CN104419812A - Heat treatment method of torsion plate forge piece of heavy duty gas turbine - Google Patents
Heat treatment method of torsion plate forge piece of heavy duty gas turbine Download PDFInfo
- Publication number
- CN104419812A CN104419812A CN201310375978.1A CN201310375978A CN104419812A CN 104419812 A CN104419812 A CN 104419812A CN 201310375978 A CN201310375978 A CN 201310375978A CN 104419812 A CN104419812 A CN 104419812A
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- workpiece
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- torsion plate
- gas turbine
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- 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
-
- 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
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/18—Hardening; Quenching with or without subsequent tempering
Abstract
The invention discloses a heat treatment method of a torsion plate forge piece of a heavy duty gas turbine, which involves heat treatment of a torsion plate forge piece with a diameter not more than 1400 mm, with a thickness of 600+/-10 mm, and made of 26NiCrMoV145MOD. The method comprises the following steps: firstly, performing heat preservation of a workpiece at 250+/-5 DEG C for 4 hours; secondly, heating the workpiece to 650+/-5 DEG C at a heating speed of 50 DEG C/hour, performing heat preservation of the workpiece at 650+/-5 DEG C for 4 hours; thirdly, performing heat preservation of the workpiece at 840+/-5 DEG C for more than 10 hours; fourthly, quenching in cooling water for 100 minutes; fifthly, performing heat preservation of the workpiece at 250+/-5 DEG C for 4 hours; sixthly, heating the workpiece to 600+/-5 DEG C at a heating speed of 50 DEG C/hour, performing heat preservation of the workpiece at 600+/-5 DEG C for 30 hours; seventhly, performing furnace cooling. The method of the invention strictly controls the furnace temperature, the heat preservation time, and the quenching time during heat treatment, and obtains the forge piece meeting the performance requirements for torsion plates.
Description
Technical field
The present invention relates to a kind of heat treating method of forging, be specifically related to a kind of heat treating method of heavy duty gas turbine torsion plate forging.
Background technology
In heavy F level internal combustion turbine, in order to realize being issued to object compared with low thermal stress in compressor delivery temperature high as far as possible, have employed the structure formation that three torsion plates replace tunnel shafts.Working environment due to heavy duty gas turbine is high temperature, has higher requirement to the performance of torsion plate.
Meet the demands for making the performance rate of torsion plate, this heavy duty gas turbine torsion plate forging needs to adopt super clean steel alloy 26NiCrMoV145MOD(chemical composition to ask for an interview to table 1), and require that the intensity of forging meets performance requriements (Fig. 1 is seen in sample position) as shown in table 2.
The requirement of table 1 torsion plate chemical composition
The mechanical property requirements of table 2 torsion plate
But, there is no the precedent that the material torsion plate forging that is 26NiCrMoV145MOD is heat-treated at present.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of heat treating method of heavy duty gas turbine torsion plate forging, and it can obtain the forging of the performance requriements meeting torsion plate.
For solving the problems of the technologies described above, the technical solution of the heat treating method of heavy duty gas turbine torsion plate forging of the present invention is:
Be not more than 1400mm to diameter, thickness is 600 ± 10mm, and material is that the torsion plate forging of 26NiCrMoV145MOD is heat-treated, and comprises the following steps:
The first step, workpiece enters process furnace, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
Second step, makes temperature rise to 650 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 4 hours at the temperature of 650 ± 5 DEG C;
3rd step, heats up with the peak power of process furnace, makes temperature rise to 840 ± 5 DEG C, makes workpiece be incubated more than 10 hours at the temperature of 840 ± 5 DEG C;
4th step, makes workpiece come out of the stove, cooling quenching-in water 100 minutes, until workpiece surface temperature is no more than 30 DEG C;
Workpiece upper and lower vibration in water coolant within first 20 minutes, is made at cooling quenching-in water 100 minutes.
The surface temperature of measuring workpieces after quenching, the surface temperature as workpiece returned temperature to more than 80 DEG C in 30 minutes, then continue cooling quenching-in water 15 minutes.
5th step, again enters process furnace by the workpiece after quenching, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
6th step, makes temperature rise to 600 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 30 hours at the temperature of 600 ± 5 DEG C;
7th step, it is cold to carry out stove.
The cold method of stove is: first make in-furnace temperature be cooled to 500 DEG C with the cooling rate being not more than 8 DEG C/h, be then cooled to 200 DEG C with the cooling rate being not more than 11 DEG C/h, come out of the stove after making workpiece be incubated 9 hours at the temperature of 200 ± 5 DEG C.
The technique effect that the present invention can reach is:
The present invention strictly controls furnace temperature, soaking time and cool time in heat treatment process, can obtain the forging of the performance requriements meeting torsion plate.
Accompanying drawing explanation
Below in conjunction with the drawings and specific embodiments, the present invention is further detailed explanation:
Fig. 1 is the sample position schematic diagram of torsion plate, and wherein T1, T2 are sampling ring;
Fig. 2 is the forging performance thermal treatment temp-time curve of the heat treating method of heavy duty gas turbine torsion plate forging of the present invention.
Embodiment
As shown in Figure 2, the heat treating method of heavy duty gas turbine torsion plate forging of the present invention, is not more than 1400mm to diameter, and thickness is 600 ± 10mm, and material is that the torsion plate forging of 26NiCrMoV145MOD is heat-treated, and comprises the following steps:
The first step, workpiece enters process furnace, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
Second step, makes temperature rise to 650 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 4 hours at the temperature of 650 ± 5 DEG C;
3rd step, heats up with the peak power of process furnace, makes temperature rise to 840 ± 5 DEG C, makes workpiece be incubated more than 10 hours at the temperature of 840 ± 5 DEG C;
4th step, makes workpiece come out of the stove, cooling quenching-in water 100 minutes, until workpiece surface temperature is no more than 30 DEG C;
Within first 20 minutes, make workpiece upper and lower vibration in water coolant;
The surface temperature of measuring workpieces after cold quenching, the surface temperature as workpiece returned temperature to more than 80 DEG C in 30 minutes, then continue cooling quenching-in water 15 minutes;
5th step, again enters process furnace by the workpiece after quenching, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
6th step, makes temperature rise to 600 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 30 hours at the temperature of 600 ± 5 DEG C;
7th step, it is cold to carry out stove;
First make in-furnace temperature be cooled to 500 DEG C with the cooling rate being not more than 8 DEG C/h, be then cooled to 200 DEG C with the cooling rate being not more than 11 DEG C/h, come out of the stove after making workpiece be incubated 9 hours at the temperature of 200 ± 5 DEG C.
The present invention strictly controls furnace temperature, soaking time and cool time in heat treatment process, after employing the present invention heat-treats workpiece, through sampling testpieces product and carrying out analyzing and testing to its performance, draw detected result as shown in table 3, the performance of this result display forging meets torsion plate performance requriements as shown in table 2.
The actual machine performance of table 3 torsion plate testpieces
The present invention, according to super clean alloy material fundamental characteristics and transformation temperature Ac1, Ac3, in conjunction with the specified property requirement of torsion plate, heat-treats torsion plate forging.
Claims (4)
1. a heat treating method for heavy duty gas turbine torsion plate forging, is characterized in that, is not more than 1400mm to diameter, and thickness is 600 ± 10mm, and material is that the torsion plate forging of 26NiCrMoV145MOD is heat-treated, and comprises the following steps:
The first step, workpiece enters process furnace, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
Second step, makes temperature rise to 650 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 4 hours at the temperature of 650 ± 5 DEG C;
3rd step, heats up with the peak power of process furnace, makes temperature rise to 840 ± 5 DEG C, makes workpiece be incubated more than 10 hours at the temperature of 840 ± 5 DEG C;
4th step, makes workpiece come out of the stove, cooling quenching-in water 100 minutes, until workpiece surface temperature is no more than 30 DEG C;
5th step, again enters process furnace by the workpiece after quenching, makes workpiece be incubated 4 hours at the temperature of 250 ± 5 DEG C;
6th step, makes temperature rise to 600 ± 5 DEG C with the heat-up rate of 50 DEG C/h, makes workpiece be incubated 30 hours at the temperature of 600 ± 5 DEG C;
7th step, it is cold to carry out stove.
2. the heat treating method of heavy duty gas turbine torsion plate forging according to claim 1, is characterized in that, within first 20 minutes, makes workpiece upper and lower vibration in water coolant at cooling quenching-in water 100 minutes in described 4th step.
3. the heat treating method of heavy duty gas turbine torsion plate forging according to claim 1, it is characterized in that, the surface temperature of measuring workpieces after quenching in described 4th step, the surface temperature as workpiece returned temperature to more than 80 DEG C in 30 minutes, then continue cooling quenching-in water 15 minutes.
4. the heat treating method of heavy duty gas turbine torsion plate forging according to claim 1, it is characterized in that, the cold method of described 7th step stove is: first make in-furnace temperature be cooled to 500 DEG C with the cooling rate being not more than 8 DEG C/h, then be cooled to 200 DEG C with the cooling rate being not more than 11 DEG C/h, come out of the stove after making workpiece be incubated 9 hours at the temperature of 200 ± 5 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310375978.1A CN104419812B (en) | 2013-08-26 | The heat treatment method of heavy duty gas turbine torsion plate forging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310375978.1A CN104419812B (en) | 2013-08-26 | The heat treatment method of heavy duty gas turbine torsion plate forging |
Publications (2)
| Publication Number | Publication Date |
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| CN104419812A true CN104419812A (en) | 2015-03-18 |
| CN104419812B CN104419812B (en) | 2016-11-30 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107739791A (en) * | 2017-11-02 | 2018-02-27 | 山东上汽汽车变速器有限公司 | A kind of flitch, bin and workpiece arrangement method for being used for heat treatment and high pressure gas quenching |
| CN111394561A (en) * | 2020-03-26 | 2020-07-10 | 杭州汽轮铸锻有限公司 | Heat treatment process method for high-strength large-section rotor of industrial steam turbine through block forging |
Citations (4)
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| JP2000319749A (en) * | 1999-05-06 | 2000-11-21 | Kobe Steel Ltd | NiCrMoV STEEL AND CAST FORGED STEEL MEMBER USING THE NiCrMoV STEEL |
| US20100003162A1 (en) * | 2006-05-29 | 2010-01-07 | Wolfgang Arrenbrecht | Method for the Production of Forged Steel for Weapons Subject to Heavy Stresses, Barrel Blanks and Thus-Equipped Weapon |
| CN102234744A (en) * | 2010-04-23 | 2011-11-09 | 宝山钢铁股份有限公司 | Ultra-pure alloy and method for manufacturing turbine rotor forging by using same |
| CN102643975A (en) * | 2012-04-23 | 2012-08-22 | 马钢(集团)控股有限公司 | Heat treatment method for grain refinement of NiCrMoV steel forging piece |
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000319749A (en) * | 1999-05-06 | 2000-11-21 | Kobe Steel Ltd | NiCrMoV STEEL AND CAST FORGED STEEL MEMBER USING THE NiCrMoV STEEL |
| US20100003162A1 (en) * | 2006-05-29 | 2010-01-07 | Wolfgang Arrenbrecht | Method for the Production of Forged Steel for Weapons Subject to Heavy Stresses, Barrel Blanks and Thus-Equipped Weapon |
| CN102234744A (en) * | 2010-04-23 | 2011-11-09 | 宝山钢铁股份有限公司 | Ultra-pure alloy and method for manufacturing turbine rotor forging by using same |
| CN102643975A (en) * | 2012-04-23 | 2012-08-22 | 马钢(集团)控股有限公司 | Heat treatment method for grain refinement of NiCrMoV steel forging piece |
Non-Patent Citations (4)
| Title |
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| MASOUD MIRZAEE等: "Dynamic recrystallization and precipitation in low carbon low alloy steel 26NiCrMoV 14-5", 《MATERIALS SCIENCE AND ENGINEERING A》 * |
| 云红等: "40CrNi2MoA钢大锻件的调质热处理", 《金属热处理》 * |
| 康大涛等: "《大型锻件材料及热处理》", 30 April 1998, 北京：龙门书局出版 * |
| 李瑞彬主编: "《典型机械零件热处理》", 30 November 2005, 北京：兵器工业出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107739791A (en) * | 2017-11-02 | 2018-02-27 | 山东上汽汽车变速器有限公司 | A kind of flitch, bin and workpiece arrangement method for being used for heat treatment and high pressure gas quenching |
| CN107739791B (en) * | 2017-11-02 | 2019-02-01 | 山东上汽汽车变速器有限公司 | A kind of flitch, material frame and workpiece arrangement method for heat treatment |
| CN111394561A (en) * | 2020-03-26 | 2020-07-10 | 杭州汽轮铸锻有限公司 | Heat treatment process method for high-strength large-section rotor of industrial steam turbine through block forging |
| CN111394561B (en) * | 2020-03-26 | 2022-02-11 | 杭州汽轮铸锻有限公司 | Heat treatment process method for high-strength large-section rotor of industrial steam turbine through block forging |
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Effective date of registration: 20161130 Address after: 200245 Jiangchuan Road, Shanghai, No. 207, building 1800, No. Patentee after: Shanghai Electric Heavy Forging Co. Ltd. Patentee after: Shanghai Heavy Machines Plant Co., Ltd. Address before: 200245 Jiangchuan Road, Shanghai, No. 1800, No. Patentee before: Shanghai Heavy Machines Plant Co., Ltd. |