CN113042669B - Rotor assembly for engine and preparation method thereof - Google Patents
Rotor assembly for engine and preparation method thereof Download PDFInfo
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- CN113042669B CN113042669B CN201911363500.0A CN201911363500A CN113042669B CN 113042669 B CN113042669 B CN 113042669B CN 201911363500 A CN201911363500 A CN 201911363500A CN 113042669 B CN113042669 B CN 113042669B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
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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
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/174—Titanium alloys, e.g. TiAl
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- Mechanical Engineering (AREA)
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- Crystallography & Structural Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Forging (AREA)
Abstract
The invention relates to a rotor assembly for an engine and a preparation method thereof. A method of making a rotor assembly for an engine, comprising: providing a titanium alloy raw material, heating the titanium alloy raw material to 25-40 ℃ below a beta phase transition point, then performing die forging on the titanium alloy raw material, and performing mechanical processing after die forging to obtain a rotor assembly blank; the rotor assembly blank comprises a blank disc part and a blank drum part, wherein the blank drum part is an annular flange protruding from one side surface of the blank disc part, and the protruding direction is the axial direction along the central rotation axis of the rotor assembly; heating the blank drum part to 20-50 ℃ above the beta phase transition point of the blank drum part, and then ring rolling the blank drum part, wherein the pressure direction of ring rolling is along the radial direction; then solid solution treatment and aging treatment are carried out.
Description
Technical Field
The invention relates to the field of materials, in particular to a rotor assembly for an engine and a preparation method thereof.
Background
At least some known rotating machinery, such as turbine engines, include various rotor assemblies, such as fan assemblies, compressors, and/or turbines, each of which includes a rotor assembly.
For a compressor, it may include a drum-and-disc hybrid rotor assembly. As shown in fig. 1, the drum-disc hybrid rotor assembly includes a plurality of rotor assemblies 20 connected in series, the rotor assemblies 20 including a disc portion 200 and a drum portion 220, the disc portion 200 and the drum portion 220 being rotatable about a central rotational axis 30. Blades 240 may be further installed at the rim of the tray portion 200.
Disclosure of Invention
The inventor finds that the service environment of the aviation aircraft engine is complex, and the stress conditions and the service environment of different parts are different for the same disc. Under some conditions, the cruising condition of the drum part of the rotor assembly exceeds 350 ℃ and the working stress exceeds 450MPa, so that the high-temperature high-stress working condition puts higher thermal creep performance demands on the performance of the drum part of the rotor disc of the high-pressure compressor.
The present disclosure provides a dual performance rotor assembly and method of making the same. The disk part and the drum part of the rotor assembly have different microstructures, and can meet the requirements of different working conditions. Moreover, the rotor assembly is integrally formed, and the joint of the disc part and the drum part is not welded or bolted.
In some aspects, a method of preparing a rotor assembly for an engine is provided, comprising:
(1) Providing a titanium alloy raw material, heating the titanium alloy raw material to a temperature T 1 Then die forging is carried out on the titanium alloy raw material, and a rotor assembly blank is obtained by machining after the die forging, wherein T is as follows 1 25-40 ℃ below the beta transus point of the titanium alloy (e.g., 30-35 ℃ below the beta transus point);
the rotor assembly blank comprises a blank disc part and a blank drum part, wherein the blank drum part is an annular flange protruding from one side surface of the blank disc part, and the protruding direction is the axial direction along the central rotation axis of the rotor assembly;
(2) Heating the blank drum part to a temperature T 2 Then ring rolling is carried out on the blank drum part, the pressure direction of the ring rolling is along the radial direction, wherein T is 2 20-50 ℃ above the beta transus point of the titanium alloy (for example, 30-40 ℃ above the beta transus point);
(3) Heating the product of the previous step to a temperature T 3 Preserving heat for 0.5-1.5 h, and then cooling by air or cooling at a lower speed, wherein T is 3 10 to 50 ℃ below the beta transus (e.g., 20 to 30 ℃ below the beta transus or 30 to 40 ℃ below the beta transus);
(4) Heating the product of the previous step to a temperature T 4 Preserving heat for 6-10 hours (e.g., 7-8 hours or 8-9 hours), then air cooling or cooling at a slower speed, wherein T 4 550-650 deg.c (e.g., 600 deg.c).
In some embodiments, step (3) is solution heat treatment.
In some embodiments, step (4) is an aging heat treatment.
And (2) selecting a ring rolling process to process the blank drum part, which is critical for realizing the beneficial technical effects of the invention. In the ring rolling process, the blank drum part is exposed to air, the cooling rate is air cooling, the cooling rate is very stable, and then the product obtained after ring rolling has uniform structure and stable performance.
In some embodiments, the swaging of step (1) is performed in a die at 300-400 ℃.
In some embodiments, the steps (2) and (3) further comprise the steps of: machining the product of step (2) according to the shape and size requirements of the rotor assembly product.
In some embodiments, the above method further comprises: and removing the region with the equivalent plastic strain value (e) of more than 2 in the ring rolling process of the blank disc part and the blank drum part by mechanical processing.
The inventors found that the region of equivalent plastic strain value (e) > 2 eventually failed to form the desired basket structure during ring rolling, so that this region was removed by machining.
In some embodiments, the above method further comprises: areas of the blank disc and blank drum having macroscopic defects (e.g., cracks, wrinkles) are removed by machining.
In some embodiments, the blank tray portion or the machined product thereof after the machining of steps (1) - (4) comprises a bimodal structure.
In some embodiments, the blank drum or machined product thereof after the machining of steps (1) - (4) contains basket tissue.
In some embodiments, at any point in the radial direction of the blank disc, the blank disc is reserved with a tooling allowance in the axial direction of 10% or more (e.g., 20% or more, such as 30% or more, such as 40% or more, such as 50% or more, such as 60% or more).
In some embodiments, at any point of the blank drum in the axial direction, the blank disc is reserved with a tooling allowance in the radial direction of 10% or more (e.g., 20% or more, such as 30% or more, such as 40% or more, such as 50% or more, such as 60% or more).
In some embodiments, the tooling allowance reserve percentage value for a location = (the location blank size-the location final product size)/the location blank size. For example, the thickness of the blank is 100mm, the thickness of the product is 40mm, and the thickness corresponds to the allowance of 60 percent reserved in the thickness direction.
In some embodiments, in step (1), the titanium alloy feedstock is obtained as follows: heating the titanium alloy bar stock to a temperature T 1 Upsetting to obtain a pier cake.
In some embodiments, in step (2), the blank drum is heated using a heat source, and the heat source is not in contact with the blank tray.
In some embodiments, in step (2), the blank tray portion is isolated from the heat source by an insulating layer while the blank drum portion is heated using the heat source.
In some embodiments, in step (2), the ring rolling results in an equivalent plastic strain value of the blank drum of ≡0.7.
In some embodiments, in step (2), the ring rolling results in a blank drum having an equivalent plastic strain value of a minimum of 0.7.
In some embodiments, the blank disc is machined to form a disc of the rotor assembly, the disc including a radially inner hub, a web extending radially outwardly from the hub, and a rim extending radially outwardly from the web.
In some embodiments, the blank drum is machined to form a rotor assembly drum that projects from the radial flange to form an annular flange in a direction that is axial along the central rotational axis of the rotor assembly.
In some aspects, there is provided a rotor assembly for an engine, prepared by the method of any one of the above.
In some aspects, a rotor assembly for an engine is provided, comprising a disc portion and a drum portion;
the rotor component is made of titanium alloy, the disk part is provided with a titanium alloy bimodal structure, and the drum part is provided with a titanium alloy basket structure;
the rotor assembly is integrally formed.
In some embodiments, the blank drum has basket tissue. The titanium alloy basket structure has higher high-temperature tensile property, higher fracture toughness and excellent thermal creep resistance, and is suitable for the working condition.
In some embodiments, the blank tray portion has a bimodal structure. The blank disc part is in a low-temperature high-stress working condition area, and the bimodal structure has higher fatigue performance and is suitable for the working condition.
In some embodiments, the titanium alloy is a near alpha titanium alloy.
In some embodiments, the titanium alloy is Ti6242 titanium alloy. The Ti6242 titanium alloy is a titanium alloy material with a composition of basically Ti-6Al-2Sn-4Zr-2 Mo.
Ti6242 is a near alpha titanium alloy with a nominal beta transus of about 1005 ℃.
The Ti6242 material is forged by alpha+beta to obtain a bimodal structure, and can obtain the comprehensive properties of room temperature tensile strength, high-low cycle fatigue and the like.
The Ti6242 material is forged on a beta phase transition point, so that a basket structure can be obtained, and comprehensive performances such as high-temperature tensile property, fracture toughness, creep property and the like are obtained.
In some embodiments, the rotor assembly of the present disclosure is a rotor assembly for a turbine.
In some embodiments, the rotor assembly of the present disclosure is a rotor assembly for a compressor (compressor).
Description of the terminology:
if the following terms are used in the present invention, they may have the following meanings:
various relative terms such as "front," "rear," "top" and "bottom," "upper," "lower," "above," "below," and the like may be used to facilitate description of the various embodiments. Relative terms are defined with respect to a conventional orientation of the structure and do not necessarily refer to the actual orientation of the structure as manufactured or in use. The following detailed description is, therefore, not to be taken in a limiting sense. As used in the description and the appended claims, the singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.
The terms "bimodal structure", "basket structure" are two microstructures of titanium alloys. The following documents describe in detail the definition of the two microstructures mentioned above, which are incorporated herein in their entirety. Zhu Zhishou research and development of novel aviation high-performance titanium alloy materials [ M ]. Beijing: aviation industry Press 2013.12 pages 48-50. Or Zhao Yongqing, chen Yongnan titanium alloy phase transition and heat treatment [ M ]: middle and south university press, 2012.01, pages 128-130.
The term "radial" is a direction substantially perpendicular to the central axis of rotation of the rotor assembly.
The term "axial" is a direction substantially parallel to the central rotational axis of the rotor assembly.
The term "beta transus" refers to the alpha + beta/beta transus temperature on the titanium alloy phase diagram.
Advantageous effects
One or more technical solutions of the present disclosure have one or more of the following beneficial effects:
(1) The rotor component is integrally formed, and the disc part and the drum part have different microstructures, so that the performance of the rotor component under respective use conditions can be respectively met;
(2) The processing method is simple, quick and low in cost.
Drawings
FIG. 1 is a schematic illustration of a drum-and-disc hybrid rotor assembly.
Fig. 2 is a schematic view of a rotor assembly blank of example 1.
FIG. 3 is a schematic diagram of an isolated heating apparatus.
Fig. 4 is a schematic illustration of machining a ring rolled rotor assembly blank.
Fig. 5 is a photomicrograph of the rim position of the disk portion of one rotor assembly.
Fig. 6 is a photomicrograph of the drum portion of one rotor assembly.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but it will be understood by those skilled in the art that the following examples are only for illustrating the present invention and should not be construed as limiting the scope of the present invention. The specific conditions are not noted in the examples and are carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or apparatus used were conventional products commercially available without the manufacturer's attention.
Example 1
The method of preparing the rotor assembly is as follows:
ti6242 titanium alloy bar stock with the length of 700mm and the diameter of 230mm is provided. Heating the bar stock to 35 ℃ below the beta phase transition point, preserving heat for 1 hour, and then upsetting, wherein the upsetting deformation is controlled to be 40-60%. Upsetting and then forging again by 6 times to obtain the upsetting. And heating the pier cake to 35 ℃ below the beta phase transition point, preserving heat for 1 hour, performing die forging, wherein the die temperature is 350 ℃, the transfer time (the practice that a die forging object is transferred to a die from a heating furnace) is less than 45s, and performing air cooling. After the swaging, the swaged product with the black skin condition is machined to the rotor assembly blank 10 shown in fig. 2.
As shown in fig. 1, the rotor assembly blank 10 includes a blank disc portion 100 and a blank drum portion 120. The blank disc 100 includes a radially inner blank hub 112, a blank web 114 extending radially outwardly from the blank hub 112, and a blank rim 116 extending radially outwardly from the blank web 114. The blank drum 120 is an annular flange projecting from one side of the blank disc 100 in an axial direction along the central axis of rotation 30 of the rotor assembly.
As shown in fig. 1, the inner diameter d1 of the blank disk portion 100 is
The outer diameter d4 is
Inner diameter d2 of blank drum 120 is +.>
The outer diameter d3 is
The thickness h1 of the blank hub 112 is 32 mm.+ -.2 mm, the thickness h2 of the blank web 114 is 25 mm.+ -.2 mm, and the thickness h3 of the blank rim 116 is +.>
The thickness h4 of the blank drum part is 32mm plus or minus 2mm.
The rotor assembly blank 10 is placed into the insulated heating apparatus shown in fig. 3 and the blank drum 120 is heated in isolation. Specifically, the insulating heating means includes a heat source 41 and an insulating layer 42, the heat source 41 contacting only the blank drum portion 120 and not contacting the blank tray portion 100, the insulating layer 42 separating the blank tray portion 100 from the heat source 41. The blank drum 120 is heated to 40 ℃ above the beta transus point and held for one hour.
After heating, the blank drum 120 is cerclaged, and the direction of the ring rolling pressure is along the radial direction of the rotor assembly. And simulating a ring rolling deformation process by using a finite element simulation method before ring rolling, and determining an equivalent plastic strain value e of each region. The ring rolling process parameters are regulated, so that the equivalent plastic strain value of the blank drum 120 is more than or equal to 0.7 (the minimum value is 0.7). Meanwhile, a region with an equivalent plastic strain value more than 2 after ring rolling is determined according to the simulation result.
And (5) machining the product after ring rolling. As shown in fig. 4, the dashed box shows the area 31 removed by machining. The region 31 includes a defective region 33 (e.g., crack, fold) caused by ring rolling and a region 32 where an equivalent plastic strain value (e) > 2 occurs in ring rolling.
Fig. 4 shows a rotor assembly. As shown in fig. 4, blank disc 100 is machined to form a rotor assembly disc 200. Disc 200 includes a radially inner hub 212, a web 214 extending radially outwardly from hub 212, and a rim 216 extending radially outwardly from web 214. The blank drum 120 is machined to form a rotor assembly drum 220. The drum 220 is an annular flange projecting from the radial flange 216 in a direction axially along the central axis of rotation 30 of the rotor assembly. The inner diameter of the drum 220 is
The outer diameter is->
The thickness h5 of the web 214 is 19mm, and the thickness h6 of the drum 200 is 58mm + -2 mm.
And carrying out solution heat treatment on the product of the last step, wherein the heat treatment temperature is 50 ℃ below the beta phase transition point, and the heat preservation is carried out for 1 hour, and the air cooling is carried out.
The product of the previous step is subjected to an aging heat treatment at a temperature of about 600 c for 8 hours and then air cooled.
The integrally formed blank was dissected and its microstructure was observed using an optical microscope. The observation results show that:
(1) Hub 212, web 214 and rim 216 are typically alpha + beta phase bin structures, and the microstructure of rim 216 is shown in fig. 5 as being typically alpha + beta phase bin structures.
(2) Drum 200 is a typical beta-phase basket tissue, and the microstructure is shown in fig. 6, and is a typical basket tissue.
From the above, example 1 did result in a titanium alloy rotor assembly having dual performance through an integral molding process.
Although specific embodiments of the invention have been described in detail, those skilled in the art will appreciate that: many modifications and variations of details may be made to the disclosed embodiments in light of the overall teachings of the invention and remain within its scope. The full scope of the invention is given by the appended claims and any equivalents thereof.
Claims (9)
1. A method of preparing a rotor assembly for an engine, comprising:
(1) Providing a titanium alloy raw material, heating the titanium alloy raw material to a temperature T 1 Then die forging is carried out on the titanium alloy raw material, and a rotor assembly blank (10) is obtained by machining after the die forging, wherein T is 1 The temperature is 25-40 ℃ below the beta transformation point of the titanium alloy;
wherein the rotor assembly blank (10) comprises a blank disc portion (100) and a blank drum portion (120), the blank drum portion (120) is an annular flange protruding from one side surface of the blank disc portion (100), and the protruding direction is along the axial direction of the central rotation axis (30) of the rotor assembly;
(2) Heating the blank drum (120) to a temperature T of the blank drum (120) 2 Then ring rolling is carried out on the blank drum part (120), the pressure direction of the ring rolling is along the radial direction, wherein T is as follows 2 20-50 ℃ above the beta transformation point of the titanium alloy; the method comprises the steps of simulating a ring rolling deformation process by using a finite element simulation method before ring rolling, determining an equivalent plastic strain value e of each region, and regulating and controlling ring rolling process parameters to ensure that the equivalent plastic strain value of a blank drum part is more than or equal to 0.7;
(3) Heating the product of the previous step to a temperature T 3 Preserving heat for 0.5-1.5 h, and then cooling by air or cooling at a lower speed, wherein T is 3 Is 10-50 ℃ below the beta transformation point of the titanium alloy;
(4) Heating the product of the previous step to a temperature T 4 Preserving heat for 6-10 h, and then cooling by air or slower, wherein T is 4 550-650 ℃;
wherein, the steps (2) and (3) further comprise the following steps: machining the product in the step (2) according to the shape and size requirements of the rotor assembly product, removing areas with equivalent plastic strain e & gt 2 of the blank disc part (100) and the blank drum part (120) in the ring rolling process through machining, and removing areas with macroscopic defects on the blank disc part (100) and the blank drum part (120) through machining;
after the processing in the step (4), the blank disc (100) or the product thereof after the mechanical processing contains a bimodal structure, and the blank drum (120) or the product thereof after the mechanical processing contains a basket structure.
2. A method according to claim 1, wherein more than 10% of machining allowance in the axial direction is reserved at any point of the blank disc (100) in the radial direction of the rotor assembly.
3. A method according to claim 1, wherein more than 10% of the machining allowance in the radial direction is reserved at any point of the blank drum (120) in the axial direction of the rotor assembly.
4. The method of claim 1, wherein in step (1), the titanium alloy feedstock is obtained by: heating the titanium alloy bar stock to a temperature T 1 Upsetting, wherein the upsetting deformation is controlled to be 40-60%, and the upsetting is obtained.
5. The method of claim 1, wherein in step (2), the blank drum (120) is heated using a heat source, and the heat source is not in contact with the blank tray (100).
6. The method of claim 5, wherein in step (2), the blank tray portion (100) is insulated from the heat source by an insulating layer while the blank drum portion (120) is heated using the heat source.
7. The method according to claim 1 to 4, wherein,
the blank disc (100) is machined to form a disc 200 of the rotor assembly, the disc 200 including a radially inner hub (212), a web (214) extending radially outwardly from the hub (212), and a rim (216) extending radially outwardly from the web (214);
the blank drum (120) is machined to form a rotor assembly drum (220), the drum (220) being formed as an annular flange projecting from the radial flange (216) in a direction axially along a central rotational axis (30) of the rotor assembly.
8. The method of claim 1, the titanium alloy being a near alpha titanium alloy.
9. A rotor assembly for an engine, prepared by the method of any one of claims 1 to 8.
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Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101804441A (en) * | 2008-12-25 | 2010-08-18 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of TC17 biphase titanium alloy disc forge piece |
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| CN1159472C (en) * | 2001-09-04 | 2004-07-28 | 北京航空材料研究院 | Titanium alloy quasi-beta forging process |
| US20080124210A1 (en) * | 2006-11-28 | 2008-05-29 | Peter Wayte | Rotary assembly components and methods of fabricating such components |
| US8083872B2 (en) * | 2007-08-03 | 2011-12-27 | Rolls-Royce Plc | Method of heat treating a superalloy component and an alloy component |
| CN101480689B (en) * | 2008-12-25 | 2010-12-29 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of two-phase titanium alloy disk-type forgeable piece |
| KR101512164B1 (en) * | 2013-12-20 | 2015-04-16 | 주식회사 케이,에스,피 | Manufacturing method of Titanium alloy blade for steam turbine |
| CN105728617A (en) * | 2014-12-12 | 2016-07-06 | 陕西宏远航空锻造有限责任公司 | Ti60 titanium alloy isothermal forging and heat treatment method |
| CN106862452A (en) * | 2015-12-14 | 2017-06-20 | 陕西宏远航空锻造有限责任公司 | A kind of isothermal β forging methods of TC17 titanium alloys blisk |
| CN107470526A (en) * | 2016-12-01 | 2017-12-15 | 贵州安大航空锻造有限责任公司 | The rolling and fetal membrane forging of the double flange semi-rings of titanium alloy are unified into shape method |
| CN107803454A (en) * | 2017-10-24 | 2018-03-16 | 陕西海恩得工贸有限公司 | A kind of method for forging and molding of high tenacity titanacycle |
| CN109439936B (en) * | 2018-12-19 | 2020-11-20 | 宝钛集团有限公司 | Preparation method of medium-strength high-toughness titanium alloy ultra-large-specification ring material |
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| CN101804441A (en) * | 2008-12-25 | 2010-08-18 | 贵州安大航空锻造有限责任公司 | Near-isothermal forging method of TC17 biphase titanium alloy disc forge piece |
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