CN101648252B - Forging process for directionally solidifying titanium aluminum alloy blades - Google Patents
Forging process for directionally solidifying titanium aluminum alloy blades Download PDFInfo
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- CN101648252B CN101648252B CN2009103069597A CN200910306959A CN101648252B CN 101648252 B CN101648252 B CN 101648252B CN 2009103069597 A CN2009103069597 A CN 2009103069597A CN 200910306959 A CN200910306959 A CN 200910306959A CN 101648252 B CN101648252 B CN 101648252B
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- China
- Prior art keywords
- aluminum alloy
- forging
- titanium aluminum
- directionally solidified
- alloy blades
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Links
- 238000005242 forging Methods 0.000 title claims abstract description 56
- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 46
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 17
- 239000000314 lubricant Substances 0.000 claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 claims abstract description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 238000000137 annealing Methods 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 2
- 239000000843 powder Substances 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 5
- 238000003825 pressing Methods 0.000 abstract description 2
- 239000011248 coating agent Substances 0.000 abstract 1
- 238000000576 coating method Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 12
- 239000000956 alloy Substances 0.000 description 9
- 229910045601 alloy Inorganic materials 0.000 description 8
- 238000007493 shaping process Methods 0.000 description 8
- 239000013078 crystal Substances 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 238000005495 investment casting Methods 0.000 description 4
- 238000007711 solidification Methods 0.000 description 4
- 230000008023 solidification Effects 0.000 description 4
- 229910000601 superalloy Inorganic materials 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 3
- 239000008186 active pharmaceutical agent Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910000943 NiAl Inorganic materials 0.000 description 1
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- OQPDWFJSZHWILH-UHFFFAOYSA-N [Al].[Al].[Al].[Ti] Chemical compound [Al].[Al].[Al].[Ti] OQPDWFJSZHWILH-UHFFFAOYSA-N 0.000 description 1
- 229910000905 alloy phase Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 235000006708 antioxidants Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000011819 refractory material Substances 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 229910021324 titanium aluminide Inorganic materials 0.000 description 1
- 229910006281 γ-TiAl Inorganic materials 0.000 description 1
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- Forging (AREA)
Abstract
The invention discloses a forging process for directionally solidifying titanium aluminum alloy blades, relating to a forging process of titanium aluminum alloy blades, and solving the problems that the prior forming method of directionally solidified titanium aluminum alloy blades is hard to form blades and has poor quality of the formed blades. The method comprises the following steps: determining the size of blade blanks; manufacturing forging mould by a high-temperature mould; coating a lubricant; placing the blank materials of the directionally solidified titanium aluminum alloy blades in an electric furnace under 900-1170 DEG C for two hours; placing the forging mould in the electric furnace to be heated and then rapidly taking out; placing the forging mould between two pads to be heated to 300-400 DEG C, rapidly folding the two pads and the forging mould on a pressing machine to be forged for 30-60 seconds; placing the forging mould in the electric furnace at 200-300 DEG C to be annealed for 15 minutes, and then obtaining the directionally solidified titanium aluminum alloy blades. The forging process is easy to form the directionally solidified titanium aluminum alloy blades so as to obtain the directionally solidified titanium aluminum alloy blades with better surface quality.
Description
Technical field
The present invention relates to a kind of Forging Technology of titanium aluminum alloy blades.
Background technology
Engine blade material preparation process technology is the key problem of Aero-Space development all the time.Along with the raising of aircraft performance, more and more higher to the thrust-weight ratio requirement of engine, and, be decided by the raising of Blade Properties to a great extent in order to improve the performance of engine.The development of modern technical aeronautics shows that the raising of Blade Properties need concur from material and technology of preparing two aspects.
The research that begins titanium aluminium (TiAl) alloy from the fifties in last century is exactly to be located to be middle high-temperature structural material.With intermetallic compound phase γ-TiAl and α
2-Ti
3A1 for the titanium aluminide on basis owing to have high-melting-point, low-density, high elastic modulus, low diffusion coefficient, good non-oxidizability and corrosion resistance and anti-flammability than the low emphasis that becomes people's research day by day of conventional titanium alloy.Further investigation through surplus 50 years, basic data becomes increasingly abundant, ratio elastic modelling quantity and specific strength in certain temperature range, the ratio elastic modelling quantity of TiAl alloy is higher than titanium alloy and nickel-base alloy, also be higher than the NiAl intermetallic compound, such characteristics can significantly increase the rigidity of TiAl alloy components, improve its stability.The specific strength of TiAl alloy has remarkable advantages in the 500-1200K scope, be higher than titanium alloy and polycrystalline nickel-base alloy, in addition can with monocrystal nickel-base alloy phase ratio.These advantages have determined the TiAl alloy to be very suitable for making moving component in all kinds of engines.The high specific strength of TiAl alloy, high anti-oxidant, creep resistant temperature make it become the preferred material of compressor blade.And the characteristics of directionally solidifying titanium aluminum alloy are: can make the direction of growth of crystal grain consistent with the loading direction of power, consequently improve the service life of blade greatly.
At present, the shaping for directionally solidifying titanium aluminum alloy blades mainly contains two kinds of methods: precision-investment casting and plastic deformation are shaped.The problem that precision-investment casting runs into for directionally solidifying titanium aluminum alloy mainly contains 3 points: one, ceramic die worsens metallurgical quality to the pollution of alloy material, though people are exploring the refractory material of new high chemical stability always, produces little effect; Two, the directionally solidifying titanium aluminum alloy solidification shrinkage makes and produces loose class defective in the blade, though it is loose to adopt hot isostatic pressing technique to eliminate, the distortion of high temperature insostatic pressing (HIP) rear blade is obvious; Three, the crystal boundary cracking is easy to occur in the directional solidification turbo blade, its reason is: on the one hand because the horizontal crystal boundary of directionally solidified superalloy, DS superalloy blade is a weak link, then be owing to need ceramic core during production directional solidification turbo blade on the other hand, melt again behind the casting solidification, because the thermal coefficient of expansion of ceramic core is littler than the thermal coefficient of expansion of directionally solidified superalloy, DS superalloy, thereby when cooling was shunk, core produced the radial stress effect on every side and causes the crystal boundary cracking.To sum up, the leaf quality of described precision-investment casting shaping is poor.Method for the directionally solidifying titanium aluminum alloy plastic deformation is come shaping blade, because directionally solidifying titanium aluminum alloy exists plasticity very low (plasticity under the room temperature≤0.7%), resistance of deformation height, narrow forging temperature, very strong anisotropic, to characteristics such as strain rate and stress state sensitivities, thereby bring very big difficulty for the forging and molding of directionally solidifying titanium aluminum alloy.
Summary of the invention
The blade that the objective of the invention is the to exist problem of difficulty and blade forming quality difference that is shaped for the manufacturing process that solves existing directionally solidifying titanium aluminum alloy blades, and then a kind of Forging Technology of directionally solidifying titanium aluminum alloy blades is provided.
The step of the Forging Technology of a kind of directionally solidifying titanium aluminum alloy blades of the present invention is:
Step 1: the size of determining the directionally solidifying titanium aluminum alloy blades blank;
Step 2: adopt hot-die steel to make forging mold, the die cavity of forging mold is consistent with the profile of directionally solidifying titanium aluminum alloy blades;
Step 3: lubricant is spread upon uniformly on the surface of directionally solidifying titanium aluminum alloy blades blank and on the surface of the die cavity of forging mold;
Step 4: the directionally solidifying titanium aluminum alloy blades blank is placed in the die cavity of forging mold, then matched moulds;
Step 5: it is heating 2 hours in 900～1170 ℃ the electric furnace that the forging mold behind the matched moulds is placed on temperature, takes out rapidly then;
Step 6: the forging mold that will take out rapidly is placed between two backing plates that are preheated to 300～400 ℃, is that quick-make is forged on the forcing press of 315～500t in nominal pressure, and forging time is 30～60 seconds;
Step 7: forge finish after, forging mold is placed in 200～300 ℃ the electric furnace and anneals, annealing time is 15 minutes, obtains directionally solidifying titanium aluminum alloy blades.
The present invention compared with prior art has following beneficial effect: Forging Technology of the present invention is taked is that the method for plastic deformation is come shaping blade.The method of taking to forge can be avoided the shortcoming of above-mentioned precision-investment casting blade.Forging Technology of the present invention has been formulated rational Forging Technology and subsequent heat treatment technology simultaneously, is easy to the shaping of directionally solidifying titanium aluminum alloy blades, has finally obtained surface quality directionally solidifying titanium aluminum alloy blades preferably.
The specific embodiment
The specific embodiment one: the step of the Forging Technology of a kind of directionally solidifying titanium aluminum alloy blades of present embodiment is:
Step 1: the size of determining the directionally solidifying titanium aluminum alloy blades blank;
Step 2: adopt hot-die steel to make forging mold, the die cavity of forging mold is consistent with the profile of directionally solidifying titanium aluminum alloy blades;
Step 3: lubricant is spread upon uniformly on the surface of directionally solidifying titanium aluminum alloy blades blank and on the surface of the die cavity of forging mold;
Step 4: the directionally solidifying titanium aluminum alloy blades blank is placed in the die cavity of forging mold, then matched moulds;
Step 5: it is heating 2 hours in 900～1170 ℃ the electric furnace that the forging mold behind the matched moulds is placed on temperature, takes out rapidly then;
Step 6: the forging mold that will take out rapidly is placed between two backing plates that are preheated to 300～400 ℃, be that quick-make is forged on the forcing press of 315～500t in nominal pressure, forging time is 30～60 seconds, and the heating backing plate is in order to prevent that the forging mold cooling is too fast in forging process;
Step 7: forge finish after, forging mold is placed in 200～300 ℃ the electric furnace and anneals, annealing time is 15 minutes, obtains surperficial flawless, no shrinkage cavity, directionally solidifying titanium aluminum alloy blades that allowance is little.
The specific embodiment two: what present embodiment and the specific embodiment one were different is: that the forging mold in the step 2 adopts is hot-die steel K403.The surface quality of shaping directionally solidifying titanium aluminum alloy blades is better.
The specific embodiment three: what present embodiment was different with the specific embodiment one or two is: the lubricant in the step 3 is a glass dust.The surface quality of shaping directionally solidifying titanium aluminum alloy blades is better.
The specific embodiment four: what present embodiment and the specific embodiment three were different is: the matched moulds gap of the forging mold in the step 4 is 2mm.The surface quality of shaping directionally solidifying titanium aluminum alloy blades is better.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103069597A CN101648252B (en) | 2009-09-14 | 2009-09-14 | Forging process for directionally solidifying titanium aluminum alloy blades |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009103069597A CN101648252B (en) | 2009-09-14 | 2009-09-14 | Forging process for directionally solidifying titanium aluminum alloy blades |
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| Publication Number | Publication Date |
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| CN101648252A CN101648252A (en) | 2010-02-17 |
| CN101648252B true CN101648252B (en) | 2011-01-05 |
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| CN2009103069597A Expired - Fee Related CN101648252B (en) | 2009-09-14 | 2009-09-14 | Forging process for directionally solidifying titanium aluminum alloy blades |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102011078B (en) * | 2010-12-23 | 2012-03-28 | 哈尔滨工业大学 | A method for refining the surface structure of directionally solidified titanium-aluminum alloy slab |
| CN107116167A (en) * | 2017-07-12 | 2017-09-01 | 安徽凯密克企业管理咨询有限公司 | A kind of forging technology of auto parts |
| CN108580770B (en) * | 2018-03-29 | 2019-12-27 | 西北工业大学 | Superplastic creep age forming method for TiAl-based alloy blade blank |
| CN114703436B (en) * | 2021-05-20 | 2023-05-12 | 哈尔滨工业大学 | Alloying method for improving high-temperature performance of directional solidification titanium aluminum alloy and prepared titanium aluminum alloy |
| CN114951522B (en) * | 2022-06-28 | 2023-08-11 | 中南大学 | Isothermal forging method of monocrystalline TiAl |
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2009
- 2009-09-14 CN CN2009103069597A patent/CN101648252B/en not_active Expired - Fee Related
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| CN101648252A (en) | 2010-02-17 |
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Granted publication date: 20110105 Termination date: 20200914 |