CN109778092B - Titanium alloy processing method - Google Patents
Titanium alloy processing method Download PDFInfo
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- CN109778092B CN109778092B CN201910146348.4A CN201910146348A CN109778092B CN 109778092 B CN109778092 B CN 109778092B CN 201910146348 A CN201910146348 A CN 201910146348A CN 109778092 B CN109778092 B CN 109778092B
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Abstract
The titanium alloy processing method provided by the invention is used for carrying out primary annealing treatment on the titanium alloy; carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment; carrying out rough machining on the titanium alloy subjected to the annealing treatment twice; carrying out primary cryogenic treatment on the titanium alloy after rough machining; performing semi-finishing on the titanium alloy subjected to primary cryogenic treatment; carrying out secondary subzero treatment on the titanium alloy subjected to the semi-finish machining; the titanium alloy processing method provided by the invention adopts a processing scheme from primary annealing, secondary annealing, rough machining, primary cryogenic treatment, semi-finishing, secondary cryogenic circulating treatment to finish machining, and reasonably combines the titanium alloy annealing treatment, the cryogenic treatment and the machining procedures to release residual stress generated in each process of the manufacturing link of the titanium alloy part to the maximum extent and improve the dimensional stability of the titanium alloy part.
Description
Technical Field
The invention relates to the technical field of titanium alloy structural member production and manufacturing, in particular to a titanium alloy processing method.
Background
The titanium alloy has the characteristics of small density, high specific strength, high temperature resistance, corrosion resistance and the like, is a novel structural material developed in the middle of the 20 th century, and has been widely applied to many fields, particularly the aerospace field. For example, titanium alloys are required for aircraft fan blades, compressor blades, disks, shafts, casings, frameworks, skins, fuselage bulkheads and landing gears; in the aerospace industry, titanium and its alloys are used to make fuel tanks, rocket motor casings, rocket nozzle ducts, satellite housings, and the like. Therefore, titanium is known as an indispensable space metal in the modern aerospace industry. In recent years, titanium alloys for aviation have rapidly developed against the background of national demand. The titanium consumption of the second-generation machine is not more than 2 percent, and the titanium alloy consumption of the third-generation machine is rapidly increased to 15 percent. The demand of titanium alloy in the field of aviation contributes to the current situation that the demand of titanium alloy in China is large and the development is rapid to a certain extent.
However, titanium alloy structural members in the aerospace field are often large in size, complex in structure, poor in symmetry, large in machining removal amount, residual stress is easily generated on the surface and inside of a part in the machining process, and the appearance size of the material is changed due to the existence of uneven residual stress. Therefore, dimensional stability during machining has been a bottleneck problem in the manufacturing process of titanium alloy parts. Conventional methods for stabilizing the dimensions of components generally include mechanical methods (including stretching or compressing methods, vibration aging methods, and pulsating methods), heat treatment methods (including constant temperature aging methods, heat aging methods, counter-quenching methods, deformation heat treatment methods, and the like), natural aging methods, and magnetic field treatment methods, and the effects of the various methods are different. At present, most of the common solutions for the dimensional stabilization of titanium alloy structural parts are to add multiple aging treatment, benchmark correction and other processes in the machining process, but the processes are time-consuming and costly, the production period of products is longer, the qualification rate is lower, and in addition, the basic mechanical properties of the materials are easily influenced by overhigh aging temperature. Therefore, the method for exploring the novel method for stabilizing the size of the titanium alloy part has important significance.
In order to reduce the internal stress of alloy and parts and improve the dimensional stability of parts, the deep cooling circulating treatment method is started in the Soviet Union before the later half of the 50 years, but due to the limitation of the low temperature condition, the treatment specification is to cool the alloy to-75 to-95 ℃, then heat the alloy to room temperature or annealing (aging) temperature, and circulate for one to five times, but the information about the specification and the effect of the treatment cannot be agreed. However, as the low temperature technology is continuously developed, the lower temperature is easier to obtain, the development of the cryogenic treatment technology is strongly promoted, and the application of the cryogenic treatment in the aspects of reducing the macroscopic residual stress of materials and structural members and improving the dimensional stability is widely accepted.
However, the combination of cryogenic treatment with conventional heat treatment and conventional processing is a key factor affecting the final dimensional stabilization effect. The traditional scheme does not fully consider the effect in the aspect, only carries out cryogenic treatment on the titanium alloy after heat treatment, and cannot effectively realize the modification of the dimensional stability of the titanium alloy.
Disclosure of Invention
Therefore, there is a need to provide a method for processing titanium alloy that can maintain the dimensional stability of the titanium alloy processing process.
In order to achieve the purpose, the invention adopts the following technical scheme:
a titanium alloy processing method comprises the following steps:
carrying out primary annealing treatment on the titanium alloy;
carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment;
carrying out rough machining on the titanium alloy subjected to the annealing treatment twice;
carrying out primary cryogenic treatment on the titanium alloy after rough machining;
performing semi-finishing on the titanium alloy subjected to primary cryogenic treatment;
carrying out secondary subzero treatment on the titanium alloy subjected to the semi-finish machining;
and performing finish machining on the titanium alloy subjected to the secondary subzero treatment.
In some preferred embodiments, in the step of performing the primary annealing treatment on the titanium alloy, the temperature of the primary annealing treatment is 650 to 850 ℃.
In some preferred embodiments, the primary annealing treatment is performed in an air furnace, a vacuum furnace or an atmosphere protection furnace, and the cooling is furnace cooling.
In some preferred embodiments, in the step of performing the secondary annealing treatment on the titanium alloy after the primary annealing treatment, the temperature of the secondary annealing treatment is 650 to 850 ℃.
In some preferred embodiments, in the step of performing a cryogenic treatment on the roughly processed titanium alloy, the steps are specifically:
preserving the heat of the titanium alloy after rough machining for 2-24 hours at the temperature of-80 to-180 ℃;
and then low-temperature tempering is carried out at the temperature of 120-180 ℃, and the temperature is kept for 2-24 hours.
In some preferred embodiments, the temperature increase/decrease rate in the low temperature tempering is controlled to be 1-5 ℃/min.
In some preferred embodiments, in the step of performing the second cryogenic treatment on the roughly processed titanium alloy, the steps are specifically:
preserving the heat of the titanium alloy after rough machining for 2-24 hours at the temperature of-80 to-180 ℃;
and then low-temperature tempering is carried out at the temperature of 120-180 ℃, and the temperature is kept for 2-24 hours.
In some preferred embodiments, the temperature increase/decrease rate in the low temperature tempering is controlled to be 1-5 ℃/min.
The invention adopts the technical scheme that the method has the advantages that:
the titanium alloy processing method provided by the invention is used for carrying out primary annealing treatment on the titanium alloy; carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment; carrying out rough machining on the titanium alloy subjected to the annealing treatment twice; carrying out primary cryogenic treatment on the titanium alloy after rough machining; performing semi-finishing on the titanium alloy subjected to primary cryogenic treatment; carrying out secondary subzero treatment on the titanium alloy subjected to the semi-finish machining; the titanium alloy processing method provided by the invention adopts a processing scheme from primary annealing, secondary annealing, rough machining, primary cryogenic treatment, semi-finishing, secondary cryogenic circulating treatment to finish machining, and reasonably combines the titanium alloy annealing treatment, the cryogenic treatment and the machining procedures to release residual stress generated in each process of the manufacturing link of the titanium alloy part to the maximum extent and improve the dimensional stability of the titanium alloy part.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a flowchart illustrating steps of a titanium alloy processing method according to an embodiment.
Fig. 2 is a process schematic diagram of a titanium alloy processing method according to an embodiment.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, a flow chart of steps of a titanium alloy processing method according to the present invention is provided, and for convenience of illustration, only the parts related to the embodiment of the present invention are shown, which is described in detail below.
The invention provides a titanium alloy processing method, which comprises the following steps:
step S110: carrying out primary annealing treatment on the titanium alloy;
in some preferred embodiments, the temperature of the primary annealing treatment is 650 to 850 ℃.
In some preferred embodiments, the primary annealing treatment is performed in an air furnace, a vacuum furnace or an atmosphere protection furnace, and the cooling is furnace cooling.
Step S120: carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment;
in some preferred embodiments, the temperature of the secondary annealing treatment is 650 to 850 ℃.
It can be understood that the residual stress in the material can be effectively reduced by annealing the titanium alloy twice, and the dimensional stability of the raw material is improved.
Step S130: carrying out rough machining on the titanium alloy subjected to the annealing treatment twice;
it can be understood that in the rough machining process, because the removal amount of the titanium alloy material is large, the machining stress can be generated in the removal process of the material of the surface layer of the part, meanwhile, because the temperature gradient exists in the cutting process, the thermal stress can be generated, the residual stress generated in the process can be effectively reduced through the deep cooling treatment, and the condition that the oxidation is generated in the aging process of a processed product in a common air furnace is avoided.
Step S140: carrying out primary cryogenic treatment on the titanium alloy after rough machining;
in some preferred embodiments, in the step of performing a cryogenic treatment on the roughly processed titanium alloy, the steps are specifically:
step S141: preserving the heat of the titanium alloy after rough machining for 2-24 hours at the temperature of-80 to-180 ℃;
step S142: and then low-temperature tempering is carried out at the temperature of 120-180 ℃, and the temperature is kept for 2-24 hours.
In some preferred embodiments, the temperature increase/decrease rate in the low temperature tempering is controlled to be 1-5 ℃/min.
It can be understood that because the primary subzero treatment is carried out by adopting the cryogenic box with the tempering function, the subzero treatment comprises the low-temperature tempering process, and the machining stress is released under the combined action of the subzero treatment and the tempering; in addition, because the primary cryogenic treatment is realized by adopting the cryogenic treatment equipment with the tempering function, the treatment process is simple, and the material cannot be oxidized, thereby ensuring the intact surface state of the material.
Step S150: performing semi-finishing on the titanium alloy subjected to primary cryogenic treatment;
the semi-finishing process such as traditional turning and milling is adopted, the cutting amount is larger compared with rough machining, the cutting amount of the semi-finishing process is less, and the specific steps are determined according to the machining procedures of actual parts.
It can be understood that after primary cryogenic treatment, the titanium alloy is subjected to semi-finishing, and a small amount of allowance is reserved according to the size of the titanium alloy part.
Step S160: carrying out secondary subzero treatment on the titanium alloy subjected to the semi-finish machining;
the process of the second sub-zero treatment is the same as the step of the first sub-zero treatment, and is not described in detail here.
It can be understood that the processing stress of the titanium alloy can be released through twice cryogenic treatment, the performance of the titanium alloy can be improved, the condition that the material performance is reduced in the annealing process is avoided, and therefore the stability of the semi-finished parts is guaranteed.
Step S170: and performing finish machining on the titanium alloy subjected to the secondary subzero treatment.
It will be appreciated that the residual stresses produced are lower due to the small amount removed by the finish cutting process, thereby ensuring that the overall residual stresses in the final product are lower.
The titanium alloy processing method provided by the invention adopts the processing scheme from primary annealing, secondary annealing, rough machining, primary cryogenic treatment, semi-finishing, secondary cryogenic circulating treatment to finish machining.
Examples
Fig. 2 is a process diagram of a titanium alloy processing method according to an embodiment.
Carrying out primary annealing treatment on the titanium alloy raw material by adopting vacuum heat treatment or an atmosphere furnace, wherein the annealing temperature is 650 ℃; before machining, carrying out secondary annealing treatment on the titanium alloy raw material again, wherein the annealing temperature is 650 ℃, so as to release the residual stress of the raw material to the maximum extent; after annealing treatment, rough machining is carried out according to product design, and after rough machining, cryogenic treatment is carried out on the workpiece, the lowest temperature of the cryogenic treatment is-180 ℃, the heat preservation time is 12 hours, supplementary low-temperature tempering is carried out after the cryogenic heat preservation is finished, the tempering temperature is 180 ℃, the heat preservation is carried out for 3 hours, the cooling mode is air cooling, and the temperature rising and falling rate in the cryogenic treatment process is 3 ℃/min; performing semi-finishing on the workpiece after the primary subzero treatment, and performing secondary subzero treatment after the semi-finishing, wherein the subzero treatment process is the same as the primary subzero treatment process; the machining stress generated in the machining process is reduced to the maximum extent through the cryogenic treatment; and (3) performing final finish machining on the workpiece after secondary cryogenic treatment, wherein the machined titanium alloy part has high dimensional stability.
Of course, the titanium alloy processing method of the present invention may have various changes and modifications, and is not limited to the specific structure of the above embodiment. In conclusion, the scope of the present invention should include those changes or substitutions and modifications which are obvious to those of ordinary skill in the art.
Claims (4)
1. The titanium alloy processing method is characterized by comprising the following steps:
carrying out primary annealing treatment on the titanium alloy;
carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment;
carrying out rough machining on the titanium alloy subjected to the annealing treatment twice;
carrying out primary cryogenic treatment on the titanium alloy after rough machining;
performing semi-finishing on the titanium alloy subjected to primary cryogenic treatment;
carrying out secondary subzero treatment on the titanium alloy subjected to the semi-finish machining;
performing finish machining on the titanium alloy subjected to the secondary subzero treatment;
in the step of carrying out primary annealing treatment on the titanium alloy, the temperature of the primary annealing treatment is 650-850 ℃;
in the step of carrying out secondary annealing treatment on the titanium alloy subjected to the primary annealing treatment, the temperature of the secondary annealing treatment is 650-850 ℃;
in the step of carrying out primary cryogenic treatment on the titanium alloy after rough machining, the method specifically comprises the following steps:
preserving the heat of the titanium alloy after rough machining for 2-24 hours at the temperature of-80 to-180 ℃;
then carrying out low-temperature tempering at the temperature of 120-180 ℃, and preserving heat for 2-24 hours;
in the step of carrying out secondary subzero treatment on the titanium alloy after rough machining, the method specifically comprises the following steps:
preserving the heat of the titanium alloy after rough machining for 2-24 hours at the temperature of-80 to-180 ℃;
and then low-temperature tempering is carried out at the temperature of 120-180 ℃, and the temperature is kept for 2-24 hours.
2. The method of processing a titanium alloy according to claim 1, wherein the primary annealing is performed in an air furnace, a vacuum furnace or an atmosphere protection furnace, and the cooling is performed by furnace cooling.
3. The method for processing a titanium alloy according to claim 1, wherein a temperature increase/decrease rate in the low-temperature tempering is controlled to be 1 to 5 ℃/min.
4. The method for processing a titanium alloy according to claim 1, wherein a temperature increase/decrease rate in the low-temperature tempering is controlled to be 1 to 5 ℃/min.
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| CN111360362B (en) * | 2020-04-01 | 2021-11-16 | 中国科学院理化技术研究所 | Deep cooling treatment method for brazing diamond tool and brazing diamond tool |
| CN111360199A (en) * | 2020-04-08 | 2020-07-03 | 安徽羿维表面工程技术有限公司 | Alloy composition of alloy casting side guide plate |
| CN112372005B (en) * | 2020-04-13 | 2023-12-19 | 广东佳悦美视生物科技有限公司 | Preparation method of collar buckle type artificial cornea |
| CN112372255B (en) * | 2020-11-30 | 2021-10-12 | 贵州精立航太科技有限公司 | Processing technology of damping bowl |
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| CN104668918A (en) * | 2014-12-12 | 2015-06-03 | 吴明铂 | High-precision titanium-alloy thin-walled ring gear machining method |
| CN106917057A (en) * | 2015-12-24 | 2017-07-04 | 北京有色金属研究总院 | A kind of processing method of the residual stress for eliminating light alloy material |
| CN108374135A (en) * | 2018-03-30 | 2018-08-07 | 江苏大学 | A kind of processing technology improving TC6 titanium alloys intensity and high-temperature stability |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104668918A (en) * | 2014-12-12 | 2015-06-03 | 吴明铂 | High-precision titanium-alloy thin-walled ring gear machining method |
| CN106917057A (en) * | 2015-12-24 | 2017-07-04 | 北京有色金属研究总院 | A kind of processing method of the residual stress for eliminating light alloy material |
| CN108374135A (en) * | 2018-03-30 | 2018-08-07 | 江苏大学 | A kind of processing technology improving TC6 titanium alloys intensity and high-temperature stability |
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