CN116770130A - 700 ℃ high-temperature-resistant titanium alloy for aero-engine and preparation method thereof - Google Patents
700 ℃ high-temperature-resistant titanium alloy for aero-engine and preparation method thereof Download PDFInfo
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Abstract
The invention relates to the technical field of titanium alloy processing, in particular to a 700 ℃ high-temperature resistant titanium alloy for an aeroengine and a preparation method thereof, wherein the high-temperature resistant titanium alloy comprises the following preparation raw materials in percentage by weight: al:5.5 to 7.0 percent, sn:3.0 to 5.0 percent, hf:2.0 to 4.5 percent, mo:0.0 to 1.0 percent, si:0.5 to 0.7 percent, nb:0.2 to 0.5 percent, ta:3.5 to 4.5 percent, W:0.6 to 1.2 percent, C:0.04 to 0.08 percent, O is less than or equal to 0.15 percent, fe is less than or equal to 0.015 percent, and the balance is Ti. The method designs the traditional solid solution aging strengthening type high-temperature titanium alloy, which is different from intermetallic compounds such as TiB grain boundary strengthening type high-temperature titanium alloy, tiAl base, ti2AlNb base and the like, and the final structure state is a double-state structure, so that the using temperature range of the traditional solid solution aging strengthening type high-temperature titanium alloy is increased to 700 ℃, and the traditional solid solution aging strengthening type high-temperature titanium alloy can be used as a high-temperature part of an aeroengine under the long-term working condition of 650-700 ℃.
Description
Technical Field
The invention relates to the technical field of titanium alloy processing, in particular to 700 ℃ high-temperature resistant titanium alloy for an aeroengine and a preparation method thereof.
Background
Advanced aeroengines are continually evolving towards "three high", i.e. high turbine front temperature, high thrust to weight ratio, high boost ratio. The three "high" requirements are mainly achieved by increasing the working stress of the components, reducing the weight of the components and increasing the stiffness. Although the high-temperature titanium alloy has obvious advantages of specific strength, specific rigidity and specific fatigue strength compared with other common materials, the high-temperature titanium alloy is a non-two choice of weight reduction of a gas compressor, but the development trend of the new generation of advanced aeroengine has the advantages of reduction of the number of stages of a gas compressor disc, increase of rotating speed, forward movement of a high-temperature section and structural integration, the requirement on the low-temperature titanium alloy is reduced, and the titanium alloy has a great trend of developing to higher temperature and even replacing part of nickel-based superalloy. And the limit use temperature of the traditional solid solution aging strengthening high-temperature titanium alloy is 600-650 ℃, and the use requirement of the rear section of the new generation aero-engine compressor cannot be met.
The titanium alloy material is designed according to various criteria, such as damage tolerance criteria for aircraft structural materials, strength design criteria for some non-rotating engine components, and creep and fatigue strength design criteria for rotating engine components at temperatures of 600-700 ℃.
Chinese patent CN 104018027B 'a heat-resistant titanium alloy, a processing and manufacturing method and application thereof' designs a high-temperature titanium alloy component which can be used for a long time at 600-650 ℃, and can obtain different matches of tensile strength and plasticity, durability, creep and thermal stability through different processing and heat treatment combinations, and can be used for manufacturing parts such as blades, disks and the like of advanced aeroengine high-temperature parts; the heat-resistant composite material can also be used for a short time on temperature-resistant structural members such as the skin of an aerospace vehicle at 700 ℃; it can also be used as the material for high temperature and corrosion resistant valve of automobile and boiler. Only a part of the high temperature tensile properties and endurance properties (450 mpa,0.3h break) at 700 ℃ were tested, creep and fatigue properties at 700 ℃ were not involved, and the requirements for long-term use at 700 ℃ could not be met.
Therefore, in order to meet the requirements of new generation advanced aeroengines on titanium alloys, it is highly desirable to design a novel high-temperature titanium alloy which is used at 700 ℃ for a long time according to the high creep and fatigue performance criteria, and according to the creep residual strain as an evaluation basis, the fatigue life is improved by 20% compared with the existing 650 ℃ high-temperature titanium alloy, and the fatigue life is improved by 20% compared with the existing 650 ℃ high-temperature titanium alloy under the same experimental conditions.
Disclosure of Invention
The invention provides a 700 ℃ high-temperature resistant titanium alloy for an aeroengine, which is prepared from the following raw materials in percentage by weight: al:5.5 to 7.0 percent, sn:3.0 to 5.0 percent, hf:2.0 to 4.5 percent, mo:0.0 to 1.0 percent, si:0.5 to 0.7 percent, nb:0.2 to 0.5 percent, ta:3.5 to 4.5 percent, W:0.6 to 1.2 percent, C:0.04 to 0.08 percent, and the balance of Ti and impurities.
Further, the impurities comprise unavoidable O and Fe, wherein O is less than or equal to 0.15% and Fe is less than or equal to 0.015%.
In some embodiments, the high temperature titanium alloy has a rotational bending fatigue limit of 300-320mpa at 700 ℃, a creep stress of 70mpa at 700 ℃, and a residual strain of 0.2% or less under 100h test conditions.
The second aspect of the invention provides a preparation method of a 700 ℃ high temperature resistant titanium alloy for an aeroengine, which comprises the following steps:
s1, ingot casting smelting: uniformly mixing the first titanium sponge and the hafnium sponge, placing the mixture at the bottom of a smelting crucible, starting an electron beam smelting furnace to melt alloy materials in the crucible, cooling to obtain a Ti-Hf intermediate alloy ingot, and finally cleaning, crushing and screening the alloy ingot to obtain granular Ti-Hf intermediate alloy;
s2, adding Ti-Sn, ti-Hf, al-Mo, al-Si, al-Nb, al-Ta and Al-W intermediate alloy, pure aluminum and carbon powder into the granular second titanium sponge, pressing an electrode, welding an electrode block, and performing vacuum consumable smelting on the electrode block to obtain an alloy ingot;
s3, homogenizing heat treatment and cogging forging of cast ingots: carrying out homogenization heat treatment on the alloy cast ingot in the step S2; preheating the ingot subjected to the homogenization heat treatment, performing cogging forging, and performing air cooling after forging deformation to finally obtain a blank subjected to cogging in a beta phase region;
s4, preparing a bar blank or a die forging blank: sequentially deforming the blank in the step S3 in three stages, wherein the first stage of deformation is to heat the blank to 100-20 ℃ below the beta phase transition point and then heat-preserving the blank for 1-3 fire deformation; the second stage of deformation is to heat the blank to 20-40 ℃ above the beta phase transition point and then carry out 1-2 fire deformation; the third stage of deformation is to heat the blank to 100-20 ℃ below the beta phase transition point and then to perform 3-8 fire deformation; air cooling is carried out after deformation, and finally a bar blank or a die forging blank is obtained;
s5, heat treatment of a bar blank or a die forging blank: and (3) carrying out solid solution and aging heat treatment on the rod blank or the die forging blank in the step S4 to obtain the high-temperature titanium alloy.
In some embodiments, the first titanium sponge and the second titanium sponge have a particle size of 2 to 12.7mm and the hafnium sponge has a particle size of 2 to 25.4mm.
In the step of ingot casting smelting, an alloy package is adopted for distributed arrangement, electrodes are pressed, the alloy ingot is prepared by combining multiple times of vacuum consumable smelting, alloy elements Sn, hf, mo, si, nb, ta, W are added in a mode of intermediate alloy, al part is brought in by the intermediate alloy, the insufficient part is added in a mode of high-purity Al beans and Al foil, ti is respectively added in a mode of sponge titanium, ti-Sn and Ti-Hf intermediate alloy, C is added in a mode of carbon powder, the electrode blocks are welded and then used for vacuum consumable smelting, and the alloy ingot is obtained after the alloy ingot is smelted for 3-4 times in a vacuum consumable mode. The high-temperature titanium alloy designed by the invention can be used at 700 ℃ for a long time, and experiments and researches prove that Hf, ta and Si with higher mass fraction are added into the alloy, and the high-temperature creep and fatigue performance of the alloy are improved by utilizing the high oxidation resistance of Hf element, the strengthening effect of Ta element and the precipitation of tiny dispersed silicide; the upper limit and the lower limit of the element C are accurately controlled, so that the high C content can be avoided to reduce the alloy plasticity, the content of the equiaxial primary alpha phase can be accurately controlled in the subsequent heat treatment process, and the volume fraction of the equiaxial primary alpha phase under the target ideal tissue can be obtained; impurity element Fe is accurately controlled, and creep property of the alloy is improved.
Further, the intermediate alloy containing Hf in S1 is prepared by adopting vacuum consumable smelting, raw materials are titanium sponge with granularity of 2-12.7 mm and hafnium sponge with granularity of 2-25.4 mm, 50% of titanium sponge and hafnium are uniformly mixed at the bottom of a smelting crucible, an electron beam smelting furnace is started to raise the current to 500-1500A to melt alloy materials in the crucible, a Ti-Hf intermediate alloy ingot is obtained by cooling, and finally the alloy ingot is cleaned, crushed and screened to obtain granular Ti-Hf intermediate alloy.
By searching national and industry standards (YS/T399-2013 hafnium sponge, GB/T38524-2020 hafnium rod and hafnium wire) for the raw materials containing hafnium in the country, the domestic market can only purchase metal hafnium and hafnium sponge. The known titanium alloy smelting adopts a vacuum consumable smelting process, the melting bath temperature in the conventional smelting process is difficult to exceed the melting temperature of Hf element alloy by 150-300 ℃ (the melting point of Hf element is known to reach 2233 ℃), and the experimental verification proves that the addition of the titanium alloy in the form of hafnium sponge and fine-chip metal hafnium can cause Hf inclusion in an ingot, seriously influence the uniformity of components of the ingot and influence the mechanical properties of subsequent finished products. In addition, the temperature of the molten pool is obviously raised, and a large amount of low-melting-point elements (Al and Sn) in the alloy volatilize, so that the designed target components cannot be reached, and the comprehensive mechanical properties of the subsequent finished product parts are reduced. Therefore, other added alloy elements are comprehensively considered, preferably, firstly, a 1-time vacuum consumable smelting mode is adopted to prepare the Ti-Hf intermediate alloy, then the Hf element is introduced in the form of granular Ti-Hf intermediate alloy, the intermediate alloy can obviously reduce the defects of segregation, inclusion and the like of refractory elements, and the uniformity and stability of alloy components are effectively improved.
Further, the Si-containing master alloy in S2 is selected from Al-Si master alloy, the mass fraction of the master alloy Si is more than or equal to 15%, the Ta-containing master alloy in S2 is selected from Al-Ta master alloy, the mass fraction of the master alloy Ta is more than or equal to 60%, the W-containing master alloy in S2 is selected from Al-W master alloy, and the mass fraction of the master alloy W is more than or equal to 50%.
In some embodiments, the step of homogenizing heat treatment in S3 comprises: preheating the alloy ingot in S2 to 900-1000 ℃ for heat preservation, then heating to 1150-1200 ℃ for 12-24 h.
In some embodiments, the step of cogging forging in S3 comprises: heating the cast ingot to 30-200 ℃ above the beta transformation point, preserving heat, and then performing cogging forging with 2-4 fires.
In some embodiments, the upsetting and drawing amounts of the first, second, and third stage deformation in S4 are each 30-70%.
In some embodiments, the final 1 fire of the second stage in S4 is followed by water cooling, and the final 1 fire is followed by air cooling.
In some embodiments, the last 1 fire pre-deformation of the third deformation in S4 is 1 upsetting and drawing, the amount of upsetting and drawing deformation is 30-50%, the last 1 fire is upsetting and drawing or die forging forming, the amount of deformation is 30-70%.
In some embodiments, the die-forging forming strain rate of the die-forging blank in S4 is 0.01 to 0.1S -1 。
Further, the upsetting and drawing deformation described in S2 and S3 are performed on a rapid forging machine or a hydraulic press, and the die forging formation described in S3 is performed on a hydraulic press.
Compared with the prior art, the invention has the following beneficial effects:
1. the method designs the traditional solid solution aging strengthening type high-temperature titanium alloy, which is different from intermetallic compounds such as TiB grain boundary strengthening type high-temperature titanium alloy, tiAl base, ti2AlNb base and the like, and the final structure state is a double-state structure, so that the using temperature range of the traditional solid solution aging strengthening type high-temperature titanium alloy is increased to 700 ℃, and the traditional solid solution aging strengthening type high-temperature titanium alloy can be used as a high-temperature part of an aeroengine under the long-term working condition of 650-700 ℃.
2. The alloy composition designed by the invention contains various refractory elements with high melting point, and the cast ingot alloy obtained by optimizing the adding mode of the intermediate alloy has uniform and stable composition and does not have the defects of segregation, inclusion and the like of the refractory alloy elements.
3. The bar material prepared by the method has good plastic matching with the high temperature and high temperature strength (the room temperature tensile strength is equal to or more than 1050MPa, the room temperature yield strength is equal to or more than 950MPa, the 700 ℃ tensile strength is equal to or more than 580MPa, and the room temperature yield strength is equal to or more than 450 MPa).
4. The bar and the forging prepared by the method have excellent high-temperature creep property and high-temperature fatigue property. According to the creep residual strain as an evaluation basis, the alloy is improved by 20 percent (the residual strain is less than or equal to 0.2 percent under the test conditions of 650 ℃, 120MPa of creep stress and 100h, and the residual strain is less than or equal to 0.2 percent under the test conditions of 700 ℃ and 70MPa of creep stress and 100 h) compared with the existing 650 ℃ high-temperature titanium alloy; the fatigue life is improved by 20 percent (650 ℃ and 1 multiplied by 10) compared with the prior high-temperature titanium alloy with the temperature of 650 ℃ under the same experimental condition 7 The rotational bending fatigue limit is more than or equal to 380MPa,700 ℃ and 1 multiplied by 10 7 The rotational bending fatigue limit is more than or equal to 290 MPa).
Drawings
FIG. 1 is a microstructure of a 150mm diameter rod blank of example 1.
FIG. 2 is a microstructure of a forging stock of 220mm diameter and 85mm thickness in example 2.
FIG. 3 is a microstructure of a 250mm diameter rod blank of example 3.
FIG. 4 is a drawing showing the microstructure of a bar of 150mm diameter in comparative example 1.
Detailed Description
The following description of the technical solutions in the embodiments of the present invention will be clear and complete, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
700 ℃ high-temperature resistant titanium alloy for aero-engines, wherein the high-temperature resistant titanium alloy comprises the following preparation raw materials in percentage by weight: al:5.9%, sn:3.9%, hf:2.5%, mo:0.3%, si:0.55%, nb:0.4%, ta:3.5%, W:0.8%, C:0.055%, 0.09% of O and 0.01% of Fe, and the balance of Ti, wherein the beta phase transition point is 1048 ℃.
A method for preparing 700 ℃ high temperature resistant titanium alloy for an aeroengine, comprising the following steps:
s1, preparing a Ti-Hf intermediate alloy by adopting vacuum consumable smelting, wherein the raw materials comprise a first titanium sponge with the granularity of 2-12.7 mm (the market selling company is Kogyo Jinda titanium industry Co., ltd.) and a hafnium sponge with the granularity of 2-25.4 mm (the market selling company is Beijing Jin Boyu metal technology Co., ltd.), uniformly mixing 50% by weight of the first titanium sponge and the hafnium sponge, placing the mixture at the bottom of a smelting crucible, starting an electron beam smelting furnace to lift current to alloy materials in the 1200A smelting crucible, cooling to obtain a Ti-Hf intermediate alloy ingot, and finally cleaning, crushing and screening the alloy ingot to obtain the granular Ti-Hf intermediate alloy.
S2, adding 2540g of Ti-Sn (Sn content is 79%), 2600g of Ti-Hf (Hf content is 50%), 245g of Al-Mo (Mo content is 64%), 1900g of Al-Si (Si content is 15%), 290g of Al-Nb (Nb content is 73%), 2600g of Al-Ta (Ta content is 70%), 840g of Al-W (W content is 50%), 70g of Al foil and 25.2g of carbon powder into 42.2kg of granular second titanium sponge, pressing an electrode, welding an electrode block, performing vacuum consumable smelting, and adopting 3 times of vacuum consumable smelting to obtain an alloy ingot, wherein the diameter of the ingot is 200mm, and the weight of the ingot is 53kg.
S3, preheating the cast ingot in the S2 to 950 ℃, preserving heat for 60min, then heating to 1200 ℃, preserving heat for 12h, and carrying out homogenization heat treatment; and (3) performing cogging forging on the ingot subjected to the homogenization heat treatment by 2 fires, wherein the 1 st fire is firstly preheated to 950 ℃ and is insulated for 60min, then heated to 1180 ℃ and is insulated for 120min, the 2 nd fire is firstly preheated to 950 ℃ and is insulated for 60min, then heated to 1100 ℃ and is insulated for 120min, each fire deformation is upsetting and drawing for 1 time, the upsetting and drawing deformation amounts are 45 percent, the forging deformation is air-cooled, and finally, the blank subjected to cogging in the beta-phase region is obtained.
S4, firstly carrying out 1-fire deformation on the blank in the S3, heating to 1020 ℃, preserving heat for 120min, and carrying out air cooling after deformation, wherein the deformation is 1-time upsetting and drawing, and the deformation of upsetting and drawing is 40%; then carrying out the second stage of 1 fire deformation, heating to 1080 ℃, preserving heat for 120min, deforming into 1-time upsetting and drawing, wherein the deformation of upsetting and drawing is 50%, and cooling by water after deformation; and finally, carrying out 5-fire deformation in the third stage, wherein the heating temperature of 5-fire is 1020 ℃, 1010 ℃, 1000 ℃ and 990 ℃ respectively, the heat preservation time is 120min, the deformation before 1-fire is 1 time upsetting and drawing, the deformation amount of upsetting and drawing is 40%, the deformation amount after 1-fire is 1 time upsetting and drawing, the deformation amount is 30%, and the air cooling is carried out after the deformation. Finally, a bar blank with the diameter of 150mm is obtained.
S5, cutting 50mm of the rod blank in the S4 in the length direction, carrying out solid solution and aging heat treatment, and carrying out solid solution treatment: heat preservation is carried out for 2h at 1030 ℃, oil cooling is carried out, and aging treatment is carried out: preserving the temperature at 710 ℃ for 5 hours, and air cooling.
The bar blank with the diameter of 150mm prepared by the method has a microstructure shown in figure 1, and the content of the equiaxed primary alpha phase is 6-10%. The creep and fatigue properties at 650 ℃ and 700 ℃ are shown in Table 1, and the comprehensive properties are excellent.
TABLE 1
Example 2
700 ℃ high-temperature resistant titanium alloy for aero-engines, wherein the high-temperature resistant titanium alloy comprises the following preparation raw materials in percentage by weight: al:5.9%, sn:3.9%, hf:2.5%, mo:0.3%, si:0.55%, nb:0.4%, ta:3.5%, W:0.8%, C:0.055%, 0.09% of O and 0.01% of Fe, and the balance of Ti, wherein the beta phase transition point is 1048 ℃.
A method for preparing 700 ℃ high temperature resistant titanium alloy for an aeroengine, comprising the following steps:
s1, preparing a Ti-Hf intermediate alloy by adopting vacuum consumable smelting, wherein the raw materials comprise a first titanium sponge (market selling company is Kogyo Jinda titanium industry Co., ltd.) with granularity of 2-12.7 mm and a hafnium sponge (market selling company is Beijing Jin Boyu metal technology Co., ltd.) with granularity of 2-25.4 mm, respectively mixing 50% by weight of the first titanium sponge and the hafnium sponge uniformly, placing the mixture at the bottom of a smelting crucible, starting an electron beam smelting furnace to lift current to alloy materials in the 1200A smelting crucible, cooling to obtain a Ti-Hf intermediate alloy ingot, and finally cleaning, crushing and screening the alloy ingot to obtain the granular Ti-Hf intermediate alloy.
S2, adding 2540g of Ti-Sn (Sn content is 79%), 2600g of Ti-Hf (Hf content is 50%), 245g of Al-Mo (Mo content is 64%), 1900g of Al-Si (Si content is 15%), 290g of Al-Nb (Nb content is 73%), 2600g of Al-Ta (Ta content is 70%), 840g of Al-W (W content is 50%), 70g of Al foil and 25.2g of carbon powder into 42.2kg of granular second titanium sponge, pressing an electrode, welding an electrode block, performing vacuum consumable smelting, and adopting 3 times of vacuum consumable smelting to obtain an alloy ingot, wherein the diameter of the ingot is 200mm, and the weight of the ingot is 53kg.
S3, preheating the cast ingot in the S2 to 950 ℃, preserving heat for 60min, then heating to 1200 ℃, preserving heat for 12h, and carrying out homogenization heat treatment; and (3) performing cogging forging on the ingot subjected to the homogenization heat treatment by 2 fires, wherein the 1 st fire is firstly preheated to 950 ℃ and is insulated for 60min, then heated to 1180 ℃ and is insulated for 120min, the 2 nd fire is firstly preheated to 950 ℃ and is insulated for 60min, then heated to 1100 ℃ and is insulated for 120min, each fire deformation is upsetting and drawing for 1 time, the upsetting and drawing deformation amounts are 45 percent, the forging deformation is air-cooled, and finally, the blank subjected to cogging in the beta-phase region is obtained.
S4, firstly carrying out 1-fire deformation on the blank in the S3, heating to 1020 ℃, preserving heat for 120min, and carrying out air cooling after deformation, wherein the deformation is 1-time upsetting and drawing, and the deformation of upsetting and drawing is 40%; then carrying out the second stage of 1 fire deformation, heating to 1080 ℃, preserving heat for 120min, deforming into 1-time upsetting and drawing, wherein the deformation of upsetting and drawing is 50%, and cooling by water after deformation; finally, 6-fire deformation is carried out in the third stage, the heating temperature of 6-fire is 1020 ℃, 1010 ℃, 1000 ℃, 990 ℃ and 1000 ℃ respectively, the heat preservation time is 120min, the deformation before 1-fire is 1 time upsetting and drawing, the deformation of upsetting and drawing is 40%, the die forging forming is carried out after 1-fire, the deformation is 30%, and the strain rate is 0.02s -1 Air cooling is performed after deformation. Finally, a forging stock with the diameter of 220mm and the thickness of 85mm is obtained.
S5, carrying out solid solution and aging heat treatment on the forging stock in the step S4, and carrying out solid solution treatment: heat preservation is carried out for 2h at 1030 ℃, oil cooling is carried out, and aging treatment is carried out: preserving the temperature at 710 ℃ for 5 hours, and air cooling.
The forging stock with the diameter of 220mm and the thickness of 85mm prepared by the method has the equiaxed primary alpha phase content of 6-8 percent. The creep and fatigue properties at 650℃and 700℃are shown in Table 2, and the overall properties are excellent.
TABLE 2
Example 3
700 ℃ high-temperature resistant titanium alloy for aero-engines, wherein the high-temperature resistant titanium alloy comprises the following preparation raw materials in percentage by weight: al:6.0%, sn:3.8%, hf:3.8%, mo:0.3%, si:0.58%, nb:0.4%, ta:4.0%, W:0.9%, C:0.058%, 0.08% of O and 0.01% of Fe, and the balance of Ti, wherein the beta phase transition point is 1050 ℃.
A method for preparing 700 ℃ high temperature resistant titanium alloy for an aeroengine, comprising the following steps:
s1, preparing a Ti-Hf intermediate alloy by adopting vacuum consumable smelting, wherein the raw materials comprise a first titanium sponge with the granularity of 2-12.7 mm (the market selling company is Kogyo Jinda titanium industry Co., ltd.) and a hafnium sponge with the granularity of 2-25.4 mm (the market selling company is Beijing Jin Boyu metal technology Co., ltd.), uniformly mixing 50% by weight of the first titanium sponge and the hafnium sponge, placing the mixture at the bottom of a smelting crucible, starting an electron beam smelting furnace to lift current to alloy materials in the 1200A smelting crucible, cooling to obtain a Ti-Hf intermediate alloy ingot, and finally cleaning, crushing and screening the alloy ingot to obtain the granular Ti-Hf intermediate alloy.
S2, 19.2kg of Ti-Sn (with the Sn content of 79%), 3.1kg of Ti-Hf (with the Hf content of 50%), 1.9kg of Al-Mo (with the Mo content of 64%), 15.6kg of Al-Si (with the Si content of 15%), 2.2kg of Al-Nb (with the Nb content of 73%), 23.0kg of Al-Ta (with the Ta content of 70%), 6.0kg of Al-W (with the W content of 60%), 299g of Al foil and 209g of carbon powder are added into 320kg of granular second titanium sponge, an electrode is pressed, and an electrode block is welded and then used for vacuum consumable smelting, an alloy ingot is obtained by adopting 4 times of vacuum consumable smelting, the diameter of the ingot is 320mm, and the weight of the ingot is 418kg.
S3, preheating the cast ingot in the S2 to 950 ℃, preserving heat for 100min, then heating to 1200 ℃, preserving heat for 18h, and carrying out homogenization heat treatment; and (3) performing cogging forging on the ingot subjected to the homogenization heat treatment by 3 fires, wherein the 1 st fire is firstly preheated to 950 ℃ for 60min, then heated to 1200 ℃ for 120min, the 2 nd fire is firstly preheated to 950 ℃ for 60min, then heated to 1150 ℃ for 120min, the 3 rd fire is firstly preheated to 950 ℃ for 60min, then heated to 1100 ℃ for 120min, each fire deformation is 1 upsetting and drawing, the deformation amounts of upsetting and drawing are 45%, the forging deformation is air cooling, and finally, the blank subjected to cogging in the beta phase region is obtained.
S4, firstly carrying out 3-fire deformation on the blank in the S3, wherein the heating temperature of 3 fires is 1030 ℃, 1020 ℃ and 1010 ℃ respectively, the heat preservation is 180 minutes, each 1-fire deformation is 1 upsetting and drawing, the deformation of upsetting and drawing is 40%, and the air cooling is carried out after the deformation; then carrying out 2-fire deformation in the second stage, wherein the heating temperature is 1080 ℃, the heat preservation is 120min, each 1-fire deformation is 1-time upsetting and drawing, the deformation amount of upsetting and drawing is 45%, the air cooling is carried out after the 1-fire deformation, and the water cooling is carried out after the 2-fire deformation; and finally, 8-fire deformation is carried out in the third stage, the heating temperature of 8-fire is 1020 ℃, 1010 ℃, 1000 ℃ and 990 ℃ respectively, the heat preservation time is 120min, each 1-fire deformation is 1 upsetting and drawing, the deformation amounts of upsetting and drawing are 35%, and the air cooling is carried out after the deformation. Finally obtaining the rod blank with the diameter of 250 mm.
S5, cutting the rod blank in the S4 by 40mm in the length direction, carrying out solid solution and aging heat treatment, and carrying out solid solution treatment: heat preservation is carried out for 2h at 1035 ℃, oil cooling is carried out, and aging treatment is carried out: preserving the temperature at 710 ℃ for 5 hours, and air cooling.
The rod blank with the diameter of 250mm prepared by the method has the equiaxial primary alpha phase content of 6-8 percent. The creep and fatigue properties at 650℃and 700℃are shown in Table 3, and the overall properties are excellent.
TABLE 3 Table 3
Comparative example 1 (ingot melting Using pure hafnium Metal, poor results)
700 ℃ high-temperature resistant titanium alloy for aero-engines, wherein the high-temperature resistant titanium alloy comprises the following preparation raw materials in percentage by weight: al:5.8%, sn:3.9%, hf:4.4%, mo:0.3%, si:0.42%, nb:0.4%, ta:3.5%, W:0.8%, C:0.058%, 0.08% of O and 0.02% of Fe, and the balance of Ti, wherein the beta phase transition point is 1060 ℃.
A preparation method of 700 ℃ high-temperature resistant titanium alloy for aero-engines, the specific implementation mode is the same as example 2, and the specific implementation mode is characterized in that:
s1, preparing 0-2 mm of chip-shaped metal hafnium by adopting a metal hafnium rod (market selling company is Beijing Jin Boyu metal technology Co., ltd.).
S2, 2610g of Ti-Sn (with the Sn content of 79%), 2290g of scrap-shaped metallic hafnium (with the Hf content of 99.8%), 245g of Al-Mo (with the Mo content of 64%), 1460g of Al-Si (with the Si content of 15%), 286g of Al-Nb (with the Nb content of 73%), 2600g of Al-Ta (with the Ta content of 70%), 835g of Al-W (with the W content of 50%), 518g of Al foil and 25.4g of carbon powder are added to 41.1kg of granular titanium sponge, an electrode is pressed, and an electrode block is welded and then used for vacuum consumable smelting, and an alloy ingot is obtained by adopting 3 times of vacuum consumable smelting, wherein the diameter of the ingot is 200mm, and the weight is 52kg.
S3, the specific implementation mode is the same as that of the example 1.
S4, the specific implementation mode is the same as that of the example 1.
S5, cutting 50mm of the rod blank in the S4 in the length direction, carrying out solid solution and aging heat treatment, and carrying out solid solution treatment: preserving heat for 2h at 1048 ℃, cooling with oil, and aging treatment: preserving the temperature at 710 ℃ for 5 hours, and air cooling.
The 150mm diameter bar blank prepared by the method is shown in figure 4, hf inclusions appear in the bar in a low-power mode, the uniformity of components is seriously influenced, the mechanical properties of the bar are influenced, the properties of the segregation are shown in table 4, the room-temperature plasticity of the segregation is extremely low, and the property dispersibility is large.
TABLE 4 Table 4
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (10)
1. The 700 ℃ high temperature resistant titanium alloy for the aeroengine is characterized by comprising the following raw materials in percentage by weight: al:5.5 to 7.0 percent, sn:3.0 to 5.0 percent, hf:2.0 to 4.5 percent, mo:0.0 to 1.0 percent, si:0.5 to 0.7 percent, nb:0.2 to 0.5 percent, ta:3.5 to 4.5 percent, W:0.6 to 1.2 percent, C:0.04 to 0.08 percent, and the balance of Ti and impurities.
2. The high temperature titanium alloy according to claim 1, wherein the high temperature titanium alloy has a rotational bending fatigue limit of 300-320mpa at 700 ℃, a creep stress of 70mpa at 700 ℃, and a residual strain of 0.2% or less under 100h test conditions.
3. A method for preparing a 700 ℃ high temperature resistant titanium alloy for an aeroengine according to any of claims 1-2, said method comprising the steps of:
s1, ingot casting smelting: uniformly mixing the first titanium sponge and the hafnium sponge, placing the mixture at the bottom of a smelting crucible, starting an electron beam smelting furnace to melt alloy materials in the crucible, cooling to obtain a Ti-Hf intermediate alloy ingot, and finally cleaning, crushing and screening the alloy ingot to obtain granular Ti-Hf intermediate alloy;
s2, adding Ti-Sn, ti-Hf, al-Mo, al-Si, al-Nb, al-Ta and Al-W intermediate alloy, pure Al and carbon powder into the second titanium sponge, pressing an electrode, welding an electrode block, and performing vacuum consumable smelting on the electrode block to obtain an alloy ingot;
s3, homogenizing heat treatment and cogging forging of cast ingots: carrying out homogenization heat treatment on the alloy cast ingot in the step S2; preheating the alloy cast ingot subjected to homogenization heat treatment, performing cogging forging, and performing air cooling after forging deformation to finally obtain a blank subjected to cogging in a beta phase region;
s4, preparing a bar blank or a die forging blank: sequentially deforming the blank in the step S3 in three stages, wherein the first stage of deformation is to heat the blank to 100-20 ℃ below the beta phase transition point and then heat-preserving the blank for 1-3 fire deformation; the second stage of deformation is to heat the blank to 20-40 ℃ above the beta phase transition point and then carry out 1-2 fire deformation; the third stage of deformation is to heat the blank to 100-20 ℃ below the beta phase transition point and then to perform 3-8 fire deformation; air cooling is carried out after deformation, and finally a bar blank or a die forging blank is obtained;
s5, heat treatment of a bar blank or a die forging blank: and (3) carrying out solid solution and aging heat treatment on the rod blank or the die forging blank in the step S4 to obtain the high-temperature titanium alloy.
4. The method according to claim 3, wherein the particle size of the first titanium sponge and the second titanium sponge is 0.83-12.7 mm, and the particle size of the hafnium sponge is 2-25.4 mm.
5. A method of preparing as claimed in claim 3, wherein the step of homogenizing heat treatment in S3 comprises: preheating the alloy ingot in S2 to 900-1000 ℃ for heat preservation, then heating to 1150-1200 ℃ for 12-24 h.
6. A method of manufacturing according to claim 3, wherein the step of cogging forging in S3 comprises: heating the alloy ingot to 30-200 ℃ above the beta transformation point, preserving heat, and then performing cogging forging with 2-4 fires.
7. The method according to claim 3, wherein the deformation amounts of upsetting and drawing in the first stage, the second stage and the third stage in S4 are each 30 to 70%.
8. The method according to claim 3, wherein the final 1-fire deformation in the second stage in S4 is followed by water cooling, and the final 1-fire deformation is followed by air cooling.
9. The method according to claim 3, wherein the final 1-fire deformation in the third stage in S4 is 1 upsetting and drawing, the deformation amount of upsetting and drawing is 30-50%, the final 1-fire is upsetting and drawing or die forging, and the deformation amount is 30-70%.
10. The method according to claim 3, wherein the die forging forming strain rate of the die forging blank in S4 is 0.01 to 0.1S -1 。
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