CN112496215A - Forging method of titanium alloy thin-wall component - Google Patents
Forging method of titanium alloy thin-wall component Download PDFInfo
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- CN112496215A CN112496215A CN202011279569.8A CN202011279569A CN112496215A CN 112496215 A CN112496215 A CN 112496215A CN 202011279569 A CN202011279569 A CN 202011279569A CN 112496215 A CN112496215 A CN 112496215A
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- titanium alloy
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- forging
- alloy thin
- heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/06—Heating or cooling methods or arrangements specially adapted for performing forging or pressing operations
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
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- 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
- C22F1/008—Using a protective surface layer
-
- 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
- C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
-
- 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
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
Abstract
The scheme discloses a forging method of a titanium alloy thin-wall component in the technical field of titanium alloy product production, which comprises the following steps: step one, selecting a TA15 titanium alloy bar with a microstructure lower than 4 types (excluding 4 types) as a blank according to GJB 2218A-2008; step two, coating the blank with a titanium alloy coating, heating to 940-960 ℃ according to 0.7-0.9 mm/min, and preserving heat for 40 +/-5 min; then the blank after heat preservation is forged to be flat, and the forging force is 540 kg-560 kg; then putting the flattened blank into a preforging die for heating, and finally stamping to obtain a preforging blank, wherein the stamping pressure is 15000 KN-18000 KN; step three, pressing the preforging blank according to 0.7 toHeating to 910-930 ℃ at the speed of 0.9mm/min, preserving heat for 20 +/-5 min, then putting the preserved pre-forged blank into a precision forging die for stamping, and trimming after stamping to obtain a forged piece, wherein the stamping pressure is 16000-18000 KN; step four, heating the forging to 795 ℃, and then preserving heat
And finally, carrying out air cooling to obtain the titanium alloy thin-walled component. The preparation method in the scheme can obviously improve the mechanical property and the microstructure of the titanium alloy thin-wall component.
Description
Technical Field
The invention belongs to the technical field of titanium alloy product production, and particularly relates to a forging method of a titanium alloy thin-wall component.
Background
The TA15 titanium alloy material is an alpha-type titanium alloy, the nominal component of the alloy is Ti-6.5Al-2 Zr-1 Mo-1V, the alloy has medium room temperature and high temperature strength, good welding performance, thermal stability and process plasticity; therefore, the method is widely applied to the aerospace field.
The TA15 titanium alloy material is mainly applied to thin-wall components in the aerospace field, particularly the empennage of an aircraft. The forging of thin-walled components from TA15 titanium alloy materials generally comprises the steps of: blanking → heating → forging → heat treatment → inspection → packaging → warehousing.
The production of the titanium alloy thin-wall component can be realized in the above mode, but in the forging process, the strip alpha phase length of the TA15 titanium alloy material in the microstructure is easy to be large and thick in the forming process, so that the microstructure of the produced titanium alloy thin-wall component can only reach 5-7 types; although the titanium alloy thin-wall member can meet the requirements of parts of equipment with lower mechanical property requirements on the titanium alloy thin-wall member, when the titanium alloy thin-wall member is applied to the conditions that the requirement on performance indexes is high, and the microstructure of the titanium alloy thin-wall member is required to be in 3 types or below, such as an aircraft empennage, the titanium alloy thin-wall member produced by the existing forging method is difficult to meet the actual requirements.
Therefore, by optimizing the forging process of the conventional titanium alloy thin-wall component, the microstructure class of the titanium alloy thin-wall component is reduced, the mechanical property of the titanium alloy thin-wall component is improved, and the titanium alloy thin-wall component has important significance for expanding the application range of the TA15 titanium alloy material.
Disclosure of Invention
Aiming at the defects of the prior art, the mechanical property and the microstructure category of the titanium alloy thin-wall component are improved by optimizing the forging process of the titanium alloy thin-wall component.
The forging method of the titanium alloy thin-wall component comprises the following steps:
step one, selecting a TA15 titanium alloy bar with a microstructure lower than 4 types (excluding 4 types) as a blank according to GJB 2218A-2008;
step two, coating the blank with a titanium alloy coating, heating to 940-960 ℃ according to 0.7-0.9 mm/min, and preserving heat for 40 +/-5 min; then the blank after heat preservation is forged to be flat, and the forging force is 540 kg-560 kg; then putting the flattened blank into a preforging die for heating, and finally stamping to obtain a preforging blank, wherein the stamping pressure is 15000 KN-18000 KN;
step three, heating the pre-forging blank to 910-930 ℃ according to 0.7-0.9 mm/min, preserving heat for 20 +/-5 min, then putting the pre-forging blank after heat preservation into a precision forging die for punching, and trimming after punching to obtain a forged piece, wherein the punching pressure is 16000 KN-18000 KN;
step four, heating the forging to 795 ℃, and then preserving heat
And finally, carrying out air cooling to obtain the titanium alloy thin-walled component.
The beneficial effect of this scheme: according to the scheme, the titanium alloy coating is coated on the blank in the step two, so that the adverse effect of a heating link on the blank is reduced; and then, by optimizing heating, heat preservation and stamping parameters, the prepared titanium alloy thin-wall component has better mechanical property and a better microstructure.
Further, in the third step, the pre-forged blank is coated with a titanium alloy coating before being heated. And coating the titanium alloy coating on the pre-forged blank to enable the blank in the step two and the pre-forged blank in the step three to mutually influence each other, so that the mechanical property and the microstructure of the titanium alloy thin-wall member are obviously improved.
Further, in the second step, the billet is heated to 940 ℃ according to the speed of 0.8 mm/min. Can simultaneously give consideration to both quality and production efficiency.
Further, in the second step, the pressing pressure of the blank is 16000 KN. The performance of the preforging blank can be improved by heating the blank to 940 ℃ in combination with the blank of 0.8mm/min and adopting the stamping pressure of 16000 KN.
Further, in the third step, the preforged blank is heated to 920 ℃ at a rate of 0.8 mm/min. The preforging blank is heated to 920 ℃ according to 0.8mm/min, so that the protection effect of the titanium alloy coating on the preforging blank can reach the best.
Further, in the third step, the pressing pressure of the blank is 16000 KN. The performance of the forge piece can be improved by heating the combined pre-forging blank to 920 ℃ at the speed of 0.8mm/min and adopting the stamping pressure of 16000 KN.
Further, in the fourth step, the air cooling is performed in an inert gas atmosphere. And inert gas is adopted for air cooling, so that the oxidation of the forging can be effectively prevented.
Drawings
Fig. 1 is a three-dimensional view of an aircraft tail produced in example 1 of the present invention.
Detailed Description
The following is further detailed by way of specific embodiments:
the titanium alloy thin-wall component produced by the method of the invention is consistent with the structure of the prior art, and the embodiment takes the manufacturing method of the empennage of the aircraft as an example. The titanium alloy coating in the embodiment is KBC-12 titanium alloy coating produced by Zhejiang yellow rock special coating factories.
Example 1: a forging method of an aircraft empennage comprises the following steps:
step one, selecting a TA15 titanium alloy bar material with the specification of phi 50 and the microstructure of 3 types as a blank according to GJB 2218A-2008; the pre-forging die and the precision forging die are made of H13 material, and the trimming die is made of 5 CrNiMo;
step two, blanking according to phi 50 multiplied by 180, coating the blank with titanium alloy coating, heating to 940 ℃ through a box type electric furnace, heating according to 0.8mm/min, and preserving heat for 42min after heating the blank; flattening the blank after heat preservation under 560kg of pressure by using a 560kg air hammer; after the blank is forged to be flat, repairing and coloring inspection is carried out, then the blank qualified by inspection is placed into a preforging die for heating and is stamped on a 16000KN press machine to obtain a preforging blank;
step three, coating titanium alloy coating after repairing damage and coloring check of the pre-forged blank, heating to 920 ℃ according to 0.8mm/min, preserving heat for 23min, then placing the pre-forged blank after heat preservation into a precision forging die, stamping by using a 16000KN press with the stamping pressure of 16000KN, and trimming through a trimming die after stamping to obtain a forged piece;
and step four, putting the forging into a vacuum furnace, heating to 795 ℃ (heating along with the furnace), preserving heat for 55min, and then performing air cooling in an inert gas environment (in the scheme, nitrogen is used as the inert gas) to obtain the titanium alloy thin-wall component (the tail wing of the aircraft), as shown in the attached figure 1.
Example 2 differs from example 1 only in that: and the blank in the second step is not coated with titanium alloy coating.
Example 3 differs from example 1 only in that: the preforging blank in step three is not coated with titanium alloy coating.
Example 4 differs from example 1 only in that: and the blank in the second step and the pre-forged blank in the third step are not coated with titanium alloy coating.
Comparative example: the aircraft tail is produced according to the state of the art.
And (3) experimental detection:
sampling and carrying out physicochemical detection on the titanium alloy thin-wall components produced in the examples 1-4 and the comparative example:
1) mechanical properties
TABLE 1 Room temperature mechanical Properties parameters
Two values of the measured values (longitudinal direction) in table 1 represent the respective results detected under the conditions of room-temperature stretching and room-temperature impact.
TABLE 2 high temperature mechanical Properties parameters
In table 2, the σ b (mpa) value of the measured value (longitudinal direction) represents the result of the measurement under the conditions of high-temperature tension and high-temperature impact.
2) Metallographic examination
Sampling and checking a thin-wall complex forging piece to obtain a macroscopic and microscopic test result: the transverse macroscopic structure is free of cracks, inclusions, segregation, shrinkage cavities, air holes, layering and other metallurgical defects, is graded according to a GJB2744A-2007 standard figure 1 (the grade 1-4 is qualified), the microstructure is graded according to a GJB2744A-2007 standard figure 3, and the grade 1-5 is qualified. The results are shown in table 3:
TABLE 3
3) Flaw detection
And the forging defects of cracks, folding, thick tissues and the like are not found in the 100% fluorescence flaw detection of the thin-wall complex forging.
Surface treatment: and (5) performing 100% electrochemical polishing on the forged piece.
And comprehensively inspecting, marking, packaging and warehousing.
As can be seen from tables 1 and 2: compared with the prior art, the aircraft empennage prepared by the forging method has good mechanical property; the key link is that the blank in the step two and the preforging blank in the step three are coated with titanium alloy coating, and the technological parameters are adaptively optimized, so that the mechanical property of the aircraft empennage is obviously improved. And only the blank in the step two or the pre-forged blank in the step three is coated with the titanium alloy coating, compared with the aircraft empennage produced by the prior art, the mechanical property is improved, but the improvement is small, and the coating of the titanium alloy coating in the step two and the step three is related to each other. And after two links of coating the blank in the step two and the preforging blank in the step three with the titanium alloy coating are removed, the mechanical property of the produced aircraft empennage is obviously reduced, and the mechanical property of the aircraft empennage is not as good as that of the prior art.
In addition, as can be seen from table 3: the microstructure of the aircraft empennage prepared by the forging method is better than that of the prior art.
Claims (7)
1. A forging method of a titanium alloy thin-wall component is characterized by comprising the following steps: step one, selecting a TA15 titanium alloy bar with a microstructure lower than 4 types as a blank according to GJB 2218A-2008;
step two, coating the blank with a titanium alloy coating, heating to 940-960 ℃ according to 0.7-0.9 mm/min, and preserving heat for 40 +/-5 min; then the blank after heat preservation is forged to be flat, and the forging force is 540 kg-560 kg; then putting the flattened blank into a preforging die for heating, and finally stamping to obtain a preforging blank, wherein the stamping pressure is 15000 KN-18000 KN;
step three, heating the pre-forging blank to 910-930 ℃ according to 0.7-0.9 mm/min, preserving heat for 20 +/-5 min, then putting the pre-forging blank after heat preservation into a precision forging die for punching, and trimming after punching to obtain a forged piece, wherein the punching pressure is 16000 KN-18000 KN;
step four, heating the forging to 795 ℃, and then preserving heat by 55 DEG C0 +5And min, finally performing air cooling to obtain the titanium alloy thin-walled component.
2. The forging method of a titanium alloy thin-walled member according to claim 1, wherein: and in the third step, coating titanium alloy coating on the pre-forged blank before heating.
3. The forging method of a titanium alloy thin-walled member according to claim 2, wherein: in the second step, the blank is heated to 940 ℃ according to the speed of 0.8 mm/min.
4. The forging method of a titanium alloy thin-walled member according to claim 3, wherein: in the second step, the stamping pressure of the blank is 16000 KN.
5. The forging method of a titanium alloy thin-walled component as claimed in any one of claims 2 to 4, wherein: in the third step, the preforged blank is heated to 920 ℃ according to the speed of 0.8 mm/min.
6. The forging method of a titanium alloy thin-walled member according to claim 5, wherein: in the third step, the stamping pressure of the blank is 16000 KN.
7. The forging method of a titanium alloy thin-walled member according to claim 6, wherein: in the fourth step, the air cooling is carried out in an inert gas environment.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5076858A (en) * | 1989-05-22 | 1991-12-31 | General Electric Company | Method of processing titanium aluminum alloys modified by chromium and niobium |
| EP1624084A1 (en) * | 2004-07-28 | 2006-02-08 | Rolls-Royce Plc | A method of forging a titanium alloy |
| CN1830617A (en) * | 2006-02-09 | 2006-09-13 | 沈阳黎明航空发动机(集团)有限责任公司 | TA15 alloy ring-shaped piece mould forge piece forging and heat treatment technology |
| CN102489952A (en) * | 2011-12-04 | 2012-06-13 | 西北有色金属研究院 | Method for manufacturing titanium alloy thick-wall pressure-resistant cylinder body |
| CN103357806A (en) * | 2013-07-22 | 2013-10-23 | 上海驳原金属材料有限公司 | Manufacturing process for ultra-fine grain titanium alloy TC4 blade |
| CN106555076A (en) * | 2017-01-09 | 2017-04-05 | 北京工业大学 | A kind of resistance to 650 DEG C of high-temperature titanium alloy materials and preparation method thereof |
| CN109226622A (en) * | 2018-09-18 | 2019-01-18 | 西安三角防务股份有限公司 | A kind of TA15 titanium alloy forging forging forming method with high-intensity and high-tenacity |
| CN110976727A (en) * | 2019-12-19 | 2020-04-10 | 陕西宏远航空锻造有限责任公司 | Forging method for improving structure uniformity of titanium alloy forging |
-
2020
- 2020-11-16 CN CN202011279569.8A patent/CN112496215B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5076858A (en) * | 1989-05-22 | 1991-12-31 | General Electric Company | Method of processing titanium aluminum alloys modified by chromium and niobium |
| EP1624084A1 (en) * | 2004-07-28 | 2006-02-08 | Rolls-Royce Plc | A method of forging a titanium alloy |
| CN1830617A (en) * | 2006-02-09 | 2006-09-13 | 沈阳黎明航空发动机(集团)有限责任公司 | TA15 alloy ring-shaped piece mould forge piece forging and heat treatment technology |
| CN102489952A (en) * | 2011-12-04 | 2012-06-13 | 西北有色金属研究院 | Method for manufacturing titanium alloy thick-wall pressure-resistant cylinder body |
| CN103357806A (en) * | 2013-07-22 | 2013-10-23 | 上海驳原金属材料有限公司 | Manufacturing process for ultra-fine grain titanium alloy TC4 blade |
| CN106555076A (en) * | 2017-01-09 | 2017-04-05 | 北京工业大学 | A kind of resistance to 650 DEG C of high-temperature titanium alloy materials and preparation method thereof |
| CN109226622A (en) * | 2018-09-18 | 2019-01-18 | 西安三角防务股份有限公司 | A kind of TA15 titanium alloy forging forging forming method with high-intensity and high-tenacity |
| CN110976727A (en) * | 2019-12-19 | 2020-04-10 | 陕西宏远航空锻造有限责任公司 | Forging method for improving structure uniformity of titanium alloy forging |
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