CN105274373A - Powder metallurgy preparation technology of gamma'' phase reinforced high temperature alloy - Google Patents
Powder metallurgy preparation technology of gamma'' phase reinforced high temperature alloy Download PDFInfo
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- CN105274373A CN105274373A CN201410247794.1A CN201410247794A CN105274373A CN 105274373 A CN105274373 A CN 105274373A CN 201410247794 A CN201410247794 A CN 201410247794A CN 105274373 A CN105274373 A CN 105274373A
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Abstract
The invention belongs to the field of powder metallurgy high temperature alloys, and concretely relates to a powder metallurgy preparation technology of a gamma'' phase reinforced high temperature alloy. The technology is suitable for preparing a gamma'' phase reinforced nickel-based or nickel-iron-based high temperature alloy member. The technology mainly comprises the following steps: 1, carrying out hot isostatic pressing on powder at 1190-1260DEG C under 90MPa or above for 2h or above; and 2, carrying out heat treatment on hot isostatic pressed alloy in a direct ageing mode at 600-750DEG C, and carrying out air cooling on the obtained alloy to room temperature. The gamma'' phase reinforced nickel-based or nickel-iron-based high temperature alloy member with few defects and excellent mechanical performances can be prepared, and a near-net forming technology is combined to prepare the powder high temperature alloy member with complex shape, so the utilization rate of alloy materials is improved.
Description
Technical field
The invention belongs to powder metallurgy high-temperature alloy field, be specially a kind of γ the preparation of the Ni-based or ferronickel based high-temperature alloy component that " powder metallurgy preparation technique of the superalloy strengthened mutually is applicable to γ " strengthens mutually.
Background technology
γ is " superalloy strengthened mutually due to the mechanical property of excellence, in aerospace and field of petrochemical industry widespread use.The alloy utilizing deformation technique to produce is mainly used in the load parts such as dish, axle of aircraft engine and the key part of other field, and the alloy of casting is mainly used in the relatively large and complex-shaped parts of production size.The alloy defect utilizing forging process to produce is less, dependable performance, but in order to obtain net shape in component production process, need a large amount of material machining to fall, this can increase the process-cycle of component, causes very large waste; For casting alloy, because cooling rate in conventional casting is comparatively slow, the crystal grain of alloy is very thick, and interdendritic also can exist serious element segregation.The common casting flaws such as loose, shrinkage cavity also can exist in foundry goods.Coarse grain and macrosegregation can make alloy property worsen, and loosen, the defect of shrinkage cavity will reduce the reliability of component, these defects are all unfavorable for casting alloy overall performance.
Summary of the invention
The object of the present invention is to provide a kind of γ " powder metallurgy preparation technique of the superalloy strengthened mutually, the alloy billet that grain-size is relatively uniform to obtain, defect is less.
Technical scheme of the present invention is:
A kind of γ " powder metallurgy preparation technique of the superalloy strengthened mutually, concrete technology step is as follows:
(1). prepare superalloy powder with gas atomization or additive method, by screening to obtain the powder that size is less than or equal to 155 μm, the powder that sieves out is loaded the carbon steel or stainless steel jacket of definite shape, high-temperature degassing soldering and sealing;
(2). the powder jacket the first step prepared puts into hot isostatic apparatus, with while increasing temperature and pressure or first the heat up mode of boosting afterwards reach predetermined condition after start hot isostatic pressing;
The processing condition of hot isostatic pressing are, hip temperature is higher than 1190 DEG C, and lower than 1260 DEG C, pressure is more than or equal to 90MPa, be more than or equal to 2 hours, be cooled to room temperature after being incubated in body of heater to the rear soaking time of temperature;
(3). carry out direct aging thermal treatment to the alloy of previous step hot isostatic pressing, aging temp 600 ~ 750 DEG C, after thermal treatment completes, air cooling is to room temperature.
The preparation of the Ni-based or ferronickel based high-temperature alloy component that described γ " powder metallurgy preparation technique of the superalloy strengthened mutually, this technique is applicable to γ " strengthens mutually.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (1), is less than or equal to 105 μm by sieving to obtain being preferably dimensioned to be to described γ.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (1), obtains size by screening and is preferably and is less than or equal to 55 μm described γ.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (1), the hip temperature preferable range of powder is 1200 ~ 1240 DEG C to described γ.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (1), the hip temperature of powder more preferably scope is 1210 ~ 1220 DEG C to described γ.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (2), the pressure preferable range of hot isostatic pressing is 120 ~ 150MPa to described γ, and the soaking time preferable range of hot isostatic pressing is 2 ~ 6 hours.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (2), the speed of cooling of sample after hot isostatic pressing, rapid cooling is excellent to described γ.
" powder metallurgy preparation technique of the superalloy strengthened mutually, in step (3), direct aging thermal treatment preferred range is 620 ~ 720 DEG C to described γ.
Described γ " powder metallurgy preparation technique of the superalloy strengthened mutually, in step (3), the preferred aging strengthening model system of direct aging thermal treatment is:
Advantage of the present invention and beneficial effect are:
1, present invention process mainly comprises two steps: the first step is the hip moulding of powder, object obtains the alloy billet that grain-size is relatively uniform, defect is less, second step is the thermal treatment of alloy, and object is that the precipitated phase distribution of optimized alloy is to improve mechanical property.The present invention is applicable to γ, and " preparation of the Ni-based or ferronickel based high-temperature alloy component strengthened mutually, can prepare complex-shaped powder metallurgy superalloy component in conjunction with near-net-shape technology, thus improves the utilization ratio of alloy material.
2, the present invention can realize in traditional hot isostatic press and heat treatment furnace, and this technique scope of application is γ " the ferronickel base strengthened mutually, the preparation of nickel base superalloy component.
3, the present invention is simple and practical, can shorten the manufacturing process of powder metallurgy superalloy component, thus reduces its manufacturing cost.
In a word, the present invention utilizes Powder hot isostatic pressure heating treatment process to prepare γ " the Ni-based or ferronickel based high-temperature alloy strengthened mutually; namely can obtain grain-size relatively little and without the microstructure of macrosegregation; component preparation section can be shortened again, reduce amount of finish; thus reduce manufacturing cost, this method has application potential on some complex-shaped but higher to mechanical property requirements components of preparation.
Accompanying drawing explanation
The microstructure of the powder metallurgy GH4169G alloy that Fig. 1 (a) is the hot isostatic pressing state that utilizes the present invention to prepare, the stretching fracture pattern that Fig. 1 (b) is hot isostatic pressing temper alloy.
Fig. 2 (a) is the microstructure through the heat treated alloy of direct aging, 650 DEG C of stretching fracture patterns that Fig. 2 (b) is direct aging alloy.
Embodiment
In the specific embodiment of the present invention, γ " powder metallurgy preparation technique of the superalloy strengthened mutually, specific as follows:
1. use gas atomization and other party legal system thereof for superalloy powder, obtain size by screening to be less than or equal to 155 μm and (to be preferably less than or equal to 105 μm, be preferably and be less than or equal to 55 μm) powder, powder is loaded low-carbon (LC) steel or stainless steel jacket, soldering and sealing after high-temperature degassing.Fine powder is used to be to reduce ceramic inclusions size in powder and reducing the quantity of hollow powder; Use carbon steel or stainless steel jacket to be because in the temperature range that the present invention is used, sheath material for completely solid-state, there is some strength and can not react with powder; High-temperature degassing is the gas in order to remove powder surface absorption to greatest extent, and to reduce the tendency that alloy forms thermal induction hole in follow-up heat treatment process, the temperature range of high-temperature degassing is 180 DEG C to 500 DEG C.
2. the powder jacket the first step prepared puts into hot isostatic apparatus, reaches design temperature start hot isostatic pressing in the mode of boosting again with stove increasing temperature and pressure or first heat up.The processing condition of hot isostatic pressing are, temperature is higher than 1190 DEG C, lower than 1260 DEG C, (temperature preferable range is 1200 ~ 1240 DEG C, optimum is 1210 ~ 1220 DEG C), pressure is more than or equal to 90MPa (pressure preferable range is 120 ~ 150MPa), in body of heater after temperature, soaking time is more than or equal to 2 hours (soaking time preferable range is 2 ~ 6 hours).Select the object of these processing condition to be: the first, make powder completely fine and close; The second, reduce the quantity of precipitated phase in powder particle surface hot isostatic pressing; 3rd, obtain relatively tiny grain-size.Be incubated rear sample and cooled to room temperature with the furnace, preferred rapid cooling, namely fast as far as possible by sample cool to room temperature.After hot isostatic pressing, rapid cooling realizes by following two kinds of methods: the first, optimization design powder jacket shape, reduces thickness of sample and size, and in the cold process of stove, the heat exchange efficiency of sample and gas is better like this, and cooling rate is faster; The second, accelerate the gas circulation in hot isostatic pressing stove, cryogenic gas is squeezed in hot isostatic pressing body of heater, high-temperature gas is discharged gradually.After hot isostatic pressing completes, the main purpose increasing the speed of cooling of sample reduces the quantity that in process of cooling interalloy, strengthening phase is separated out.Because the heat treatment mode of alloy is direct aging, the alloy strengthening phase of separating out in hot isostatic pressing process of cooling can alligatoring in ag(e)ing process, affects the final mechanical property of alloy.And sample hot isostatic pressing complete in the speed of cooling of 915 DEG C ~ 700 DEG C of temperature range the bests should be more than or equal to 30 DEG C of per minutes, because the strengthening phase of alloy is mainly 915 DEG C ~ 700 DEG C interval precipitations, and can suppress the precipitation of strengthening phase when cooling rate is more than or equal to 30 DEG C of per minutes.
3. the alloy of pair hot isostatic pressing is heat-treated, and heat treatment mode is direct aging, temperature 600 ~ 750 DEG C (preferred range is 620 ~ 720 DEG C, and optimum aging strengthening model system is:
after thermal treatment completes, air cooling is to room temperature.
Below in conjunction with drawings and Examples, the present invention is described in more detail.
Embodiment 1
The composition of the present embodiment alloy is in table 1:
The alloying constituent of table 1.GH4169G
| Cr | Mo | Al | Ti | Nb | C | B | P | Ni | Fe |
| 19.3 | 2.98 | 0.5 | 1.04 | 4.94 | 0.031 | 0.008 | 0.023 | 53.5 | Surplus |
The present embodiment adopts the powder of this alloy of argon gas atomization preparation, is loaded in stainless steel jacket by the powder of size below 105 μm, does hot isostatic pressing after vacuum stripping.Following process system is have selected for this alloy:
The hot isostatic pressing of powder, with stove increasing temperature and pressure, 1210 DEG C/150MPa/4 hour, furnace cooling after completing;
The direct aging heat treating regime of hot isostatic pressing alloy:
namely first sample is incubated 8 hours at 720 DEG C, has been incubated rear Quality control cooling rate, has made it be chilled to 620 DEG C after 2 hours, then 620 DEG C of insulations 8 hours, after being incubated, sample air cooling was to room temperature.
The microstructure of hot isostatic pressing temper alloy and 650 DEG C of stretching fractures are as shown in Fig. 1 (a) He Fig. 1 (b), can find out, the homogeneous microstructure of hot isostatic pressing temper alloy is tiny, precipitated phase is evenly distributed, seldom see the vestige of starting powder particle, fracture mode is perfect plasticity fracture simultaneously, illustrates there is good combination between particle.
The microstructure of the alloy after direct aging and 650 DEG C of stretching fractures are as shown in Fig. 2 (a) He Fig. 2 (b), can find out, its microstructure and hot isostatic pressing state without significant difference, its fracture mode is also perfect plasticity fracture simultaneously, illustrate after thermal treatment, between particle, also have extraordinary combination.
As shown in table 2, the mechanical property of the powder metallurgy GH4169G alloy utilizing present invention process to prepare, comprises: 650 DEG C of tensile properties of hot isostatic pressing temper alloy and the heat treatment state alloy after direct aging process and 650 DEG C/690MPa enduring quality.As can be seen from the table, after direct aging thermal treatment, the intensity of alloy significantly increases, and the tensile property of 650 DEG C is far above K4169 alloy.The creep rupture life of 650 DEG C/690MPa, the GH4169G produced with deformation technique was suitable more than 400 hours.
The stretching of the GH4169G alloy of table 2. hot isostatic pressing and direct aging and lasting mechanical property
This embodiment result shows, present invention process mainly comprises two steps: the first step is the hot isostatic pressing densification of powder, complete in the temperature range of 1190 DEG C to 1260 DEG C, the hot isostatic pressing time is more than or equal to 2 hours, and gaseous tension should be more than or equal to 90MPa.Second step is the thermal treatment of hot isostatic pressing alloy, and take the mode of direct aging to carry out, aging temp 600 ~ 750 DEG C, after second step completes, alloy air cooling is to room temperature.Defect is less, powder particle bonding force is high to utilize present invention process to obtain, the after heat treatment γ of excellent in mechanical performance " the Ni-based or ferronickel based high-temperature alloy strengthened mutually; this technique can shorten the manufacturing process of powder metallurgy high-temperature alloy component, thus reduces its manufacturing cost.
Claims (10)
1. γ " powder metallurgy preparation technique for the superalloy strengthened mutually, is characterized in that, concrete technology step is as follows:
(1). prepare superalloy powder with gas atomization or additive method, by screening to obtain the powder that size is less than or equal to 155 μm, the powder that sieves out is loaded the carbon steel or stainless steel jacket of definite shape, high-temperature degassing soldering and sealing;
(2). the powder jacket the first step prepared puts into hot isostatic apparatus, with while increasing temperature and pressure or first the heat up mode of boosting afterwards reach predetermined condition after start hot isostatic pressing;
The processing condition of hot isostatic pressing are, hip temperature is higher than 1190 DEG C, and lower than 1260 DEG C, pressure is more than or equal to 90MPa, be more than or equal to 2 hours, be cooled to room temperature after being incubated in body of heater to the rear soaking time of temperature;
(3). carry out direct aging thermal treatment to the alloy of previous step hot isostatic pressing, aging temp 600 ~ 750 DEG C, after thermal treatment completes, air cooling is to room temperature.
2. " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, this technique is applicable to γ " preparation of Ni-based or ferronickel based high-temperature alloy component of strengthening mutually according to γ according to claim 1.
3. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (1), is less than or equal to 105 μm by sieving to obtain being preferably dimensioned to be.
4. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (1), obtains size be preferably and be less than or equal to 55 μm by screening.
5. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (1), the hip temperature preferable range of powder is 1200 ~ 1240 DEG C.
6. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (1), the hip temperature of powder more preferably scope is 1210 ~ 1220 DEG C.
7. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually; it is characterized in that; in step (2), the pressure preferable range of hot isostatic pressing is 120 ~ 150MPa, and the soaking time preferable range of hot isostatic pressing is 2 ~ 6 hours.
8. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (2), the speed of cooling of sample after hot isostatic pressing, rapid cooling is excellent.
9. according to γ according to claim 1, " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (3), direct aging thermal treatment preferred range is 620 ~ 720 DEG C.
10. according to γ according to claim 1 " powder metallurgy preparation technique of the superalloy strengthened mutually, is characterized in that, in step (3), the preferred aging strengthening model system of direct aging thermal treatment is:
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105603259A (en) * | 2016-04-11 | 2016-05-25 | 西安欧中材料科技有限公司 | Powder metallurgical method for IN718 alloy |
| CN110343908A (en) * | 2019-08-30 | 2019-10-18 | 江苏奇纳新材料科技有限公司 | The hip moulding and heat treatment process of IN718 alloy powder and its alloy |
| CN113732285A (en) * | 2021-11-05 | 2021-12-03 | 西安赛隆金属材料有限责任公司 | Iron-nickel-cobalt-based powder alloy and method for improving elongation thereof |
| CN114672680A (en) * | 2022-03-07 | 2022-06-28 | 中南大学 | Step-by-step hot isostatic pressing method for additive manufacturing of nickel-based high-temperature alloy |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Non-Patent Citations (2)
| Title |
|---|
| LITAO CHANG ETC: "Effect of heat treatment on microstructure and mechanical properties of the hot-isostatic-pressed Inconel 718 powder compact", 《JOURNAL OF ALLOYS AND COMPOUNDS》 * |
| 韩凤麟等编: "《粉末冶金技术手册》", 31 July 2009 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105603259A (en) * | 2016-04-11 | 2016-05-25 | 西安欧中材料科技有限公司 | Powder metallurgical method for IN718 alloy |
| CN110343908A (en) * | 2019-08-30 | 2019-10-18 | 江苏奇纳新材料科技有限公司 | The hip moulding and heat treatment process of IN718 alloy powder and its alloy |
| CN113732285A (en) * | 2021-11-05 | 2021-12-03 | 西安赛隆金属材料有限责任公司 | Iron-nickel-cobalt-based powder alloy and method for improving elongation thereof |
| CN113732285B (en) * | 2021-11-05 | 2022-03-01 | 西安赛隆金属材料有限责任公司 | Iron-nickel-cobalt-based powder alloy and method for improving elongation thereof |
| CN114672680A (en) * | 2022-03-07 | 2022-06-28 | 中南大学 | Step-by-step hot isostatic pressing method for additive manufacturing of nickel-based high-temperature alloy |
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