CN106378456A - Rapid densifying method for powder high-temperature alloy component - Google Patents
Rapid densifying method for powder high-temperature alloy component Download PDFInfo
- Publication number
- CN106378456A CN106378456A CN201611022013.4A CN201611022013A CN106378456A CN 106378456 A CN106378456 A CN 106378456A CN 201611022013 A CN201611022013 A CN 201611022013A CN 106378456 A CN106378456 A CN 106378456A
- Authority
- CN
- China
- Prior art keywords
- powder
- ingot blank
- forging
- mould
- powder ingot
- 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
Links
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
- B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
-
- 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
- B22F3/10—Sintering only
-
- 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
- B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
- B22F2003/175—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging by hot forging, below sintering temperature
-
- 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
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
Abstract
The invention belongs to the technical field of direct forging forming of a powder high-temperature alloy component, and relates to the improvement of a preparation process for the powder high-temperature alloy component. The improvement of the preparation process for the powder high-temperature alloy component is implemented by the following steps: preparing a suitable powder ingot blank; designing a reasonable direct forging forming mould for powder; selecting forging process parameters. According to the technology, a sheath is filled with the powder, and the powder is forged and formed directly, so that a powder high-temperature alloy forging blank which has dense tissues and uniform and fine crystal grains can be obtained; the process flow is simplified; the research period is shortened; the component manufacturing cost is reduced.
Description
Technical field
The present invention is a kind of method for rapidly densifying for powder metallurgy superalloy component, belongs to technical field of hot working,
It is related to the improvement of powder metallurgy superalloy component preparation technology.
Background technology
Powder metallurgy superalloy is that the solidifying segregation causing to solve casting wrought alloy high-alloying develops with deforming difficult
The diskware material getting up.It is comprehensive that high-alloying powder metallurgy superalloy has high temperature resistant, high-strength tenacity and low crack growth rate etc.
The advantage of excellent performance, is to manufacture the high temperature resistant components such as high-performance, high reliability, the long-life advanced aero engine turbine disk
Preferred material.But, typically to temperature and its sensitivity, process window is narrow for high-alloying powder metallurgy superalloy, belongs to difficult deformation
Alloy, lead to technique execution and organizational controls during there be difficulties involved when.
External powder metallurgy superalloy is mainly used to prepare the hot-end components such as the high-performance enginer turbine disk, mainly adopts powder
The process preparation of high temperature insostatic pressing (HIP)+extruding+superplastic forging, its process characteristic is complex process, long preparation period, cost
High.
Content of the invention
The present invention is exactly directed to above-mentioned existing domestic the deficiencies in the prior art and designs and provide one kind for powder
The method for rapidly densifying of last superalloy components, its objective is to improve the production efficiency of powder metallurgy superalloy component.
The purpose of the present invention is achieved through the following technical solutions：
This kind be used for powder metallurgy superalloy component method for rapidly densifying it is characterised in that：The step of the method is：
Step one, the preparation of powder ingot blank
Volume according to component calculates and makes cylindrical stainless steel capsule, and the trade mark of stainless steel material is 304, and high temperature is closed
Bronze end is filled in jacket, to soldering and sealing after the evacuation of jacket inside, obtains columned powder ingot blank (5), in powder ingot blank
(5) upper end, by being welded to connect a upper end cover (4) for protecting jacket powder inlet pipe, leads in the lower end of powder ingot blank (5)
Cross be welded to connect one with upper end cover (4) form fit make the pressurized uniform bottom end cover (6) of jacket；
Step 2, prepare forging mold
Forging mold is prepared using the Steel material more than 2000MPa for the fracture strength, this forging mold is by circular upper mould
(2), mould outer tube (3) and circular lower die-cushion block (1) constitute forging die cavity, and wherein, circular lower die-cushion block (1) is fixing
On the lower table of press, the circular excircle of lower die-cushion block (1) is fitted close with the inwall of mould outer tube (3), lower end
The bottom of lid (6) is arranged on lower die-cushion block (1) above, and mould outer tube (3) inner sleeve loads onto mould (2), the inwall of mould outer tube (3) with
Gap between the outer circumference surface of upper mould (2) is 5mm, and upper mould (2) can slide up and down in the inner chamber of mould outer tube (3), on
Mould (2) is arranged on the upper table of press, and the top of upper end cover (4) is contacted with the bottom of upper mould (2), in this forging mold,
The big 3mm of outer annular diameter of the upper and lower end cap than powder ingot blank (5) for the intracavity diameter of mould outer tube (3)；
Step 3, heating powder ingot blank (5)
Powder ingot blank (5) is heated to 1050 DEG C, is incubated, temperature retention time calculates as follows：
TTemperature retention time=LPowder ingot blank diameter× 1.7min/mm formula 1
The direct forging molding of step 4, powder
Powder ingot blank (5) after insulation is put into rapid forge molding in forging die cavity, the transfer of powder ingot blank (5)
Within 1min, Forging Equipment Speed is 17mm/s～20mm/s to time control, in forging process, works with being arranged on press
The decline of the upper mould (2) on platform, powder ingot blank (5) in forging die cavity to surrounding expansion deformation, with forging die cavity
After contact in the state of three dimension stress, the superalloy powder in powder ingot blank (5) start mutually to collide with plastic deformation after
Molding, the pressure in forming process is 800～1300MPa, and dwell time of molding is 5～60s, the deflection of molding is 50～
60%, then by powder ingot blank (5) depanning, it is placed in natural cooling in asbestic blanket；
Step 5, jacket remove
After powder ingot blank (5) cooling, blast, and jacket is removed using the method for machining, obtain powder metallurgy superalloy
Component.
Technical solution of the present invention has the special feature that with beneficial effect is：
Present invention is generally directed to powder metallurgy superalloy component is prepared using high temperature insostatic pressing (HIP)+isothermal forging process there is forging system
The high state of the art of standby cycle length, manufacturing cost, the method with the direct forging molding of powder is quiet to substitute original powder heat etc.
The mode of pressure+isothermal forging, solves long preparation period, the high problem of manufacturing cost.
The ultimate principle of the inventive method is the mobility that make use of dusty material good, powder is attached to prefabricated in jacket
Become ingot blank, then dusty material is heated to more than recrystallization temperature, in forging mold, using deformation velocity faster with relatively
Under high-stress state power, powder particle is made to produce severe plastic deformation, compared to the deflection of high temperature insostatic pressing (HIP) generally 10%, this
Deflection in technical scheme increases substantially to 50～60%, promotes recrystallization to occur, the primary granule border of powder obtains
Broken, thus preparing dense structure and there is the powder metallurgy superalloy component of tiny recrystal grain.
, with compared with the technology of preparing of domestic and international powder metallurgy superalloy annular construction member, its advantage is main for technical solution of the present invention
It is embodied in：
(1) utilize the good mobility of powder, powder loaded direct forging molding forging stock in pre-designed jacket,
Decrease forging stock allowance, improve forging stock utilization；
(2) dusty material is heated to more than recrystallization temperature, under very fast deformation velocity and higher stress state power, makes
Powder particle produces severe plastic deformation recrystallization, the forging stock dense structure preparing and to have tiny recrystallization brilliant
Grain；
(3) powder loads direct forging molding in jacket, simplifies technological process, shortens the lead time, reduces component
Manufacturing cost.
Brief description
Fig. 1 is the structural representation of forging mold in technical solution of the present invention
Fig. 2 is the microstructure morphology of the total component of high temperature of technical solution of the present invention embodiment 1
Fig. 3 is the microstructure morphology of the total component of high temperature of technical solution of the present invention embodiment 2
Specific embodiment
Below with reference to embodiment, technical solution of the present invention is further described：
Embodiment 1
This kind be used for powder metallurgy superalloy component quick forming method it is characterised in that：The step of the method is：
Step one, the preparation of powder ingot blank
Volume according to component calculates and makes cylindrical stainless steel capsule, and the trade mark of stainless steel material is 304, and high temperature is closed
Bronze end is filled in jacket, to soldering and sealing after the evacuation of jacket inside, obtains columned powder ingot blank 5, in powder ingot blank 5
Upper end, by being welded to connect a upper end cover 4 for protecting jacket powder inlet pipe, is passed through to be welded to connect in the lower end of powder ingot blank 5
One makes the pressurized uniform bottom end cover 6 of jacket with upper end cover 4 form fit；
Step 2, prepare forging mold
Forging mold is prepared using the Steel material more than 2000MPa for the fracture strength, this forging mold by circular upper mould 2,
Mould outer tube 3 and circular lower die-cushion block 1 constitute forging die cavity, and wherein, circular lower die-cushion block 1 is fixed under press
On workbench, the circular excircle of lower die-cushion block 1 is fitted close with the inwall of mould outer tube 3, and the bottom of bottom end cover 6 is arranged on
Above lower die-cushion block 1, mould outer tube 3 inner sleeve loads onto mould 2, the gap between the outer circumference surface of the inwall of mould outer tube 3 and upper mould 2
For 5mm, upper mould 2 can slide up and down in the inner chamber of mould outer tube 3, and upper mould 2 is arranged on the upper table of press, upper end cover
4 top is contacted with the bottom of upper mould 2, and in this forging mold, the intracavity diameter of mould outer tube 3 is than the upper and lower end of powder ingot blank 5
The big 3mm of outer annular diameter of lid；
Step 3, heating powder ingot blank 5
Powder ingot blank 5 is heated to 1050 DEG C, is incubated, temperature retention time calculates as follows：
TTemperature retention time=LPowder ingot blank diameter× 1.7min/mm formula 1
The direct forging molding of step 4, powder
Powder ingot blank 5 after insulation is put into rapid forge molding in forging die cavity, the transfer time of powder ingot blank 5
Control within 1min, Forging Equipment Speed is 17mm/s, in forging process, with the upper mould 2 being arranged on press upper table
Decline, powder ingot blank 5 in forging die cavity to surrounding expansion deformation, in three dimension stress after contacting with forging die cavity
In the state of, the superalloy powder in powder ingot blank 5 starts mutually to collide and plastic deformation aftershaping, the pressure in forming process
Power is 900MPa, and the dwell time of molding is 5s, and the deflection of molding is 50%, then by powder ingot blank 5 depanning, is placed in asbestos
Natural cooling in felt；
Step 5, jacket remove
After powder ingot blank 5 cooling, blast, and jacket is removed using the method for machining, obtain powder metallurgy superalloy structure
Part.
Referring to shown in accompanying drawing 2, the microstructure of powder metallurgy superalloy annular construction member uniformly, can't see obvious primary granule
Border.
Embodiment 2
This kind be used for powder metallurgy superalloy component quick forming method it is characterised in that：The step of the method is：
Step one, the preparation of powder ingot blank
Volume according to component calculates and makes cylindrical stainless steel capsule, and the trade mark of stainless steel material is 304, and high temperature is closed
Bronze end is filled in jacket, to soldering and sealing after the evacuation of jacket inside, obtains columned powder ingot blank 5, in powder ingot blank 5
Upper end, by being welded to connect a upper end cover 4 for protecting jacket powder inlet pipe, is passed through to be welded to connect in the lower end of powder ingot blank 5
One makes the pressurized uniform bottom end cover 6 of jacket with upper end cover 4 form fit；
Step 2, prepare forging mold
Forging mold is prepared using the Steel material more than 2000MPa for the fracture strength, this forging mold by circular upper mould 2,
Mould outer tube 3 and circular lower die-cushion block 1 constitute forging die cavity, and wherein, circular lower die-cushion block 1 is fixed under press
On workbench, the circular excircle of lower die-cushion block 1 is fitted close with the inwall of mould outer tube 3, and the bottom of bottom end cover 6 is arranged on
Above lower die-cushion block 1, mould outer tube 3 inner sleeve loads onto mould 2, the gap between the outer circumference surface of the inwall of mould outer tube 3 and upper mould 2
For 5mm, upper mould 2 can slide up and down in the inner chamber of mould outer tube 3, and upper mould 2 is arranged on the upper table of press, upper end cover
4 top is contacted with the bottom of upper mould 2, and in this forging mold, the intracavity diameter of mould outer tube 3 is than the upper and lower end of powder ingot blank 5
The big 3mm of outer annular diameter of lid；
Step 3, heating powder ingot blank 5
Powder ingot blank 5 is heated to 1100 DEG C, is incubated, temperature retention time calculates as follows：
TTemperature retention time=LPowder ingot blank diameter× 1.7min/mm formula 1
The direct forging molding of step 4, powder
Powder ingot blank 5 after insulation is put into rapid forge molding in forging die cavity, the transfer time of powder ingot blank 5
Control within 1min, Forging Equipment Speed is 20mm/s, in forging process, with the upper mould 2 being arranged on press upper table
Decline, powder ingot blank 5 in forging die cavity to surrounding expansion deformation, in three dimension stress after contacting with forging die cavity
In the state of, the superalloy powder in powder ingot blank 5 starts mutually to collide and plastic deformation aftershaping, the pressure in forming process
Power is 1200MPa, and the dwell time of molding is 30s, and the deflection of molding is 60%, then by powder ingot blank 5 depanning, is placed in stone
Natural cooling in cotton felt；
Step 5, jacket remove
After powder ingot blank 5 cooling, blast, and jacket is removed using the method for machining, obtain powder metallurgy superalloy structure
Part.
Referring to shown in accompanying drawing 3, the microstructure of powder metallurgy superalloy component uniformly, can't see obvious primary granule side
Boundary.
Claims (1)
1. a kind of method for rapidly densifying for powder metallurgy superalloy component it is characterised in that：The step of the method is：
Step one, the preparation of powder ingot blank
Volume according to component calculates and makes cylindrical stainless steel capsule, and the trade mark of stainless steel material is 304, by high temperature alloy powder
End is filled in jacket, to soldering and sealing after the evacuation of jacket inside, obtains columned powder ingot blank (5), in powder ingot blank (5)
Welding, by being welded to connect a upper end cover (4) for protecting jacket powder inlet pipe, is passed through in the lower end of powder ingot blank (5) in upper end
Connecting one makes the pressurized uniform bottom end cover (6) of jacket with upper end cover (4) form fit；
Step 2, prepare forging mold
Forging mold is prepared using the Steel material more than 2000MPa for the fracture strength, this forging mold is by circular upper mould (2), mould
Tool outer tube (3) and circular lower die-cushion block (1) constitute forging die cavity, and wherein, circular lower die-cushion block (1) is fixed on press
Lower table on, the circular excircle of lower die-cushion block (1) is fitted close with the inwall of mould outer tube (3), bottom end cover (6)
Bottom is arranged on lower die-cushion block (1) above, and mould outer tube (3) inner sleeve loads onto mould (2), the inwall of mould outer tube (3) and upper mould (2)
Outer circumference surface between gap be 5mm, upper mould (2) can slide up and down in the inner chamber of mould outer tube (3), upper mould (2) peace
It is contained on the upper table of press, the top of upper end cover (4) is contacted with the bottom of upper mould (2), in this forging mold, mould outer tube
(3) the big 3mm of outer annular diameter of the upper and lower end cap than powder ingot blank (5) for the intracavity diameter；
Step 3, heating powder ingot blank (5)
Powder ingot blank (5) is heated to 1050 DEG C, is incubated, temperature retention time calculates as follows：
TTemperature retention time=LPowder ingot blank diameter× 1.7min/mm formula 1
The direct forging molding of step 4, powder
Powder ingot blank (5) after insulation is put into rapid forge molding in forging die cavity, the transfer time of powder ingot blank (5)
Control within 1min, Forging Equipment Speed is 17mm/s～20mm/s, in forging process, with being arranged on press upper table
Upper mould (2) decline, powder ingot blank (5) to surrounding expansion deformation, contacted with forging die cavity in forging die cavity
Afterwards in the state of three dimension stress, the superalloy powder in powder ingot blank (5) starts mutually to collide and plastic deformation aftershaping,
Pressure in forming process is 800～1300MPa, and the dwell time of molding is 5～60s, and the deflection of molding is 50～60%,
Then by powder ingot blank (5) depanning, it is placed in natural cooling in asbestic blanket；
Step 5, jacket remove
After powder ingot blank (5) cooling, blast, and jacket is removed using the method for machining, obtain powder metallurgy superalloy component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611022013.4A CN106378456B (en) | 2016-11-16 | 2016-11-16 | A kind of method for rapidly densifying for powder metallurgy superalloy component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611022013.4A CN106378456B (en) | 2016-11-16 | 2016-11-16 | A kind of method for rapidly densifying for powder metallurgy superalloy component |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106378456A true CN106378456A (en) | 2017-02-08 |
| CN106378456B CN106378456B (en) | 2018-01-19 |
Family
ID=57959030
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611022013.4A Active CN106378456B (en) | 2016-11-16 | 2016-11-16 | A kind of method for rapidly densifying for powder metallurgy superalloy component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106378456B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109226750A (en) * | 2018-10-26 | 2019-01-18 | 中国航发北京航空材料研究院 | Quick forming method for the powder metallurgy titanium alloy blade prefabricated blank with damping boss |
| CN109622834A (en) * | 2018-11-26 | 2019-04-16 | 抚顺特殊钢股份有限公司 | A kind of forging method of powder metallurgy superalloy bar |
| CN110116203A (en) * | 2019-06-06 | 2019-08-13 | 西北有色金属研究院 | A method of eliminating Ni-base P/M Superalloy primary granule border |
| CN111299586A (en) * | 2020-04-01 | 2020-06-19 | 上海交通大学 | Low-cost titanium-based composite material component powder direct forging forming method |
| CN112077324A (en) * | 2020-09-04 | 2020-12-15 | 中国航发北京航空材料研究院 | Horizontal extrusion integrated sheath for powder high-temperature alloy and manufacturing method thereof |
| CN112170846A (en) * | 2020-10-30 | 2021-01-05 | 中国航发湖南动力机械研究所 | Powder turbine disk blank forming method and powder turbine disk blank |
| CN112404427A (en) * | 2020-10-30 | 2021-02-26 | 西北工业大学 | Method for directly forging and forming thick plate blank by TiAl alloy powder at high temperature |
| CN114789250A (en) * | 2022-04-07 | 2022-07-26 | 中国航发北京航空材料研究院 | Preparation method of powder high-temperature alloy cylindrical straight gear component |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5839707A (en) * | 1981-09-01 | 1983-03-08 | Kobe Steel Ltd | High density sintering method for powder molding |
| EP0086417A2 (en) * | 1982-02-13 | 1983-08-24 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Case for the hot isostatic pressing of intricately shaped high-duty service parts of turbo machines |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
| CN102672174A (en) * | 2012-05-15 | 2012-09-19 | 华中科技大学 | Method for manufacturing integral annular case part by using hot isostatic pressing process |
| CN103008659A (en) * | 2011-09-28 | 2013-04-03 | 宝山钢铁股份有限公司 | Manufacturing method of ultra-fine grain high-temperature alloy plate blanks |
| CN103551573A (en) * | 2013-10-22 | 2014-02-05 | 中国科学院金属研究所 | Previous particle boundary precipitation preventable high-temperature alloy powder hot isostatic pressing process |
| CN103691952A (en) * | 2014-01-06 | 2014-04-02 | 钢铁研究总院 | Preparation method of functional gradient performance coil |
| CN104493167A (en) * | 2014-11-20 | 2015-04-08 | 中国航空工业集团公司北京航空材料研究院 | Method for forming powder high-temperature alloy annular member |
-
2016
- 2016-11-16 CN CN201611022013.4A patent/CN106378456B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5839707A (en) * | 1981-09-01 | 1983-03-08 | Kobe Steel Ltd | High density sintering method for powder molding |
| EP0086417A2 (en) * | 1982-02-13 | 1983-08-24 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Case for the hot isostatic pressing of intricately shaped high-duty service parts of turbo machines |
| CN103008659A (en) * | 2011-09-28 | 2013-04-03 | 宝山钢铁股份有限公司 | Manufacturing method of ultra-fine grain high-temperature alloy plate blanks |
| CN102615284A (en) * | 2012-04-26 | 2012-08-01 | 西北工业大学 | Manufacturing method for double-structure turbine disk |
| CN102672174A (en) * | 2012-05-15 | 2012-09-19 | 华中科技大学 | Method for manufacturing integral annular case part by using hot isostatic pressing process |
| CN103551573A (en) * | 2013-10-22 | 2014-02-05 | 中国科学院金属研究所 | Previous particle boundary precipitation preventable high-temperature alloy powder hot isostatic pressing process |
| CN103691952A (en) * | 2014-01-06 | 2014-04-02 | 钢铁研究总院 | Preparation method of functional gradient performance coil |
| CN104493167A (en) * | 2014-11-20 | 2015-04-08 | 中国航空工业集团公司北京航空材料研究院 | Method for forming powder high-temperature alloy annular member |
Non-Patent Citations (5)
| Title |
|---|
| BLANKENSHIP CP等: "RECRYSTALLIZATION AND GRAIN-GROWTH IN STRAIN GRADIENT SAMPLES", 《SCRIPTA METALLURGICA ET MATERIALIA》 * |
| CHEN ZE LIU等: "Effect of hot extrusion and heat treatment on microstructure of nickel-base superalloy", 《TRANS. NONFERROUS MET. SOC. CHINA》 * |
| 李园春等: "国内粉末高温合金涡轮盘件制造技术的发展现状", 《稀有金属》 * |
| 王淑云等: "粉末高温合金超塑性等温锻造技术研究", 《航空材料学报》 * |
| 王超渊等: "变形温度及变形量对挤压态FGH96合金晶粒异常长大的影响", 《航空材料学报》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109226750A (en) * | 2018-10-26 | 2019-01-18 | 中国航发北京航空材料研究院 | Quick forming method for the powder metallurgy titanium alloy blade prefabricated blank with damping boss |
| CN109226750B (en) * | 2018-10-26 | 2021-02-09 | 中国航发北京航空材料研究院 | Rapid forming method for powder titanium alloy blade prefabricated blank with damping boss |
| CN109622834A (en) * | 2018-11-26 | 2019-04-16 | 抚顺特殊钢股份有限公司 | A kind of forging method of powder metallurgy superalloy bar |
| CN110116203A (en) * | 2019-06-06 | 2019-08-13 | 西北有色金属研究院 | A method of eliminating Ni-base P/M Superalloy primary granule border |
| CN111299586A (en) * | 2020-04-01 | 2020-06-19 | 上海交通大学 | Low-cost titanium-based composite material component powder direct forging forming method |
| CN112077324A (en) * | 2020-09-04 | 2020-12-15 | 中国航发北京航空材料研究院 | Horizontal extrusion integrated sheath for powder high-temperature alloy and manufacturing method thereof |
| CN112170846A (en) * | 2020-10-30 | 2021-01-05 | 中国航发湖南动力机械研究所 | Powder turbine disk blank forming method and powder turbine disk blank |
| CN112404427A (en) * | 2020-10-30 | 2021-02-26 | 西北工业大学 | Method for directly forging and forming thick plate blank by TiAl alloy powder at high temperature |
| CN112170846B (en) * | 2020-10-30 | 2022-03-08 | 中国航发湖南动力机械研究所 | Powder turbine disk blank forming method and powder turbine disk blank |
| CN114789250A (en) * | 2022-04-07 | 2022-07-26 | 中国航发北京航空材料研究院 | Preparation method of powder high-temperature alloy cylindrical straight gear component |
| CN114789250B (en) * | 2022-04-07 | 2024-04-09 | 中国航发北京航空材料研究院 | Preparation method of powder superalloy cylindrical spur gear component |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106378456B (en) | 2018-01-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106378456B (en) | A kind of method for rapidly densifying for powder metallurgy superalloy component | |
| CN106623941B (en) | A kind of powder metallurgy superalloy element stages heating squeezes control shape method | |
| CN101733348B (en) | Isothermal forging method for titanium alloy blade | |
| CN101695739B (en) | Forging process of large tee and large skew tee | |
| CN103111619B (en) | Hot isostatic pressing two-step forming method of high temperature alloy compact piece | |
| CN102284588B (en) | Device for improving forming limit of plate | |
| CN104493167A (en) | Method for forming powder high-temperature alloy annular member | |
| CN104148430B (en) | A kind of amorphous alloy pipe extrusion molding apparatus and technique | |
| CN101972830A (en) | Hot upsetting process for cast ingot with large height to diameter ratio for ultra large ring forging | |
| CN104707931A (en) | Manufacturing method for large high-temperature alloy disk-type die forging parts | |
| CN107186139B (en) | The H profile steel manufacturing method of nuclear fusion stack magnet support | |
| CN104999037B (en) | A kind of running gate system and its precision casting molding method for thin-walled tubular piece | |
| CN110394410A (en) | A method of preparing big specification male sportsman fine grain bar | |
| CN109226750B (en) | Rapid forming method for powder titanium alloy blade prefabricated blank with damping boss | |
| CN100431777C (en) | Method for producing rocking-turn disk of motorcar air conditioner through technique of liquid forging | |
| CN204108005U (en) | A kind of amorphous alloy pipe extrusion molding apparatus | |
| CN104550838B (en) | The technique that a kind of radial forging strain-induced method prepares semisolid iron and steel camshaft | |
| CN104190737B (en) | A kind of amorphous metal extrusion die of fast changeable core rod and extrusion process | |
| CN110293227A (en) | A kind of the backward extrusion preparation method and mold of the powder metallurgy superalloy ingot blank with jacket | |
| CN105436373A (en) | Nickel-based powder high-temperature alloy ingot superplastic isothermal closed upset cake blank making method | |
| CN103624216B (en) | The manufacture method of piston inner-cooling oil recess salt core prefabricated component | |
| CN102974822B (en) | Hot-pressing mold and method for preparing aluminum-ferrum alloy shaped charge liner by using same | |
| CN103879085A (en) | Pure aluminum coated SiC particle reinforced magnesium matrix composite, as well as preparation and application thereof | |
| CN107695163B (en) | Nuclear island evaporator end socket integral stamping forming device and stamping forming method | |
| CN108580574B (en) | Three-dimensional near-solid pressure forming method for tee part blank |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |