CN114393056B - High-temperature alloy plate structure for aviation and plate shape control method - Google Patents
High-temperature alloy plate structure for aviation and plate shape control method Download PDFInfo
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- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
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Abstract
The invention discloses a control method of a high-temperature alloy plate structure and a plate shape for aviation, which comprises the steps of carrying out homogenizing annealing on an ingot obtained by adopting a triple smelting process; heating the cast ingot to 700-800 ℃ and preserving heat for 60-120 min, then heating to 1000-1150 ℃ and preserving heat for 0.5-0.8 mm/min; deformation: when the height-diameter ratio of the ingot is more than or equal to 1.5, upsetting the ingot to the height-diameter ratio of 1.0, and drawing the ingot to the height-diameter ratio of 2.0; forging: returning the cast ingot after cogging to a furnace for heat preservation, heating to 980-1150 ℃ and calculating the heat preservation time according to 0.4-0.7 mm/min; deformation: upsetting the ingot to the height-to-diameter ratio of about 1.2, and drawing the ingot to the height-to-diameter ratio of 1.8; returning the ingot after forging to the furnace for heat preservation, heating to 960-1150 ℃ and performing multi-fire forming; and heating the plate blank obtained by the formed ingot casting processing to 960-1150 ℃ and performing multi-fire rolling. The high-temperature alloy plate which is uniform in structure, stable in performance, plate-shaped and excellent in surface quality and is suitable for aviation is prepared.
Description
Technical Field
The invention belongs to the technical field of alloy plate processing, and particularly relates to a high-temperature alloy plate structure for aviation and a plate shape control method.
Background
The high-temperature alloy is also called super alloy and heat-resistant alloy, is a high-temperature metal material which works for a long time under the conditions of 760-1500 ℃ and certain stress, has excellent high-temperature strength, good oxidation resistance, hot corrosion resistance, good fatigue property, fracture toughness and other comprehensive properties, becomes an irreplaceable key material of a hot end part of a civil and military gas turbine engine, and is known as an advanced engine foundation stone.
In China, the high-temperature alloy bar is mainly used for post-processing into high-temperature end parts, and the bar is not used for post-cold and hot processing into plates. But in fact, in the early 90 s of the last century, europe and america have begun to use on aeroengines. The high-temperature alloy plate has wide application prospect in the aerospace field, and can be used for nozzle ceramic chips of jet turbine engines, helicopter pipelines, thermal protection systems of RLVs and the like.
The larger rebound quantity of the rolled high-temperature alloy plate is not easy to control in dimensional accuracy, the larger pressure is needed during forming, and the higher the requirement on forming equipment is. In addition, the high-temperature alloy plate is difficult to form and process, the alloy elements are more than twenty, and the forming precision and the structure performance are very difficult to control.
Disclosure of Invention
In the high-temperature deformation process of the high-temperature alloy, the grain structure in the material can generate distortion energy under the drive of stress, when the distortion energy reaches a certain critical value, the grain starts to be dynamically recrystallized, the grain starts to be refined, and the small deformation cannot trigger the dynamic recrystallization of the grain structure because the distortion energy enough for the dynamic recrystallization is not generated, and the grain will not be dynamically recrystallized. However, the excessive deformation in the rolling process can cause the phenomena of wavy plate shape, uneven thickness and the like.
The invention aims to prepare the high-temperature alloy plate which meets the requirements of aviation on uniform structure, stable performance and excellent plate shape and surface quality by controlling the whole-flow process methods such as plate blank structure control, plate rolling structure and performance control, plate forming process control, plate surface treatment process control and the like, and can be used for producing aviation high-temperature alloy plates for aero-engine parts and the like.
The invention is realized by the following technical scheme:
the invention provides a high-temperature alloy plate structure for aviation and a plate shape control method, which comprises the following steps:
step 1: ingot casting preparation: adopting a triple smelting process to obtain ingots with high purity and uniform components, wherein the chemical components of the ingots meet the requirements of the chemical components of the ingots with related brands;
step 2: annealing: homogenizing and annealing the cast ingot;
step 3: forging a plate blank:
cogging: heating the ingot annealed in the step 2 to 700-800 ℃ and preserving heat for 60-120 min, then heating to 1000-1150 ℃ and preserving heat for 0.5-0.8 mm/min; deformation: when the height-diameter ratio of the ingot is more than or equal to 1.5, upsetting the ingot to the height-diameter ratio of 1.0, and drawing the ingot to the height-diameter ratio of 2.0;
forging: returning the cast ingot after cogging to a furnace for heat preservation, heating to 980-1150 ℃ and calculating the heat preservation time according to 0.4-0.7 mm/min; deformation: upsetting the ingot to the height-to-diameter ratio of about 1.2, and drawing the ingot to the height-to-diameter ratio of 1.8;
and (3) forming: and (3) a forming step I: returning the ingot after forging to a furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: drawing until the deformation of the cross section area is 10-40%; and a second molding step: returning to the furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: deforming to the size required by the process; and step three of molding: returning to the furnace for heat preservation, heating to 960-1100 ℃, and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: shaping;
step 4: rolling: and heating the plate blank obtained by the formed ingot casting processing to 960-1150 ℃ and performing multi-fire rolling.
As a further illustration of the present invention, the triple smelting process specifically comprises: adopts a triple smelting process of vacuum induction smelting, protective atmosphere electroslag smelting and vacuum consumable smelting.
As a further illustration of the present invention, said homogenizing annealing said ingot comprises: the ingot is insulated for 60 to 120min at 700 to 800 ℃, heated to 1130 to 1160 ℃ for 20 to 30h, and heated to 1150 to 1180 ℃ for 60 to 120h.
As a further illustration of the present invention, the multi-pass rolling specifically includes:
rolling by fire: heating the plate blank obtained by the processing treatment of the formed cast ingot to 960-1150 ℃ and calculating the heat preservation time according to 0.5-0.7 mm/min; rolling pass: 6-9 times; total deformation: 45% -60%;
and (3) material separation: plate length doubling and material dividing;
and (3) rolling by two fires: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.4-0.6 mm/min; rolling pass: 4-6 times; total deformation: 50% -65% of reversing rolling.
As a further explanation of the present invention, when the thickness of the finished plate is not less than 6mm, the multi-pass rolling further comprises:
after the two-fire rolling, material is separated: plate length doubling and material dividing;
three-fire rolling: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.6-0.9 mm/min; rolling pass: 5-8 times; total deformation: 50% -70% of reversing rolling.
As a further explanation of the present invention, when delivering the sheet in solid solution state, the sheet obtained by rolling is further subjected to sheet solid solution leveling treatment: the solid solution temperature is 900-1000 ℃, and the heat preservation time is calculated according to 2-2.5 mm/min.
As a further explanation of the invention, the rolled plate is subjected to grinding and polishing processing and plate processing sizing and material dividing treatment.
As a further illustration of the present invention, the superalloy sheet is a GH1035 superalloy sheet, a GH3625 superalloy sheet, or a GH4169 superalloy sheet.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention prepares the high-temperature alloy plate which accords with the aviation high-temperature alloy plate with uniform structure, stable performance and excellent plate shape and surface quality and can be used for producing aviation high-temperature alloy plates of aero-engine parts and the like through the control of plate blank structure control, plate rolling structure and performance control, plate forming process control, plate surface treatment process control and other full-flow process methods.
Detailed Description
In order that the above objects, features and advantages of the invention will be more readily understood, a more particular description of the invention will be rendered by reference to specific embodiments thereof. It should be noted that, without conflict, the embodiments of the present invention and features in the embodiments may be combined with each other.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
The invention provides a high-temperature alloy plate structure for aviation and a plate shape control method, which comprises the following steps:
step 1: ingot casting preparation: and a triple smelting process is adopted to obtain ingots with high purity and uniform components.
The triple smelting process specifically comprises the following steps: adopts a triple smelting process of vacuum induction smelting (VIM) +protective atmosphere Electroslag Smelting (ESR) +vacuum consumable smelting (VAR).
The conventional ingot casting for the high-temperature alloy slab generally adopts a Vacuum Induction Melting (VIM) +vacuum consumable melting (VAR) duplex melting process, and partial inclusion in a vacuum induction melting electrode can be removed by adding an electroslag remelting process into the ingot casting melting process for the slab, so that a compact and defect-free electrode is provided for remelting in a vacuum consumable furnace, the stability of the remelting process is ensured, the purity is further improved, and the macrosegregation tendency is reduced.
The chemical composition test of the cast ingot obtained by the smelting process meets the requirements of the chemical compositions of the cast ingot with relevant brands.
Step 2: annealing: homogenizing and annealing the cast ingot;
in one implementation, the homogenizing annealing the ingot specifically includes: the ingot is insulated for 60 to 120min at 700 to 800 ℃, heated to 1130 to 1160 ℃ for 20 to 30h, and heated to 1150 to 1180 ℃ for 60 to 120h.
Compared with the traditional process, the annealing mode further reduces the range of the homogenizing annealing temperature of the ingot, and prevents the continuous deterioration of the tissue while improving the uniformity of components in the ingot by accurately controlling the homogenizing annealing temperature and time of the ingot.
Step 3: forging a plate blank:
cogging: heating the ingot annealed in the step 2 to 700-800 ℃ and preserving heat for 60-120 min, then heating to 1000-1150 ℃ and preserving heat for 0.5-0.8 mm/min; deformation: when the height-diameter ratio of the ingot is more than or equal to 1.5, upsetting the ingot to the height-diameter ratio of 1.0, and drawing the ingot to the height-diameter ratio of 2.0;
when in cogging forging, the initial structure of the cast ingot is a coarse as-cast structure, so that the plasticity is poor, cracking is easy to occur in the forging process, the cogging forging is performed by adopting a small deformation amount, and the shape is mainly changed, so that the forging of the subsequent blank is easy to change.
Forging: returning the cast ingot after cogging to a furnace for heat preservation, heating to 980-1150 ℃ and calculating the heat preservation time according to 0.4-0.7 mm/min; deformation: upsetting the ingot to the height-to-diameter ratio of about 1.2, and drawing the ingot to the height-to-diameter ratio of 1.8;
the forging process (tempering heat preservation and deformation) can be repeatedly performed for 2-6 times according to the blank condition, the slab grain size and the internal quality requirement.
The high-temperature alloy has low initial melting temperature, high recrystallization temperature and narrow forging temperature range (about 1/3-1/2 of carbon steel), and adopts a process scheme of multiple fires and small deformation, wherein each fire and small deformation can ensure that the deformation is completed in a short time, the final forging temperature of the alloy is high enough, and the multiple fires of deformation can ensure that coarse as-cast grains of the alloy are fully crushed, and a slab with uniform structure is obtained. Meanwhile, the continuous forging process is adopted, so that the production efficiency can be improved, and the production cost can be saved.
And (3) forming: and (3) a forming step I: returning the ingot after forging to a furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: drawing until the deformation of the cross section area is 10-40%; and a second molding step: returning to the furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: deforming to the size required by the process; and step three of molding: returning to the furnace for heat preservation, heating to 960-1100 ℃, and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: shaping;
in order to facilitate roll forming, the thickness of a plate blank is generally not more than 150mm, so that the deformation of the plate blank in the length and width directions is relatively large when the plate blank is forged and formed, grains in a certain direction are easily elongated by direct one-fire forming, the subsequent plate with uniform structure is not facilitated, and the excessive deformation of one-fire forming is avoided by adopting a multi-fire forming mode, and the grains in the deformation in a certain direction are severely elongated. Meanwhile, in the multi-fire forming process, recrystallization can be promoted to occur in the heating process, so that the original elongated crystal grains are recrystallized into equiaxed crystal grains. Reducing the elongation tendency of the grains.
Step 4: rolling: and heating the plate blank obtained by the formed ingot casting processing to 960-1150 ℃ and performing multi-fire rolling.
In one possible manner, the multi-pass rolling specifically includes:
rolling by fire: heating the plate blank obtained by the processing treatment of the formed cast ingot to 960-1150 ℃ and calculating the heat preservation time according to 0.5-0.7 mm/min; rolling pass: 6-9 times; total deformation: 45% -60%.
The slab has thicker initial rolling thickness, larger deformation resistance, larger rolling force and higher requirement on equipment. The rolling force can be reduced by selecting multiple-pass small-deformation rolling through one-firing rolling.
And (3) material separation: plate length doubling and material dividing;
and (3) rolling by two fires: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.4-0.6 mm/min; rolling pass: 4-6 times; total deformation: 50% -65% of reversing rolling.
The thickness of the two-fire rolled blank is reduced, the deformation resistance is gradually reduced, and the rolling is carried out by adopting less passes and large deformation to refine grains.
In one possible mode, when the thickness of the finished plate is not less than 6mm, the multi-pass rolling further comprises:
after the two-fire rolling, material is separated: plate length doubling and material dividing; (the material dividing dimension in the length direction of the plate is the width dimension of the finished plate)
Three-fire rolling: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.6-0.9 mm/min; rolling pass: 5-8 times; total deformation: 50% -70% of reversing rolling.
In the rolling process, the crystal grains are deformed along one direction, so that the crystal grains are elongated along one direction, the difference of the properties of the plate in different directions is large, the strength is high along the deformation direction, and the strength is low perpendicular to the deformation direction. By adopting the reversing rolling process, the sheet material has enough deformation in different directions in the rolling process, the sheet material with consistent mechanical properties in different directions is obtained, and the deformation before and after reversing rolling is kept within +/-5%.
In one possible way, when the sheet material is delivered in solid solution, the rolled sheet material is further subjected to solid solution leveling treatment: the solid solution temperature is 900-1000 ℃, and the heat preservation time is calculated according to 2-2.5 mm/min.
In one implementation manner, the rolled plate needs to be subjected to grinding, polishing, sizing and material dividing.
The following is a detailed description of preferred embodiments.
Example 1
The preparation method of the GH1035 high-temperature alloy plate comprises the following steps:
1) And (3) testing chemical components of the cast ingot: the chemical composition of the ingot meets the specifications of table 1.
Table 1 chemical composition requirements for ingots
2) Homogenizing and annealing the cast ingot: the ingot is kept at 700 ℃ for 120min, heated to 1150 ℃ for 20h, and heated to 1170 ℃ for 100h.
3) Forging a plate blank:
cogging: the ingot obtained by annealing treatment is kept at 700 ℃ for 60min, and the temperature is raised to 1170 ℃ for 225min; deformation: Φ4501050 upset Φ600× (590).
Two fires: returning to the furnace for heat preservation, and heating to 1150 ℃ for 240min; deformation: phi 600× (590) elongated ≡435× (880);
three fires: returning to the furnace for heat preservation, and heating to 1130 ℃ for 175min; deformation: in the process, the upsetting is in the range of (about) 435× (880), and the upsetting is in the range of (about) 550× (550);
four-fire: returning to heat preservation, and heating to 1110 ℃ for 220min; deformation: drawing out ≡550× (550) and ≡435× (880);
five fires: returning to heat preservation, and heating to 1110 ℃ for 135min; deformation: the board 220 x 650 x 1150 is ∈435 x 880 x;
six fire: returning to the furnace for heat preservation, and heating to 1000 ℃ for 70min; deformation: 220 x 650 x (1150) panel → 110 x 1150 x (1300);
seven fire: returning to the furnace for heat preservation, heating to 1000 ℃ for heat preservation time of 55min, and deforming: shaping.
4) And (3) milling a plate blank: milling the slab to
5) And (3) rolling a plate:
heating by a fire: heating the milled plate blank to 1000 ℃, and preserving heat for 40min;
rolling by fire:
rolled to->
Deformation pass: 7 passes of
Deformation amount: 53%
And (3) material separation:
divide the material->
And (3) rolling by two fires:
heating: heating to 980 ℃, and preserving heat for 20min;
deformation:
reversing and rolling to->
Deformation pass: 4 passes of
Deformation amount: 58%
6) And (3) carrying out solid solution leveling treatment on the plate: solid solution temperature: the temperature is 1120 ℃ and the heat preservation time is 32min;
8) Grinding and polishing the plate to
Thickness;
9) Sizing and material dividing for plate processing
10 Plate samples were taken for mechanical properties and grain size testing.
Example 2:
a preparation method of a GH3625 high-temperature alloy plate comprises the following steps:
1) And (3) testing chemical components of the cast ingot: the ingot chemistry meets the specifications of table 2.
Table 2 ingot chemical composition requirements
2) Homogenizing and annealing the cast ingot: the ingot is kept at 700 ℃ for 120min, heated to 1130 ℃ for 20h, and heated to 1150 ℃ for 80h.
3) Forging a plate blank:
cogging: heating the ingot obtained by annealing treatment to 750 ℃ and preserving heat for 90min, and heating to 1170 ℃ and preserving heat for 220min; deformation: phi 450 x 550 is drawn out ≡350 x (700).
Two fires: returning to the furnace for heat preservation, and heating to 1150 ℃ for 175min; deformation: in the process, the upsetting is in the range of (i) 350 x (700), and in the range of (i) 440 x (440);
three fires: returning to the furnace for heat preservation, and heating to 1150 ℃ for 220min; deformation: the board 200 x 650 of ≡440 x 440;
four-fire: returning to the furnace for heat preservation, and heating to 1130 ℃ for 70min; deformation: 200 x 650 x (650) spread plate 80 x 900 x (1150);
five fires: returning to the furnace for heat preservation, and heating to 1000 ℃ for 40min; deformation: shaping. 4) And (3) milling a plate blank: milling the slab to
5) And (3) rolling a plate:
heating by a fire: heating to 1000 ℃ and preserving heat for 45min.
Rolling by fire:
rolled to->
Deformation pass: 6 passes of
Deformation amount: 57%.
And (3) material separation:
divide the material->
And (3) rolling by two fires:
heating: heating to 1000 ℃ and preserving heat for 25min.
Deformation:
reversing and rolling to->
Deformation pass: 4 passes of
Deformation amount: 61%
6) And (3) carrying out solid solution leveling treatment on the plate: solid solution temperature: the temperature is 980 ℃ and the heat preservation time is 15min;
8) Grinding and polishing the plate to
Thickness;
9) Sizing and material dividing for plate processing
10 Plate samples were taken for mechanical properties and grain size testing.
Example 3:
a preparation method of GH4169 high-temperature alloy plate comprises the following steps:
1) And (3) testing chemical components of the cast ingot: the chemical composition of the ingot meets the specifications of table 1.
Table 1 chemical composition requirements for ingots
2) Homogenizing and annealing the cast ingot: heating the cast ingot to 700 ℃ and preserving heat for 120min, heating to 1160 ℃ and preserving heat for 20h, and heating to 1180 ℃ and preserving heat for 60h.
3) Forging a plate blank:
cogging: heating the ingot obtained by annealing treatment to 800 ℃ and preserving heat for 60min, and heating to 1080 ℃ and preserving heat for 380min; deformation: phi 480 x 800 is drawn ≡415× (840) upset ≡520× (535).
Two fires: returning to heat preservation, and heating to 1060 ℃ for 310min; deformation: drawing out ≡415× (840) upsetting ≡520× (535);
three fires: returning to heat preservation, and heating to 1060 ℃ for 310min; deformation: drawing out ≡415× (840) upsetting ≡520× (535);
four-fire: returning to heat preservation, and heating to 1060 ℃ for 310min; deformation: ≡520× (535) panel 200× 750× (960);
five fires: returning to heat preservation, and heating to 1060 ℃ for 120min; deformation: 200 x 750 x (960) spread board 120 x 1000 x (1200);
six fire: returning to the furnace for heat preservation, and heating to 1060 ℃ for heat preservation for 70min; deformation: shaping.
4) And (3) milling a plate blank: milling the slab to
5) And (3) rolling a plate:
heating by a fire: heating to 1000 ℃ and preserving heat for 70min.
Rolling by fire:
rolled to->
Deformation pass: 6 passes of
Deformation amount: 60%.
And (3) material separation:
divide the material->
And (3) rolling by two fires:
heating: heating to 1000 ℃ and preserving heat for 30min.
Deformation:
reversing and rolling to->
Deformation pass: 4 passes of
Deformation amount: 60 percent of
And (3) material separation:
divide the material->
Three-fire rolling:
heating: heating to 1000 ℃ and preserving heat for 16min.
Deformation:
reversing and rolling to->
Deformation pass: 5 times;
deformation amount: 61%.
6) And (3) carrying out solid solution leveling treatment on the plate: solid solution temperature: the temperature is 960 ℃ and the heat preservation time is 12min;
8) Grinding and polishing the plate to
Thickness;
9) Sizing and material dividing for plate processing
10 Taking a mechanical property sample from the plate remainder;
11 Aging heat treatment of the sample: heat preservation is carried out for 8 hours at 720 ℃, furnace cooling is carried out to 620 ℃, heat preservation is carried out for 8 hours, and air cooling is carried out;
12 Test sample mechanical properties:
finally, it should be noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention.
Claims (5)
1. The high-temperature alloy plate structure for aviation and the plate shape control method are characterized by comprising the following steps:
step 1: ingot casting preparation: adopting a triple smelting process to obtain ingots with high purity and uniform components, wherein the chemical components of the ingots meet the requirements of the chemical components of the ingots with related brands; the triple smelting process specifically comprises the following steps: a triple smelting process of vacuum induction smelting, protective atmosphere electroslag smelting and vacuum consumable smelting is adopted;
step 2: annealing: homogenizing and annealing the cast ingot;
step 3: forging a plate blank:
cogging: heating the ingot annealed in the step 2 to 700-800 ℃ and preserving heat for 60-120 min, then heating to 1000-1150 ℃ and preserving heat for 0.5-0.8 mm/min; deformation: when the height-diameter ratio of the ingot is more than or equal to 1.5, upsetting the ingot to the height-diameter ratio of 1.0, and drawing the ingot to the height-diameter ratio of 2.0;
forging: returning the cast ingot after cogging to a furnace for heat preservation, heating to 980-1150 ℃ and calculating the heat preservation time according to 0.4-0.7 mm/min; deformation: upsetting the ingot to the height-to-diameter ratio of about 1.2, and drawing the ingot to the height-to-diameter ratio of 1.8;
and (3) forming: and (3) a forming step I: returning the ingot after forging to a furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: drawing until the deformation of the cross section area is 10-40%; and a second molding step: returning to the furnace for heat preservation, heating to 960-1150 ℃ and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: deforming to the size required by the process; and step three of molding: returning to the furnace for heat preservation, heating to 960-1100 ℃, and calculating the heat preservation time according to 0.3-0.6 mm/min; deformation: shaping;
step 4: rolling: heating the plate blank obtained by the formed ingot casting processing to 960-1150 ℃ and carrying out multi-fire rolling;
the multi-pass rolling specifically comprises:
rolling by fire: heating the plate blank obtained by the processing treatment of the formed cast ingot to 960-1150 ℃ and calculating the heat preservation time according to 0.5-0.7 mm/min; rolling pass: 6-9 times; total deformation: 45% -60%;
and (3) material separation: plate length doubling and material dividing;
and (3) rolling by two fires: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.4-0.6 mm/min; rolling pass: 4-6 times; total deformation: 50% -65%, reversing rolling;
when the thickness of the finished plate is more than or equal to 6mm, the multi-fire rolling further comprises:
after the two-fire rolling, material is separated: plate length doubling and material dividing;
three-fire rolling: heating the plate blank after the material separation to 960-1150 ℃ and calculating the heat preservation time according to 0.6-0.9 mm/min; rolling pass: 5-8 times; total deformation: 50% -70% of reversing rolling.
2. The method for controlling the texture and shape of an aerospace superalloy sheet material according to claim 1, wherein the homogenizing annealing the ingot comprises: the ingot is insulated for 60 to 120min at 700 to 800 ℃, heated to 1130 to 1160 ℃ for 20 to 30h, and heated to 1150 to 1180 ℃ for 60 to 120h.
3. The aviation superalloy sheet structure and sheet shape control method according to claim 1, wherein the rolled sheet is further subjected to sheet solid solution leveling treatment when delivered in solid solution: the solid solution temperature is 900-1000 ℃, and the heat preservation time is calculated according to 2-2.5 mm/min.
4. The method for controlling the structure and the shape of the aviation superalloy sheet material according to claim 1, wherein the rolled sheet material is subjected to grinding and polishing processing and sheet material processing sizing and material dividing processing.
5. The aviation superalloy sheet structure and sheet shape control method according to claim 1, wherein the superalloy sheet is a GH1035 superalloy sheet, a GH3625 superalloy sheet or a GH4169 superalloy sheet.
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