CN113699347B - Anti-recrystallization method for turbine blade after service in repair process - Google Patents
Anti-recrystallization method for turbine blade after service in repair process Download PDFInfo
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- CN113699347B CN113699347B CN202111060609.4A CN202111060609A CN113699347B CN 113699347 B CN113699347 B CN 113699347B CN 202111060609 A CN202111060609 A CN 202111060609A CN 113699347 B CN113699347 B CN 113699347B
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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
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- C—CHEMISTRY; METALLURGY
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
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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
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Abstract
The invention belongs to the technical field of turbine blade repair treatment, and provides a recrystallization resistance method in a post-service turbine blade repair process. The recrystallization behavior of the turbine blade after service in the repair process is mainly that after the alloy is subjected to high-temperature high-load service, the alloy structure is degraded, and a large amount of dislocation structures generated by high-temperature creep are also stored in the alloy structure. When the turbine blade is subjected to a recovery heat treatment process with the temperature higher than the recrystallization temperature after service, dislocation is rearranged to form a large-angle grain boundary, and the large-angle grain boundary is rapidly migrated to finally form recrystallized grains. According to the invention, one-step recrystallization-preventing heat treatment is carried out before solid solution treatment, so that a large amount of dislocation existing in the alloy is pre-recovered, and the dislocation density is reduced, thereby inhibiting the generation of recrystallization in the subsequent heat treatment process of the alloy.
Description
Technical Field
The invention relates to the technical field of turbine blade repair treatment, in particular to a recrystallization resisting method in a post-service turbine blade repair process.
Background
With the development of aircraft engines, the requirements for thrust-weight ratio and pre-turbine temperature of aircraft engines are increasing. The temperature before the turbine of the aircraft engine is also increased from 1655K to above 2000K from the third generation to the fifth generation. Turbine blades in aircraft engines are also required to operate stably for long periods of time under such high temperature and pressure and high temperature gas corrosion conditions, resulting in very severe service environments. On the basis, the innovation of turbine blade materials and related preparation processes is inevitable, and the control of the periodic repair technology after the service of the advanced air cooling blade is also of great significance to the aircraft engine.
Under the thermal coupling effect generated by a high-temperature load environment in the service process of the turbine blade, the structure is degraded and the performance is reduced, so that the service life is reduced, and through the repairing and recovering heat treatment process of the turbine blade, the coarsened, raft-arranged and redissolved gamma' phase and other precipitated second phases are redissolved and then are redissolved, so that the turbine blade structure is recovered, namely the repairing and recovering heat treatment of the turbine blade.
Dennison and B.Wilshire et al (Dennison J P, Wilshire B.In: Taplin D M R ed., Fracter 1977, Proc 4th Int Conf on Fracter, Wateloo: University of Wateloo Press,1977:635) have suggested a mechanism for improving the creep life of alloys by heat treatment through studies on Nimonic 80A and Nimonic105 alloys, indicating that substantial recovery of creep performance can be achieved by using appropriate heat treatment cycles. Girdwood and Evans et al (R.B.Girdwood, R.W.Evans, Recovery of creep properties soft-base super alloy Nimonic105, int.J.Pres.Ves.pip.66(1996)141-153) have discovered that complete resolubilization heat treatment can repair creep-damaged tissue by studying the creep behavior of Nimonic 105. Turbine blades used in modern advanced aircraft engines generally have higher temperature capability, and if the turbine blade tissues after service are repaired by recovery heat treatment, higher temperature is needed to dissolve the coarsened gamma prime phase back, and the recrystallization temperature is exceeded for most turbine blades after service. Therefore, when a turbine blade in service is repaired directly by a general recovery heat treatment, it is highly likely that recrystallization defects will form on the turbine blade, thereby significantly affecting the in-service performance of the turbine blade.
Disclosure of Invention
In view of the above, the present invention is directed to a method of resisting recrystallization during a post-service turbine blade repair. The recrystallization-resistant method provided by the invention can avoid the defect of recrystallization and obviously improve the service performance of the turbine blade.
In order to achieve the above object, the present invention provides the following technical solutions:
the invention provides a recrystallization resistance method in a post-service turbine blade repairing process, which comprises the following steps:
sequentially carrying out anti-recrystallization heat treatment, solution treatment and aging treatment on the turbine blade after service;
the recrystallization-preventing heat treatment process comprises the following steps:
carrying out first heat preservation after first temperature rise to a first heat treatment temperature, and carrying out at least one time of temperature rise after the first heat preservation until the last stage of heat treatment;
the first heat treatment temperature is [ (T)s-150)～(Ts-50)]DEG C; the T issThe initial redissolution temperature of the gamma' phase of the turbine blade which is not in service;
in the process of the recrystallization-preventing heat treatment, the temperature delta T of each temperature rise is independently 10-15 ℃ except for the first temperature rise;
(Tf-40- Δ T) ° c < temperature of the end-stage heat treatment < (T)f-40) deg.C; the T isfIs the complete re-dissolution temperature of the gamma' phase of the turbine blade which is not in service.
Preferably, the after-service turbine blades include over-temperature after-service turbine blades or creep after-service turbine blades.
Preferably, when the turbine blade after service is the turbine blade after over-temperature service, the structural stress removing treatment is further performed before the anti-crystallization treatment; the structural stress removal treatment comprises: and heating the turbine blade after service to 900 +/-20 ℃, and preserving the heat for 2-4 hours.
Preferably, where the in-service turbine blade is an in-service creep turbine blade, the method of resisting recrystallization during the in-service creep turbine blade repair is performed after the first or second stage of turbine blade creep.
Preferably, in the anti-recrystallization heat treatment process, the time of each heat preservation is independently 20 min-120 min.
Preferably, in the process of the recrystallization-preventing heat treatment, after heat preservation each time, the temperature is respectively reduced to 1100-1150 ℃.
Preferably, in the process of the recrystallization-preventing heat treatment, the rate of each temperature rise is independently 3-15 ℃/min.
Preferably, the material of the in-service turbine blade comprises a nickel-based single crystal alloy or a directional solidification alloy.
Preferably, the temperature of the solution treatment is not lower than the complete re-dissolving temperature of the gamma' phase of the non-service turbine blade and not higher than the initial melting point temperature of the non-service turbine blade; and the heat preservation time of the solution treatment is 3-5 h.
Preferably, the aging treatment comprises sequentially performing high-temperature aging treatment and low-temperature aging treatment; the temperature of the high-temperature aging treatment is 1100 +/-20 ℃, and the heat preservation time is 1-3 h; the temperature of the low-temperature aging treatment is 870 +/-20 ℃, and the heat preservation time is 15-25 h.
The invention provides a recrystallization resistance method in a post-service turbine blade repairing process, which comprises the following steps: sequentially carrying out anti-recrystallization heat treatment, solution treatment and aging treatment on the turbine blade after service; the recrystallization-preventing heat treatment process comprises the following steps: carrying out first heat preservation after first temperature rise to a first heat treatment temperature, and carrying out at least one time of temperature rise after the first heat preservation until the last stage of heat treatment; the first heat treatment temperature is [ (T)s-150)～(Ts-50)]DEG C; the T issThe initial redissolution temperature of the gamma' phase of the turbine blade which is not in service; in the process of the recrystallization-preventing heat treatment, the temperature delta T of each temperature rise is independently 10-15 ℃ except for the first temperature rise; (T)f-40- Δ T) ° c < temperature of the end-stage heat treatment < (T)f-40) deg.C; the T isfIs the complete re-dissolution temperature of the gamma' phase of the turbine blade which is not in service. The recrystallization behavior of the turbine blade after service in the repair process is mainly because the alloy tissue is degraded after the alloy is subjected to high-temperature high-load service, and a large amount of dislocation tissues generated by high-temperature creep are also stored in the alloy tissue. When the turbine blade is subjected to a recovery heat treatment process with the temperature higher than the recrystallization temperature after service, dislocation is rearranged to form a large-angle grain boundary, and the large-angle grain boundary rapidly migrates to finally form recrystallized grainsAnd (4) granulating. According to the invention, one-step recrystallization-preventing heat treatment is carried out before solid solution treatment, so that a large amount of dislocation existing in the alloy is pre-recovered, and the dislocation density is reduced, thereby inhibiting the generation of recrystallization in the subsequent heat treatment process of the alloy.
Drawings
FIG. 1 is a prior art thermal treatment microstructure of a turbine guide vane of example 1 before service;
FIG. 2 is a structural diagram of a heat-treated state of a turbine guide vane in example 1 after being in over-temperature service;
FIG. 3 is a heat-treated structure of an overtemperature service turbine guide blade after anti-recrystallization repair;
FIG. 4 is a graph of creep performance of an original structure of a turbine rotor blade before service and a creep service turbine rotor blade recrystallized-resistant repaired structure;
FIG. 5 is a microstructure view of a turbine rotor blade creep 120 h;
FIG. 6 is an organization chart of a creep 120 h-service turbine working blade after recrystallization resistant repair;
FIG. 7 is a heat-treated metallographic structure of a creep 120h service turbine working blade repaired by scheme A;
FIG. 8 is a heat-treated metallographic structure of a creep 120h service turbine working blade repaired by scheme B.
Detailed Description
The invention provides a recrystallization resistance method in a post-service turbine blade repairing process, which comprises the following steps:
sequentially carrying out anti-recrystallization heat treatment, solution treatment and aging treatment on the turbine blade after service;
the recrystallization-preventing heat treatment process comprises the following steps:
carrying out first heat preservation after first temperature rise to a first heat treatment temperature, and carrying out at least one time of temperature rise after the first heat preservation until the last stage of heat treatment;
the first heat treatment temperature is [ (T)s-150)～(Ts-50)]DEG C; the T issThe initial redissolution temperature of the gamma' phase of the turbine blade which is not in service;
in the process of the recrystallization-preventing heat treatment, the temperature delta T of each temperature rise is independently 10-15 ℃ except for the first temperature rise;
(Tf-40- Δ T) ° c < temperature of the end-stage heat treatment < (T)f-40) deg.C; the T isfIs the complete re-dissolution temperature of the gamma' phase of the turbine blade which is not in service.
In the present invention, the starting materials used in the present invention are preferably commercially available products unless otherwise specified.
The method comprises the step of sequentially carrying out anti-recrystallization heat treatment, solution treatment and aging treatment on the turbine blade after service.
In the present invention, the after service turbine blades preferably include over temperature after service turbine blades or creep after service turbine blades. In the invention, the turbine blade after being in service at the overtemperature is the turbine blade which is in service at the temperature exceeding the normal service temperature, for example, the normal service temperature of a certain turbine blade is 1150 ℃, but the actual service temperature is 1250 ℃, so the turbine blade in service at 1250 ℃ is called the turbine blade after being in service at the overtemperature.
In the invention, when the turbine blade after service is preferably the turbine blade after over-temperature service, the method preferably further comprises a structural stress removing treatment before the anti-crystallization treatment. In the present invention, the structural stress removal treatment preferably includes: heating the in-service turbine blade to 900 +/-20 ℃; and (4) preserving heat for 2-4 h, and preferably preserving heat for 3 h. In the present invention, the structural stress removal treatment is preferably performed under vacuum conditions. After the structural stress removing treatment, the invention also comprises furnace cooling. In the invention, the structural stress removing treatment can remove the structural stress of the turbine blade after the turbine blade is in service at the over-temperature, and has the function of preventing the turbine blade from deforming or cracking in the subsequent treatment process.
In the present invention, the creep in-service turbine blade refers to a turbine blade in service under creep conditions and is referred to as a creep in-service turbine blade. In the present invention, where the in-service turbine blade is preferably an in-creep service turbine blade, the method of resisting recrystallization during the repair of the in-creep service turbine blade is preferably performed after the first or second stage of turbine blade creep.
In the invention, the material of the turbine blade after service preferably comprises nickel-based single crystal alloy or directional solidification alloy; the nickel-based single crystal alloy preferably comprises an IC21 single crystal alloy.
In the present invention, the recrystallization-preventing heat treatment process includes:
and carrying out first heat preservation after the first temperature rise to the first heat treatment temperature, and carrying out temperature rise for at least one time after the first heat preservation until the last stage of heat treatment.
In the present invention, the recrystallization-preventing heat treatment is specifically performed, for example, by: the first temperature is raised to the first heat treatment temperature for first heat preservation, the second temperature is raised to the second heat treatment temperature for second heat preservation, and the third temperature is raised to the final heat treatment temperature for final heat preservation; or: and (3) carrying out first heat preservation by first heating to the first heat treatment temperature, carrying out second heat preservation by second heating to the second heat treatment temperature, carrying out third heat preservation by third heating to the third heat treatment temperature, and … … carrying out final heat preservation by second final heating to the final heat treatment temperature.
In the present invention, the first heat treatment temperature is [ (T)s-150)～(Ts-50)]DEG C; the T issThe initial re-dissolution temperature of the gamma' phase of an unused turbine blade.
In the invention, in the process of the recrystallization-preventing heat treatment, the temperature delta T of each temperature rise except for the first temperature rise is independently and preferably 10-15 ℃.
In the present invention, (T)f-40- Δ T) ° c < temperature of the end-stage heat treatment < (T)f-40) deg.C; the T isfThe complete re-dissolution temperature of the gamma' phase of the turbine blade which is not in service. In the present invention, said Ts、TfPreferably by measuring DSC curves.
In the invention, in the anti-recrystallization heat treatment process, the rate of each temperature rise is preferably 3-15 ℃/min independently, and more preferably 5-10 ℃/min independently.
In the present invention, in the recrystallization-preventing heat treatment, the time for each heat retention is independently preferably 20min to 120min, and more preferably 30 min.
In the invention, in the process of the recrystallization-preventing heat treatment, after heat preservation each time, the temperature is preferably respectively reduced to 1100-1150 ℃; the cooling rate is preferably 5-20 ℃/min independently, and more preferably 5-10 ℃/min independently.
In the invention, the temperature of the solution treatment is preferably not lower than the complete re-dissolving temperature of the gamma' phase of the non-service turbine blade and not higher than the initial melting point temperature of the non-service turbine blade; the heat preservation time of the solution treatment is preferably 3-5 h, and more preferably 4 h. In the present invention, the rate of heating to the solution treatment temperature is preferably 3 to 10 ℃/min, and more preferably 5 ℃/min. In the present invention, the solution treatment is preferably performed under vacuum.
After the solution treatment, the invention preferably further comprises argon quenching and cooling to room temperature.
In the present invention, the aging treatment preferably includes sequentially performing a high temperature aging treatment and a low temperature aging treatment.
In the invention, the temperature of the high-temperature aging treatment is preferably 1100 +/-20 ℃; the heat preservation time is preferably 1-3 h, and more preferably 2 h. In the invention, the rate of raising the temperature to the temperature of the high-temperature aging treatment is preferably 5-15 ℃/min, and more preferably 10 ℃/min. After the high-temperature aging treatment, the invention preferably further comprises air cooling to room temperature.
In the invention, the temperature of the low-temperature aging treatment is preferably 870 +/-20 ℃; the heat preservation time is preferably 15-25 h, and more preferably 16-20 h. In the invention, the rate of raising the temperature to the temperature of the low-temperature aging treatment is preferably 5-30 ℃/min, and more preferably 10 ℃/min. After the low-temperature aging treatment, the invention preferably further comprises air cooling to room temperature.
The following provides a detailed description of the method of the present invention for resisting recrystallization during the repair of a turbine blade after service, with reference to the following examples, which should not be construed as limiting the scope of the invention.
Example 1 tissue repair of turbine guide blades after over-temperature service
The turbine guide vane is subjected to overtemperature treatment, and the overtemperature is 1250 ℃ (the normal service temperature is 1150 ℃).
Firstly: observing the original tissue of the turbine guide vane, and determining the initial re-dissolution temperature T of the gamma' phase of the original turbine guide vane by using a DSC analysis methodsAt 1280 ℃ and a complete redissolution temperature Tf1320 ℃ and the initial melting point temperature of the alloy is 1350 ℃.
Secondly, the method comprises the following steps: the method comprises the following steps of carrying out stress relief treatment on the guide vane of the service overtemperature turbine, wherein the specific parameters are as follows: heating to 900 +/-20 ℃, preserving heat for 3 hours, and cooling along with the furnace.
Then, carrying out recrystallization prevention heat treatment, wherein the specific parameters are as follows: raising the temperature to 1200 plus or minus 5 ℃ at the speed of 10 ℃/min, preserving the temperature for 0.5h, and then reducing the temperature to 1100 plus or minus 5 ℃ at the speed of 10 ℃/min; continuously heating to 1210 +/-5 ℃ at the speed of 10 ℃/min, and cooling to 1100 +/-5 ℃ at the speed of 10 ℃/min; continuously heating to 1220 plus or minus 5 ℃ at the speed of 10 ℃/min, and cooling to 1100 plus or minus 5 ℃ at the speed of 10 ℃/min; continuously heating to 1230 +/-5 ℃ at the speed of 10 ℃/min, and cooling to 1100 +/-5 ℃ at the speed of 10 ℃/min; continuously heating to 1240 +/-5 ℃ at the speed of 5 ℃/min, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min; continuously heating to 1250 +/-5 ℃ at the speed of 5 ℃/min, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min; continuously heating to 1260 plus or minus 5 ℃ at the speed of 5 ℃/min, and cooling to 1100 plus or minus 5 ℃ at the speed of 5 ℃/min; continuously heating to 1270 +/-5 ℃ at the speed of 5 ℃/min, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min;
then carrying out solid solution treatment, wherein the specific parameters are as follows: heating to 1325 ℃ at the speed of 5 ℃/min, carrying out vacuum heat preservation for 4h, and carrying out argon gas quenching and cooling.
And finally, carrying out aging treatment, wherein the specific parameters are as follows: heating to 1100 + -20 deg.C at a rate of 5 deg.C/min, maintaining for 2 hr, and air cooling; heating to 870 +/-20 ℃ at the speed of 10 ℃/min, preserving the heat for 20 hours, and cooling in air.
FIG. 1 is a prior art thermal treatment microstructure of a turbine guide vane in service; FIG. 2 is a structural diagram of a heat-treated state of a turbine guide vane after over-temperature service; FIG. 3 shows the heat-treated structure of the guide vane of the over-temperature service turbine after anti-recrystallization repair. As can be seen from FIGS. 1-3: the original heat treatment state structure gamma 'of the blade is precipitated with strengthening phase with good cubicity, the alloy blade microstructure is degenerated after overtemperature service, the gamma' strengthening phase is coarsened and has cubicity to be changed into a sphere, and the gamma-phase channel is widened. After the alloy blade with the overtemperature service thickness is subjected to recrystallization-resistant repair, the microstructure of the alloy blade is changed into a cubic shape from the microstructure shown in figure 3, and the cubic shape is similar to the original microstructure of the alloy blade before service. Therefore, the recrystallization-resistant repair heat treatment method can effectively repair the microstructure of the over-temperature service single crystal alloy turbine guide blade, thereby prolonging the service life of the blade.
Example 2 tissue repair of creep service turbine blades
For the turbine working blade, the turbine working blade bears a certain centrifugal force, mainly the tissue degradation after creep deformation, including the redissolution, coarsening and raft organization of a gamma' phase.
Firstly: a test bar simulation test is carried out on the turbine working blade, and a creep rupture test at 1100 ℃/110MPa is carried out. Referring to the creep curve, an interruption experiment was performed for the late second phase of 120h creep (strain 1.9%). Two protocols of tissue repair heat treatment were performed on creep-interrupted specimens.
Observing the original tissue of the turbine working blade, and determining the initial re-dissolution temperature T of the gamma' phase of the original turbine working blade by using a DSC analysis methodsAt 1280 ℃ and a complete redissolution temperature Tf1320 ℃ and the initial melting point temperature of the alloy is 1350 ℃.
Scheme a:
non-recrystallization-proof heat treatment: directly carrying out solid solution treatment, wherein the specific parameters are as follows: heating to 1320 deg.C at 3 deg.C/min, vacuum preserving for 4h, and cooling by argon gas quenching. And finally, carrying out aging treatment, wherein the specific parameters are as follows: heating to 1100 + -20 deg.C at a rate of 5 deg.C/min, maintaining for 2 hr, and air cooling to room temperature; then heating to 870 +/-20 ℃ at the speed of 10 ℃/min, preserving the heat for 20h, and cooling in air.
Scheme B:
carrying out recrystallization-preventing heat treatment, wherein the specific parameters are as follows: raising the temperature to 1200 ℃ at the speed of 10 ℃/min, preserving the temperature for 0.5h, and then reducing the temperature to 1100 ℃ at the speed of 10 ℃/min; continuously heating to 1210 ℃ at the speed of 10 ℃/min, keeping the temperature for 0.5h, and cooling to 1100 ℃ at the speed of 10 ℃/min; continuously heating to 1220 plus or minus 5 ℃ at the speed of 5 ℃/min, preserving heat for 0.5h, and cooling to 1100 plus or minus 5 ℃ at the speed of 5 ℃/min; continuously heating to 1230 +/-5 ℃ at the speed of 5 ℃/min, keeping the temperature for 0.5h, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min; continuously heating to 1240 +/-5 ℃ at the speed of 5 ℃/min, preserving the heat for 0.5h, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min; continuously heating to 1250 +/-5 ℃ at the speed of 5 ℃/min, preserving the heat for 0.5h, and cooling to 1100 +/-5 ℃ at the speed of 5 ℃/min; continuously heating to 1260 plus or minus 5 ℃ at the speed of 3 ℃/min, preserving the heat for 0.5h, and cooling to 1100 plus or minus 5 ℃ at the speed of 3 ℃/min; continuously heating to 1270 +/-5 ℃ at the speed of 3 ℃/min, preserving the heat for 0.5h, and cooling to 1100 +/-5 ℃ at the speed of 3 ℃/min.
Then carrying out solution treatment, wherein the specific parameters are as follows: heating to 1325 ℃ at the speed of 5 ℃/min, carrying out vacuum heat preservation for 4h, and carrying out argon gas quenching and cooling.
And finally, carrying out aging treatment on the test sample, wherein the specific parameters are as follows: heating to 1100 + -20 deg.C at a rate of 5 deg.C/min, maintaining for 2 hr, and air cooling to room temperature; heating to 870 + -20 deg.C at a speed of 10 deg.C/min, maintaining for 20h, and air cooling.
FIG. 4 is a graph of creep performance of an original structure of a turbine rotor blade before service and a creep service turbine rotor blade recrystallization-resistant repaired structure, as can be seen from FIG. 4: after the anti-recrystallization repair heat treatment process is carried out on the creep working turbine blade, the endurance quality of the turbine working blade is obviously improved.
FIG. 5 is a microstructure diagram of a creep 120h of a turbine working blade, and FIG. 6 is a microstructure diagram of a creep 120h service turbine working blade after recrystallization resistant repair. As can be seen from FIGS. 5-6: after the turbine working blade is in service, the microstructure of the turbine working blade is obviously degraded, and the gamma' phase is in a raft-dismantling state. By utilizing the recrystallization-resistant heat treatment repairing process, the microstructure of the blade is repaired, the cubic degree of the gamma' phase is higher, the microstructure is similar to the original structure of the blade before being in service, and the service life of the turbine working blade is prolonged.
FIG. 7 is a heat-treated metallographic structure of a creep 120h service turbine working blade repaired by a scheme A, and FIG. 8 is a heat-treated metallographic structure of a creep 120h service turbine working blade repaired by a scheme B. As can be seen from FIGS. 7-8: by using the scheme A repairing method without the recrystallization resistant heat treatment process, obvious large recrystallized grains appear on the inner and outer surfaces of the turbine working blade, so that the service performance of the blade is obviously reduced. And by using the scheme B of recrystallization-resistant repair heat treatment, after the microstructure of the turbine working blade is repaired, no recrystallized grains appear on the surface of the blade, and the performance of the blade is repaired.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (9)
1. A method for resisting recrystallization in the process of repairing a turbine blade after service comprises the following steps:
sequentially carrying out anti-recrystallization heat treatment, solution treatment and aging treatment on the turbine blade after service;
the recrystallization-preventing heat treatment process comprises the following steps:
firstly heating to a first heat treatment temperature for first heat preservation, and then heating for at least one time and preserving heat to the end section heat treatment;
the first heat treatment temperature is [ (T)s-150)～(Ts-50)]DEG C; the T issThe initial redissolution temperature of the gamma' phase of the turbine blade which is not in service;
in the process of the recrystallization-preventing heat treatment, the temperature delta T of each temperature rise is independently 10-15 ℃ except for the first temperature rise;
(Tf-40- Δ T) ° c < temperature of the end-stage heat treatment < (T)f-40) deg.C; the T isfThe complete re-dissolution temperature of the gamma' phase of the turbine blade which is not in service;
the in-service turbine blade comprises an over-temperature in-service turbine blade or a creep in-service turbine blade.
2. The method of claim 1, wherein when the in-service turbine blade is an over-temperature in-service turbine blade, the post-service turbine blade further comprises performing a structural stress removal treatment prior to the anti-recrystallization heat treatment; the structural stress removal treatment comprises: and heating the turbine blade after service to 900 +/-20 ℃, and preserving the heat for 2-4 h.
3. The method of claim 1, wherein the post-service turbine blade is a creep-service turbine blade, and wherein the method of resisting recrystallization during the repair of the creep-service turbine blade is performed after a first or second stage of creep of the turbine blade.
4. The recrystallization-resistant process according to claim 1, wherein the time for each holding is independently 20 to 120min during the recrystallization-resistant heat treatment.
5. The method according to claim 1 or 4, wherein the temperature of the recrystallization-preventing heat treatment is reduced to 1100-1150 ℃ after each temperature preservation.
6. The recrystallization-resistant method according to claim 1, wherein the rate of each temperature increase during the recrystallization-resistant heat treatment is independently 3 to 15 ℃/min.
7. The method of claim 1, wherein the material of the in-service turbine blade comprises a nickel-based single crystal alloy or a directionally solidified alloy.
8. The recrystallization-resistant method according to claim 1, wherein the temperature of the solution treatment is not lower than a complete re-solution temperature of a gamma' phase of the non-service turbine blade and not higher than an initial melting point temperature of the non-service turbine blade; and the heat preservation time of the solution treatment is 3-5 h.
9. The anti-recrystallization method according to claim 1, wherein the aging treatment comprises sequentially performing a high-temperature aging treatment and a low-temperature aging treatment; the temperature of the high-temperature aging treatment is 1100 +/-20 ℃, and the heat preservation time is 1-3 h; the temperature of the low-temperature aging treatment is 870 +/-20 ℃, and the heat preservation time is 15-25 h.
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| CN115354133B (en) * | 2022-08-16 | 2023-10-17 | 中国航发北京航空材料研究院 | Method for preventing local recrystallization of monocrystalline superalloy blade |
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