CN113664199A - Hot isostatic pressing near-net forming method for turbine blade of aero-engine - Google Patents
Hot isostatic pressing near-net forming method for turbine blade of aero-engine Download PDFInfo
- Publication number
- CN113664199A CN113664199A CN202110959791.0A CN202110959791A CN113664199A CN 113664199 A CN113664199 A CN 113664199A CN 202110959791 A CN202110959791 A CN 202110959791A CN 113664199 A CN113664199 A CN 113664199A
- Authority
- CN
- China
- Prior art keywords
- main body
- blade
- hot isostatic
- isostatic pressing
- sheath
- 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.)
- Pending
Links
- 238000001513 hot isostatic pressing Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 31
- 239000000843 powder Substances 0.000 claims abstract description 42
- 238000010438 heat treatment Methods 0.000 claims abstract description 20
- 238000000280 densification Methods 0.000 claims abstract description 17
- 229910052751 metal Inorganic materials 0.000 claims abstract description 15
- 239000002184 metal Substances 0.000 claims abstract description 15
- 238000003466 welding Methods 0.000 claims abstract description 11
- 239000002253 acid Substances 0.000 claims abstract description 10
- 230000007797 corrosion Effects 0.000 claims abstract description 9
- 238000005260 corrosion Methods 0.000 claims abstract description 9
- 238000012545 processing Methods 0.000 claims abstract description 8
- 238000011049 filling Methods 0.000 claims abstract description 7
- 238000007789 sealing Methods 0.000 claims abstract description 7
- 229910045601 alloy Inorganic materials 0.000 claims description 14
- 239000000956 alloy Substances 0.000 claims description 14
- 238000004321 preservation Methods 0.000 claims description 11
- 239000000203 mixture Substances 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 7
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 claims description 6
- 229910017604 nitric acid Inorganic materials 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000005056 compaction Methods 0.000 claims 2
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000000465 moulding Methods 0.000 description 6
- 230000006872 improvement Effects 0.000 description 5
- 229910052786 argon Inorganic materials 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 238000005495 investment casting Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910010038 TiAl Inorganic materials 0.000 description 1
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
- B22F2003/153—Hot isostatic pressing apparatus specific to HIP
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
Abstract
The invention discloses a hot isostatic pressing near-net forming method for turbine blades of an aero-engine, which is characterized by comprising the following steps: step 1, designing a sheath; step 2, filling metal powder into the sheath obtained in the step 1, and fully compacting the metal powder until the concave cavity and the half cavity are filled with the metal powder; step 3, heating and vacuumizing the sheath obtained in the step 2, and then welding and sealing the convex part and the concave part of the main body; step 4, placing the sheath obtained in the step 3 into a hot isostatic pressing furnace for hot isostatic pressing densification; step 5, removing acid corrosion of the sheath obtained in the step 4 to obtain a blade blank; step 6, carrying out vacuum heat treatment on the blade blank obtained in the step 5; and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
Description
Technical Field
The invention belongs to the technical field of preparation of blades of aero-generators, and particularly relates to a hot isostatic pressing near-net forming method for blades of aero-engines.
Background
The low-pressure turbine blade of the aeroengine is an important component part of the aeroengine turbine, and the manufacturing method of the low-pressure turbine blade mainly comprises the following steps: precision casting molding, isothermal die forging, additive manufacturing and the like. Wherein: (1) the main problems of the precision casting molding process are that the blade is easy to generate metallurgical defects such as looseness, inclusion and the like, and the dimensional precision of the blade is difficult to control, so that the qualification rate (especially in the initial development stage) of the TiAl alloy turbine blade prepared by the precision casting molding process is low. In addition, the microstructure of the cast blade is relatively coarse (such as the cast structure of Ti4822 alloy), the structure difference is large according to different parts of the blade, and the cast structure has a certain risk of microtexture, so that the material property dispersion of the cast blade is large and the property is relatively low. (2) The titanium-aluminum alloy has large brittleness and low plasticity, and the isothermal die forging has a narrow process window, so the processing difficulty is high, and the cost is high; (3) although the molding difficulty of the molding technology of additive manufacturing is low, the molded blade has a coarse structure and anisotropy, the molding temperature needs to be preheated to over 700 ℃, the powder is sintered, the powder is difficult to recover, and the manufacturing cost is high.
Disclosure of Invention
The invention aims to provide a hot isostatic pressing near-net forming method for an aero-engine turbine blade, which solves the problems of low yield and high manufacturing cost in the prior art for preparing an aero-engine low-pressure turbine blade.
In order to achieve the purpose, the invention adopts the technical scheme that: a hot isostatic pressing near-net forming method for an aeroengine turbine blade is implemented according to the following steps:
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine
The technical scheme of the invention also has the following characteristics:
as a further improvement of the technical solution of the present invention, in the step 2, the metal powder is Ti4822 alloy powder.
As a further improvement of the technical scheme of the invention, in the step 3, the vacuum environment is vacuumizedVacuum degree not higher than 5X 10-2Pa。
As a further improvement of the technical scheme of the invention, in the step 4, the equivalent pressure of the hot isostatic pressing densification treatment is not less than 150MPa, the hot isostatic pressing densification treatment temperature is 900-1100 ℃, and the heat preservation time is 2-4 h.
As a further improvement of the technical solution of the present invention, in the step 4: the main body convex, the main body concave, the upper cover and the lower cover are all made of steel, and the acid corrosion of the sheath is removed by using 30% -50% nitric acid solution.
As a further improvement of the technical solution of the present invention, in the step 6, the vacuum degree of the vacuum heat treatment is not higher than 4 x 10-3Pa, the temperature is 1250-1400 ℃, the heat preservation time is 2h, and finally the mixture is cooled by a vacuum furnace.
The invention has the beneficial effects that: (1) according to the hot isostatic pressing near-net forming method for the turbine blade of the aero-engine, the blank structure of the low-pressure turbine blade is optimized, the density of the blade is guaranteed, and the yield is improved; (2) the hot isostatic pressing near-net forming method for the turbine blade of the aero-engine, disclosed by the invention, has the advantages of high process controllability, high yield and production cost reduction; (3) the hot isostatic pressing near-net forming method for the turbine blade of the aero-engine, disclosed by the invention, realizes the performance isotropy of the low-pressure turbine blade material; (4) according to the hot isostatic pressing near-net forming method for the turbine blade of the aero-engine, the grain structure of the blade prepared by the process is fine, and the strength and the shape of the blade are improved; (5) compared with the traditional process, the hot isostatic pressing near-net forming method for the turbine blade of the aero-engine has the advantages of small machining amount and few internal defects.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a jacket structure
FIG. 2 is a cross-sectional view of a jacket;
FIG. 3 is a schematic view of the main body protrusion of the jacket;
FIG. 4 is a schematic view of the mechanism of the body recess of the capsule;
FIG. 5 is a schematic view of the construction of the upper cover of the jacket;
fig. 6 is a schematic view of the structure of the lower cover of the jacket.
In the figure: 1. the main body is convex, 2, the main body is concave, 3, the upper cover, 4, the powder inlet pipe, 5, the plug and 6, the lower cover.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
The invention discloses a hot isostatic pressing near-net forming method for turbine blades of an aero-engine, which is implemented according to the following steps:
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
As shown in fig. 1 and fig. 2, steel is selected as the preparation material of the sheath (the steel sheath has low cost, good welding performance and easy acid etching removal). The sheath mainly comprises the following structures: the main body is convex 1, the main body is concave 2, the upper cover 3, the lower cover 6, the powder inlet pipe 4 and the plug 5. The main body convex 1 is connected with the main body concave 2 through argon arc welding, and the main body convex 1 and the main body concave 2 are combined together according to assembly requirements to form a blade blank cavity similar to the shape of a turbine blade together and form mounting holes matched with the upper cover and the lower cover at two ends respectively.
As shown in fig. 3, the main body protrusion 1 has a rectangular parallelepiped structure, a protrusion body is formed at the middle thereof in a shape similar to the shape of the blade of the turbine blade, and half cavities are formed at both ends thereof in a shape similar to the shape of both ends of the turbine blade.
As shown in fig. 4, the main body 2 is a rectangular parallelepiped, a concave cavity similar to the blade-shaped portion of the turbine blade is formed in the middle of the main body, and the other half of the cavity similar to the shape of the two ends of the turbine blade is formed at the two ends of the main body.
As shown in fig. 5, the upper cover 3 is in the shape of a thin-wall trapezoid table, is mounted at one end of the main body concave and the main body convex, and is connected by argon arc welding, a mounting hole 3-1 is formed at the top of the upper cover 3, a powder inlet pipe 4 is mounted in the mounting hole 3-1, and a plug 5 is mounted in the powder inlet pipe 4.
As shown in fig. 6, the lower cover 6 is also in the shape of a thin-walled trapezoidal table, which is installed at the other ends of the main body concavity and the main body convexity, connected by argon arc welding,
the Ti4822 alloy powder was prepared by a plasma rotary electrode method. The technological conditions for preparing the Ti4822 alloy spherical powder by the plasma rotating electrode method are as follows:
the size requirement of raw materials is as follows: the diameter of the electrode is 50 mm-60 mm, the length is 500mm-700mm, the straightness deviation of the electrode bar is controlled to be less than or equal to 0.1mm/m, the roughness is less than 1.6 mu m, and the chemical composition requirements of the electrode are shown in Table 1.
TABLE 1 chemical composition Table of electrode bar
The powder preparation process has the following parameter requirements: the current is 1000A-1500A; the voltage is 50V-60V; the rotating speed is 15000r/min-20000 r/min; 99.999 percent argon is used for protection in the powder preparation process.
The spherical powder used for the low pressure turbine blade has a particle size in the range of 100 μm to 300. mu.m.
The aero-engine turbine blade (low-pressure turbine blade) prepared by the aero-engine turbine blade hot isostatic pressing near-net forming method is isotropic in performance, and is excellent in tensile strength and yield strength, and the specific table is shown in the following table 2.
TABLE 2
Example 1
The invention discloses a hot isostatic pressing near-net forming method for turbine blades of an aero-engine, which is implemented according to the following steps:
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
Example 2
The invention discloses a hot isostatic pressing near-net forming method for turbine blades of an aero-engine, which is implemented according to the following steps:
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
Example 3
The invention discloses a hot isostatic pressing near-net forming method for turbine blades of an aero-engine, which is implemented according to the following steps:
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
While the foregoing description shows and describes several preferred embodiments of the invention, it is to be understood, as noted above, that the invention is not limited to the forms disclosed herein, but is not to be construed as excluding other embodiments and is capable of use in various other combinations, modifications, and environments and is capable of changes within the scope of the inventive concept as expressed herein, commensurate with the above teachings, or the skill or knowledge of the relevant art. And that modifications and variations may be effected by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (6)
1. A hot isostatic pressing near-net forming method for an aeroengine turbine blade is characterized by comprising the following steps:
step 1, designing a sheath, wherein the sheath is formed by buckling a main body convex and a main body concave, a convex body matched with the blade-shaped part of the turbine blade is formed in the middle of the main body convex, a concave cavity matched with the blade-shaped part of the turbine blade is formed in the middle of the main body concave, and half cavities matched with the turbine blade are formed in both ends of the main body convex and both ends of the main body concave; the two ends of the main body convex and the main body concave are respectively provided with a lower cover and an upper cover, and a powder inlet pipe is arranged in the upper cover;
step 2, filling metal powder into the sheath obtained in the step 1, and fully compacting the metal powder until the concave cavity and the half cavity are filled with the metal powder;
step 3, heating and vacuumizing the sheath obtained in the step 2, and then welding and sealing the convex part and the concave part of the main body;
step 4, placing the sheath obtained in the step 3 into a hot isostatic pressing furnace for hot isostatic pressing densification;
step 5, removing acid corrosion of the sheath obtained in the step 4 to obtain a blade blank;
step 6, carrying out vacuum heat treatment on the blade blank obtained in the step 5;
and 7, processing tenons and blade crowns at two ends of the blade blank obtained in the step 6 to obtain the turbine blade of the aero-engine.
2. The method of near net shape hot isostatic pressing of aeroengine turbine blades according to claim 1, wherein in step 2, the metal powder is a Ti4822 alloy powder.
3. The method of near net shape Hot Isostatic Pressing (HIP) of an aero-engine turbine blade as set forth in claim 2, wherein in step 3, the vacuum environment of the vacuuming process has a vacuum degree of not higher than 5 x 10-2Pa。
4. The method for near net shape hot isostatic pressing of aeroengine turbine blades according to claim 3, wherein in step 4, the isostatic compaction treatment has an isotropic pressure of not less than 150MPa, a hot isostatic compaction treatment temperature of 900-1100 ℃, and a holding time of 2-4 h.
5. The method of near net shape hot isostatic pressing of aeroengine turbine blades according to claim 4, wherein in step 4: the main body convex, the main body concave, the upper cover and the lower cover are all made of steel, and the acid corrosion of the sheath is removed by using 30% -50% nitric acid solution.
6. The method of near net shape hot isostatic pressing of aeroengine turbine blades according to claim 5, wherein at said step6, the vacuum degree of vacuum heat treatment is not higher than 4 x 10-3Pa, the temperature is 1250-1400 ℃, the heat preservation time is 2h, and finally the mixture is cooled by a vacuum furnace.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110959791.0A CN113664199A (en) | 2021-08-20 | 2021-08-20 | Hot isostatic pressing near-net forming method for turbine blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110959791.0A CN113664199A (en) | 2021-08-20 | 2021-08-20 | Hot isostatic pressing near-net forming method for turbine blade of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113664199A true CN113664199A (en) | 2021-11-19 |
Family
ID=78544324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110959791.0A Pending CN113664199A (en) | 2021-08-20 | 2021-08-20 | Hot isostatic pressing near-net forming method for turbine blade of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113664199A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115194314A (en) * | 2022-07-12 | 2022-10-18 | 南京航空航天大学 | Multifunctional field auxiliary manufacturing method for hollow turbine blade made of hard-to-deform material |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5424027A (en) * | 1993-12-06 | 1995-06-13 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce hot-worked gamma titanium aluminide articles |
| US20060083653A1 (en) * | 2004-10-20 | 2006-04-20 | Gopal Das | Low porosity powder metallurgy produced components |
| CN102513537A (en) * | 2011-12-06 | 2012-06-27 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing TiAl alloy plate by argon atomization in powder metallurgy |
| CN102632075A (en) * | 2012-04-28 | 2012-08-15 | 中南大学 | Preparation method of large-size thin plate of niobium-containing titanium-aluminum based alloy by powder metallurgy |
| US20160059312A1 (en) * | 2014-09-01 | 2016-03-03 | MTU Aero Engines AG | PRODUCTION PROCESS FOR TiAl COMPONENTS |
| CN112620634A (en) * | 2021-01-12 | 2021-04-09 | 西安欧中材料科技有限公司 | Preparation method of hollow outlet guide vane based on hot isostatic pressing process |
-
2021
- 2021-08-20 CN CN202110959791.0A patent/CN113664199A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5424027A (en) * | 1993-12-06 | 1995-06-13 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce hot-worked gamma titanium aluminide articles |
| US20060083653A1 (en) * | 2004-10-20 | 2006-04-20 | Gopal Das | Low porosity powder metallurgy produced components |
| CN102513537A (en) * | 2011-12-06 | 2012-06-27 | 中国航空工业集团公司北京航空材料研究院 | Method for preparing TiAl alloy plate by argon atomization in powder metallurgy |
| CN102632075A (en) * | 2012-04-28 | 2012-08-15 | 中南大学 | Preparation method of large-size thin plate of niobium-containing titanium-aluminum based alloy by powder metallurgy |
| US20160059312A1 (en) * | 2014-09-01 | 2016-03-03 | MTU Aero Engines AG | PRODUCTION PROCESS FOR TiAl COMPONENTS |
| CN112620634A (en) * | 2021-01-12 | 2021-04-09 | 西安欧中材料科技有限公司 | Preparation method of hollow outlet guide vane based on hot isostatic pressing process |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115194314A (en) * | 2022-07-12 | 2022-10-18 | 南京航空航天大学 | Multifunctional field auxiliary manufacturing method for hollow turbine blade made of hard-to-deform material |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103240412B (en) | Method for preparing powder super-alloy by near net shape | |
| CN103240418B (en) | Near-net shaping method for charging turbine with hollow internal structure | |
| CN104961467B (en) | A kind of high tenacity ceramic matric composite and preparation method and application | |
| JP4119750B2 (en) | Powder metallurgy for producing high density molded parts | |
| JP6342844B2 (en) | Turbine wheel manufacturing method | |
| US20170321303A1 (en) | A method of fabricating three-dimensional parts out of an alloy of aluminum and titanium | |
| CN106319457A (en) | Manufacturing method of tungsten titanium tube target | |
| CN104550956A (en) | Component preparation method through beta-gamma titanium-aluminum alloy prealloy powder spark plasma sintering | |
| EP3085472B1 (en) | Method of manufacturing a turbine blisk through hot isostatic pressing using a metal core | |
| CN106312071A (en) | A tungsten-titanium tube target manufacture method | |
| CN108838404A (en) | Titanium alloy low cost near-net-shape method | |
| CN113664199A (en) | Hot isostatic pressing near-net forming method for turbine blade of aero-engine | |
| CN112760538B (en) | Preparation method of vanadium-tungsten alloy target blank | |
| CN110181059A (en) | A kind of method of co-injection near-net-shape ultra-fine cemented carbide cutter green body | |
| CN110983152B (en) | Fe-Mn-Si-Cr-Ni based shape memory alloy and preparation method thereof | |
| CN105931777B (en) | A kind of preparation method of high tenacity samarium cobalt permanent magnet body | |
| CN105779816A (en) | Ti-Al-Zr ternary alloy target material and preparation method thereof | |
| WO2013111694A1 (en) | Blades for axial flow compressor and method for manufacturing same | |
| CN113652657A (en) | Aluminum-scandium alloy target material and manufacturing method adopting atmospheric high-temperature diffusion sintering molding | |
| CN110918976B (en) | Forming method of NiAl-based alloy component | |
| KR100509938B1 (en) | Method for fabricating TiAl intermetallic articles by metal injection molding | |
| CN114367663A (en) | Preparation method of fully-compact titanium alloy thin-wall part with complex shape | |
| JP2014001427A (en) | Method of manufacturing sintered component | |
| WO2016158345A1 (en) | Method for manufacturing cylindrical sputtering targets | |
| JPH11315304A (en) | Manufacture of sintered body |
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 | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Country or region after: China Address after: No.45, Fengcheng 2nd Road, economic development zone, Xi'an, Shaanxi 710018 Applicant after: Xi'an Ouzhong Materials Technology Co.,Ltd. Applicant after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: No.45, Fengcheng 2nd Road, economic development zone, Xi'an, Shaanxi 710018 Applicant before: XI'AN SINO-EURO MATERIALS TECHNOLOGIES Co.,Ltd. Country or region before: China Applicant before: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. |