CN117026116A - A method to improve the medium-temperature plasticity of deformed high-temperature alloys - Google Patents
A method to improve the medium-temperature plasticity of deformed high-temperature alloys Download PDFInfo
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Abstract
The invention relates to a method for improving the medium temperature plasticity of a deformed superalloy, which comprises the following steps: carrying out solid solution treatment on the formed deformed superalloy blank to obtain a blank after solid solution treatment; carrying out rough machining treatment on the blank subjected to the solution treatment to obtain a blank subjected to the rough machining treatment; annealing the rough-processed blank for 5-10 hours at the temperature of Tw+ (10-30 ℃), and cooling to obtain a blank after the first time effect treatment; wherein Tw is the highest working temperature of the deformed superalloy; preserving heat of the blank subjected to the first aging treatment at the temperature Tw+/-10 ℃ for 25-100 h, and cooling to obtain a blank subjected to the second aging treatment; and (3) carrying out finish machining treatment on the blank subjected to the second aging treatment to obtain the deformed high-temperature alloy piece. The invention can effectively improve the grain boundary binding force of the deformed high-temperature alloy, realizes the aim of improving the plasticity of the alloy on the premise of not changing the alloy components, and provides guarantee for the safe service of the deformed high-temperature alloy with high temperature bearing capacity.
Description
Technical Field
The invention relates to the technical field of deformation superalloy, in particular to a method for improving the medium-temperature plasticity of deformation superalloy.
Background
The wrought superalloy has excellent comprehensive properties such as high-temperature strength, oxidation resistance, creep resistance and the like, so that the wrought superalloy is widely applied to the technical fields such as engines, power stations, nuclear energy, petrochemical industry and the like. The improvement of the performance of the deformation superalloy is an important means for improving the thrust-weight ratio of an engine, but when the deformation superalloy is designed, scientific researchers pay more attention to improving the high-temperature strength of the alloy, and often neglect the thermoplasticity of the alloy. However, in the actual engineering preparation process, the stretch plasticity of the wrought superalloy may have a plastic valley phenomenon in the temperature range of 650-850 ℃, and the stretch plasticity of the alloy may be even lower than 5%. The temperature interval is just coincident with the service temperature interval of the deformation alloy, so that the service performance of the deformation superalloy part is damaged by the plastic valley phenomenon, and the improvement of the performance of key parts such as an engine is not facilitated.
The medium-temperature brittleness is caused by that the grain boundary strength is lower than the intra-crystal strength in a certain temperature range, so that the alloy is easy to crack along crystals. The higher the heat-bearing capacity of the wrought superalloy, the more precipitated phases are contained in the crystal, so that the poorer the strength matching between the grain boundary and the crystal is, the more easily the grain boundary is cracked along the crystal. Therefore, the main idea for improving the medium temperature plasticity of the high temperature bearing capacity deformation superalloy is to improve the grain boundary strength of the alloy.
At present, when the alloy is designed, the grain boundary is purified or the binding force of the grain boundary is increased by adding C, B, zr or rare earth elements, but trace elements are already added into the existing commercial deformation superalloy, and if the trace elements are excessively added, continuous carbide or boride is easily formed at the grain boundary, so that the performance of the alloy is deteriorated. When the alloy is smelted, the purity of the alloy solution is improved, the content of O, N and S inclusion elements in the alloy is reduced, but the deformed high-temperature alloy with high temperature bearing capacity adopts an advanced triple smelting technology, the content of the inclusion elements in the alloy is controlled to be below 30ppm, and the content of the inclusion elements in the alloy is very low.
In summary, an effective method is urgently needed to improve the grain boundary strength of the alloy to improve the medium temperature plasticity of the high temperature bearing capacity wrought superalloy.
Disclosure of Invention
In view of the above, the present invention provides a method for improving the medium temperature plasticity of a deformed superalloy, and the main purpose of the present invention is to provide a deformed superalloy with high temperature resistance with excellent medium temperature plasticity.
In order to achieve the above purpose, the present invention mainly provides the following technical solutions:
in one aspect, embodiments of the present invention provide a method of improving the medium temperature plasticity of a wrought superalloy, comprising the steps of:
solution treatment: carrying out solid solution treatment on the formed deformed superalloy blank to obtain a blank after solid solution treatment;
rough machining: carrying out rough machining treatment on the blank subjected to the solution treatment to obtain a blank subjected to the rough machining treatment;
first time-efficient processing: annealing the rough-processed blank for 5-10 hours at the temperature of Tw+ (10-30 ℃), and cooling to obtain a blank after the first time effect treatment; wherein Tw is the highest working temperature of the deformed superalloy;
and (3) second aging treatment: preserving heat of the blank subjected to the first aging treatment at the temperature Tw+/-10 ℃ for 25-100 h, and cooling to obtain a blank subjected to the second aging treatment;
and (3) finishing treatment: and carrying out finish machining treatment on the blank subjected to the second aging treatment to obtain the deformed high-temperature alloy piece.
Preferably, the gamma prime phase content in the deformed superalloy blank after the second aging treatment is less than 55wt%.
Preferably, the gamma prime phase content in the deformed superalloy blank after the second aging treatment is not less than 15wt%.
Preferably, the gamma' phase size in the crystal of the deformed superalloy blank after the second aging treatment is 50-200nm.
Preferably, in the chemical composition of the wrought superalloy: the sum of the weight percentages of Al element, ti element and Nb element is more than or equal to 6wt%.
Preferably, in the chemical composition of the wrought superalloy: the sum of the weight percentages of the W element and the Mo element is more than or equal to 3.5 weight percent.
Preferably, in the chemical composition of the wrought superalloy: the weight percentage of Cr element is less than or equal to 20wt%.
Preferably, the wrought superalloy comprises a GH4065A alloy, a GH4720Li alloy, a GH4068 alloy.
Preferably, in the step of solution treatment: carrying out solution treatment on the formed deformed superalloy blank for 1-4 hours at the temperature of Tm- (10-50 ℃), and then cooling to room temperature to obtain a blank after solution treatment; wherein Tm is the complete dissolution temperature of the gamma' -phase of the deformed superalloy; preferably, the cooling mode is oil quenching cooling or air cooling.
Preferably, the grain size of the solid solution treated material is 7 or more.
Preferably, in the step of the rough processing: and turning the blank subjected to solution treatment, and reserving the allowance of 1-5 mm.
Preferably, in the steps of the first aging treatment and the second aging treatment: the Tw is 700-800 ℃; and/or cooling means: air cooling or gas quenching cooling.
Preferably, after the first aging treatment and the second aging treatment, the gamma' phase size in the deformed superalloy crystal is 50-200nm.
Preferably, no TCP phase is precipitated in the microstructure of the deformed superalloy through the second aging treatment, and solid solution elements are biased at the grain boundary; separating out discontinuous granular carbide and/or boride at the grain boundary; preferably, the solid solution element comprises W, mo; preferably, the particulate carbide and/or boride has a particle size of 0.5 to 3 μm.
Preferably, in the step of finishing treatment: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size, and carrying out shot blasting treatment on the alloy piece to improve the surface performance.
On the other hand, the embodiment of the invention provides a deformed superalloy component, wherein TCP phase precipitation does not exist in a microstructure of the deformed superalloy component, and solid solution elements are biased at a grain boundary; preferably, the solid solution element comprises W, mo; and separating out discontinuous granular carbide and/or boride at the grain boundary of the deformation superalloy component.
Preferably, the deformed superalloy is obtained by treating a deformed superalloy blank after forming by the method for improving the medium temperature plasticity of the deformed superalloy described in any one of the above.
Preferably, the wrought superalloy component comprises a GH4065A alloy component, a GH4720Li alloy component, a GH4068 alloy component.
Preferably, the elongation of the deformed superalloy component at the temperature of 650-800 ℃ is more than or equal to 10%, preferably more than or equal to 20%, and more preferably more than or equal to 28%.
Preferably, the elongation percentage of the deformation superalloy component at 700 ℃ is more than or equal to 20%.
Preferably, the yield strength of the deformed superalloy component at 700 ℃ is more than or equal to 1000MPa, and the yield strength of the deformed superalloy component at 800 ℃ is more than or equal to 900MPa.
Preferably, the hardness of the deformed superalloy is 35-50 HRC.
Compared with the prior art, the method for improving the medium-temperature plasticity of the deformed superalloy has at least the following beneficial effects:
the method for improving the medium-temperature plasticity of the deformed superalloy provided by the embodiment of the invention comprises the following steps: carrying out solid solution treatment on the formed deformed superalloy blank to obtain a blank after solid solution treatment; carrying out rough machining treatment on the blank subjected to the solution treatment to obtain a blank subjected to the rough machining treatment; the rough processed blank is processedAnnealing the material at the temperature of Tw+ (10-30 ℃) for 5-10 hours, and cooling to obtain a blank after the first time effect treatment; wherein Tw is the highest working temperature of the deformed superalloy; preserving heat of the blank subjected to the first aging treatment at the temperature Tw+/-10 ℃ for 25-100 h, and cooling to obtain a blank subjected to the second aging treatment; and (3) carrying out finish machining treatment on the blank subjected to the second aging treatment to obtain the deformed high-temperature alloy piece. The above steps of the present invention are as follows: the invention effectively regulates and controls element segregation and precipitated phase distribution at the alloy grain boundary by controlling the temperature and time of heat treatment, thereby realizing the purpose of improving the strength of the alloy high-temperature grain boundary. Specifically, (1) the purpose of the solution treatment is to realize a great deal of re-dissolution of the gamma' -phase in the matrix, more uniform structure regulation and control of the alloy, reduced hardness of the alloy, convenience in rough machining of the alloy and improved machining efficiency. The solid solution temperature and the holding time are selected based on the re-dissolution of the gamma' -phase and the control of the grain size, so that the temperature is selected to be T m The solution treatment is carried out for 1 to 4 hours at the temperature of- (10 to 50 ℃), on one hand, sufficient time is provided for the recrystallization to be sufficient and the gamma' phase to be dissolved back in a large amount, on the other hand, the growth of alloy grains is inhibited, the grain size is prevented from being oversized, and the hardness of the alloy after the solution treatment is lower than HRC35. (2) The purpose of rough machining treatment is to obtain near net shape and size, prevent hardness increase machining difficulty increase after alloy ageing treatment, and improve cutter service life. The step should remove the excess material as much as possible, and prevent the blank from deforming due to undersize in the subsequent aging treatment process, so that the allowance of 1-5 mm of the part is selected to be reserved. (3) The aim of the aging treatment is mainly to precipitate nano-scale gamma' phase as much as possible, so that the alloy has excellent high-temperature strength. The process should ensure that the alloy parts have stable structure in the working temperature range, contain high volume fraction of nano gamma' phase and strengthen the alloy. So choose to be T at first w Annealing for 5-10h at the temperature of plus (10-30 ℃) to separate out the gamma 'phase forming element after solution treatment, and generating nano gamma' phase with high volume fraction in the crystal grain. The aging treatment in step 4 mainly aims at enabling Mo and Wo atoms in the crystal to be biased towards the grain boundary, even forming granular carbide or boride with C or B atoms, improving the bonding strength of the grain boundary and improving the alloyModerate temperature plasticity, so at T w Preserving heat for 25-100 h at the temperature of +/-10 ℃. Through the two-step aging process, the size of gamma 'phase in the crystal is between 50 and 200nm, no significant growth occurs, meanwhile, no TCP phase occurs in the alloy, and no continuous gamma' phase occurs at the grain boundary. The purpose of the finishing in the step 5 is to obtain the final shape and size of the part, and to improve the service life of the part, shot blasting is performed on the finished part to generate a compressive stress layer on the surface of the finished part.
In summary, the invention uses the heat treatment means to induce solid solution atoms to gather toward the grain boundary, and produce discontinuous granular carbide, strengthen the grain boundary to realize the purpose of improving the medium temperature plasticity of the high temperature bearing capacity deformation superalloy, the strength of the alloy can not be obviously deteriorated, the whole process has few steps and simple operation; meanwhile, no chemical reagent and toxic and polluted gas are introduced, so that the method has the advantage of environmental friendliness; in addition, the process is a combination of traditional processing means, and most importantly, the invention realizes the aim of optimizing the alloy performance on the premise of hardly increasing the alloy cost because other alloy elements are not added.
The foregoing description is only an overview of the present invention, and is intended to provide a better understanding of the present invention, as it is embodied in the following description, with reference to the preferred embodiments of the present invention and the accompanying drawings.
Drawings
FIG. 1 is a graph showing the distribution of element concentration at grain boundaries and a microstructure photograph of a deformed superalloy with high heat resistance after being treated by the method of the present invention.
FIG. 2 is a photograph of the microstructure of a wrought superalloy treated in accordance with example 1 of the present invention.
FIG. 3 is a photograph of the microstructure of a wrought superalloy treated in accordance with example 2 of the present invention.
FIG. 4 is a photograph of the microstructure of a wrought superalloy treated in accordance with example 3 of the present invention.
FIG. 5 is a photograph of the microstructure of a wrought superalloy treated as described in comparative example 1.
FIG. 6 is a photograph of the microstructure of a wrought superalloy treated as described in comparative example 2.
FIG. 7 is a photograph of the microstructure of a wrought superalloy treated as described in comparative example 3.
Detailed Description
In order to further describe the technical means and effects adopted for achieving the preset aim of the invention, the following detailed description refers to the specific implementation, structure, characteristics and effects according to the application of the invention with reference to the accompanying drawings and preferred embodiments. In the following description, different "an embodiment" or "an embodiment" do not necessarily refer to the same embodiment. Furthermore, the particular features, structures, or characteristics of one or more embodiments may be combined in any suitable manner.
The invention utilizes a heat treatment method to make solid solution strengthening elements in the deformed high-temperature alloy to be biased towards the grain boundary, so as to improve the grain boundary strength, and further generate granular discontinuous carbide and/or boride, so that the alloy has excellent medium-temperature plasticity. The method reduces or even eliminates the waste caused by adding alloy elements, and the problem of medium-temperature brittleness which cannot be solved by the traditional preparation method, reduces the preparation cost of deformed high-temperature alloy parts and improves the safety coefficient of the aeroengine.
The scheme of the invention is mainly as follows:
the embodiment of the invention provides a method for improving the medium-temperature plasticity of a deformed superalloy, which comprises the following steps:
solution treatment: and carrying out solid solution treatment on the formed deformed superalloy blank to obtain a blank after solid solution treatment.
What should be stated here is: the term "deformed superalloy blank after forming" refers to a blank obtained by plastically deforming a deformed superalloy.
The method specifically comprises the following steps: carrying out solution treatment on the formed deformed superalloy blank for 1-4 hours at the temperature of Tm- (10-50 ℃), and then cooling to room temperature to obtain a blank after solution treatment; wherein, tm is the total dissolution temperature of the gamma' -phase of the deformed superalloy (the Tm of each alloy is different and can be measured by DTA). Wherein the cooling mode is oil quenching cooling or air cooling.
The grain size of the blank after the solution treatment is above 7 grades.
Rough machining: and carrying out rough machining treatment on the blank subjected to the solution treatment to obtain a blank subjected to the rough machining treatment.
The method specifically comprises the following steps: and turning the blank subjected to the solution treatment, and reserving the allowance of 1-5 mm of the machined piece.
First time-efficient processing: annealing the rough-processed blank for 5-10 hours at the temperature of Tw+ (10-30 ℃), and cooling to obtain a blank after the first time effect treatment; wherein Tw is the highest working temperature of the deformed superalloy.
Wherein Tw is 700-800 ℃. The cooling mode is as follows: air cooling or gas quenching cooling.
And (3) second aging treatment: and (3) preserving the temperature of the blank subjected to the first aging treatment at the temperature Tw+/-10 ℃ for 25-100 h, and cooling to obtain the blank subjected to the second aging treatment.
Here, tw±10 ℃ means: the temperature ranges from (Tw-10 ℃) to (Tw+10℃).
Wherein Tw is 700-800 ℃. The cooling mode is as follows: air cooling or gas quenching cooling.
And (3) finishing treatment: and carrying out finish machining treatment on the blank subjected to the second aging treatment to obtain the deformed high-temperature alloy piece.
Wherein, in this step: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size, and carrying out shot blasting treatment on the alloy piece to improve the surface performance.
The following steps are to be described:
the method of the present invention is directed to high temperature resistant wrought superalloys including, but not limited to, GH4065A, GH4720Li, GH4068 alloys. First, the alloy blank is put in T m The solution treatment is carried out for 1 to 4 hours at the temperature of (10 to 50 ℃), so that the structure of the alloy is kept uniform and fine, and the hardness of the alloy is reduced. After the blank is processed into the near target shapeAt T w Annealing at the temperature of plus (10-30 ℃) for 5-10 hours, so that the uniform nano gamma' phase is separated out from the alloy, and the high-temperature strength of the alloy is improved. Then further at T w The temperature is kept for 25 to 100 hours at the temperature of +/-10 ℃, the grain boundary strength of the alloy is improved, and the alloy has good plasticity in a medium temperature range. And finally, carrying out finish machining to obtain the final shape and size of the part, and carrying out shot blasting treatment on the part to obtain a surface hardening and compressive stress layer, thereby prolonging the service life.
Compared with the prior art, the method has the advantages that on the basis of not changing the alloying degree of the material, solid solution elements are partially aggregated at the alloy grain boundary and discontinuous grain carbides and borides are formed to strengthen the grain boundary by a heat treatment means with few steps, easy operation, no pollution and lower cost, so that the aim of improving the stretch plasticity of the alloy in a medium temperature range is fulfilled.
In summary, the invention uses the heat treatment means to induce solid solution atoms to gather toward the grain boundary, and produce discontinuous granular carbide, strengthen the grain boundary to realize the purpose of improving the medium temperature plasticity of the high temperature bearing capacity deformation superalloy, the strength of the alloy can not be obviously deteriorated, the whole process has few steps and simple operation; meanwhile, no chemical reagent and toxic and polluted gas are introduced, so that the method has the advantage of environmental friendliness; in addition, the process is a combination of traditional processing means, and most importantly, the invention realizes the aim of optimizing the alloy performance on the premise of hardly increasing the alloy cost because other alloy elements are not added.
The invention is further illustrated by the following examples:
in the embodiment of the invention, the solid solution temperature is between Tm and (10-50 ℃), the solid solution time is between 1 and 4 hours, and then the solution is oil quenched or air cooled to room temperature; turning scraps of the blank subjected to solution treatment, and reserving 1-5 mm of allowance of the part; then aging the rough machining blank for 5-10 hours at the temperature of Tw+ (10-30 ℃), and then air cooling or air quenching to room temperature; then preserving the temperature of the blank at Tw+/-10 ℃ for 25-100 h for aging treatment, and air cooling or air quenching to room temperature; and finally, carrying out finish machining on the blank to reach the target size, and carrying out shot blasting treatment on the part to improve the surface performance. In addition, the change of element concentration at the grain boundary was analyzed by auger electron spectroscopy, the microstructure of the alloy was observed by an aspect F50 field emission scanning electron microscope, and the alloy Jin Suxing and strength were tested by an INSTRON 5582 uniaxial tensile tester. The change chart of element concentration distribution at the grain boundary and the microstructure photo after the high-temperature-resistance deformation superalloy treatment are shown in fig. 1, and can be seen from fig. 1: solid solution element segregation occurs at the grain boundary, discontinuous carbide appears at the same time, and the comparison of the high-temperature-bearing-capacity deformation superalloy performance treated according to the embodiment of the invention and the alloy performance treated by the comparative example is shown in Table 1 in detail.
Example 1
The embodiment improves the medium temperature plasticity of GH4065A alloy (alloy blade), mainly comprising the following steps:
solution treatment: and carrying out solution treatment on the formed blade blank at the temperature of 1080 ℃ for 1h, and air-cooling to room temperature to obtain a blank after solution treatment. In addition, the alloy of this example has a Tm of 1110℃as tested.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 1mm of the part.
First time-efficient processing: the rough-processed blank was annealed at 760 ℃ for 10 hours, followed by air cooling to room temperature.
And (3) second aging treatment: and (3) preserving the heat of the blank subjected to the first time effect treatment for 50 hours at the temperature of 750 ℃, and air-cooling to room temperature. Wherein the gamma' phase size in the crystal of the deformed superalloy blank after the second aging treatment is 50-200nm.
And (3) finishing treatment: and (3) carrying out finish machining on the blank subjected to the aging treatment to reach the target size, and carrying out shot blasting treatment on the part to improve the surface performance.
The microstructure at the grain boundary of the deformed superalloy component (blade) obtained in this example is shown in FIG. 2. As can be seen from FIG. 2, the average grain size of the alloy is 9 μm, and a large number of discontinuous carbides (the grain size is 0.5-3 μm) are distributed on the grain boundary of the alloy, so that the grain boundary bonding strength is improved, and the medium temperature plasticity of the alloy is improved.
The properties of the deformed superalloy component (blade) prepared in this example are shown in Table 1, and the yield strength at 700℃is 1050MPa, the tensile strength is 1250MPa, and the elongation is 35%.
Comparative example 1
Comparative example 1 a GH4065A alloy blade was prepared, which essentially comprises the steps of,
solution treatment: the formed blade blank was subjected to solution treatment at 1080 ℃ for 1 hour and air-cooled to room temperature.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 1mm of the part.
Aging treatment: the rough-processed blank was annealed at 760 ℃ for 10 hours, followed by air cooling to room temperature.
And (3) finishing treatment: and (5) carrying out finish machining on the blank subjected to aging treatment to reach the target size.
The microstructure at the grain boundaries of the deformed superalloy component prepared in comparative example 1 is shown in FIG. 5. As can be seen from fig. 5: the average grain size of the alloy was about 9 μm, but no carbide was precipitated at the grain boundaries.
The properties of the deformed superalloy prepared in comparative example 1 are shown in Table 1, and the deformed superalloy has a 700 ℃ yield strength of 1080MPa, a tensile strength of 1297MPa and an elongation of 15%.
Example 2
The embodiment improves the medium temperature plasticity of the GH4720Li alloy turbine disk, mainly comprises the following steps,
solution treatment: the formed turbine disc blank was subjected to solution treatment at 1100 ℃ for 4 hours and oil quenched to room temperature. In addition, the alloy of this example has a Tm of 1150 ℃.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 5mm of the part.
First time-efficient processing: the rough-processed blank was annealed at 760 ℃ for 8 hours, followed by air cooling to room temperature.
And (3) second aging treatment: and (3) preserving the heat of the blank subjected to the first time effect treatment for 50 hours at the temperature of 750 ℃, and air-cooling to room temperature. Wherein the gamma' phase size in the crystal of the deformed superalloy blank after the second aging treatment is 50-200nm.
And (3) finishing treatment: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size, and carrying out shot blasting treatment on the part to improve the surface performance.
The microstructure at the grain boundary of the deformed superalloy part (turbine disk) obtained in this example is shown in FIG. 3. As can be seen from FIG. 3, the average grain size of the alloy is 6 μm, and a large number of discontinuous carbides (the grain size is 0.5-3 μm) are distributed on the grain boundary of the alloy, so that the grain boundary bonding strength is improved, and the medium temperature plasticity of the alloy is improved. The properties of the deformed superalloy component (turbine disk) obtained in this example are shown in Table 1, and the resulting alloy component has a 700 ℃ yield strength of 1060MPa, a tensile strength of 1280MPa, and an elongation of 30%.
Comparative example 2
Comparative example 2 a GH4720Li alloy turbine disk was prepared, comprising the steps of,
solution treatment: the formed turbine disc blank is subjected to solution treatment at 1100 ℃ for 4 hours and oil quenching to room temperature.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 5mm of the part.
First time-efficient processing: the rough-processed blank was annealed at 650 ℃ for 24 hours, followed by air cooling to room temperature.
And (3) second aging treatment: and (3) preserving the heat of the blank subjected to the first time effect treatment for 16 hours at 760 ℃, and air-cooling to room temperature.
And (3) finishing treatment: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size.
As shown in fig. 6, the microstructure at the grain boundary of the deformed superalloy component (GH 4720Li alloy turbine disk) obtained in comparative example 2 was found to be about 6 μm in average grain size of the alloy, but no carbide was precipitated at the grain boundary. The properties of the deformed superalloy component (GH 4720Li alloy turbine disk) obtained in comparative example 2 are shown in Table 1, and the 700 ℃ yield strength is 1070MPa, the tensile strength is 1310MPa, and the elongation is 18%.
Example 3
The invention relates to a method for improving medium temperature plasticity of a GH4068 alloy turbine disk, which comprises the following steps,
solution treatment: the formed turbine disc blank was subjected to solution treatment at 1100 ℃ for 4 hours and oil quenched to room temperature. Wherein, the Tm of the alloy of this example is 1141 ℃.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 5mm of the part.
First time-efficient processing: the rough-processed blank was annealed at 760 ℃ for 10 hours, followed by air cooling to room temperature. Wherein the gamma' phase size in the crystal of the deformed superalloy blank after the second aging treatment is 50-200nm.
And (3) second aging treatment: and (3) preserving the heat of the blank subjected to the first time effect treatment for 50 hours at the temperature of 750 ℃, and air-cooling to room temperature.
And (3) finishing treatment: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size, and carrying out shot blasting treatment on the part to improve the surface performance.
The microstructure of the deformed superalloy component (GH 4068 alloy turbine disk) obtained in this example at the grain boundary is shown in FIG. 4, and it can be seen from FIG. 4 that the average grain size of the alloy is 5 μm, and a large number of discontinuous carbides (grain size of 0.5-3 μm) are distributed on the grain boundary of the alloy, thereby improving the grain boundary bonding strength and the medium temperature plasticity of the alloy. The properties of the deformed superalloy component (GH 4068 alloy turbine disk) obtained in this example are shown in Table 1, and the yield strength at 700℃is 1100MPa, the tensile strength is 1250MPa, and the elongation is 28%.
Comparative example 3
Comparative example 3 a GH4068 alloy turbine disk was prepared, comprising the steps of,
solution treatment: the formed turbine disc blank is subjected to solution treatment at 1100 ℃ for 4 hours and oil quenching to room temperature.
Rough machining: and turning scraps of the blank subjected to the solution treatment, and reserving the allowance of 5mm of the part.
First time-efficient processing: the rough-processed blank was annealed at 650 ℃ for 24 hours, followed by air cooling to room temperature.
And (3) second aging treatment: and (3) preserving the heat of the blank subjected to the first time effect treatment for 16 hours at 760 ℃, and air-cooling to room temperature.
And (3) finishing treatment: and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size.
The microstructure at the grain boundaries of the deformed superalloy component (GH 4068 alloy turbine disk) obtained in comparative example 3 is shown in fig. 7. As can be seen from fig. 7, although the average grain size of the alloy is also about 5 μm, no carbide is precipitated at the grain boundaries (white bright in fig. 7 is not carbide, but only grain boundaries, which has been confirmed by energy spectrum). The properties of the deformed superalloy component (GH 4068 alloy turbine disk) obtained in comparative example 3 are shown in Table 1, and the yield strength at 700℃is 1130MPa, the tensile strength is 1290MPa, and the elongation is 15%.
The properties of the deformed superalloy articles obtained after the treatments of examples 1-3 and comparative examples 1-3 are shown in Table 1.
TABLE 1
As can be seen from table 1: the treatment method of the embodiment of the invention improves the medium temperature plasticity of the deformed high-temperature alloy (greatly improves the elongation) on the premise of not changing the alloy components, and provides guarantee for the safe service of the deformed high-temperature alloy with high temperature bearing capacity. In addition, the method disclosed by the invention is simple to operate, low in cost and environment-friendly, and is beneficial to the application of the Gao Chengwen deformation superalloy in high-temperature structural members.
The above description is only of the preferred embodiments of the present invention, and is not intended to limit the present invention in any way, but any simple modification, equivalent variation and modification made to the above embodiments according to the technical substance of the present invention still fall within the scope of the technical solution of the present invention.
Claims (10)
1. A method of improving the medium temperature plasticity of a wrought superalloy comprising the steps of:
solution treatment: carrying out solid solution treatment on the formed deformed superalloy blank to obtain a blank after solid solution treatment;
rough machining: carrying out rough machining treatment on the blank subjected to the solution treatment to obtain a blank subjected to the rough machining treatment;
first time-efficient processing: annealing the rough-processed blank for 5-10 hours at the temperature of Tw+ (10-30 ℃), and cooling to obtain a blank after the first time effect treatment; wherein Tw is the highest working temperature of the deformed superalloy;
and (3) second aging treatment: preserving heat of the blank subjected to the first aging treatment at the temperature Tw+/-10 ℃ for 25-100 h, and cooling to obtain a blank subjected to the second aging treatment;
and (3) finishing treatment: and carrying out finish machining treatment on the blank subjected to the second aging treatment to obtain the deformed high-temperature alloy piece.
2. The method of improving the medium temperature plasticity of a wrought superalloy according to claim 1, wherein the gamma prime phase content in the wrought superalloy billet after the second aging treatment is below 55wt%; and/or
The gamma' phase content in the deformed superalloy blank after the second aging treatment is not less than 15wt%; and/or
And the gamma' phase size in the crystal of the deformed superalloy blank after the second aging treatment is 50-200nm.
3. Method for improving the medium temperature plasticity of a wrought superalloy according to claim 1 or 2, characterised in that in the chemical composition of the wrought superalloy:
the sum of the weight percentages of Al element, ti element and Nb element is more than or equal to 6wt%; and/or
The sum of the weight percentages of the W element and the Mo element is more than or equal to 3.5wt%; and/or
The weight percentage of Cr element is less than or equal to 20wt%.
4. A method of improving the medium temperature plasticity of a wrought superalloy according to any of claims 1 to 3, wherein the wrought superalloy comprises a GH4065A alloy, a GH4720Li alloy, a GH4068 alloy.
5. The method for improving the medium temperature plasticity of a wrought superalloy according to any of claims 1 to 4, wherein in the step of solution treating:
carrying out solution treatment on the formed deformed superalloy blank for 1-4 hours at the temperature of Tm- (10-50 ℃), and then cooling to room temperature to obtain a blank after solution treatment; wherein Tm is the complete dissolution temperature of the gamma' -phase of the deformed superalloy;
preferably, the cooling mode is oil quenching cooling or air cooling.
6. The method for improving the medium temperature plasticity of a wrought superalloy according to any of claims 1 to 5, wherein the grain size of the solution treated billet is grade 7 or more.
7. The method for improving the medium temperature plasticity of a wrought superalloy according to any of claims 1 to 6, wherein in the step of roughing:
and turning the blank subjected to solution treatment, and reserving the allowance of 1-5 mm.
8. The method of improving the medium temperature plasticity of a wrought superalloy according to any of claims 1 to 7, wherein in the steps of the first and second ageing treatments:
the Tw is 700-800 ℃; and/or
The cooling mode is as follows: air cooling or gas quenching cooling; and/or
After the first aging treatment and the second aging treatment, the gamma' phase size in the deformed superalloy crystal is 50-200 nm; and/or
Through the second aging treatment, no TCP phase is separated out from the microstructure of the deformed superalloy, and solid solution elements are partially aggregated at the grain boundary; separating out discontinuous granular carbide and/or boride at the grain boundary; preferably, the solid solution element comprises W, mo; preferably, the particulate carbide and/or boride has a particle size of 0.5 to 3 μm.
9. Method for improving the medium temperature plasticity of wrought superalloys according to any of claims 1-8, characterized in that in the step of finishing treatment:
and (3) carrying out finish machining on the blank subjected to the second aging treatment to reach the target size, and carrying out shot blasting treatment on the alloy piece to improve the surface performance.
10. The deformation superalloy component is characterized in that TCP phase precipitation does not exist in a microstructure of the deformation superalloy component, and solid solution elements are concentrated at a grain boundary; preferably, the solid solution element comprises W, mo; separating out discontinuous granular carbide and/or boride at the grain boundary of the deformed superalloy component;
preferably, the deformed superalloy component is obtained by processing a deformed superalloy blank after forming by adopting the method for improving the medium-temperature plasticity of the deformed superalloy according to any one of claims 1 to 9;
preferably, the wrought superalloy component comprises a GH4065A alloy component, a GH4720Li alloy component, a GH4068 alloy component;
preferably, the elongation of the deformation superalloy component at 650-800 ℃ is more than or equal to 10%, preferably more than or equal to 20%, and more preferably more than or equal to 28%;
preferably, the elongation of the deformation superalloy component at 700 ℃ is more than or equal to 20%;
preferably, the yield strength of the deformed superalloy component at 700 ℃ is more than or equal to 1000MPa, and the yield strength of the deformed superalloy component at 800 ℃ is more than or equal to 900MPa;
preferably, the hardness of the deformed superalloy is 35-50 HRC.
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