement of residual stress generated IN the process from forging to quenching of an alloy disk manufactured by IN718 alloy is carried out by S.tin of Cambridge university IN UK, and the result shows that the central residual stress of the end part of the alloy disk is as high as 400MPa tensile stress, and the surface of the alloy disk is as high as 600MPa compressive stress. Neutron diffraction residual stress measurement is carried out on the IN718 alloy disk which is forged and quenched with water and has the diameter of 40 cm by M.A.Rist, so that the compressive stress on the surface of the alloy disk is balanced by the tensile stress at the center of the disk, and the tangential maximum compressive stress on the surface of the alloy disk is 400MPa to 500 MPa. The numerical simulation technology is widely applied to research on residual stress of metal parts, and although the numerical simulation cannot obtain an accurate value of the residual stress in the disc, a credible distribution rule can be given to the distribution state of the residual stress of the disc through calculation, so that the numerical simulation technology has certain guiding significance. Finite element simulation of residual stress generated IN the process from forging to quenching of an IN718 alloy manufacturing alloy disc by Cambridge university IN England shows that the maximum residual stress of an alloy disc forging is distributed on the surface and is up to 750 MPa, and the maximum residual stress is similar to a neutron diffraction measurement value.
In the research aspect of residual stress of high-temperature alloy materials, related research work is also carried out by related domestic units. The patent (CN106637012A, a manufacturing method of a low-stress GH4169 high-temperature alloy ring) provides a manufacturing method of a low-stress GH4169 high-temperature alloy ring, which comprises the steps of heating and insulating a GH4169 alloy bar, upsetting and punching the bar, pre-rolling the bar and finishing the bar to form the ring, carrying out solution treatment on the ring, cooling the ring by using a water medium with the temperature of more than or equal to 160 ℃, carrying out cold bulging, wherein the bulging amount is 1.8-2.2%, and carrying out aging treatment after bulging to obtain the low-stress GH4169 high-temperature alloy ring. This patent is of little relevance to the present disclosure. The patent (CN106086729A, a process for controlling stress change of high-temperature alloy by aging time) relates to a process for controlling stress change of high-temperature alloy GH141 by aging time, and belongs to the technical field of heat treatment of high-temperature alloy. The method is characterized in that: and simulating the welding process of the sample on a thermal simulation experiment machine. Adding a load which is uniformly loaded along the axial direction in the temperature reduction process to obtain a heat affected zone which is equivalent to the residual stress and is subjected to welding heat impact. The stress with smaller value can be obtained conveniently, and the generation of age cracks can be avoided. The innovation point of the patent is greatly different from that of the invention. In addition, a patent (CN104707929A, a die forging method of a high-temperature alloy disc) relates to a hot working method of the structure and performance of a high-temperature alloy turbine disc forging, and proposes a forging method of performing die forging, reaming and die forging, which includes determining the specification and size of a blank required by finish forging, preparing a finish forging die and a preform forging die, performing die forging, reaming to the blank required by finish forging, and performing the finish forging process; determining a ring blank as a rough shape according to the shape of the forging; the alloy bar is forged by a preforming die at first fire, and the traditional processes of cake upsetting, punching and expanding are combined at the first fire; removing the core material; reaming the preformed forging to a rough shape size required by finish forging; and finally forging and firing to form. This invention is greatly different from the present invention. In addition, the residual stress characteristic of the powder superalloy disk in the preparation process is determined by the Beijing aviation material institute by an XRD method. The residual stress in three states of isothermal forging, annealing and machining, oil quenching and aging heat treatment is determined and analyzed by an XRD method, and the conclusion that the residual stress in the disc after quenching is the largest and is at the level of-600 MPa (the negative value represents the compressive stress) in the compressive stress state, and the residual stress after isothermal forging, annealing and machining is smaller and is lower than-300 MPa is obtained. After quenching, thermal stress in the disc can be effectively eliminated through aging, but when the disc is aged, a part of strengthening phases are precipitated to generate phase change stress, and the internal stress of the disc after aging is the resultant force of the two stresses.
Through retrieval, no technical literature which is completely the same as the innovation point of the invention is found at present.
Disclosure of Invention
The purpose of the invention is as follows: the process method is used for controlling and relieving the residual stress of the GH4169 alloy large-size (the outer diameter phi is more than 400mm) disc forging, reducing the processing and use size deformation of the disc, and accurately controlling the shape and the size of the disc, so that the problems of engine thrust attenuation, vibration and the like caused by the size deformation of the GH4169 alloy disc under the working conditions of high temperature, high pressure and high load after the installation is in service are avoided, and the use requirements of advanced aeroengines in China on high-performance deformation high-temperature alloy discs are met.
The technical scheme of the invention is as follows:
a process method for reducing residual stress in a GH4169 alloy large-size disc forging is characterized by comprising the following steps:
step 1, batching according to the target value of the chemical components of the GH4169 alloy;
step 2, vacuum induction melting;
step 3, carrying out electroslag remelting in inert gas protective atmosphere;
step 4, preparing GH4169 alloy cast ingot through vacuum consumable remelting;
step 5, homogenizing and heat treating the GH4169 alloy ingot;
6, sawing the GH4169 alloy cast ingot subjected to the homogenization heat treatment to remove loose heads and holes, and machining to remove oxide skin;
step 7, placing the treated GH4169 alloy ingot into a heat treatment furnace for heating, wherein the heating temperature and the heat preservation time of the center of the ingot are 1050 +/-30 ℃ multiplied by 1-2 h;
8, cogging the GH4169 alloy cast ingot, and forging to prepare a bar;
step 9, according to the size specification of the forged disc forging piece, sawing a GH4169 alloy bar into a cylindrical section blank, and manufacturing the heated cylindrical section blank into a cake blank by using a hydraulic press;
step 10, compounding and sheathing: adopting aluminum silicate heat preservation cotton and a stainless steel band to coat the GH4169 alloy cake blank;
step 11, charging into a furnace for heating: loading the sheathed GH4169 alloy cake blank into a trolley type precision heat treatment furnace, and heating and preserving heat at the maximum temperature of 1010 +/-20 ℃;
step 12, preparing a GH4169 alloy disc forging by gradient speed-control isothermal die forging and cooling;
step 13, carrying out heat treatment on the die-forged GH4169 alloy disc forging;
step 14, roughly machining the GH4169 alloy disc forging, and then carrying out water immersion ultrasonic nondestructive testing;
and 15, performing stress relief annealing on the GH4169 alloy disc forging.
The gradient speed-control isothermal die forging is to adopt a hot die forging process to perform near isothermal forging: the method comprises the following steps that the pressure of a hydraulic press is more than or equal to 10000 tons, the heating temperature of a die is 950 +/-10 ℃, a three-stage speed-controlled forging process is designed, and the three-stage speed-controlled forging process is divided into a first forging stage, a second forging stage and a third forging stage according to the forging stroke of the hydraulic press, wherein the control range of a forging rate parameter is 3-5 mm/S in the first stage of the forging stroke; in the second stage, the control range of the forging rate parameter is 1-1.5 mm/S; then the forging rate is suspended and kept for 10S +/-5S; in the third stage of the forging stroke, the forging rate technological parameter is 0.5-1 mm/S, and 20S +/-5S is kept after the forging is completed.
Chemical composition target values of the GH4169 alloy. The metal nickel Ni adopts Jinchuan No. 1 nickel Ni which is more than or equal to 99.96 percent by weight; carbon C adopts spectrum electrode carbon; the metal niobium Nb adopts a pure niobium strip with the specification of Nb-1; the purity of the metallic aluminum Al is more than or equal to 99.90 percent by weight.
The capacity of the vacuum induction smelting furnace equipment is more than or equal to 2 tons during vacuum induction smelting, and the smelting crucible is equipped with an electromagnetic stirring device.
The electroslag furnace equipment during electroslag remelting is provided with an argon atmosphere protection device and a slag resistance swing control system.
The vacuum consumable remelting adopts a vacuum consumable furnace with a molten drop solidification control forming system to smelt.
Homogenizing and heat treating the cast ingot: slowly heating from room temperature to 120 ℃/h to 500 ℃ for 2h, and heating to 900 +/-20 ℃ for 2h at 3 ℃/min; heating to 1150-1160 ℃ x (20-30 h) at the speed of 5 ℃/min; and continuously heating to 1190 +/-10 ℃ multiplied by (preserving heat for 40-75 h), cutting off the power, cooling the furnace to room temperature, and discharging.
During the sheathing, the stainless steel band is arranged on the outer layer of the GH4169 alloy cake blank and is sealed by adopting argon arc welding spot welding.
The stress relief annealing of the GH4169 alloy disc forging is to perform stress relief annealing on the roughly machined GH4169 alloy disc forging by adopting a precise heat treatment furnace, and the specific process comprises the following steps: raising the temperature from room temperature (about 20 ℃) to 460 +/-20 ℃ after 1h, and preserving the temperature for 1 h; heating to 580 +/-10 ℃ from 460 ℃ for 1h according to the temperature of 90 ℃/h, preserving the temperature for 2h, and cooling to room temperature from 580 ℃ for 5h according to the temperature of 50 ℃/h.
The cylindrical section blank has a smooth surface and no burrs, and two ends of the cylindrical section blank are rounded.
This advantage and effect:
the GH4169 alloy is one of backbone materials used by aeroengines in China, and is mainly used for manufacturing key parts such as turbine discs, high-pressure compressor discs, blades, shafts and the like. In a certain type of engine, the dosage of the GH4169 alloy accounts for more than 30 percent of the total weight of the engine, wherein the number of key rotating disc pieces is as high as 11, and moreover, the GH4169 alloy material is also selected in large-scale engines under research in China. The invention provides a process for controlling the internal residual stress of a deformed high-temperature alloy GH4169 disc forging piece, which fully combines the process advantages of stress-relief heat treatment process design and gradient speed-control forging, can solve the technical problems of processing, use deformation and the like caused by the residual stress in the batch production of the GH4169 alloy disc forging piece in China, and simultaneously provides technical reference and guidance for the residual stress control of other large-size deformed high-temperature alloy disc forging pieces. The main innovation points of the invention are as follows: (1) a gradient speed-control forging process. The invention provides a process for reducing residual stress in a GH4169 alloy die forging process, which is innovatively combined with engineering application. The GH4169 alloy has the advantages of narrow plastic processing range and large deformation resistance, the internal stress of the alloy is increased due to deformation in the forging process, and the forging process parameters are designed by combining numerical simulation and test to dynamically release the input capacity in the forging process, so that the internal residual stress value can be effectively reduced, and the size deformation in the machining and using processes is avoided although part of the forging cost is improved. At present, the technical feasibility is technically verified by measuring the residual stress through a neutron diffraction technology in the prepared GH4169 alloy disc forging to obtain the comparison of the measurement results. (2) And designing a stress relief heat treatment process. The adoption of the destressing annealing mainly takes two reasons into consideration: because the alloying degree of the deformed high-temperature alloy is very high, high internal stress is remained in the cast ingot due to the shrinkage of the solidification volume, the separation and crystallization and the like in the solidification process, and the alloy is easy to fall off due to the stress release in the smelting process, so that the metallurgical quality of the alloy is seriously influenced. Before electroslag and vacuum consumable remelting, a stress relief heat treatment process is designed by combining the physical metallurgy characteristics of GH4169 alloy materials, so that the internal stress of a deformed high-temperature alloy ingot is ensured to be slowly released, and the metallurgical quality inside the alloy ingot is improved.
Detailed Description
The technical implementation of the invention comprises the following specific steps:
a process method for reducing residual stress in a GH4169 alloy disc forging is characterized by comprising the following preparation steps:
step 1, batching. Batching according to the chemical composition target value of GH4169 alloy, wherein metal nickel (Ni) is required to adopt Jinchuan 1# nickel (Ni is more than or equal to 99.96 wt%); carbon (C) is spectrum electrode carbon; the metal niobium (Nb) adopts a pure niobium strip (the specification is Nb-1); the purity of the metal aluminum (Al) is more than or equal to 99.90 percent by weight;
and 2, vacuum induction melting. An induction melting crucible of vacuum induction melting furnace equipment (the capacity is more than or equal to 2 tons) is required to be provided with an electromagnetic stirring device and is mainly used for stirring melt in the GH4169 alloy melting process so as to improve the uniformity of alloy components;
and 3, electroslag remelting. The electroslag furnace equipment is provided with an argon atmosphere protection device, and the smelting control system is designed and prepared by adopting a slag resistance swing control principle, wherein the argon atmosphere is used for avoiding the oxidation and volatilization of trace elements in an alloy melt in the smelting process, and the slag resistance swing control system is used for reducing the element segregation of the alloy, so that the reduction and the relief of the internal stress of an ingot casting are facilitated;
and 4, vacuum consumable remelting. The melting control system of the vacuum consumable electrode furnace is designed and prepared by adopting the principle of 'molten drop solidification control forming'. Mainly reduces the segregation of elements (particularly Nb) in the GH4169 alloy, and is helpful for relieving the residual stress inside the GH4169 alloy ingot;
and step 5, homogenizing and heat treating the GH4169 alloy ingot. Slowly raising the temperature from room temperature (about 120 ℃/h) to 500 ℃ for 2h, and raising the temperature to 900 +/-20 ℃ for 2h at about 3 ℃/min; heating to 1150-1160 ℃ X at 5 ℃/min (keeping the temperature for 30 h); continuously heating to 1190 +/-10 ℃ (keeping the temperature for more than or equal to 70 hours), cutting off the power, and discharging the furnace when the furnace temperature is close to the room temperature;
and 6, machining. Cutting loose and holes at the head of the GH4169 alloy ingot subjected to the homogenization heat treatment, and removing oxide skin by machining;
and 7, heating. Placing the GH4169 alloy ingot into a heat treatment furnace for heating, and heating the core of the GH4169 alloy ingot to 1010 ℃ for 1.5 h;
and 8, cogging. And (4) cogging the homogenized GH4169 alloy ingot to prepare a bar.
And 9, blanking. According to the size specification of the forged disc forging, after calculation, a band saw is adopted to saw and cut a wrought alloy GH4169 bar into a cylindrical section blank with a proper length, the surface of the cylindrical section blank is required to be flat and free of burrs, and two ends of the cylindrical section blank are required to be chamfered (the radius of the fillet is 6 mm);
and step 10, upsetting the cake. Adopting a hydraulic press to upset GH4169 alloy cylindrical section blanks into cakes;
and step 11, covering. Adopting aluminum silicate heat-insulating cotton and a stainless steel band (the thickness is about 1mm), coating the cake-upset GH4169 alloy cake blank, wherein the heat-insulating cotton is arranged on the inner layer, the stainless steel band is arranged on the outer layer of the cake blank, and adopting argon arc welding spot welding to seal tightly;
and step 12, putting the materials into a furnace for heating. Placing the GH4169 alloy cake blank adopting the heat preservation measure into a trolley type precision heat treatment furnace, and heating and preserving heat at the highest temperature of 1010 +/-10 ℃;
and step 13, gradient speed control isothermal die forging. And performing near isothermal forging by adopting a hot die forging process. The pressure of the hydraulic press is more than or equal to 10000 tons, and the heating temperature of the die is 950 +/-10 ℃. The heating temperature of the cake blank is 1010 +/-10 ℃. And designing a three-stage speed-controlled forging process by combining numerical simulation research and a test process. According to the forging stroke of the hydraulic press, the forging process is divided into a first forging stage, a second forging stage and a third forging stage. Wherein, in the first stage of the forging stroke, the control range of the technological parameters of the forging rate is 5 mm/S; in the second stage, the control range of the technological parameters of the forging rate is 1.5 mm/S; then, the forging is suspended and kept for 10S; in the third stage of the forging stroke, the forging rate process parameters were 0.5 mm/S. The 20S is maintained. After forging, taking out the GH4169 alloy disc forging and cooling;
and step 14, carrying out heat treatment on the GH4169 alloy disc forging. Carrying out heat treatment on the die forged GH4169 alloy disc forging;
and step 15, roughly machining the GH4169 alloy disc forging. Roughly machining the GH4169 alloy disc forging subjected to heat treatment;
and step 16, performing stress relief annealing on the GH4169 alloy disc forging. The roughly processed GH4169 alloy disc forging is subjected to stress relief annealing by adopting a precision heat treatment furnace, and the specific process comprises the following steps: raising the temperature from room temperature (about 20 ℃) to 460 ℃ over 1h, and preserving the temperature for 1 h; heating to 580 +/-10 ℃ from 460 ℃ for 1h according to the temperature of 90 ℃/h, preserving the temperature for 2h, and cooling to room temperature from 580 ℃ for 5h according to the temperature of 50 ℃/h.
Examples
Batching according to the chemical composition target value of GH4169 alloy, wherein the used raw material is Ni 9996; cr: JCr 99-A; al: 99.90 of the total weight of the steel; ti: MHT-100, Nb: nb-1, Mo: mo-1, C: carbon spectrum electrode carbon in TSC high-purity graphite; charging metal raw materials into a furnace, and carrying out vacuum induction melting by adopting vacuum induction melting furnace equipment (with the capacity of 2 tons) provided with an electromagnetic stirring device to prepare GH4169 alloy cast ingots. Welding the GH4169 alloy cast ingot with a false electrode of an electroslag furnace; adopting an electroslag furnace with an argon atmosphere protection device to carry out electroslag remelting; machining a steel ingot, cutting a head, polishing the surface until no oxide skin is formed, and welding the surface with a false electrode; GH4169 cast ingot is prepared by vacuum consumable remelting; carrying out homogenization heat treatment on the consumable ingot, and adopting the following process: slowly raising the temperature from room temperature (the temperature raising rate is 120 ℃/h) to 500 ℃ for 2h, and raising the temperature to 900 ℃ for 2h at about 3 ℃/min; heating at 5 deg.c/min, maintaining at 1160 deg.c for 30 hr; continuously heating to 1190 ℃ and keeping the temperature for 70h, cutting off the power, cooling to be close to the room temperature, and discharging; cogging and forging to prepare a bar; cutting a GH4169 bar into a cylindrical section blank by sawing by using a band saw, wherein the surface of the cylindrical section blank is required to be smooth and has no burrs, and two ends of the cylindrical section blank are rounded (the radius of a fillet is 8 mm); heating at 1010 +/-10 ℃; adopting a hydraulic press to upset GH4169 alloy material sections into cakes; adopting aluminum silicate heat-insulating cotton and a stainless steel band (the thickness is 80mm), coating a cake blank of GH4169 alloy after cake heading, wherein the heat-insulating cotton is arranged on the inner layer, the stainless steel band is arranged on the outer layer of the cake blank, and adopting argon arc welding spot welding to seal tightly; heating in a furnace at 1010 ℃. Placing the GH4169 alloy cake blank adopting the heat preservation measure into a trolley type precision heat treatment furnace, and heating and preserving heat at the highest temperature of 1010 ℃; and performing near isothermal forging by adopting a hot die forging process. The pressure of the hydraulic press is more than or equal to 10000 tons, and the heating temperature of the die is 950 ℃ for forging. In the first stage of the forging stroke, the control range of the technological parameters of the forging rate is 5 mm/S; in the second stage, the control range of the technological parameters of the forging rate is 1.5 mm/S; then the forging rate is suspended and kept for 10S; in the third stage of the forging stroke, the forging rate process parameters were 0.5 mm/S. The 20S is maintained. After the forging is finished, taking out the disc forging for cooling; carrying out heat treatment on the die forged GH4169 alloy disc forging; roughly machining a GH4169 alloy disc forging, and then carrying out water immersion ultrasonic nondestructive inspection; the roughly processed GH4169 alloy disc forging is subjected to stress relief annealing by adopting a precision heat treatment furnace, and the specific process comprises the following steps: raising the temperature from room temperature (about 20 ℃) to 460 ℃ over 1h, and preserving the temperature for 1 h; heating to 580 +/-10 ℃ from 460 ℃ for 1h according to the temperature of 90 ℃/h, preserving the temperature for 2h, and cooling to room temperature from 580 ℃ for 5h according to the temperature of 50 ℃/h.
Claims (9)
1. A method for reducing internal residual stress of a GH4169 alloy large-size disc forging is characterized by comprising the following steps:
step 1, batching according to the target value of the chemical components of the GH4169 alloy;
step 2, vacuum induction melting;
step 3, electroslag remelting under the protection of argon atmosphere;
step 4, preparing GH4169 alloy cast ingot through vacuum consumable remelting;
step 5, homogenizing and heat treating the GH4169 alloy ingot;
6, cutting loose and holes at the head of the GH4169 alloy cast ingot after the homogenization heat treatment, and machining to remove oxide skin;
step 7, placing the treated GH4169 alloy ingot into a heat treatment furnace for heating, wherein the heating temperature and the heat preservation time of the center of the ingot are 1050 +/-30 ℃ multiplied by 1-2 h;
8, cogging GH4169 alloy cast ingot, and forging to prepare a bar;
step 9, processing the GH4169 alloy bar into a cylindrical section blank according to the size specification of the forged disc forging, and manufacturing the heated cylindrical section blank into a GH4169 alloy cake blank by using a hydraulic press;
step 10, compounding and sheathing: adopting aluminum silicate heat preservation cotton and a stainless steel band to coat the GH4169 alloy cake blank;
step 11, charging into a furnace for heating: loading the coated GH4169 alloy cake blank into a trolley type precise heat treatment furnace, and heating and preserving heat at the highest temperature of 1010 +/-20 ℃;
step 12, preparing a GH4169 alloy disc forging by gradient speed-control isothermal die forging, and then cooling; the gradient speed-control isothermal die forging is to adopt a hot die forging process to perform near isothermal forging: the method comprises the following steps that the pressure of a hydraulic press is more than or equal to 10000 tons, the heating temperature of a die is 950 +/-10 ℃, a three-stage speed-controlled forging process is designed, and the three-stage speed-controlled forging process is divided into a first forging stage, a second forging stage and a third forging stage according to the forging stroke of the hydraulic press, wherein in the first forging stroke stage, the control range of technological parameters of a forging rate is 3-5 mm/S; in the second stage, the control range of the technological parameters of the forging rate is 1-1.5 mm/S; then the forging process is suspended and kept for 10S +/-5S; in the third stage of the forging process, the forging rate process parameter is 0.5-1 mm/S, and 20S +/-5S is kept after the forging is finished;
step 13, carrying out heat treatment on the GH4169 alloy disc forging;
step 14, roughly machining the GH4169 disc forging, and then carrying out water immersion ultrasonic nondestructive testing;
and 15, performing stress relief annealing on the GH4169 alloy disc forging.
2. The method of reducing residual stress inside a GH4169 alloy large size disc forging of claim 1, wherein the GH4169 alloy is formulated for a target chemical composition value; the metallic nickel Ni adopts Jinchuan 1# nickel Ni which is more than or equal to 99.96 wt%; carbon C adopts spectrum electrode carbon; the metal niobium Nb adopts a pure niobium strip with the specification of Nb-1; the purity of the metallic aluminum Al is more than or equal to 99.90 wt%.
3. The method for reducing the residual stress in the GH4169 alloy large-size disc forging according to claim 1, wherein the capacity of a vacuum induction melting furnace device during vacuum induction melting is more than or equal to 2 tons, and a melting crucible is provided with an electromagnetic stirring device.
4. The method for reducing the residual stress in the GH4169 alloy large-size disc forging according to claim 1, wherein the electroslag furnace equipment for electroslag remelting is provided with an argon atmosphere protection device and a slag resistance swing control system.
5. The method for reducing residual stress inside a GH4169 alloy large-size disc forging according to claim 1, wherein the vacuum consumable remelting adopts a vacuum consumable furnace device with a droplet solidification forming control system.
6. The method for reducing residual stress inside a GH4169 alloy large-size disc forging of claim 1, wherein the ingot is subjected to homogenization heat treatment: slowly raising the temperature from room temperature at a speed of 120 ℃/h to 500 ℃ for 2h, and then raising the temperature to 900 +/-20 ℃ for 2h at a speed of 3 ℃/min; then heating to 1150-1160 ℃ at a speed of 5 ℃/min, and preserving heat for 20-30 h; and continuously heating to 1190 +/-10 ℃, preserving the heat for 40-75 h, cutting off the power, cooling to be close to the room temperature, and discharging.
7. The method for reducing the residual stress in the GH4169 alloy large-size disc forging according to claim 1, wherein the stainless steel band is wrapped on the outer layer of the GH4169 alloy cake blank and sealed by argon arc spot welding.
8. The method for reducing the internal residual stress of the GH4169 alloy large-size disc forging according to claim 1, wherein the stress relief annealing of the GH4169 alloy disc forging is the stress relief annealing of the roughly machined GH4169 alloy disc forging by using a precision heat treatment furnace, and the specific process is as follows: heating to 460 +/-20 ℃ from room temperature for 1h, and keeping the temperature for 1 h; heating to 580 +/-10 ℃ from 460 ℃ for 1h at the speed of 90 ℃/h, preserving the heat for 2h, and cooling to room temperature from 580 ℃ for 5h at the speed of 50 ℃/h.
9. The method for reducing the residual stress in the GH4169 alloy large-size disc forging according to claim 1, wherein the surface of the cylindrical section blank is flat and free of burrs, and the two ends of the cylindrical section blank are rounded.
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| CN111485126B (en) * | 2020-04-07 | 2021-07-16 | 中国航发北京航空材料研究院 | Preparation method of nickel-chromium-iron-cobalt base wrought superalloy wire |
| CN111394590B (en) * | 2020-04-07 | 2021-08-03 | 中国航发北京航空材料研究院 | Vacuum consumable remelting method for wrought superalloy GH4169 |
| CN111519068B (en) * | 2020-05-06 | 2021-02-09 | 北京钢研高纳科技股份有限公司 | Triple smelting process of difficult-deformation nickel-based high-temperature alloy GH4151 |
| CN111471944B (en) * | 2020-05-19 | 2021-07-23 | 北京钢研高纳科技股份有限公司 | Method for regulating and controlling residual stress of high-temperature alloy blank disc forging through prerotation |
| CN112016223B (en) * | 2020-07-20 | 2024-04-19 | 浙江海骆航空科技有限公司 | Test device and method for eliminating residual stress by pre-rotation of turbine blank disc |
| CN112342368A (en) * | 2020-10-16 | 2021-02-09 | 中国航发北京航空材料研究院 | Process method for reducing residual stress of deformed high-temperature alloy disc by rotation method |
| CN113388726B (en) * | 2021-06-04 | 2022-07-12 | 中国航发北京航空材料研究院 | Automatic control device and method for solid solution-quenching heat treatment of powder high-temperature alloy disc |
| CN113798341A (en) * | 2021-08-18 | 2021-12-17 | 青海中钛青锻装备制造有限公司 | Composite sheath for hot extrusion and method for preparing hard alloy |
| CN116043043A (en) * | 2021-10-28 | 2023-05-02 | 宝武特种冶金有限公司 | Quadruple smelting process of high-temperature alloy |
| CN113999982B (en) * | 2021-11-03 | 2022-08-02 | 钢铁研究总院 | Smelting process of GH4169 alloy cast ingot |
| CN114160728A (en) * | 2021-11-18 | 2022-03-11 | 王江明 | Machining process of aviation part turbine fan blade |
| CN114318191A (en) * | 2021-11-26 | 2022-04-12 | 西安聚能高温合金材料科技有限公司 | Homogenization treatment method of nickel-based superalloy GH4169G alloy |
| CN115323298B (en) * | 2022-08-11 | 2023-03-03 | 江苏大学 | Physical simulation method for nickel-based superalloy forging process |
| CN115709255B (en) * | 2023-01-04 | 2023-04-07 | 北京钢研高纳科技股份有限公司 | GH4780 alloy forging and preparation method and application thereof |
| CN116732372B (en) * | 2023-08-04 | 2023-11-21 | 无锡亿缘科技机械有限公司 | Preparation method of GH4151 nickel-based superalloy |
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| CN105344901B (en) * | 2015-12-16 | 2017-10-24 | 中国第二重型机械集团德阳万航模锻有限责任公司 | Diameter is more than or equal to the manufacture method of 1800mm high temperature alloy disk forge piece |
| CN106637012A (en) * | 2016-12-01 | 2017-05-10 | 贵州安大航空锻造有限责任公司 | Low-stress GH4169 superalloy ring part manufacturing method |
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