CN113881909A - Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging - Google Patents
Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging Download PDFInfo
- Publication number
- CN113881909A CN113881909A CN202110985607.XA CN202110985607A CN113881909A CN 113881909 A CN113881909 A CN 113881909A CN 202110985607 A CN202110985607 A CN 202110985607A CN 113881909 A CN113881909 A CN 113881909A
- Authority
- CN
- China
- Prior art keywords
- temperature
- heat treatment
- gh4720li
- blade forging
- forging
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application relates to the technical field of high-temperature alloy heat treatment, and particularly discloses a heat treatment method of a GH4720Li high-temperature alloy blade forging and the blade forging. The heat treatment method of the GH4720Li high-temperature alloy blade forging comprises the steps of sub-solution treatment and two-step aging treatment, wherein the temperature of the sub-solution treatment is 1050-; the first step has the aging temperature of 750-; the aging temperature of the second step is 630-. In addition, the preparation method is suitable for small-size bars with the diameter of 15-50mm and high-pressure compressor rotor blades prepared from the small-size bars, can enable the average grain size of the blades to reach ASTM 11 grade or thinner, and has better mechanical properties at the temperature of 400 ℃, 650 ℃ and 750 ℃.
Description
Technical Field
The application relates to the technical field of high-temperature alloy heat treatment, in particular to a heat treatment method of a GH4720Li high-temperature alloy blade forging and the blade forging.
Background
The GH4720Li high-temperature alloy is an advanced nickel-based high-temperature alloy difficult to deform, has excellent high-temperature strength and high-temperature corrosion resistance, has a service temperature of 750 ℃, and is mainly used for preparing turbine disc forgings at the early stage. But currently, it has been applied to aircraft engines as a new type of vane material.
However, the grain size and the size, distribution, matching and other factors of the gamma' phase and the GH4720Li superalloy can significantly influence the mechanical properties of the alloy, and the structure and properties of the blade forging are very sensitive to the heat treatment process. Improper control of the heat treatment process easily causes coarsening of the structure and influences the service performance of the material.
Disclosure of Invention
In order to provide a GH4720Li high-temperature alloy blade forging with uniform internal structure and better mechanical property, the application provides a heat treatment method of the GH4720Li high-temperature alloy blade forging and the blade forging.
In a first aspect, the application provides a heat treatment method for a GH4720Li high-temperature alloy blade forging, which adopts the following technical scheme:
a heat treatment method of a GH4720Li high-temperature alloy blade forging comprises a sub-solution treatment and a two-step aging treatment, wherein the temperature of the sub-solution treatment is 1050-;
the first step is that the aging temperature is 750-;
the aging temperature of the second step is 630-.
By adopting the technical scheme, the performance of the high-temperature alloy is mainly determined by chemical elements and the structure (grain size and precipitated phase) of the high-temperature alloy. When the alloy elements are definite, the factors influencing the alloy structure mainly comprise plastic deformation and heat treatment, wherein the heat treatment process is very important for adjusting the alloy structure. If the heat treatment process is reasonably selected, the proper grain size and the uniform distribution of precipitated phases in the blade forging can be ensured, so that excellent mechanical properties and service performance can be obtained.
Therefore, in order to enable the GH4720Li superalloy blade forging to obtain better mechanical properties and adjust the grain size and the structure distribution inside the alloy or blade forging, the GH4720Li superalloy blade forging structure change and property matching are realized by adopting a heat treatment process of sub-solid solution treatment and two-step aging and changing the heating temperature, the heat preservation time and the cooling mode in the steps.
After the GH4720Li high-temperature alloy blade forging is subjected to the hypo-solutionizing treatment, the solubility of a gamma ' precipitated phase in a matrix is increased along with the temperature rise, the gamma ' precipitated phase in the material can be dissolved into the matrix, the gamma ' precipitated phase is re-precipitated through reasonable hypo-soluting temperature and a cooling mode, the structure morphology, the content, the size and the distribution which are different from those before the hypo-soluting treatment are obtained, the performance of the GH4720Li high-temperature alloy is improved, and conditions are created for the aging treatment.
In the heat treatment process of the GH4720Li high-temperature alloy, the sub-solution heat treatment is usually used as the first stage heat treatment, part of strengthening phases and grain boundary phases are dissolved to form a supersaturated solid solution, and meanwhile, the grain size with a proper size is obtained to prepare for the subsequent aging treatment, and the sub-solution heat treatment can be said to be an important heat treatment process in the GH4720Li high-temperature alloy. The purpose of the sub-solution heat treatment is generally three: (1) dissolving part of main strengthening phases such as gamma' and carbide or boride to prepare for precipitating strengthening phases with uniform, fine and dispersed distribution in the aging process and a secondary precipitation phase precipitated in crystal; (2) the size of the crystal grains is adjusted, the size and the distribution of the crystal grains are more uniform by adjusting the heat preservation time and the heat preservation temperature, and the crystal grains are grown by generally increasing the sub-solid solution temperature and prolonging the heat preservation time; (3) reducing or eliminating segregation, and reducing or eliminating component segregation through sub-solid solution heat treatment for the high-temperature alloy part blank, so that the strengthening phase is uniformly distributed.
The aging aims to ensure that solute atoms form second phase particles to be dispersed and precipitated on a matrix of a mother phase, and the interface of the solute atoms generates interface mismatching with the mother phase, generates interaction with dislocation and blocks the movement of slip dislocation, thereby comprehensively achieving the purpose of precipitation strengthening.
The precipitation process of the gamma ' phase of the GH4720Li high-temperature alloy is complex, and the size and distribution of the gamma ' phase show various shapes under different heat treatment processes, so the aging process is particularly important for regulating and controlling the small-size gamma ' phase. The significance of the two-step aging is mainly to adjust the precipitation size and the distribution rule of the small-size gamma' phase.
Preferably, the cooling mode can also be air cooling, oil cooling, water cooling or argon cooling.
Preferably, when the cooling mode is air cooling, oil cooling and water cooling, the adopted heat treatment equipment is a box-type heat treatment furnace.
Preferably, when the cooling mode is argon cooling, the adopted heat treatment equipment is a vacuum heat treatment furnace.
By adopting the technical scheme, different cooling modes are adopted for cooling to room temperature, solute atoms dissolved into the matrix are left in the matrix of the mother phase without generating a slow cooling precipitation second phase phenomenon, the mother phase is a supersaturated solid solution, and the strength of the GH4720Li high-temperature alloy blade forging alloy is improved. Particularly, the cooling is carried out by adopting an argon cooling mode, and the effect is more obvious. Argon is an inert gas, has stable property, can not react with the treated product, and has better heat treatment effect than nitrogen and ammonia. Generally, when the casting or the forging is subjected to heat treatment operation, a box type heat treatment furnace is adopted, the heat treatment furnaces with different specifications can be selected according to the size and the treatment quantity of the casting or the forging, and in the industry, a gas box type heat treatment furnace is generally selected, so that the method is economical and saves cost. But for the cooling mode of argon gas cooling, the adopted heat treatment equipment is a vacuum heat treatment furnace, compared with the conventional heat treatment, the method can realize no oxidation, no decarburization and no carburization, can remove phosphorus chips on the surface of a workpiece, and can remove degreasing and degassing, thereby achieving the effect of bright purification of the surface. Has the advantages of small deformation, high efficiency, energy saving, less pollution and the like.
Preferably, the temperature of the sub-solid solution treatment is 1080-;
the first step has the aging temperature of 750-;
the aging temperature of the second step is 640-.
By adopting the technical scheme, the GH4720Li high-temperature alloy blade forging is placed in a heat treatment furnace for heating, the temperature is heated from room temperature to the temperature range of the sub-solid solution or aging, and when the temperature reaches the temperature range, the heat preservation time is recorded. The heat treatment process within the temperature and time ranges of the sub-solid solution treatment and the aging treatment is more suitable for blade forgings with the average grain size reaching ASTM 11 grade or thinner, and is mainly used for preparing high-pressure compressor rotor blade forgings.
Preferably, the temperature of the sub-solid solution treatment is 1080-;
the aging temperature of the first step is 760 ℃, and the heat preservation time is 8 h;
the aging temperature of the second step is 650 ℃, and the heat preservation time is 24 h.
By adopting the technical scheme, the performance is optimal under the aging temperature and the heat preservation time, the internal structure of the alloy or blade forging is more uniform, the average grain size can reach ASTM 12, the yield strength at 400 ℃ reaches more than 1172MPa, the yield strength at 650 ℃ reaches more than 1102MPa, the yield strength at 750 ℃ reaches more than 1067.5MPa through the detection of mechanical properties, and higher high-temperature strength is obtained.
Preferably, the temperature of the sub-solid solution treatment is 1120-1150 ℃, and the heat preservation time is 0.5-4 h;
the first step has the aging temperature of 800-;
the aging temperature of the second step is 680-720 ℃, and the heat preservation time is 16-24 h.
By adopting the technical scheme, the alloy or the forged piece with the grain size of ASTM 4-8 grade is more suitable in the temperature and time range of the sub-solid solution treatment and the aging, and is mainly used for producing and preparing the static blade.
Preferably, the temperature of the sub-solid solution treatment is 1120-1150 ℃, and the heat preservation time is 0.5-4 h;
the aging temperature of the first step is 820 ℃, and the heat preservation time is 4 h;
the aging temperature of the second step is 700 ℃, and the heat preservation time is 16 h.
By adopting the technical scheme, the alloy or blade forging piece has optimal performance at the aging temperature and the heat preservation time, high-temperature durability and good creep property, the internal structure of the alloy is uniform, the yield strength reaches 1053.5MPa at 400 ℃, the yield strength reaches 987MPa at 650 ℃, and the durability time reaches more than 55.4h at 704 ℃/828 MPa.
In a second aspect, the application provides an aeroengine blade forging, adopts following technical scheme:
the blade forging of the aero-engine is prepared by the heat treatment method of the GH4720Li high-temperature alloy blade forging.
Preferably, the blade forging is a high-pressure compressor rotor blade or a static blade.
By adopting the technical scheme, the GH4720Li superalloy blade forging is prepared by the following method, wherein the GH4720Li superalloy forging comprises the following elements in percentage by mass, namely C (0.006-0.012)%; cr (16.0-17.0)%; ti (4.95-5.20)%; al (2.45-2.65)%; b (0.01-0.02)%; co (14.00-15.00)%; fe is less than or equal to 0.50 percent; w (1.10-1.40)%; mo (2.75-3.25)%; zr (0.025-0.05)%; the balance of Ni. By utilizing a duplex or triplet smelting process, GH4720Li high-temperature alloy cast ingot with the diameter of phi 406mm or phi 508mm is prepared after smelting.
The duplex smelting process comprises three stages of vacuum induction smelting (VIM), vacuum consumable melting (VAR) and homogenizing annealing, wherein the vacuum induction smelting (VIM) comprises three stages of a melting period, a refining period and a pouring period, the total melting temperature in the melting period is 1470-; in the stage of vacuum consumable melting (VAR), the vacuum degree is controlled to be 0.2-0.55Pa during the vacuum consumable melting period, helium is filled after a molten pool is formed, and the melting speed of the induction electrode bar is 2.5-3.5 kg/min. Finally, carrying out homogenization annealing treatment on the alloy ingot, wherein the annealing temperature is 1150-1200 ℃, and the heat preservation time is 60-90h, and the method is mainly used for producing the alloy ingot with the diameter of phi 406 mm.
The triple smelting process comprises four stages of vacuum induction smelting (VIM), electroslag remelting (ESR), vacuum consumable melting (VAR) and homogenizing annealing, wherein in the stage of the electroslag remelting (ESR), the selected slag system is CaF2/CaO/Al2O3/TiO2MgO, slag CaF2：CaO：Al2O3：TiO2: the weight ratio of MgO is 55: 20: 15: 5: 5, mainly used for preparing alloy ingots with the diameter of phi 508 mm.
Forging and rolling the prepared GH4720Li high-temperature alloy cast ingot on a quick forging machine, a radial forging machine and a rolling mill to obtain a small-specification GH4720Li high-temperature alloy bar with the diameter of 15-50 mm; forging the small-size GH4720Li high-temperature alloy bar on a press machine to obtain a GH4720Li high-temperature alloy blade forging; finally, the blade forging is subjected to sub-solid solution and two-step aging heat treatment, the structure inside the forging is adjusted, the structure is more uniform, and the mechanical property is improved.
The aircraft engine is the heart of the aircraft, and the performance of the engine directly determines the performance of the whole aircraft. The high-pressure compressor rotor blade and the static blade can be divided into a high-pressure compressor rotor blade and a static blade according to the use requirements of different parts on an aircraft engine, the high-pressure compressor rotor blade is a rotating part and has a poor service condition, so that the performance requirements of the high-pressure compressor rotor blade are naturally higher than those of the static blade, and the application also focuses on the research on the performance of the high-pressure compressor rotor blade.
In summary, the present application has the following beneficial effects:
1. the solubility of a gamma' precipitation phase in a GH4720Li high-temperature alloy blade forging in a matrix is increased along with the temperature rise by adopting a heat treatment method of sub-solid solution and two-step aging, and the regulation and control of the structure and the performance of the GH4720Li high-temperature alloy are realized by adjusting the sub-solid solution, the two-step aging temperature and the cooling mode;
2. in the application, the temperature of the sub-solid solution treatment is preferably 1080-; the aging temperature of the first step is 760 ℃, and the heat preservation time is 8 h; the aging temperature of the second step is 650 ℃, and the heat preservation time is 24 h. The heat treatment method is suitable for blade forgings with the average grain size reaching ASTM 11 grade or finer, and has optimal mechanical properties at the temperatures of 400 ℃, 650 ℃ and 750 ℃;
3. in the application, the temperature of the sub-solid solution treatment is preferably 1120-1150 ℃, and the heat preservation time is 0.5-4 h; the aging temperature of the first step is 850 ℃, and the heat preservation time is 4 hours; the aging temperature of the second step is 720 ℃, and the heat preservation time is 16 h. The heat treatment method is suitable for blade forgings requiring the average grain size to reach ASTM 4-8 level, and has excellent mechanical properties at the temperature of 400 ℃, 650 ℃ and 750 ℃;
4. by adopting the heat treatment method, the GH4720Li high-temperature alloy blade forging has excellent performance after heat treatment, and provides support for material selection of an aeroengine;
5. the heat treatment method is also suitable for small-size bars with the diameter of 15-50 mm.
Drawings
FIG. 1 is a 100 times grain photograph of the GH4720Li superalloy of example 1;
FIG. 2 is a 100 times grain photograph of the GH4720Li superalloy of example 2;
FIG. 3 is a 100 times grain photograph of the GH4720Li superalloy of example 3;
FIG. 4 is a 100 times grain photograph of the GH4720Li superalloy of example 4;
FIG. 5 is a 100 times grain photograph of the GH4720Li superalloy of example 5;
FIG. 6 is a 100 times grain photograph of the GH4720Li superalloy of example 6;
FIG. 7 is a 100 times grain photograph of the GH4720Li superalloy of example 7;
FIG. 8 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 1;
FIG. 9 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 2;
FIG. 10 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 3;
FIG. 11 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 4;
FIG. 12 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 5;
FIG. 13 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 6;
FIG. 14 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 7;
FIG. 15 is a 100 times grain photograph of the GH4720Li superalloy of comparative example 8.
Detailed Description
The present application is described in further detail below with reference to figures 1-15 and examples.
The application provides a heat treatment method of a GH4720Li high-temperature alloy blade forging, which adopts a treatment mode of hypo-solid solution and two-step aging, and adjusts the temperature and time of the hypo-solid solution and the aging, thereby changing the internal structure of the alloy, enabling the average grain size to reach the use requirement of the blade forging and improving the mechanical property of the blade forging. The blade forging is made of a small-sized bar material, and as shown in the following,
vacuum Induction Melting (VIM)
1. Preparing raw materials, namely C (0.006-0.012%) by using the following chemical elements in percentage by weight; cr (16.0-17.0)%; ti (4.95-5.20)%; al (2.45-2.65)%; b (0.01-0.02)%; co (14.00-15.00)%; fe is less than or equal to 0.50 percent; w (1.10-1.40)%; mo (2.75-3.25)%; zr (0.025-0.05)%; the balance being Ni.
2. Loading and vacuumizing, namely putting the raw materials into a vacuum induction furnace and vacuumizing;
3. the raw materials are fully melted, the raw materials containing W, Mo, Co and Ni elements are added in the melting period, and the full melting temperature is 1510 +/-3 ℃; raw materials containing Cr, Ti and Al elements are added in the refining period, and electromagnetic stirring is carried out; the refining temperature is 1535 +/-3 ℃;
4. sampling and detecting, namely after the element content reaches a specified range, adding Ni-Mg rare earth, and discharging;
5. pouring, before pouring, filling argon into an ingot mold (the diameter is phi 100-;
6. and (4) cooling and solidifying, namely continuously cooling the alloy liquid to room temperature in the ingot mould, and solidifying to obtain the induction electrode bar.
(II) electroslag remelting (ESR)
The surface is polished, a riser is cut, and then the electrode head is welded.
Carrying out electroslag remelting smelting on the induction electrode bar, introducing argon in the whole smelting process, wherein the adopted slag system is CaF2/CaO/Al2O3/TiO2The proportion of MgO is 55 wt% -20 wt% -15 wt% -5 wt%, and the electroslag remelting electrode rod is obtained through the stages of slagging → arcing → remelting → feeding → cooling → demoulding and the like.
(III) vacuum consumable melting (VAR)
And (3) performing car polishing treatment on the surface of the remelting electrode rod, removing surface oxide skin, processing until the head end face and the tail end face are parallel, and then welding the head of the electrode.
Controlling the vacuum degree of vacuum consumable melting to be 0.5Pa, filling helium gas after a molten pool is formed, controlling the pressure of the helium gas to be 600Pa, controlling the melting speed of the induction electrode bar to be 3.4kg/min, solidifying the molten alloy in a steel ingot mould (the diameter is phi 508mm or phi 406mm), and demoulding to obtain an alloy ingot;
homogenizing annealing of (IV) alloy ingot
And (3) placing the alloy ingot into a heat treatment furnace for homogenizing annealing, wherein the heat treatment furnace is a gas heat treatment furnace generally, the annealing temperature is 1180 +/-5 ℃, and the heat preservation time is 75 +/-0.5 h.
(V) quick forging
And (3) reheating the alloy ingot after the homogenizing annealing, wherein the heating temperature is 1120 +/-5 ℃, carrying out 1-fire upsetting and 2-fire unidirectional drawing on the alloy ingot in the axial direction of the alloy ingot on a quick forging machine, and the finish forging temperature of each fire is not lower than 1000 ℃ to obtain an alloy bar blank, and sheathing the alloy ingot in the forging process by adopting heat-insulating cotton.
(VI) radial forging
Heating the alloy bar blank to 1120 +/-5 ℃ in a heating furnace, carrying out unidirectional drawing-out on the alloy bar blank for 1 fire time on a radial forging machine along the axial direction of the alloy bar blank, wherein the final forging temperature for each fire time is 950 ℃, obtaining an intermediate blank, and sheathing the alloy bar blank by using heat-insulating cotton in the radial forging process;
(VII) Hot Rolling
Heating the intermediate billet to 1120 +/-5 ℃ in a heating furnace, carrying out 3 times of fire rolling on a hot rolling mill along the axial direction of the intermediate billet, and finally obtaining the GH4720Li high-temperature alloy small-specification bar with the diameter of phi 15-50mm, wherein the finish forging temperature is 980 ℃.
(eight) blade forging
Heating a GH4720Li high-temperature alloy small-specification bar with the diameter of 15-50mm to 1120 +/-5 ℃ in a heating furnace, and then forging the blade forging on a press by adopting a die forging or precision forging mode to obtain the GH4720Li high-temperature alloy blade forging.
(nine) Heat treatment Process
Firstly, carrying out component detection, appearance inspection and internal defect detection on the blade forging or the small-size bar, and carrying out heat treatment on the blade forging with qualified components, no obvious defects such as cracking and the like in appearance and no defects (shrinkage cavity, shrinkage porosity) in the blade forging or the small-size bar.
1. Sub-solid solution treatment: putting the blade forging into a heat treatment furnace for heating, and cooling after preserving heat for a period of time;
2. the first step of aging: putting the blade forging subjected to the sub-solid solution treatment into a heat treatment furnace again for heating, and cooling after preserving heat for a period of time;
3. and a second step of aging: and (4) putting the blade forging subjected to the first-step aging treatment into a heat treatment furnace again for heating, and cooling after preserving heat for a period of time.
Examples
The heat treatment process parameters in examples 1-7 of the present application are shown in Table 1:
table 1 parameters in the heat treatment process in examples 1-7
In the above table, the heat treatment furnace used in examples 1 to 6 was a box-type resistance furnace, and the heat treatment furnace used in example 7 was a vacuum heat treatment furnace.
Comparative example
The differences between comparative examples 1 to 7 and examples 1 to 7 are shown in Table 2:
table 2 parameters in the heat treatment process in comparative examples
Comparative example 8 is a blade forging obtained by subjecting an alloy ingot to rapid forging, radial forging, hot rolling, and die forging without any heat treatment.
Performance test
First, component detection
According to the ASTM E354 standard, elements and contents in the blade forging are detected by a wet chemical method or a spectrochemical method, and specific results are shown in Table 3:
TABLE 3 ingredient content (wt%)
| Element(s) | C | Cr | Ti | Al | B | Co | W | Mo |
| Content (wt.) | 0.009 | 16.34 | 5.07 | 2.54 | 0.013 | 14.7 | 1.28 | 3.07 |
| Element(s) | Zr | Fe | Si | P | S | O | N | Ni |
| Content (wt.) | 0.033 | 0.096 | 0.014 | ＜0.005 | ＜0.0004 | 0.0004 | 0.001 | Balance of |
Second, observation of metallographic structure
1. Sampling: the sample should be taken in a square shape with a size of 30X 50mm, which ensures that the observation surface of the sample does not change the structure.
2. Preparing a metallographic sample: rough grinding → fine grinding → polishing → corrosion, the structure observation is carried out under the metallographic microscope.
Thirdly, detecting the mechanical property
According to the standard of ASTME 21, the tensile strength and the yield strength of the heat-treated blade forging under the conditions of 400 ℃, 650 ℃ and 750 ℃ are detected, and the specific results are shown in tables 4, 5 and 6:
TABLE 4 mechanical Properties at 400 deg.C
TABLE 5 mechanical Properties at 650 deg.C
| Categories | Tensile strength/MPa | Yield strength/MPa |
| Example 1 | 1477 | 1102 |
| Example 2 | 1368.5 | 1081.5 |
| Example 3 | 1356 | 970 |
| Example 4 | 1350 | 972 |
| Example 5 | 1351 | 969.5 |
| Example 6 | 1372 | 987 |
| Example 7 | 1510 | 1124 |
| Comparative example 1 | 1342 | 958 |
| Comparative example 2 | 1100 | 802 |
| Comparative example 3 | 1325 | 945 |
| Comparative example 4 | 1321 | 930 |
| Comparative example 5 | 1330 | 942 |
| Comparative example 6 | 1306 | 843 |
| Comparative example 7 | 1294 | 837 |
| Comparative example 8 | 1105 | 800 |
TABLE 6 mechanical Properties at 750 ℃
According to the standard of ASTME E139, the endurance time and the elongation of the blade forging pieces in the example 5, the example 6 and the comparative example 7 under the condition of 704 ℃/828MPa are detected, and the specific results are shown in the table 7:
TABLE 7 durability test results at 704 deg.C/828 MPa
| Categories | Duration/h | Elongation/percent |
| Example 5 | 65 | 7.5 |
| Example 6 | 55.4 | 5 |
| Comparative example 6 | 20 | 4.3 |
| Comparative example 7 | 22.5 | 4 |
As can be seen by combining examples 1-7 and comparative examples 1-8 with tables 4, 5 and 6, the tensile strength and yield strength of examples 1-7 are higher than those of comparative examples 1-8 under different temperature conditions, especially the tensile strength of example 7 reaches 1214.5MPa and the yield strength reaches 1095.5MPa under the condition of 750 ℃.
Combining examples 1-7 with comparative example 8, and combining tables 4, 5, and 6, it can be seen that comparative example 8, without any heat treatment, had lower tensile strength and yield strength at 400 ℃, 650 ℃, and 750 ℃ than comparative example 8, tensile strength examples 1-7 were 169MPa or more higher than comparative example 8 at 750 ℃, and yield strength examples 1-7 were 100MPa or more higher than comparative example 8.
Combining example 1 with comparative examples 1-2 and combining tables 4, 5 and 6, it can be seen that the sub-solid solution temperature of comparative examples 1-2 is lower or higher than the range of 1050-.
Combining example 7 with comparative example 3 and tables 4, 5 and 6, it can be seen that the tensile strength and yield strength of example 7 are higher than those of comparative example 3 under different temperature conditions.
When the example 5 and the example 6 are combined with the comparative example 6 and the comparative example 7 and the table 7 is combined, the endurance performance under the condition of 704 ℃/828MPa is higher in the examples 5 and 6 than in the comparative examples 6 and 7, and the endurance time of the example 5 is 65 h.
As can be seen by combining examples 1, 2, 4 and 7 with comparative examples 1 to 5 and by combining FIG. 1/2/4/7/8/9/10/11/12, the grain sizes of examples 1, 2, 4 and 7 can reach ASTM grade 11 or even finer, and are more uniform in grain size distribution and free of mixed crystal structure than those of comparative examples 1 to 5.
Combining examples 3, 5 and 6 with comparative examples 6 and 7 and combining fig. 3/5/6/13/14, it can be seen that the grain sizes of examples 3, 5 and 6 can be controlled in 4-8 grades, the distribution is more uniform than comparative examples 6 and 7, and a clear mixed crystal structure can be observed in the structures of comparative examples 6 and 7.
As can be seen by combining example 7 with comparative example 2 and by combining FIGS. 7 and 9, the grain size of example 7 can reach ASTM13 grade, and in comparative example 2, because the solid solution temperature is too high and exceeds the upper limit of the sub-solid solution temperature, the gamma' precipitation phase is completely dissolved, the pinning effect on the grain boundary is lost, the grains are excessively grown, and the grain size is coarser than ASTM 00 grade.
As can be seen by combining example 1 with comparative example 8 and by combining fig. 1 and fig. 15, the grain size is 11 or more, and the grain structure of example 1 is more uniform than that of comparative example 8.
The present embodiment is only for explaining the present application, and it is not limited to the present application, and those skilled in the art can make modifications of the present embodiment without inventive contribution as needed after reading the present specification, but all of them are protected by patent law within the scope of the claims of the present application.
Claims (10)
1. A heat treatment method of a GH4720Li high-temperature alloy blade forging is characterized by comprising a sub-solution treatment and a two-step aging treatment,
the temperature of the sub-solid solution treatment is 1050-;
the first step is that the aging temperature is 750-;
the aging temperature of the second step is 630-.
2. The heat treatment method of the GH4720Li superalloy blade forging of claim 1, wherein: the cooling mode can also be air cooling, oil cooling, water cooling or argon cooling.
3. The heat treatment method of the GH4720Li superalloy blade forging of claim 2, wherein: when the cooling mode is air cooling, oil cooling and water cooling, the adopted heat treatment equipment is a box-type heat treatment furnace.
4. The heat treatment method of the GH4720Li superalloy blade forging of claim 2, wherein: when the cooling mode is argon cooling, the adopted heat treatment equipment is a vacuum heat treatment furnace.
5. The heat treatment method of the GH4720Li superalloy blade forging of claim 1, wherein: the temperature of the sub-solid solution treatment is 1080-;
the first step has the aging temperature of 750-;
the aging temperature of the second step is 640-.
6. The heat treatment method of the GH4720Li superalloy blade forging of claim 5, wherein: the temperature of the sub-solid solution treatment is 1080-;
the aging temperature of the first step is 760 ℃, and the heat preservation time is 8 h;
the aging temperature of the second step is 650 ℃, and the heat preservation time is 24 h.
7. The heat treatment method of the GH4720Li superalloy blade forging of claim 1, wherein: the temperature of the sub-solid solution treatment is 1120-1150 ℃, and the heat preservation time is 0.5-4 h;
the first step has the aging temperature of 800-;
the aging temperature of the second step is 680-720 ℃, and the heat preservation time is 16-24 h.
8. The heat treatment method of the GH4720Li superalloy blade forging of claim 5, wherein: the temperature of the sub-solid solution treatment is 1120-1150 ℃, and the heat preservation time is 0.5-4 h;
the aging temperature of the first step is 820 ℃, and the heat preservation time is 4 h;
the aging temperature of the second step is 700 ℃, and the heat preservation time is 16 h.
9. An aeroengine blade forging which characterized in that: the blade forging is prepared by the heat treatment method of the GH4720Li superalloy blade forging of any of claims 1-8.
10. An aircraft engine blade forging according to claim 9, wherein: the blade forging is a high-pressure compressor rotor blade or a static blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110985607.XA CN113881909A (en) | 2021-08-26 | 2021-08-26 | Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110985607.XA CN113881909A (en) | 2021-08-26 | 2021-08-26 | Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113881909A true CN113881909A (en) | 2022-01-04 |
Family
ID=79011083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110985607.XA Pending CN113881909A (en) | 2021-08-26 | 2021-08-26 | Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113881909A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115261755A (en) * | 2022-08-04 | 2022-11-01 | 西部超导材料科技股份有限公司 | Heat treatment process and application of GH2150A high-temperature alloy |
| CN115774036A (en) * | 2023-02-15 | 2023-03-10 | 西南科技大学 | Method, system and device for detecting sand inclusion rate of blade surface |
| CN115927987A (en) * | 2022-12-29 | 2023-04-07 | 北京钢研高纳科技股份有限公司 | Heat treatment method of high-temperature alloy disc shaft type forge piece and disc shaft type forge piece manufactured by same |
| CN116949380A (en) * | 2023-09-20 | 2023-10-27 | 北京钢研高纳科技股份有限公司 | Heat treatment method of high-heat-strength high-temperature alloy |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4685977A (en) * | 1984-12-03 | 1987-08-11 | General Electric Company | Fatigue-resistant nickel-base superalloys and method |
| US5593519A (en) * | 1994-07-07 | 1997-01-14 | General Electric Company | Supersolvus forging of ni-base superalloys |
| US5693159A (en) * | 1991-04-15 | 1997-12-02 | United Technologies Corporation | Superalloy forging process |
| US5759305A (en) * | 1996-02-07 | 1998-06-02 | General Electric Company | Grain size control in nickel base superalloys |
| US20120282106A1 (en) * | 2011-05-05 | 2012-11-08 | General Electric Company | Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby |
| CN103341586A (en) * | 2013-06-07 | 2013-10-09 | 北京科技大学 | Method for achieving forming of GH4738 nickel-base superalloy turbine discs |
| US20180002793A1 (en) * | 2016-06-30 | 2018-01-04 | General Electric Company | Methods for preparing superalloy articles and related articles |
| US20180023176A1 (en) * | 2015-02-12 | 2018-01-25 | Hitachi Metals, Ltd. | Method for manufacturing ni-based super-heat-resistant alloy |
| US20200080183A1 (en) * | 2016-12-15 | 2020-03-12 | General Electric Company | Treatment processes for superalloy articles and related articles |
| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
-
2021
- 2021-08-26 CN CN202110985607.XA patent/CN113881909A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4685977A (en) * | 1984-12-03 | 1987-08-11 | General Electric Company | Fatigue-resistant nickel-base superalloys and method |
| US5693159A (en) * | 1991-04-15 | 1997-12-02 | United Technologies Corporation | Superalloy forging process |
| US5593519A (en) * | 1994-07-07 | 1997-01-14 | General Electric Company | Supersolvus forging of ni-base superalloys |
| US5759305A (en) * | 1996-02-07 | 1998-06-02 | General Electric Company | Grain size control in nickel base superalloys |
| US20120282106A1 (en) * | 2011-05-05 | 2012-11-08 | General Electric Company | Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby |
| CN103341586A (en) * | 2013-06-07 | 2013-10-09 | 北京科技大学 | Method for achieving forming of GH4738 nickel-base superalloy turbine discs |
| US20180023176A1 (en) * | 2015-02-12 | 2018-01-25 | Hitachi Metals, Ltd. | Method for manufacturing ni-based super-heat-resistant alloy |
| US20180002793A1 (en) * | 2016-06-30 | 2018-01-04 | General Electric Company | Methods for preparing superalloy articles and related articles |
| US20200080183A1 (en) * | 2016-12-15 | 2020-03-12 | General Electric Company | Treatment processes for superalloy articles and related articles |
| CN111235434A (en) * | 2020-03-02 | 2020-06-05 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
Non-Patent Citations (3)
| Title |
|---|
| 万志鹏: "GH4720LI镍基合金高温变形行为及组织性能控制研究", 《中国博士学位论文全文数据库(电子期刊)工程科技I辑》 * |
| 佴启亮 等: "GH4720Li合金疲劳裂纹扩展速率的温度敏感性", 《稀有金属材料与工程》 * |
| 言建 等: "冷却方式对GH720Li合金固溶处理组织及力学性能的影响", 《金属热处理》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115261755A (en) * | 2022-08-04 | 2022-11-01 | 西部超导材料科技股份有限公司 | Heat treatment process and application of GH2150A high-temperature alloy |
| CN115927987A (en) * | 2022-12-29 | 2023-04-07 | 北京钢研高纳科技股份有限公司 | Heat treatment method of high-temperature alloy disc shaft type forge piece and disc shaft type forge piece manufactured by same |
| CN115774036A (en) * | 2023-02-15 | 2023-03-10 | 西南科技大学 | Method, system and device for detecting sand inclusion rate of blade surface |
| CN116949380A (en) * | 2023-09-20 | 2023-10-27 | 北京钢研高纳科技股份有限公司 | Heat treatment method of high-heat-strength high-temperature alloy |
| CN116949380B (en) * | 2023-09-20 | 2023-12-12 | 北京钢研高纳科技股份有限公司 | Heat treatment method of high-heat-strength high-temperature alloy |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113881909A (en) | Heat treatment method of GH4720Li high-temperature alloy blade forging and blade forging | |
| US9322090B2 (en) | Components formed by controlling grain size in forged precipitation-strengthened alloys | |
| US6231692B1 (en) | Nickel base superalloy with improved machinability and method of making thereof | |
| Loria | The status and prospects of alloy 718 | |
| CN113877982B (en) | Hardly-deformable GH4720Li high-temperature alloy small-size bar, preparation method and blade forging | |
| JP2022512537A (en) | High-strength titanium alloy for additive manufacturing | |
| CN110157988A (en) | High-purity, the homogeneous rare earth cold roll steel alloy material of one kind and preparation method | |
| KR20070012274A (en) | Powder metal rotating components for turbine engines and process therefor | |
| CN113862520B (en) | GH4720Li high-temperature alloy for aero-engine forged blade, preparation method and application thereof, and alloy ingot | |
| CN111560550A (en) | Homogenization heat treatment method for Mg-Gd-Y rare earth magnesium alloy ingot | |
| CN116065057A (en) | High-quality high-temperature alloy bar for aerospace and subjected to high W-Mo solid solution strengthening and preparation method thereof | |
| CN115572871B (en) | Commercial aluminum alloy forged wheel and preparation method thereof | |
| CN111676411A (en) | Microalloyed high-toughness dynamic sealing material and preparation method thereof | |
| CN108015255B (en) | Preparation method of high-speed tool steel | |
| CN116065010B (en) | Homogenization treatment method for ultra-high strength maraging steel | |
| CN112708788B (en) | Method for improving plasticity of K403 alloy, die material and product | |
| CN114657415B (en) | 750 ℃ high-temperature titanium alloy bar and forging method thereof | |
| CN114934162A (en) | Thermal deformation method of high-alloy martensitic stainless steel and stainless steel | |
| CN110777286B (en) | Preparation method of medium-strength weldable corrosion-resistant scandium-containing high-magnesium aluminum alloy forging | |
| CN111155021B (en) | High-temperature alloy ingot blank, preparation method thereof and high-temperature alloy part | |
| Lippard et al. | Process metallurgy of wrought CoCrMo alloy | |
| Chang et al. | Spray-formed high-strength superalloys | |
| CN114908264B (en) | Preparation method capable of eliminating 2219 aluminum alloy extruded bar coarse grain ring | |
| CN115896594B (en) | High-strength and high-toughness H13 die steel for aluminum extrusion and preparation method thereof | |
| CN115852186B (en) | Method for refining carbonitride in GH4169 alloy by controlling addition amount of return material |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20220104 |
|
| RJ01 | Rejection of invention patent application after publication |