CN114317921A - Annealing process method for preparing turbine disk and turbine disk - Google Patents
Annealing process method for preparing turbine disk and turbine disk Download PDFInfo
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- CN114317921A CN114317921A CN202111573382.3A CN202111573382A CN114317921A CN 114317921 A CN114317921 A CN 114317921A CN 202111573382 A CN202111573382 A CN 202111573382A CN 114317921 A CN114317921 A CN 114317921A
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Abstract
The invention provides an annealing process method for preparing a turbine disc and the turbine disc, wherein the method comprises the following steps: carrying out finite element modeling on the turbine disc by using computer simulation software, and designing an annealing process; placing the workpiece after hot extrusion in a furnace for an annealing process, setting heating power according to a simulation result, and slowly heating to a preset temperature; after the whole workpiece reaches a preset temperature, preserving heat for a preset time; cooling the workpiece to room temperature. By the method, the experiment cost can be reduced, the product structure can be stably controlled, and the extruded structure (1) has uniform and fine grains; (2) coarse grain boundary gamma' phase; (3) the fine intragranular gamma' phase provides excellent initial structure for the subsequent forging process.
Description
Technical Field
The invention relates to the technical field of nickel-based powder superalloy and heat treatment, in particular to an annealing process method for preparing a turbine disc and the turbine disc.
Background
Nickel-based powder superalloys are widely used for the manufacture of aircraft engine turbine disks because of their excellent high temperature properties. The inside of the composite has a higher volume fraction of gamma' strengthening phase. The gamma' strengthening phase widely distributed in the alloy crystal boundary plays a role in pinning relative to the grain structure, and can inhibit the grain growth in a high-temperature environment. Alloys with uniform fine grains have higher yield strength and tensile strength at medium and low temperatures, better formability at high temperatures, lower deformation resistance, and lower tendency to crack.
The advanced process for preparing the nickel-based powder superalloy turbine disc at home and abroad generally comprises the following steps: hot isostatic pressing, hot extrusion and isothermal forging.
In actual production, the equipment conditions and the size of the disc greatly affect the temperature field, strain field and strain rate inside the disc, thereby affecting the microstructure after the hot forming process. When the deformation is less than the critical deformation, abnormal grain growth easily caused by high-temperature heat treatment is caused. Part of the crystal grains in the local region may not be dynamically recrystallized, but coarsened in a high temperature environment. The crystal grains which are not dynamically recrystallized or are not completely dynamically recrystallized have larger size difference and phase difference with the crystal grains which are completely dynamically recrystallized, and the interior of the crystal grains has higher energy storage, thereby bringing hidden troubles for the subsequent further hot forming process or heat treatment.
Disclosure of Invention
The main object of the present invention is to provide an annealing process method for preparing a turbine disc and a turbine disc in order to solve the problems of the prior art.
In order to achieve the above object, the present invention provides an annealing process method for preparing a turbine disk, comprising:
carrying out finite element modeling on the turbine disc by using computer simulation software, and designing an annealing process;
placing the workpiece after hot extrusion in a furnace for an annealing process, setting heating power according to a simulation result, and slowly heating to a preset temperature;
after the whole workpiece reaches a preset temperature, preserving heat for a preset time;
cooling the workpiece to room temperature.
Optionally, before the finite element modeling is performed on the turbine disk by using computer simulation software and the annealing process is designed, the method further includes:
setting process parameters: setting technological parameters of an annealing process according to different turbine disc materials, and selecting a proper furnace for the annealing process;
testing and measuring temperature: placing a test workpiece or a test standard block into the annealing process furnace, welding a thermocouple on the surface of the test workpiece or the test standard block, or placing the thermocouple after drilling, and monitoring the overall temperature field change of the temperature rise and the cooling process of the test workpiece or the test standard block;
simulation: and using computer simulation software to perform finite element modeling according to the shape and the size of the test workpiece or the test standard block, and adjusting the simulated boundary conditions according to the test data until the temperature field change result is consistent with the temperature measurement result.
Optionally, the performing finite element modeling on the turbine disk by using computer simulation software specifically includes:
modeling according to the shape and size of the turbine disc workpiece, and inputting the adjusted boundary conditions to design the annealing process so that the temperature field distribution in the production process meets the requirements of process parameters.
Optionally, a thermocouple is placed on the surface of the workpiece to monitor the instantaneous temperature, and if the instantaneous temperature recorded by the thermocouple is consistent with a simulation value, the overall temperature distribution of the workpiece is indirectly deduced according to the simulation result.
Optionally, the furnace for the annealing process comprises a conventional air furnace or a vacuum gas quenching furnace, the minimum service temperature of the furnace for the annealing process is not lower than 1200 ℃, and the temperature deviation of an effective heating area of a hearth is within 5 ℃.
Optionally, the workpiece is heated with the furnace at a heating rate of 1-4 ℃/min to a temperature 50-100 ℃ below the gamma' phase remelting temperature of the alloy.
Optionally, after the lowest temperature region of the workpiece reaches a preset temperature, continuously preserving the heat for 0-16 hours.
Optionally, the workpiece is cooled to room temperature, and the cooling mode is air cooling or oil cooling.
Optionally, the thermocouple deviation is not more than 4 ℃, and the thermocouple minimum use temperature is not lower than 1200 ℃.
The invention also provides a turbine disc prepared by the method.
The invention has the beneficial effects that: the method comprises the steps of (1) coarsening a gamma' phase of a crystal boundary by using a slower heating rate, and statically recrystallizing a part of incompletely recrystallized grains by adding a homogenization annealing process; (2) through specific annealing temperature, enough recrystallization activation energy and grain growth driving force are provided for an alloy system, the condition of static recrystallization is met, and meanwhile, small recrystallized crystal nuclei grow properly, so that the grain structure is homogenized, and the coarsening rate of a grain boundary gamma' phase can be accelerated; (3) by the heat preservation time, small crystal grains can further grow properly, large crystal grains maintain the size in the presence of a grain boundary gamma ' phase, the gamma ' phase in the crystal can be dissolved back, the grain boundary gamma ' phase grows to be close to the size of the crystal grains, the structure is further homogenized, and a dual-phase crystal structure is formed; (4) by the cooling mode, the gamma' phase in the crystal precipitated after cooling is uniform and fine, and is completely dissolved back in the subsequent forging process so as to reduce the deformation resistance.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic flow chart of an annealing process method for manufacturing a turbine disk according to an embodiment of the present invention;
FIG. 2 illustrates a metallographic structure of an extruded nickel-based powder superalloy turbine disk according to an embodiment of the present invention;
FIG. 3 is a metallographic structure diagram showing the temperature of a nickel-based powder superalloy turbine disk in an extruded state after the disk is slowly heated up to a predetermined temperature according to an embodiment of the invention;
FIG. 4 shows a metallographic structure of an extruded nickel-based powder superalloy turbine disk of an embodiment of the present invention after being held for 4 hours to reach a predetermined temperature;
FIG. 5 shows a metallographic structure of an extruded nickel-based powder superalloy turbine disk of an embodiment of the present invention after being held for 8 hours to reach a predetermined temperature;
FIG. 6 shows a metallographic structure of an extruded nickel-based powder superalloy turbine disk of an embodiment of the present invention after 12 hours of incubation to a predetermined temperature;
FIG. 7 illustrates a dual phase grain structure diagram of an as-pressed nickel-based powder superalloy turbine disk according to an embodiment of the present invention.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
As shown in fig. 1, a schematic flow chart of an annealing process method for manufacturing a turbine disk according to an embodiment of the present invention is shown, including:
s101, carrying out finite element modeling on the turbine disc by using computer simulation software, and designing an annealing process;
s102, placing the workpiece subjected to hot extrusion in a furnace for an annealing process, setting heating power according to a simulation result, and slowly heating to a preset temperature;
optionally, the predetermined temperature is a temperature set by the annealing process;
s103, preserving heat for a preset time after the whole workpiece reaches a preset temperature;
and S104, cooling the workpiece to room temperature.
Optionally, before the finite element modeling is performed on the turbine disk by using computer simulation software and the annealing process is designed, the method further includes:
setting process parameters: setting technological parameters of an annealing process according to different turbine disc materials, and selecting a proper furnace for the annealing process;
testing and measuring temperature: placing a test workpiece or a test standard block into the annealing process furnace, welding a thermocouple on the surface of the test workpiece or the test standard block, or placing the thermocouple after drilling, and monitoring the overall temperature field change of the temperature rise and the cooling process of the test workpiece or the test standard block;
simulation: and using computer simulation software to perform finite element modeling according to the shape and the size of the test workpiece or the test standard block, and adjusting the simulated boundary conditions according to the test data until the temperature field change result is consistent with the temperature measurement result.
Optionally, the performing finite element modeling on the turbine disk by using computer simulation software specifically includes:
modeling according to the shape and size of the turbine disc workpiece, and inputting the adjusted boundary conditions to design the annealing process so that the temperature field distribution in the production process meets the requirements of process parameters.
The simulation software can accurately calculate the temperature field change, such as Pandat, Abaqus and the like. The simulation of the temperature measurement test needs to be modeled strictly according to the shape and the size of a test piece. And adjusting the boundary conditions of the simulation, such as the heat exchange coefficient of the system, the heat conduction coefficient of the alloy and the like, according to the instantaneous temperature and temperature field change of each part measured by the temperature measurement test.
And then, accurately modeling according to the turbine disc workpiece by using the simulation software, inputting boundary conditions obtained by the test, and designing the annealing flow of production according to the requirements of the process parameters, so that the temperature field distribution in the production process meets the requirements of the process parameters.
Optionally, a thermocouple is placed on the surface of the workpiece to monitor the instantaneous temperature, and if the instantaneous temperature recorded by the thermocouple is consistent with a simulation value, the overall temperature distribution of the workpiece is indirectly deduced according to the simulation result.
Optionally, the furnace for the annealing process comprises a conventional air furnace or a vacuum gas quenching furnace, the minimum service temperature of the furnace for the annealing process is not lower than 1200 ℃, and the temperature deviation of an effective heating area of a hearth is within 5 ℃.
Optionally, the workpiece is heated with the furnace at a heating rate of 1-4 ℃/min to a temperature 50-100 ℃ below the gamma' phase remelting temperature of the alloy. Specifically, a thermocouple is welded on a temperature measuring point on the surface of the workpiece, and the temperature is raised to 50-100 ℃ below the gamma' phase solid solution temperature by 1-4 ℃/min. The slower temperature rise rate is beneficial to coarsening of the gamma' phase of the grain boundary. Heating to 50-100 deg.C below the solid solution temperature of gamma' phase can provide sufficient static recrystallization activation energy. A large amount of gamma' phase is redissolved into a gamma phase matrix, which is beneficial to subsequent cooling and precipitation. The specific temperature is comprehensively determined according to alloy components, a hot extrusion process, product performance indexes, equipment conditions and the like. If the temperature is lower than the range, the starting difficulty of static recrystallization is higher, and a large amount of intragranular gamma' phases are difficult to dissolve back a matrix, so that the adjustment of a dual-phase crystal structure is not facilitated. If the temperature is higher than the above temperature, the grain growth phenomenon is obvious, and the subsequent high-temperature thermal deformation is not facilitated. The instantaneous temperature field of the workpiece can be obtained by combining simulation.
Optionally, after the lowest temperature region of the workpiece reaches a preset temperature, continuously preserving the heat for 0-16 hours.
Because the size of the workpiece is larger, the temperature of each part is in sequence. To ensure the tissue uniformity, the temperature-keeping stage is performed after the lowest temperature position reaches a predetermined temperature. The heat preservation time is 0-16 hours. If the extruded microstructure is not completely recrystallized and the size of the γ' phase of the grain boundary is large, the holding time may be set to 0 hour. If the extruded microstructure does not have a completely recrystallized structure and the difference between the size of the gamma 'phase of the grain boundary and the size of the gamma' phase in the crystal is not large, the holding time can be set to 16 hours. As the holding time increases, static recrystallization of incompletely recrystallized grains is facilitated. The prolonged heat preservation time can dissolve the gamma 'phase in the crystal and coarsen the gamma' phase of the crystal boundary, which is beneficial to forming a dual-phase crystal structure.
Optionally, the workpiece is cooled to room temperature, and the cooling mode is air cooling or oil cooling.
And after the heat preservation is finished, cooling the workpiece by using air cooling or oil cooling. For large-size workpieces, the cooling speed of the two cooling modes is faster than that of furnace cooling, salt cooling and air cooling. The faster cooling speed makes the gamma' phase in the crystal uniformly and finely precipitated. Is beneficial to the redissolution in the subsequent forging stage, thereby reducing the deformation resistance.
Optionally, the thermocouple deviation is not more than 4 ℃, and the thermocouple minimum use temperature is not lower than 1200 ℃.
The invention has the beneficial effects that: the method comprises the steps of (1) coarsening a gamma' phase of a crystal boundary by using a slower heating rate, and statically recrystallizing a part of incompletely recrystallized grains by adding a homogenization annealing process; (2) through specific annealing temperature, enough recrystallization activation energy and grain growth driving force are provided for an alloy system, the condition of static recrystallization is met, and meanwhile, small recrystallized crystal nuclei grow properly, so that the grain structure is homogenized, and the coarsening rate of a grain boundary gamma' phase can be accelerated; (3) by the heat preservation time, small crystal grains can further grow properly, large crystal grains maintain the size in the presence of a grain boundary gamma ' phase, the gamma ' phase in the crystal can be dissolved back, the grain boundary gamma ' phase grows to be close to the size of the crystal grains, the structure is further homogenized, and a dual-phase crystal structure is formed; (4) by the cooling mode, the gamma' phase in the crystal precipitated after cooling is uniform and fine, and is completely dissolved back in the subsequent forging process so as to reduce the deformation resistance.
The embodiment of the invention also provides a turbine disc prepared by the method.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the specific details of the above embodiments, and various simple modifications can be made to the technical solution of the present invention within the technical idea of the present invention, and these simple modifications are within the protective scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and the invention is not described in any way for the possible combinations in order to avoid unnecessary repetition.
In addition, any combination of the various embodiments of the present invention is also possible, and the same should be considered as the disclosure of the present invention as long as it does not depart from the spirit of the present invention.
Claims (10)
1. An annealing process method for preparing a turbine disk, comprising:
carrying out finite element modeling on the turbine disc by using computer simulation software, and designing an annealing process;
placing the workpiece after hot extrusion in a furnace for an annealing process, setting heating power according to a simulation result, and slowly heating to a preset temperature;
after the whole workpiece reaches a preset temperature, preserving heat for a preset time;
cooling the workpiece to room temperature.
2. The method of claim 1, wherein prior to designing an annealing process using finite element modeling of the turbine disk using computer simulation software, the method further comprises:
setting process parameters: setting technological parameters of an annealing process according to different turbine disc materials, and selecting a proper furnace for the annealing process;
testing and measuring temperature: placing a test workpiece or a test standard block into the annealing process furnace, welding a thermocouple on the surface of the test workpiece or the test standard block, or placing the thermocouple after drilling, and monitoring the overall temperature field change of the temperature rise and the cooling process of the test workpiece or the test standard block;
simulation: and using computer simulation software to perform finite element modeling according to the shape and the size of the test workpiece or the test standard block, and adjusting the simulated boundary conditions according to the test data until the temperature field change result is consistent with the temperature measurement result.
3. The method of claim 2, wherein the finite element modeling of the turbine disk using computer simulation software specifically comprises:
modeling according to the shape and size of the turbine disc workpiece, and inputting the adjusted boundary conditions to design the annealing process so that the temperature field distribution in the production process meets the requirements of process parameters.
4. The method of claim 3, wherein a thermocouple is placed on the surface of the workpiece to monitor the instantaneous temperature, and the temperature distribution of the workpiece is inferred indirectly from the simulation if the instantaneous temperature recorded by the thermocouple matches the simulated value.
5. The method of claim 4, wherein the furnace for the annealing process comprises a conventional air furnace or a vacuum gas quenching furnace, the minimum service temperature of the furnace for the annealing process is not lower than 1200 ℃, and the temperature deviation of an effective heating area of a hearth is within 5 ℃.
6. The method of claim 5, wherein the workpiece is heated to 50-100 ℃ below the γ' phase resolubilization temperature of the alloy in the furnace at a rate of 1-4 ℃/min.
7. The method of claim 6, wherein the holding is continued for 0 to 16 hours after the lowest temperature region of the workpiece reaches the predetermined temperature.
8. The method of claim 7, wherein the workpiece is cooled to room temperature by air cooling or oil cooling.
9. The method of claim 8, wherein the thermocouple deviation is no more than 4 ℃ and the thermocouple minimum use temperature is no less than 1200 ℃.
10. A turbine disc produced by the method of any one of claims 1 to 9.
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| CN202111573382.3A CN114317921A (en) | 2021-12-21 | 2021-12-21 | Annealing process method for preparing turbine disk and turbine disk |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0024031D0 (en) * | 2000-09-29 | 2000-11-15 | Rolls Royce Plc | A nickel base superalloy |
| EP2540963A2 (en) * | 2011-06-30 | 2013-01-02 | General Electric Company | Turbine disk preform, welded turbine rotor made therewith and methods of making the same |
| CN103970965A (en) * | 2014-05-26 | 2014-08-06 | 中国航空动力机械研究所 | Test run method for accelerated life test of gas turbine engine |
| CN109680184A (en) * | 2017-10-19 | 2019-04-26 | 丹阳宏图激光科技有限公司 | A kind of 3D printing forming method of nickel-base alloy powder powder material and the material |
| 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 |
| CN112464533A (en) * | 2020-11-27 | 2021-03-09 | 西北工业大学 | Turbine disk gradual change structure regulation and control method based on numerical simulation of whole process of preform and forging |
-
2021
- 2021-12-21 CN CN202111573382.3A patent/CN114317921A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB0024031D0 (en) * | 2000-09-29 | 2000-11-15 | Rolls Royce Plc | A nickel base superalloy |
| EP2540963A2 (en) * | 2011-06-30 | 2013-01-02 | General Electric Company | Turbine disk preform, welded turbine rotor made therewith and methods of making the same |
| CN103970965A (en) * | 2014-05-26 | 2014-08-06 | 中国航空动力机械研究所 | Test run method for accelerated life test of gas turbine engine |
| CN109680184A (en) * | 2017-10-19 | 2019-04-26 | 丹阳宏图激光科技有限公司 | A kind of 3D printing forming method of nickel-base alloy powder powder material and the material |
| 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 |
| CN112464533A (en) * | 2020-11-27 | 2021-03-09 | 西北工业大学 | Turbine disk gradual change structure regulation and control method based on numerical simulation of whole process of preform and forging |
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