CN112620383A - Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft - Google Patents

Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft Download PDF

Info

Publication number
CN112620383A
CN112620383A CN202011200989.2A CN202011200989A CN112620383A CN 112620383 A CN112620383 A CN 112620383A CN 202011200989 A CN202011200989 A CN 202011200989A CN 112620383 A CN112620383 A CN 112620383A
Authority
CN
China
Prior art keywords
rolling
temperature
forging
nickel
percent
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202011200989.2A
Other languages
Chinese (zh)
Other versions
CN112620383B (en
Inventor
于杰
张鹏
王志刚
谷强
邹善仁
吴伟
王树财
王艾竹
李飞扬
侯智鹏
赵长顺
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FUSHUN SPECIAL STEEL SHARES CO LTD
Original Assignee
FUSHUN SPECIAL STEEL SHARES CO LTD
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by FUSHUN SPECIAL STEEL SHARES CO LTD filed Critical FUSHUN SPECIAL STEEL SHARES CO LTD
Priority to CN202011200989.2A priority Critical patent/CN112620383B/en
Publication of CN112620383A publication Critical patent/CN112620383A/en
Application granted granted Critical
Publication of CN112620383B publication Critical patent/CN112620383B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21CMANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C37/00Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape
    • B21C37/02Manufacture of metal sheets, bars, wire, tubes or like semi-manufactured products, not otherwise provided for; Manufacture of tubes of special shape of sheets
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21BROLLING OF METAL
    • B21B3/00Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21BROLLING OF METAL
    • B21B37/00Control devices or methods specially adapted for metal-rolling mills or the work produced thereby
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21BROLLING OF METAL
    • B21B37/00Control devices or methods specially adapted for metal-rolling mills or the work produced thereby
    • B21B37/74Temperature control, e.g. by cooling or heating the rolls or the product
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21JFORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
    • B21J5/00Methods for forging, hammering, or pressing; Special equipment or accessories therefor
    • B21J5/002Hybrid process, e.g. forging following casting
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22BPRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B9/00General processes of refining or remelting of metals; Apparatus for electroslag or arc remelting of metals
    • C22B9/006General processes of refining or remelting of metals; Apparatus for electroslag or arc remelting of metals with use of an inert protective material including the use of an inert gas
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22BPRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B9/00General processes of refining or remelting of metals; Apparatus for electroslag or arc remelting of metals
    • C22B9/16Remelting metals
    • C22B9/18Electroslag remelting
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C1/00Making non-ferrous alloys
    • C22C1/02Making non-ferrous alloys by melting
    • C22C1/023Alloys based on nickel
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C19/00Alloys based on nickel or cobalt
    • C22C19/03Alloys based on nickel or cobalt based on nickel
    • C22C19/05Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B21MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21BROLLING OF METAL
    • B21B3/00Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
    • B21B2003/001Aluminium or its alloys
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02PCLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00Technologies related to metal processing
    • Y02P10/25Process efficiency

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Metal Rolling (AREA)
  • Forging (AREA)

Abstract

The invention discloses a method for manufacturing a nickel-based high-temperature alloy wide and thick flat material for a high-speed aircraft, wherein GH4099 alloy is a dispersion hardening material with high heat strength, and the high-temperature strength of the GH4099 alloy is improved by mainly depending on a gamma' strengthening phase formed by aluminum, titanium and nickel and carbide formed by carbon and chromium; the comprehensive performance is best when the carbon content is controlled to be 0.03-0.05 percent, the aluminum content is controlled to be 2.00-2.20 percent and the titanium content is controlled to be 1.20-1.40 percent; the smelting process adopts protective atmosphere electroslag remelting, forging cogging adopts a 3150-ton quick forging machine to upset step by step and a billet soft sleeve is drawn out, and the rolling heating temperature of a finished product is controlled according to 1130-1150 ℃. The invention has the beneficial effects that: manufacturing wide and thick flat materials; the specification, high temperature performance and plate type of the plate all meet the technical index requirements.

Description

Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft
Technical Field
The invention belongs to the field of high-temperature alloy manufacturing, and particularly relates to a manufacturing method of a nickel-based high-temperature alloy wide and thick flat material for a high-speed aircraft pneumatic structural component within the temperature range of 900-950 ℃, wherein the nickel-based deformed high-temperature alloy is of a brand GH 4099.
Background
GH4099 is nickel-chromium-based precipitation hardening type nickel-based wrought superalloy which is strengthened by precipitation of a second phase, has high heat strength, stable structure and good cold and hot processing forming and welding process performance, and is mainly used for manufacturing high-temperature welded structural parts such as an aircraft engine combustion chamber, an afterburner and the like. In view of the advantage of stable comprehensive performance of GH4099, the aerospace design department selects GH4099 as a pneumatic structural component of a high-speed aircraft, and the design requirements are as follows: the thickness is 40 mm-60 mm, the width is 400 mm-650 mm, the length is 1000 mm-1100 mm, the plate shape meets the condition that the unevenness is not more than 15mm/m, and the high-temperature performance meets the specification of table 1. However, the content of aluminum and titanium in the alloy is 3.3 percent, the content of tungsten, molybdenum and cobalt is 17 percent, segregation is easy to form in the alloy smelting process, the deformation resistance of forging cogging and hot rolling cogging is large, the edge and corner of the blank are easy to have large crack tendency, and the current domestic and foreign data does not have the record of the GH4099 wide and thick flat material manufacturing method with the performance of 900-950 ℃ meeting the specification of the table 1.
TABLE 1 GH4099 mechanical property indexes of wide, thick and flat material
Figure BDA0002755039790000011
Disclosure of Invention
The invention discloses a method for manufacturing a nickel-based high-temperature alloy wide and thick flat material for a high-speed aircraft, and aims to obtain a GH4099 alloy wide and thick flat material with supernormal specification, good plate shape and excellent performance.
The technical scheme of the invention is as follows:
the purpose is achieved by optimizing the component proportion, designing the electroslag remelting smelting process under the protective atmosphere and improving the forging cogging and plate rolling processes.
The process route is as follows:
optimized component proportion → vacuum induction furnace + electroslag furnace smelting under protective atmosphere → 3150t rapid forging machine cogging → blank finishing → 1200 t double-roller rotation irreversible hot rolling mill rolling → physicochemical inspection → packaging.
1. Smelting
The chemical composition of the GH4099 alloy should meet the specifications of Table 2.
TABLE 2 GH4099 alloy chemistry
Figure BDA0002755039790000021
Pouring 340mm phi electrode in vacuum induction furnace, smelting 460mm phi ingot with protective atmosphere electroslag furnace, and making slag system CaF2:Al2O360% of CaO and 20% of MgO and 10% of CaO, and the melting rate is set to 210 kg/h.
2. Forging and cogging
The 3150t quick forging machine adopts upsetting and drawing-out cogging, the rolling reduction during upsetting is controlled between 300mm and 400mm, the forging heating temperature is 1150-1170 ℃, the alloy finish forging temperature is not lower than 920 ℃, and the diameter of the steel ingot after upsetting is not smaller than phi 510 mm; the single-hammer reduction amount is controlled to be 50 mm-80 mm during drawing, the total deformation amount of drawing is controlled to be 75% -85%, and a flat blank of 70 mm-80 mm multiplied by 550mm is forged.
3. Blank finishing
After forging and cogging, finishing the flat blank, and polishing the whole body of the flat blank by using a 24-grain grinding wheel of a square steel polishing machine to ensure that the surface of the alloy flat blank has no defects such as cracks.
4. Rolling of sheet material
Adopting a 1200-ton double-roller rotary irreversible hot rolling mill to perform cogging, controlling the rolling heating temperature according to 1130-1150 ℃, performing rolling for 1 heating time, controlling the rolling deformation to be 20-40 percent, ensuring that the final rolling temperature is not lower than 950 ℃, and performing hot straightening on a rolling line by using the residual temperature after rolling.
The reasons for selecting the chemical components of the GH4099 alloy wide and thick plate are as follows: the GH4099 alloy is a dispersion hardening material with high heat strength, has a complex phase composition, and is mainly characterized in that a gamma' strengthening phase formed by aluminum, titanium and nickel is adopted, and carbide formed by carbon and chromium improves the high-temperature strength of the GH4099 alloy. Controlling the carbon content: the high-temperature performance of the GH4099 alloy is reduced more and more along with more primary carbides in the steel, and in order to improve the high-temperature performance of the alloy, the carbon content in the steel is controlled to be 0.03-0.05%. Controlling the content of aluminum and titanium: in order to ensure that the strength at the high temperature of 900 ℃ is not less than 425MPa and the yield strength is not less than 370 MPa; the strength at 950 ℃ is not less than 220MPa, the yield strength is not less than 175MPa, the aluminum content in the alloy is controlled to be 2.00-2.20%, and the titanium content is controlled to be 1.20-1.40%, so that the comprehensive performance is optimal.
The innovation points of the invention are as follows:
1. the smelting process adopts protective atmosphere electroslag remelting to produce GH4099 alloy phi 460mm steel ingots, wherein the content of aluminum and titanium elements in the GH4099 alloy is 3.3%, the content of tungsten, molybdenum and cobalt elements is 17%, segregation is easy to form in the alloy smelting process, and the GH4099 alloy is smelted by adopting a protective atmosphere electroslag furnace in order to ensure uniform burning loss of the aluminum and the titanium elements; in order to avoid the phenomenon that the solid-liquid two-phase area is too wide and easily segregated elements are fully accumulated during electroslag smelting of GH4099 alloy, the flow of argon is 6m3H, slag-resisting swing button4, the melting rate was set at 210 kg/h.
2. Forging cogging adopts a 3150-ton quick forging machine to upset step by step and stretch a steel billet flexible sheath
In order to enable the width of a plate blank to meet the design requirement, a 3150-ton quick forging machine is adopted to carry out upsetting forging on the steel ingot, and due to the characteristics of poor heat conductivity of high-temperature alloy, low initial melting temperature of the alloy and the like, in order to avoid overheating the core part and deteriorating the product quality when the steel ingot is upset, step-by-step pressing is adopted, namely, the total pressure drop of a single fire is uniformly distributed; the GH4099 alloy is mainly strengthened by a gamma ' phase, the maximum precipitation amount of the gamma ' phase accounts for 22-24% of the alloy, when the finish forging temperature of the alloy is lower than 920 ℃, the gamma ' phase is precipitated in a large amount, so that the plasticity of a steel billet is reduced sharply, low-temperature tension cracks are easily formed at the corner of the steel billet, in order to ensure that the finish forging temperature of the corner of the steel billet is higher than 920 ℃, a soft sleeve is covered when the steel billet is drawn out, the rapid heat dissipation in the forging process is reduced, the early temperature loss at the corner of the steel billet is avoided, and the quality of a plate.
3. The heating temperature of the finished product is controlled according to 1130-1150 DEG C
The test shows that the crystal grains of the GH4099 alloy grow rapidly after being heated at 1150 ℃, the rolling temperature is controlled at 1130-1150 ℃, and the gamma' strengthening phase and secondary carbide precipitated in the forging process of the GH4099 alloy can be fully dissolved, the deformation resistance in the rolling process is reduced, and the dynamic recrystallization of the alloy is more uniform.
4. Finished wide and thick flat material on-line hot straightening by utilizing rolling waste heat
The plate with the specification is easy to generate plate type warpage in the rolling process, and the GH4099 alloy is subjected to thermal straightening by utilizing rolling waste heat. The straightening direction is vertical to the rolling direction of the finished product, and the plate shape meets the design requirement by adjusting the gap between the rolls and the cooperation of a rolling mill manipulator and a rolling mill worker.
The invention has the beneficial effects that: by accurately controlling the contents of carbon, aluminum and titanium, a new process of a phi 460mm ingot type protective atmosphere electroslag furnace is formulated, and the processes of forging cogging and wide, thick and flat rolling are improved, so that the GH4099 alloy wide, thick and flat material is manufactured; the plate specification, high-temperature performance and plate type meet the following requirements:
plate specification: 40mm to 60mm (thickness) x 400mm to 650mm (width) x 1000mm to 1100mm (length);
the high temperature performance meets the specification of table 1;
plate type: the unevenness of the plate is not more than 15 mm/m.
Detailed Description
The present invention is described in detail below by way of examples.
Example 1, example 2 and example 3 adopt a vacuum induction furnace together to cast an electrode with phi 340mm, adopt a protective atmosphere electroslag furnace to smelt an ingot with phi 460mm, and adopt CaF2:Al2O3: CaO: 60% of MgO: 20%: 10%: the melting rate of 10% slag system was set at 210 kg/h.
Example 1
Specification of a finished product: 45mm × 650mm × 1100mm
The chemical composition is shown in Table 3.
TABLE 3 chemical composition
Figure BDA0002755039790000041
The alloy is subjected to upsetting and elongation by a 3150t quick forging machine for cogging, the rolling reduction during upsetting is controlled to be 370mm, the forging heating temperature is 1150-1170 ℃, the finish forging temperature is not lower than 950 ℃, and the diameter of an upset steel ingot is not smaller than phi 510 mm; during drawing, the single hammer rolling reduction is 80mm, the total drawing deformation is 81.14%, and a flat blank of 70mm multiplied by 550mm is forged; after forging and cogging, finishing the flat blank, and polishing the whole body of the flat blank by using a 24-grain grinding wheel of a square steel polishing machine to ensure that the surface of the alloy flat blank has no defects such as cracks; adopting a 1200-ton double-roller rotary irreversible hot rolling mill to perform cogging, controlling the rolling heating temperature according to 1130-1150 ℃, performing rolling for 1 heating time, wherein the rolling deformation is 35.71 percent, the finish rolling temperature is 960 ℃, and performing hot straightening on a rolling line by using the residual temperature after rolling.
The finished product meets the standard requirements after performance and unevenness inspection, the measured unevenness is 10mm/m, and the performance results are shown in Table 4.
TABLE 4 mechanical Properties
Figure BDA0002755039790000051
Example 2
Specification of a finished product: 50mm × 650mm × 1100mm
The chemical composition is shown in Table 5.
TABLE 5 chemical composition
Figure BDA0002755039790000052
The alloy is cogging by adopting upsetting and drawing out through a 3150t quick forging machine. The rolling reduction during upsetting is controlled at 370mm, the forging heating temperature is 1150-1170 ℃, the finish forging temperature is not lower than 950 ℃, and the diameter of the steel ingot after upsetting is not smaller than phi 510 mm; during drawing, the single hammer rolling reduction is 80mm, the total drawing deformation is 79.79 percent, and a flat blank of 75mm multiplied by 550mm is forged; after forging and cogging, finishing the flat blank, and polishing the whole body of the flat blank by using a 24-grain grinding wheel of a square steel polishing machine to ensure that the surface of the alloy flat blank has no defects such as cracks; adopting a 1200-ton double-roller rotary irreversible hot rolling mill to perform cogging, controlling the rolling heating temperature according to 1130-1150 ℃, performing rolling for 1 heating time, wherein the rolling deformation is 33.33 percent, the finish rolling temperature is 970 ℃, and performing hot straightening on a rolling line by using the residual temperature after rolling.
The finished product meets the standard requirements after performance and unevenness inspection, the unevenness is measured to be 9mm/m, and the performance results are shown in Table 6.

Claims (5)

1. The manufacturing method of the nickel-based high-temperature alloy wide and thick flat material for the high-speed aircraft is characterized by comprising the following process routes: optimizing the component ratio → smelting in a vacuum induction furnace and a protective atmosphere electroslag furnace → opening in 3150t of a rapid forging machine → finishing blank → rolling in a 1200-ton double-roller rotating irreversible hot rolling mill → physical and chemical inspection → packaging;
the optimized component proportion is carbon: 0.03% -0.05%, chromium: 17.00% -20.00%, tungsten: 5.00% -7.00%, molybdenum: 3.50% -4.50%, aluminum: 2.00% -2.20%, titanium:
1.20% -1.40%, cobalt: 5.00-8.00%, iron not more than 2.00%, boron not more than 0.005%, Ce not more than 0.02%, manganese not more than 0.40%, silicon not more than 0.50%, phosphorus not more than 0.015%, sulfur not more than 0.015%, and the balance nickel;
the vacuum induction furnace and the protective atmosphere electroslag furnace are used for smelting, the vacuum induction furnace is adopted to cast a phi 340mm electrode, the protective atmosphere electroslag furnace is adopted to smelt a phi 460mm ingot mold, and a slag system CaF2:Al2O360 percent of CaO, 20 percent of MgO, 10 percent of CaO and 10 percent of MgO, and the melting speed is set according to 210 kg/h;
upsetting and stretching cogging are adopted for cogging of the 3150t quick forging machine, the rolling reduction amount during upsetting is controlled to be 300-400 mm, the forging heating temperature is 1150-1170 ℃, the alloy final forging temperature is not lower than 920 ℃, and the diameter of an upset steel ingot is not smaller than phi 510 mm; controlling the single-hammer reduction amount to be 50-80 mm during drawing, controlling the total drawing deformation amount to be 75-85%, and forging into a flat blank of 70-80 mm multiplied by 550 mm;
finishing the blank, after forging and cogging, finishing the flat blank, and polishing the whole body of the flat blank by using a 24-grain grinding wheel of a square steel polishing machine to ensure that the surface of the alloy flat blank has no defects such as cracks;
the 1200-ton double-roller rotation irreversible hot rolling mill is used for rolling, the rolling heating temperature is controlled according to 1130-1150 ℃, the rolling is carried out for 1 heating time, the rolling deformation is controlled to be 20-40 percent, the final rolling temperature is not lower than 950 ℃, and the hot straightening is carried out on a rolling line by using the residual temperature after the rolling.
2. The method for manufacturing the nickel-based superalloy wide and thick flat material for the high-speed aircraft as claimed in claim 1, wherein the protective atmosphere electroslag furnace is used for smelting, and argon flow is 6m3H control; the 3150-ton quick forging machine adopts step-by-step reduction for upsetting and forging the steel ingot, namely, the total reduction of a single fire is uniformly distributed; the soft sheath covers the billet after drawing and cogging, so that the rapid heat dissipation in the forging process is reduced.
3. The manufacturing method of the nickel-based superalloy wide and thick flat material for the high-speed aircraft according to claim 1 or 2, wherein the finished product specification is as follows: 45mm × 650mm × 1100 mm;
the composition, carbon: 0.07%, chromium: 18.49%, tungsten: 6.50%, molybdenum: 3.99%, aluminum: 2.15%, titanium: 1.30%, cobalt: 6.00%, iron: 0.5%, boron: 0.003%, cerium: 0.01%, manganese: 0.02%, silicon: 0.05%, phosphorus: 0.003%, sulfur: 0.001% of nickel;
the 3150t quick forging machine adopts upsetting, the rolling reduction during upsetting is controlled at 370mm, the forging heating temperature is 1150-1170 ℃, the finish forging temperature is not lower than 950 ℃, and the diameter of the steel ingot after upsetting is not smaller than phi 510 mm; the single hammer rolling reduction is 80mm when drawing and cogging are carried out, the total drawing deformation is 81.14%, and a flat blank of 70mm multiplied by 550mm is forged;
the 1200-ton double-roller rotary irreversible hot rolling mill is opened, the rolling heating temperature is controlled according to 1130-1150 ℃, the rolling is carried out for 1 heating, the rolling deformation is 35.71 percent, and the final rolling temperature is 960 ℃.
4. The manufacturing method of the nickel-based superalloy wide and thick flat material for the high-speed aircraft according to claim 1 or 2, wherein the finished product specification is as follows: 50mm × 650mm × 1100 mm;
the composition, carbon: 0.04%, chromium: 18.51%, tungsten: 6.49%, molybdenum: 3.97%, aluminum: 2.16%, titanium: 1.31%, cobalt: 6.01%, iron: 0.54%, boron: 0.003%, cerium: 0.01%, manganese: 0.03%, silicon: 0.05%, phosphorus: 0.003%, sulfur: 0.001% of nickel;
the 3150t quick forging machine adopts upsetting, the rolling reduction during upsetting is controlled at 370mm, the forging heating temperature is 1150-1170 ℃, the finish forging temperature is not lower than 950 ℃, and the diameter of the steel ingot after upsetting is not smaller than phi 510 mm; the single hammer rolling reduction is 80mm when drawing and cogging are carried out, the total drawing deformation is 79.79 percent, and a flat blank with the thickness of 75mm multiplied by 550mm is forged;
the 1200-ton double-roller rotary irreversible hot rolling mill is opened, the rolling heating temperature is controlled according to 1130-1150 ℃, the rolling is carried out for 1 heating, the rolling deformation is 33.33 percent, and the final rolling temperature is 970 ℃.
5. The manufacturing method of the nickel-based superalloy wide and thick flat material for the high-speed aircraft according to claim 1 or 2, wherein the finished product specification is as follows: 50mm × 650mm × 1100 mm;
the composition, carbon: 0.039%, chromium: 18.52%, tungsten: 6.51%, molybdenum: 3.98%, aluminum: 2.19%, titanium: 1.25%, cobalt: 6.02%, iron: 0.61%, boron: 0.003%, cerium: 0.01%, manganese: 0.03%, silicon: 0.04%, phosphorus: 0.003%, sulfur: 0.001% of nickel;
the 3150t quick forging machine adopts upsetting, the rolling reduction during upsetting is controlled at 390mm, the forging heating temperature is 1150-1170 ℃, the finish forging temperature is not lower than 950 ℃, and the diameter of the steel ingot after upsetting is not smaller than phi 510 mm; the single hammer rolling reduction is 80mm when drawing and cogging are carried out, the total drawing deformation is 78.78%, and flat blanks of 78mm multiplied by 550mm are forged;
the 1200-ton double-roller rotary irreversible hot rolling mill is opened, the rolling heating temperature is controlled according to 1130-1150 ℃, the rolling is carried out for 1 heating, the rolling deformation is 29.48 percent, and the final rolling temperature is 970 ℃.
CN202011200989.2A 2020-11-02 2020-11-02 Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft Active CN112620383B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011200989.2A CN112620383B (en) 2020-11-02 2020-11-02 Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011200989.2A CN112620383B (en) 2020-11-02 2020-11-02 Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft

Publications (2)

Publication Number Publication Date
CN112620383A true CN112620383A (en) 2021-04-09
CN112620383B CN112620383B (en) 2022-10-14

Family

ID=75303221

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011200989.2A Active CN112620383B (en) 2020-11-02 2020-11-02 Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft

Country Status (1)

Country Link
CN (1) CN112620383B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113293344A (en) * 2021-06-04 2021-08-24 航天特种材料及工艺技术研究所 Brazing aging integrated treatment process for GH4099 nickel-based high-temperature alloy
CN114318193A (en) * 2022-01-07 2022-04-12 无锡派克新材料科技股份有限公司 Method for homogenizing crystal grains of nickel-based superalloy casing

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080038148A1 (en) * 2006-08-09 2008-02-14 Paul Crook Hybrid corrosion-resistant nickel alloys
CN108441705A (en) * 2018-03-16 2018-08-24 中国航发北京航空材料研究院 A kind of high intensity ni-base wrought superalloy and preparation method thereof
CN109136653A (en) * 2017-06-15 2019-01-04 宝钢特钢有限公司 For the nickel-base alloy of nuclear power generating equipment and its manufacturing method of hot rolled plate
CN109136652A (en) * 2017-06-15 2019-01-04 宝钢特钢有限公司 Nuclear power key equipment nickel-base alloy extrusion bar of large cross section and its manufacturing method
CN109985926A (en) * 2019-03-25 2019-07-09 永兴特种不锈钢股份有限公司 The production method of Ni-based GH4080A alloy wire rod
CN111187934A (en) * 2019-12-27 2020-05-22 国机金属江苏有限公司 Production method of GH4080A wire bar
CN111235434A (en) * 2020-03-02 2020-06-05 北京钢研高纳科技股份有限公司 Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080038148A1 (en) * 2006-08-09 2008-02-14 Paul Crook Hybrid corrosion-resistant nickel alloys
CN109136653A (en) * 2017-06-15 2019-01-04 宝钢特钢有限公司 For the nickel-base alloy of nuclear power generating equipment and its manufacturing method of hot rolled plate
CN109136652A (en) * 2017-06-15 2019-01-04 宝钢特钢有限公司 Nuclear power key equipment nickel-base alloy extrusion bar of large cross section and its manufacturing method
CN108441705A (en) * 2018-03-16 2018-08-24 中国航发北京航空材料研究院 A kind of high intensity ni-base wrought superalloy and preparation method thereof
CN109985926A (en) * 2019-03-25 2019-07-09 永兴特种不锈钢股份有限公司 The production method of Ni-based GH4080A alloy wire rod
CN111187934A (en) * 2019-12-27 2020-05-22 国机金属江苏有限公司 Production method of GH4080A wire bar
CN111235434A (en) * 2020-03-02 2020-06-05 北京钢研高纳科技股份有限公司 Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature

Non-Patent Citations (5)

* Cited by examiner, † Cited by third party
Title
丁五洲等: "高品质、大规格N06625板材生产工艺研究", 《中国金属通报》 *
刘建强等: "GH99合金锻棒的研制", 《宝钢技术》 *
夏长林等: "GH4099合金轧制棒材高温持久性能研究", 《钢铁研究学报》 *
梁艳等: "GH141高温合金的热加工工艺", 《金属热处理》 *
王福: "新型GH4099板材的制备与性能研究", 《特钢技术》 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113293344A (en) * 2021-06-04 2021-08-24 航天特种材料及工艺技术研究所 Brazing aging integrated treatment process for GH4099 nickel-based high-temperature alloy
CN113293344B (en) * 2021-06-04 2021-12-14 航天特种材料及工艺技术研究所 Brazing aging integrated treatment process for GH4099 nickel-based high-temperature alloy
CN114318193A (en) * 2022-01-07 2022-04-12 无锡派克新材料科技股份有限公司 Method for homogenizing crystal grains of nickel-based superalloy casing

Also Published As

Publication number Publication date
CN112620383B (en) 2022-10-14

Similar Documents

Publication Publication Date Title
CN103949805B (en) A kind of method preparing nickel-base alloy bare welding filler metal
CN106734805B (en) Φ 500~650mm Cr6 swaged forging Electro Slag Remelting Steel cold roll blank forging deformation techniques
CN106947908B (en) A kind of method of continuous casting electroslag production 4Cr5MoSiV1 die steels
CN110935827B (en) Forging method of large-specification fine-grain austenitic stainless steel SNCrW bar
CN103949798B (en) A kind of preparation method of nickel-base alloy bare welding filler metal
CN108034895A (en) A kind of Valve Steel 50Cr21Mn9Ni4Nb2WN polishes the production method of bright as silver bar
CN103949806B (en) A kind of preparation method of welding wire
CN112695255B (en) Preparation method of ferrite martensite steel clad tube
CN112620383B (en) Manufacturing method of nickel-based high-temperature alloy wide and thick flat material for high-speed aircraft
CN103962747B (en) A kind of diameter is less than the nickel-base alloy bare welding filler metal of 3mm
CN102000954A (en) Method for manufacturing continuous pipe mill retained mandrel
CN111394620A (en) Machining and forming process of high-strength nickel-based high-temperature alloy bar
CN112143975A (en) Economical high-efficiency X70-grade pipeline steel and manufacturing method thereof
CN114058906B (en) Large-size Ni-Cr electrothermal alloy blank and hot working method
CN105108377A (en) Nickel alloy welding wire for welding cast iron pipe
CN114101969A (en) Nuclear-grade nickel-chromium-iron alloy welding wire and preparation method and application thereof
CN108950134B (en) Remelting method of electroslag ingot for cold roll
CN103949800B (en) A kind of welding wire be made up of Cr28Ni48W5 nickel-base alloy
CN112575227B (en) Manufacturing method of high-silicon nickel-based alloy cold-rolled sheet
CN104250712A (en) Method for manufacturing large-size, high-toughness and wear-resistant alloy roller
CN103949801B (en) A kind of welding wire
CN103949799B (en) A kind of nickel-base alloy bare welding filler metal
CN103949807B (en) A kind of preparation method of nickel-base alloy bare welding filler metal
CN103962756B (en) Cr28Ni48W5 nickel-base alloy is made the method for welding wire
CN106756578B (en) A kind of SAE8660 hot rolled sheet and production technology

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant