CN111850458A - Boronizing process for supercritical and above turbine annular nozzle - Google Patents
Boronizing process for supercritical and above turbine annular nozzle Download PDFInfo
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- 238000005271 boronizing Methods 0.000 title claims abstract description 92
- 238000000034 method Methods 0.000 title claims abstract description 32
- 230000008569 process Effects 0.000 title claims abstract description 30
- 239000000463 material Substances 0.000 claims abstract description 10
- 238000004140 cleaning Methods 0.000 claims abstract description 9
- 238000005496 tempering Methods 0.000 claims abstract description 8
- 230000008595 infiltration Effects 0.000 claims abstract description 5
- 238000001764 infiltration Methods 0.000 claims abstract description 5
- 238000007781 pre-processing Methods 0.000 claims abstract description 5
- 238000001816 cooling Methods 0.000 claims description 18
- 238000010438 heat treatment Methods 0.000 claims description 17
- 238000007599 discharging Methods 0.000 claims description 10
- 230000032683 aging Effects 0.000 claims description 6
- 238000007689 inspection Methods 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 abstract description 23
- 230000007547 defect Effects 0.000 abstract description 3
- 238000009792 diffusion process Methods 0.000 abstract description 3
- 239000011248 coating agent Substances 0.000 abstract description 2
- 238000000576 coating method Methods 0.000 abstract description 2
- 239000011159 matrix material Substances 0.000 abstract description 2
- 230000035882 stress Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 2
- 238000004321 preservation Methods 0.000 description 2
- 238000001878 scanning electron micrograph Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910001563 bainite Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 229910001105 martensitic stainless steel Inorganic materials 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C8/60—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using solids, e.g. powders, pastes
- C23C8/62—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using solids, e.g. powders, pastes only one element being applied
- C23C8/68—Boronising
- C23C8/70—Boronising of ferrous surfaces
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
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- C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C8/02—Pretreatment of the material to be coated
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C8/80—After-treatment
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Abstract
A boronizing process for an annular nozzle of a supercritical or above steam turbine relates to a boronizing process. The invention aims to solve the problems of insufficient carburized layer and cracks and deformation after the existing supercritical and above turbine annular nozzle is subjected to boronization. The method comprises the following steps: firstly, preprocessing; secondly, charging; thirdly, boronizing; fourthly, tempering after infiltration; and fifthly, cleaning the boronizing agent to finish the boronizing process of the supercritical and above annular nozzle of the steam turbine. The boronizing process of the supercritical and above turbine annular nozzle can successfully enable the matrix material to be 1Cr9Mo1VNbN material to realize boronizing and layer coating meeting the standard requirements and deformation control, and the boronizing agent on the surface of the boronizing nozzle has no defects of obvious adhesion, no cracks, no peeling and the like; the depth (including a diffusion zone) of the boronized layer is not less than 0.06mm, the hardness of the boronized layer is not less than HV1000, and the boronized layer has no micro-cracks; the deformation is controlled within 0.10 mm.
Description
Technical Field
The invention relates to a boronizing process.
Background
The steam inlet temperature of a nozzle of a steam turbine in a supercritical state or above is generally over 566 ℃, the supercritical state can be over 600 ℃, the nozzle part bears a high-temperature and high-pressure steam environment, the selected material is an improved 12% Cr martensitic stainless steel 1Cr9Mo1VNbN material with high-temperature resistance and high strength, the alloy components are complex, and the structure transformation mechanism needs to be deeply researched. In addition, the previous deep experimental research and related reports on the boriding of supercritical and above turbine nozzles do not exist in China, the existing process cannot meet the current boriding requirement, the inner and outer rings of the nozzle belong to thin-walled parts, the deformation of the nozzle after high temperature is not easy to control, and the quality problems of insufficient thickness of a boriding layer, fine cracks vertical to a base body from inside to outside, large deformation of the nozzle caused by high-temperature boriding and the like often occur after the nozzle boriding due to various difficulties, so that the requirements of installation and later-period safe operation of the turbine are influenced.
Disclosure of Invention
The invention aims to solve the problems of insufficient boronizing layer and cracks and deformation after the existing annular nozzle of a supercritical or above steam turbine is boronized, and provides a boronizing process of the annular nozzle of the supercritical or above steam turbine.
A boronizing process for an annular nozzle of a supercritical or above steam turbine is completed according to the following steps:
firstly, preprocessing:
firstly, checking the roughness of the surface of a boronizing area of an annular nozzle of a supercritical or above steam turbine to ensure that the roughness is not higher than Ra6.3;
the natural aging time of the supercritical and above turbine annular nozzle is not less than 48h before boronizing;
secondly, charging:
firstly, putting a boronizing agent into a boronizing tank, then embedding an annular nozzle of a turbine with a supercritical state or above into the boronizing agent, and finally putting the boronizing tank into a furnace;
thirdly, boronizing:
firstly, heating the furnace from room temperature to 735-755 ℃, preserving heat for 2-4 h at 735-755 ℃, then heating the furnace from 735-755 ℃ to 990-1010 ℃, preserving heat for 8-12 h at 990-1010 ℃, finally cooling to 750-800 ℃ along with the furnace, discharging from the furnace and air cooling to room temperature to obtain the supercritical and above turbine annular nozzle after boronization;
fourthly, tempering after infiltration:
firstly, loading the boronized supercritical and above turbine annular nozzle into a furnace again, then heating the furnace from room temperature to 690-710 ℃, then preserving heat at the temperature of 690-710 ℃ for 4-6 h, finally discharging from the furnace and air cooling to room temperature to obtain the tempered supercritical and above turbine annular nozzle;
fifthly, cleaning the boronizing agent:
cleaning the boronizing agent on the tempered supercritical and above turbine annular nozzle, and then carrying out deformation inspection on the body of the boronized supercritical and above turbine annular nozzle, thus completing the boronizing process of the supercritical and above turbine annular nozzle.
The principle and the advantages of the invention are as follows:
the boronizing process of the supercritical and above turbine annular nozzle of the invention can reduce the occurrence of FeB phase with larger thermal expansion coefficient (the expansion coefficient is 8.4 multiplied by 10) to the maximum extent-8K-1Expansion coefficient of 5.7X 10 greater than that of steel-8K-1) The occurrence of large deformation after the boronizing of the annular nozzle is reduced;
secondly, the roughness of the surface of the boronized area of the annular nozzle of the supercritical and above steam turbine is not higher than Ra6.3, and the thickness of a boronized layer can meet the standard requirement; under the condition that the roughness is larger than Ra6.3, even if the boronizing time is increased, the boronizing depth required by the standard is difficult to reach, and the risk of coarse crystals and reduced mechanical property of the body substrate is easily caused by increasing the boronizing time;
thirdly, the boronizing process of the supercritical and above annular nozzle of the steam turbine can obtain a crack-free boronized layer meeting the thickness requirement, and the mechanical property of the body base material still meets the standard requirement;
the invention adopts a natural aging mode, namely the natural aging time of the supercritical and above turbine annular nozzle is not less than 48 hours before boronizing to release the mechanical residual stress (but not enough to completely eliminate the residual stress), and the preheating process is increased in the heating process, the temperature is kept at 735-755 ℃ for 2-4 hours, so as to eliminate the residual machining stress and reduce the action of thermal stress; martensite and bainite with small phase change structure change are obtained by adopting a mode of keeping the temperature of 990-1010 ℃ for 8-12 h, then cooling the furnace to 750-800 ℃ and then discharging the furnace for air cooling, and the deformation of a workpiece caused by the structure stress can be effectively reduced;
the boronizing process of the supercritical and above turbine annular nozzle can successfully enable the matrix material to be 1Cr9Mo1VNbN material to realize boronizing and layer coating meeting the standard requirements and deformation control, and the boronizing agent on the surface of the boronizing nozzle has no defects of obvious adhesion, no cracks, no peeling and the like; the depth (including a diffusion zone) of the boronized layer is not less than 0.06mm, the hardness of the boronized layer is not less than HV1000, and the boronized layer has no micro-cracks; the deformation is controlled within 0.10 mm.
Drawings
FIG. 1 is an SEM image of the surface of a boronized supercritical and above turbine annular nozzle obtained in the fifth step of the example at a magnification of 500.
Detailed Description
The first embodiment is as follows: the boronizing process of the supercritical and above annular nozzle of the steam turbine is completed according to the following steps:
firstly, preprocessing:
firstly, checking the roughness of the surface of a boronizing area of an annular nozzle of a supercritical or above steam turbine to ensure that the roughness is not higher than Ra6.3;
the natural aging time of the supercritical and above turbine annular nozzle is not less than 48h before boronizing;
secondly, charging:
firstly, putting a boronizing agent into a boronizing tank, then embedding an annular nozzle of a turbine with a supercritical state or above into the boronizing agent, and finally putting the boronizing tank into a furnace;
thirdly, boronizing:
firstly, heating the furnace from room temperature to 735-755 ℃, preserving heat for 2-4 h at 735-755 ℃, then heating the furnace from 735-755 ℃ to 990-1010 ℃, preserving heat for 8-12 h at 990-1010 ℃, finally cooling to 750-800 ℃ along with the furnace, discharging from the furnace and air cooling to room temperature to obtain the supercritical and above turbine annular nozzle after boronization;
fourthly, tempering after infiltration:
firstly, loading the boronized supercritical and above turbine annular nozzle into a furnace again, then heating the furnace from room temperature to 690-710 ℃, then preserving heat at the temperature of 690-710 ℃ for 4-6 h, finally discharging from the furnace and air cooling to room temperature to obtain the tempered supercritical and above turbine annular nozzle;
fifthly, cleaning the boronizing agent:
cleaning the boronizing agent on the tempered supercritical and above turbine annular nozzle, and then carrying out deformation inspection on the body of the boronized supercritical and above turbine annular nozzle, thus completing the boronizing process of the supercritical and above turbine annular nozzle.
The second embodiment is as follows: the present embodiment differs from the present embodiment in that: and the boronizing agent in the second step is HX104B boronizing agent or KMB101 granular boronizing agent. Other steps are the same as in the first embodiment.
In this embodiment, HX104B was purchased from New thermal processing materials works, Anqiu, and KMB101 granular boronizing agent was purchased from academy of sciences, Shandong province.
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that: in the third step, the furnace is firstly heated to 735-745 ℃ from the room temperature, the heat preservation is carried out for 2-3 h at 735-745 ℃, then the furnace is heated to 990-1000 ℃ from 735-745 ℃, the heat preservation is carried out for 8-10 h at 990-1000 ℃, finally the furnace is cooled to 750-780 ℃ along with the furnace, the furnace is taken out and air-cooled to the room temperature, and the supercritical and above turbine annular nozzle after boronization is obtained. The other steps are the same as in the first or second embodiment.
The fourth concrete implementation mode: the difference between this embodiment and one of the first to third embodiments is as follows: in the third step, the furnace is firstly heated to 745-755 ℃ from the room temperature, the temperature is preserved for 3-4 h at 745-755 ℃, then the furnace is heated to 1000-1010 ℃ from 745-755 ℃, the temperature is preserved for 10-12 h at 1000-1010 ℃, finally the furnace is cooled to 780-800 ℃ along with the furnace, and the furnace is taken out and air-cooled to the room temperature, thus obtaining the supercritical and above turbine annular nozzle after boronization. The other steps are the same as those in the first to third embodiments.
The fifth concrete implementation mode: the difference between this embodiment and one of the first to fourth embodiments is: in the third step, the furnace is firstly heated to 745 ℃ from the room temperature, the temperature is kept for 3h at 745 ℃, then the furnace is heated to 1000 ℃ from 745 ℃, the temperature is kept for 10h at 1000 ℃, finally the furnace is cooled to 800 ℃ along with the furnace, and the furnace is taken out and air-cooled to the room temperature, so that the supercritical and above turbine annular nozzle after boronization is obtained. The other steps are the same as those in the first to fourth embodiments.
The sixth specific implementation mode: the difference between this embodiment and one of the first to fifth embodiments is as follows: and step four, firstly, the supercritical and above turbine annular nozzle after boronizing is loaded into the furnace again, then the furnace is heated to 690-700 ℃, then the temperature is kept at 690-700 ℃ for 4-5 h, and finally the nozzle is taken out of the furnace and cooled to room temperature in an air cooling mode, so that the supercritical and above turbine annular nozzle after tempering is obtained. The other steps are the same as those in the first to fifth embodiments.
The seventh embodiment: the difference between this embodiment and one of the first to sixth embodiments is: and step four, firstly, the supercritical and above turbine annular nozzle after boronizing is loaded into the furnace again, then the furnace is heated to 700-710 ℃, the temperature is kept at 700-710 ℃ for 5-6 h, and finally the annular nozzle is taken out of the furnace and cooled to room temperature in an air cooling mode, so that the supercritical and above turbine annular nozzle after tempering is obtained. The other steps are the same as those in the first to sixth embodiments.
The specific implementation mode is eight: the difference between this embodiment and one of the first to seventh embodiments is: and step four, firstly, putting the boronized supercritical and above turbine annular nozzle into the furnace again, then heating the furnace to 700 ℃, preserving the heat for 5 hours at 700 ℃, finally discharging the furnace and air-cooling to room temperature to obtain the tempered supercritical and above turbine annular nozzle. The other steps are the same as those in the first to seventh embodiments.
The specific implementation method nine: the difference between this embodiment and the first to eighth embodiments is: the material of the supercritical and above turbine annular nozzle in the first step is 1Cr9Mo1VNbN, and the mass fraction of Cr is 12%. The other steps are the same as those in the first to eighth embodiments.
The detailed implementation mode is ten: the difference between this embodiment and one of the first to ninth embodiments is as follows: the heating rates in the third step and the fourth step are both less than or equal to 120 ℃/h. The other steps are the same as those in the first to ninth embodiments.
The following examples were used to demonstrate the beneficial effects of the present invention:
the first embodiment is as follows: a boronizing process for an annular nozzle of a supercritical or above steam turbine is completed according to the following steps:
firstly, preprocessing:
firstly, checking the roughness of the surface of a boronizing area of an annular nozzle of a supercritical or above steam turbine to ensure that the roughness is not higher than Ra6.3;
the material of the supercritical and above turbine annular nozzle in the first step is 1Cr9Mo1VNbN, and the mass fraction of Cr is 12%;
the natural aging time of the supercritical and above turbine annular nozzle is not less than 48h before boronizing;
secondly, charging:
firstly, putting a boronizing agent into a boronizing tank, then embedding an annular nozzle of a turbine with a supercritical state or above into the boronizing agent, and finally putting the boronizing tank into a furnace;
the boronizing agent in the second step is HX104B boronizing agent, and the model number of HX104B boronizing agent purchased from Hua Xin Heat treatment Material works in Anqiu city is HX 104B;
thirdly, boronizing:
firstly, heating the furnace from room temperature to 745 ℃, preserving heat for 3h at 745 ℃, then heating the furnace from 745 ℃ to 1000 ℃, preserving heat for 10h at 1000 ℃, finally cooling to 800 ℃ along with the furnace, discharging from the furnace and air cooling to room temperature to obtain the boronized supercritical and above turbine annular nozzle;
the heating rate of the step three is 60 ℃/h;
fourthly, tempering after infiltration:
firstly, loading the turbine annular nozzle subjected to boronizing into a furnace again, then heating the furnace from room temperature to 700 ℃, then preserving heat for 5 hours at 700 ℃, finally discharging from the furnace and air-cooling to room temperature to obtain the turbine annular nozzle subjected to tempering;
fifthly, cleaning the boronizing agent:
cleaning the boronizing agent on the tempered supercritical and above turbine annular nozzle, and then carrying out deformation inspection on the body of the boronized supercritical and above turbine annular nozzle, thus completing the boronizing process of the supercritical and above turbine annular nozzle.
The surface boronizing agent of the supercritical and above turbine annular nozzle obtained in the fifth step of the embodiment has no obvious defects of adhesion, cracks, peeling and the like; the depth (including a diffusion area) of the boronized layer is 0.06 mm-0.09 mm, the hardness of the boronized layer is HV 1150-HV 1250, and the boronized layer has no micro-cracks; the deformation is 0.07 mm-0.09 mm.
FIG. 1 is an SEM image of the surface of a boronized supercritical and above turbine annular nozzle obtained in the fifth step of the example at a magnification of 500.
Claims (10)
1. The boronizing process for the supercritical and above annular nozzle of the steam turbine is characterized by being completed according to the following steps:
firstly, preprocessing:
firstly, checking the roughness of the surface of a boronizing area of an annular nozzle of a supercritical or above steam turbine to ensure that the roughness is not higher than Ra6.3;
the natural aging time of the supercritical and above turbine annular nozzle is not less than 48h before boronizing;
secondly, charging:
firstly, putting a boronizing agent into a boronizing tank, then embedding an annular nozzle of a turbine with a supercritical state or above into the boronizing agent, and finally putting the boronizing tank into a furnace;
thirdly, boronizing:
firstly, heating the furnace from room temperature to 735-755 ℃, preserving heat for 2-4 h at 735-755 ℃, then heating the furnace from 735-755 ℃ to 990-1010 ℃, preserving heat for 8-12 h at 990-1010 ℃, finally cooling to 750-800 ℃ along with the furnace, discharging from the furnace and air cooling to room temperature to obtain the supercritical and above turbine annular nozzle after boronization;
fourthly, tempering after infiltration:
firstly, loading the boronized supercritical and above turbine annular nozzle into a furnace again, then heating the furnace from room temperature to 690-710 ℃, then preserving heat at the temperature of 690-710 ℃ for 4-6 h, finally discharging from the furnace and air cooling to room temperature to obtain the tempered supercritical and above turbine annular nozzle;
fifthly, cleaning the boronizing agent:
cleaning the boronizing agent on the tempered supercritical and above turbine annular nozzle, and then carrying out deformation inspection on the body of the boronized supercritical and above turbine annular nozzle, thus completing the boronizing process of the supercritical and above turbine annular nozzle.
2. The boronizing process of a supercritical and above turbine annular nozzle according to claim 1, wherein in step two the boronizing agent is HX104B boronizing agent or KMB101 granular boronizing agent.
3. The boronizing process of supercritical and above turbine annular nozzle as claimed in claim 1, wherein the third step is to heat the furnace from room temperature to 735-745 ℃, keep the temperature at 735-745 ℃ for 2-3 h, then heat the furnace from 735-745 ℃ to 990-1000 ℃, keep the temperature at 990-1000 ℃ for 8-10 h, finally cool to 750-780 ℃ with the furnace, take out of the furnace and air cool to room temperature, to obtain the boronized supercritical and above turbine annular nozzle.
4. The boronizing process of supercritical and above turbine annular nozzle according to claim 1, characterized in that the third step is to heat the furnace from room temperature to 745-755 ℃, keep the temperature at 745-755 ℃ for 3 h-4 h, then heat the furnace from 745-755 ℃ to 1000-1010 ℃, keep the temperature at 1000-1010 ℃ for 10 h-12 h, finally cool to 780-800 ℃ with the furnace, take out of the furnace and air cool to room temperature, to obtain the boronized supercritical and above turbine annular nozzle.
5. The boronizing process of a supercritical and above turbine annular nozzle according to claim 1, characterized in that the furnace is first heated from room temperature to 745 ℃ and kept at 745 ℃ for 3 hours, then heated from 745 ℃ to 1000 ℃ and kept at 1000 ℃ for 10 hours, finally cooled to 800 ℃ with the furnace, taken out of the furnace and cooled to room temperature in air, so as to obtain the boronized supercritical and above turbine annular nozzle.
6. The boronizing process of the supercritical and above turbine annular nozzle according to claim 1, characterized in that the boronized supercritical and above turbine annular nozzle is first loaded into the furnace again, then the furnace is heated to 690 ℃ -700 ℃, then the temperature is kept at 690 ℃ -700 ℃ for 4 h-5 h, finally the furnace is taken out and air-cooled to room temperature, and the tempered supercritical and above turbine annular nozzle is obtained.
7. The boronizing process of the supercritical and above turbine annular nozzle according to claim 1, characterized in that the boronized supercritical and above turbine annular nozzle is firstly loaded into the furnace again, then the furnace is heated to 700 ℃ -710 ℃, and then the temperature is kept at 700 ℃ -710 ℃ for 5 h-6 h, finally the furnace is taken out and air-cooled to room temperature, and the tempered supercritical and above turbine annular nozzle is obtained.
8. The boronizing process of the supercritical and above turbine annular nozzle according to claim 1, wherein the boronized supercritical and above turbine annular nozzle is first loaded into the furnace again, then the furnace is heated to 700 ℃, and then kept at 700 ℃ for 5 hours, and finally discharged from the furnace and cooled to room temperature in an air cooling manner, so as to obtain the tempered supercritical and above turbine annular nozzle.
9. The boronizing process for the supercritical and above turbine annular nozzle according to claim 1, wherein the material of the supercritical and above turbine annular nozzle in the first step is 1Cr9Mo1VNbN, and the mass fraction of Cr is 12%.
10. The boronizing process of a turbine annular nozzle of the supercritical and above turbine as claimed in claim 9, wherein the rate of temperature rise in both step three and step four is less than or equal to 120 ℃/h.
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| CN114774842A (en) * | 2022-04-13 | 2022-07-22 | 华南理工大学 | Preparation of single-phase Fe2B-diffusion layer method and application thereof |
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| CN1772944A (en) * | 2005-10-08 | 2006-05-17 | 上海汽轮机有限公司 | Boronizing treatment and heat treatment process of martensitic stainless steel for steam turbine nozzle set |
| CN101265564A (en) * | 2007-12-26 | 2008-09-17 | 上海电气电站设备有限公司 | High-heat strong performance martensitic stainless steel boriding and performance combined treatment process |
| CN104805398A (en) * | 2015-03-23 | 2015-07-29 | 哈尔滨汽轮机厂有限责任公司 | Method for reducing boronizing deformation of nozzle set for steam turbine |
| CN106939403A (en) * | 2017-02-14 | 2017-07-11 | 哈尔滨汽轮机厂有限责任公司 | The method of 1Cr9Mo1VNbN material nozzle of steam turbine boronisings |
| CN109468579A (en) * | 2018-11-29 | 2019-03-15 | 杨浩鹏 | A kind of mold targeting surface treatment method and boriding medium based on vacuum heat treatment |
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| CN114774842A (en) * | 2022-04-13 | 2022-07-22 | 华南理工大学 | Preparation of single-phase Fe2B-diffusion layer method and application thereof |
| CN114774842B (en) * | 2022-04-13 | 2023-06-20 | 华南理工大学 | Preparation of single-phase Fe 2 B-penetrating layer method and application thereof |
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