CN110964996A - Method for reducing heat treatment residual stress of thick-section titanium alloy forging - Google Patents
Method for reducing heat treatment residual stress of thick-section titanium alloy forging Download PDFInfo
- Publication number
- CN110964996A CN110964996A CN201911247993.1A CN201911247993A CN110964996A CN 110964996 A CN110964996 A CN 110964996A CN 201911247993 A CN201911247993 A CN 201911247993A CN 110964996 A CN110964996 A CN 110964996A
- Authority
- CN
- China
- Prior art keywords
- heat treatment
- titanium alloy
- residual stress
- cooling
- reducing
- 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
- C22F1/16—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 invention relates to a method for reducing heat treatment residual stress of a thick-section titanium alloy forging, and relates to the technical field of titanium alloy heat treatment. Firstly, heat treatment and furnace charging are carried out, and a forge piece is tamped, so that the forge piece is prevented from deforming or generating stress due to gravity at high temperature; then, heating to 730-790 ℃, and keeping the temperature for more than or equal to 1 hour (according to the effective thickness of the maximum section, the temperature is increased by 1 hour for every 1 inch of thickness increase); and finally, slowly cooling the heat-treated forge piece, firstly furnace-cooling to below 450 ℃ at the speed of less than or equal to 1 ℃/min, and then discharging and air-cooling. The invention can fully reduce the residual stress of the forging heat treatment, avoid the deformation of parts after machining and reduce the stress relief annealing between machining processes.
Description
Technical Field
The invention relates to the technical field of titanium alloy heat treatment.
Background
The titanium alloy has the characteristics of high specific strength, high temperature resistance, corrosion resistance and the like, and is widely applied to various fields. However, the forgings with thick sections, long rods and complex structures have residual stress after heat treatment annealing, so that parts are deformed or products are scrapped after machining; in order to remove stress and reduce part deformation, stress relief annealing is required between machining processes, so that the production cost is increased and the period is long. In order to avoid the situations, the invention fully eliminates the residual stress in the original forging by controlling the heating system of the heat treatment, and reduces the thermal stress generated in the cooling process as much as possible by controlling the cooling speed of the heat treatment.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the residual stress of the forging heat treatment is fully reduced, and the deformation of parts after machining is avoided or the stress relief annealing between machining processes is reduced.
The technical scheme of the invention is as follows:
the method for reducing the residual stress of the thick-section titanium alloy forging in the heat treatment process is characterized by comprising the following steps of 1: heating the forging stock to 730-790 ℃ through heat treatment, wherein the heat preservation time is more than or equal to 1 hour, and the residual stress in the original forging stock is fully eliminated; step 2: and (3) slowly cooling the heat-treated forge piece, firstly furnace-cooling to below 450 ℃ at the speed of less than or equal to 1 ℃/min, then discharging and air-cooling, and reducing the thermal stress generated in the cooling process.
Preferably, a heat treatment charging process is performed before step 1.
Preferably, the forging padding treatment is carried out during the furnace loading treatment, so that the forging is ensured not to deform or generate stress due to gravity at high temperature.
Preferably, the heat preservation time in the step 1 is calculated according to the effective thickness of the maximum section of the titanium alloy forging, and the heat preservation time is increased by 1 hour when the effective thickness is increased by 1 inch.
Preferably, the heating temperature of the heat treatment in the step 1 is 750-780 DEG C
Preferably, the cooling mode of the heat-treated forge piece in the step 2 is slow cooling
Preferably, the slow cooling requirement of the heat treatment forge piece in the step 2 is that the forge piece is firstly furnace-cooled to below 450 ℃ at the speed of less than or equal to 1 ℃/min, and then discharged from the furnace for air cooling.
The invention has the beneficial effects that:
(1) and (4) performing heat treatment and charging, wherein the forged piece is tamped, so that the forged piece is prevented from deforming or generating stress due to gravity at high temperature.
(2) And controlling the heating temperature and the heat preservation time of the heat treatment, and fully eliminating the residual stress in the original forging.
(3) The cooling speed of the heat treatment is controlled, and the thermal stress generated in the cooling process is reduced as much as possible.
Drawings
FIG. 1 is a schematic view of a forging charge.
Detailed Description
The following description will explain specific embodiments with reference to examples.
The structural member of a certain airplane adopts Ti-6Al-4V titanium alloy, the service state is an annealing state, and the maximum section effective thickness is 100 mm.
Example one
Step one, heat treatment and furnace charging, wherein a forged piece is to be tamped, as shown in figure 1;
step two, heating by heat treatment, raising the temperature to 750 +/-10 ℃, and keeping the temperature for 4 hours;
and step three, cooling the forged piece, and performing air cooling after the forged piece is discharged from the furnace.
Example two
Step one, heat treatment and furnace charging, wherein a forged piece is to be tamped, as shown in figure 1;
step two, heating by heat treatment, raising the temperature to 750 +/-10 ℃, and keeping the temperature for 4 hours;
and step three, slowly cooling the heat-treated forge piece, firstly furnace-cooling to below 450 ℃ at the speed of less than or equal to 1 ℃/min, and then discharging and air-cooling.
Example one and two machine results comparison: the same forging is respectively processed into the same part according to the same machining program after being subjected to heat treatment according to the first embodiment and the second embodiment, the part subjected to heat treatment according to the first embodiment is seriously deformed and scrapped, and the part subjected to heat treatment according to the second embodiment is not deformed and is qualified.
Claims (8)
1. The method for reducing the residual stress of the thick-section titanium alloy forging in the heat treatment process is characterized by comprising the following steps of 1: heating the forging stock to 730-790 ℃ through heat treatment, wherein the heat preservation time is more than or equal to 1 hour, and the residual stress in the original forging stock is fully eliminated; step 2: and (3) slowly cooling the heat-treated forge piece, firstly furnace-cooling to below 450 ℃ at the speed of less than or equal to 1 ℃/min, then discharging and air-cooling, and reducing the thermal stress generated in the cooling process.
2. The method for reducing the residual stress of the heat treatment of the thick section titanium alloy forging according to claim 1, wherein the method comprises the following steps: the heat treatment charging treatment is carried out before the step 1.
3. The method for reducing the residual stress of the heat treatment of the thick section titanium alloy forging according to claim 2, wherein the method comprises the following steps: and the forging piece is tamped during the charging treatment, so that the forging piece is prevented from deforming or generating stress due to gravity at high temperature.
4. The method for reducing the residual stress of the heat treatment of the thick section titanium alloy forging according to claim 3, wherein the method comprises the following steps: and (3) calculating the heat preservation time in the step 1 according to the maximum section effective thickness of the titanium alloy forging.
5. The method for reducing the residual stress of the heat treatment of the thick section titanium alloy forging according to claim 4, wherein the method comprises the following steps: and the heat preservation time is increased by 1 hour for every 1 inch of the effective thickness of the maximum section of the titanium alloy forging.
6. The method for reducing the residual stress of the heat treatment of the thick-section titanium alloy forging according to claim 5, wherein the heating temperature of the heat treatment is 750-780 ℃.
7. The method for reducing the residual stress of the heat treatment of the thick section 6 titanium alloy forging according to claim 6, wherein the method comprises the following steps: the cooling mode of the heat-treated forge piece is slow cooling.
8. The method of reducing the residual stress of heat treatment of thick section titanium alloy forgings according to claim 7, wherein: the slow cooling requirement of the heat-treated forge piece is that the forge piece is firstly furnace-cooled to below 450 ℃ at the speed of less than or equal to 1 ℃/min, and then discharged from the furnace for air cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911247993.1A CN110964996A (en) | 2019-12-06 | 2019-12-06 | Method for reducing heat treatment residual stress of thick-section titanium alloy forging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911247993.1A CN110964996A (en) | 2019-12-06 | 2019-12-06 | Method for reducing heat treatment residual stress of thick-section titanium alloy forging |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110964996A true CN110964996A (en) | 2020-04-07 |
Family
ID=70033352
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911247993.1A Pending CN110964996A (en) | 2019-12-06 | 2019-12-06 | Method for reducing heat treatment residual stress of thick-section titanium alloy forging |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110964996A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112921259A (en) * | 2021-01-28 | 2021-06-08 | 西安泰金工业电化学技术有限公司 | Residual stress eliminating method for titanium part subjected to powerful spinning deformation |
| CN113981348A (en) * | 2021-10-19 | 2022-01-28 | 宝鸡钛业股份有限公司 | Method for reducing residual stress of titanium alloy plate |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB843457A (en) * | 1958-09-22 | 1960-08-04 | Mallory Sharon Metals Corp | High-strength titanium base aluminum-vanadium-iron alloys |
| JP2012251219A (en) * | 2011-06-03 | 2012-12-20 | National Institute For Materials Science | Heat resistant titanium alloy |
| CN103938136A (en) * | 2014-04-08 | 2014-07-23 | 中国航空工业集团公司北京航空材料研究院 | Titanium alloy quasi-recrystallization annealing process |
| CN104694863A (en) * | 2013-12-10 | 2015-06-10 | 陕西宏远航空锻造有限责任公司 | Novel titanium alloy heat treatment method |
| CN106637014A (en) * | 2016-12-07 | 2017-05-10 | 陕西宏远航空锻造有限责任公司 | Heat treatment method for reducing nonuniformity and dimensional instability of large-size TC4 forging |
| US20170321313A1 (en) * | 2013-03-15 | 2017-11-09 | Ati Properties Llc | Thermomechanical processing of alpha-beta titanium alloys |
| CN109722615A (en) * | 2019-01-31 | 2019-05-07 | 中国兵器科学研究院宁波分院 | A kind of heat-treatment technology method of titanium alloy welding component |
-
2019
- 2019-12-06 CN CN201911247993.1A patent/CN110964996A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB843457A (en) * | 1958-09-22 | 1960-08-04 | Mallory Sharon Metals Corp | High-strength titanium base aluminum-vanadium-iron alloys |
| JP2012251219A (en) * | 2011-06-03 | 2012-12-20 | National Institute For Materials Science | Heat resistant titanium alloy |
| US20170321313A1 (en) * | 2013-03-15 | 2017-11-09 | Ati Properties Llc | Thermomechanical processing of alpha-beta titanium alloys |
| CN104694863A (en) * | 2013-12-10 | 2015-06-10 | 陕西宏远航空锻造有限责任公司 | Novel titanium alloy heat treatment method |
| CN103938136A (en) * | 2014-04-08 | 2014-07-23 | 中国航空工业集团公司北京航空材料研究院 | Titanium alloy quasi-recrystallization annealing process |
| CN106637014A (en) * | 2016-12-07 | 2017-05-10 | 陕西宏远航空锻造有限责任公司 | Heat treatment method for reducing nonuniformity and dimensional instability of large-size TC4 forging |
| CN109722615A (en) * | 2019-01-31 | 2019-05-07 | 中国兵器科学研究院宁波分院 | A kind of heat-treatment technology method of titanium alloy welding component |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112921259A (en) * | 2021-01-28 | 2021-06-08 | 西安泰金工业电化学技术有限公司 | Residual stress eliminating method for titanium part subjected to powerful spinning deformation |
| CN113981348A (en) * | 2021-10-19 | 2022-01-28 | 宝鸡钛业股份有限公司 | Method for reducing residual stress of titanium alloy plate |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109454188A (en) | Ti55531 titanium alloy large size bar free forging method | |
| CN110964996A (en) | Method for reducing heat treatment residual stress of thick-section titanium alloy forging | |
| US10822682B2 (en) | Method to prevent abnormal grain growth for beta annealed Ti—6AL—4V forgings | |
| CN104532057A (en) | Ti6242 titanium alloy and preparation method of small-size bar thereof | |
| CN105441845A (en) | Forging technology for abnormal structure of TC18 titanium alloy raw material | |
| CN112122540B (en) | High-temperature alloy ring-shaped piece micro-stress forging process | |
| CN107350406B (en) | The free forging method of TC19 titanium alloy large size bar | |
| CN114042847A (en) | Forging method for improving fracture toughness of TB6 titanium alloy | |
| CN110548827B (en) | Forging method for improving yield of nickel-based corrosion-resistant alloy forging stock | |
| CN114226616A (en) | Isothermal forging method of TB17 titanium alloy | |
| CN107716840B (en) | Production process of ring forging | |
| CN106834642B (en) | Optimized forging process of GH6783 alloy bar | |
| JP2001123257A (en) | Manufacturing method of large forged stock | |
| CN112662974A (en) | Heat treatment method of TC21 alloy forging | |
| CN111001742A (en) | Forging method for improving performance of 7050-T7452 free forge piece | |
| CN105583251B (en) | A kind of forging method of big specification Inconel690 alloy bar materials | |
| CN111842748B (en) | Forging method of low-plasticity steel forging | |
| CN105369022A (en) | Method for carrying out grain refinement on 2Cr12NiMo1W1V forge piece in production process | |
| CN109023185B (en) | Method for refining surface grain of GH80A high-temperature alloy part | |
| CN106040954A (en) | Forging technology of small motor shaft | |
| CN116891955B (en) | Cold working and heat treatment method of Ni-Cr electrothermal alloy hot rolled wire rod | |
| CN110629141A (en) | Heat treatment process for improving mechanical property of GH4220 bolt | |
| CN117324522B (en) | Forging forming method for improving flaw detection level of titanium alloy bar | |
| CN111745114B (en) | GH4163 annular forging piece die forging method | |
| CN114749592B (en) | Method for eliminating 9Cr18 martensitic stainless steel net-shaped carbide |
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: 20200407 |
|
| RJ01 | Rejection of invention patent application after publication |