EP0387976A2 - New superalloys and the methods for improving the properties of superalloys - Google Patents
New superalloys and the methods for improving the properties of superalloys Download PDFInfo
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- EP0387976A2 EP0387976A2 EP90250070A EP90250070A EP0387976A2 EP 0387976 A2 EP0387976 A2 EP 0387976A2 EP 90250070 A EP90250070 A EP 90250070A EP 90250070 A EP90250070 A EP 90250070A EP 0387976 A2 EP0387976 A2 EP 0387976A2
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- alloy
- superalloys
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- boron
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
Definitions
- the present invention relates to improved superalloys and methods for improving superalloys.
- Superalloys are important materials used as hot components of gas turbines in aeroplanes, warships and industrial and traffic machines. Recently, they have also been widely used in aerospace nuclear reactors and chemical industries, etc. How to improve their resistant ability to oxidation and corrosion, and raise they strength and service temperature are of significant importance. And researches on these problems have been paid much attentions by many metallurgists and designers in the world. Since the late forties, superallloys have been developed rapidly. However, the progress of the development and improvement in composition design of superalloys has been slowed down after 1970's. the main reasons are as follows:
- the alloys of the present invention contain at least about 25% nickel (all percents expressed herein and in the claims are by weight unless otherwise specified) and up to about 0.001% phosphorus, for nickel-base superalloys the phosphorus content should be lower than 0.0005%, up to about 0.05% silicon, about 0.001 to about 0.015% boron.
- the balance of the alloy will consist of other elements which are conventionally alloyed with nickel to form superalloys such as elements selected from the group consisting of chromium, iron, cobalt, molybdenum, titanium, tantalum, tungsten, aluminum, niobium, carbon, vitriol and combinations thereof. These alloys will be zirconium-free.
- the alloy for the cast consists essentially of about 6.0% to about 22.0% chromium, up to about 16.0% cobalt, up to about 8% molybdenum, about 2% to about 5.5% titanium, about 2% to about 6.5 aluminum, up to about 12.0% tungsten, about 10 to about 150 ppm boron, up to about 4.0 niobium, up to about 12.0% tantalum, and about 0.02% to about 0.22% carbon, up to about 0.0005% phosphorus, up to about 0.05 silicon, hafnium-free, zirconium-free and the balance nickel.
- the alloy for the wrought consists essentially of about 25 to 55% nickel, about 0.01 to 0.1% carbon, about 0.1 to about 0.5% vitriol, about 10 to 22% chromium, up to about 3% tungsten, up to about 7% molybdenum, up to about 6% niobium, up to about 6% tantalum, about 0.1 to about 3% aluminum, about 0.5 to about 3% titanium, about 0.001 to about 0.01% boron, up to about 0.001% phosphorus, up to about 0.05% silicon, zirconium-free and the balance iron.
- the invention provides a new method of raising the incipient temperature, reducing the segregation, eliminating technological properties of the superalloys effectively by means of strictly controlling the contents of P and B and eliminating Zr.
- the key points are: the P content in the present superalloys must be reduced below 0.001 ( in wt%); for nickel-base superalloys the P content should be lower than 0.0005 (wt%); for the existing superalloys using Zr as the grain boundary strengthening element, besides reducing the P content less than 0.0005, it is also necessary to eliminate the Zr from the superalloys.
- the inventors developed a series of low segregration superalloys with excellent properties.
- the incipient melting temperature of Fe-Ni-Cr-base wrought superalloy GH901 (Namely Alloy IN 901) can be raised from 1140°C to 1260°C and the starting forging temperature can be raised to 1190-1225°C accordingly.
- the precision mould forging technology can be used very easily and the materials can be utilized very savingly without any loss in tensile and stress rupture properties, for cast superalloys the contents of Al and Ti can be added by 1% more without any loss in hot corrosion resistance and formation of harmful phases.
- This invention also provides the composition of new superalloy modified by the new method mentioned above. They are as follows: (1) an analogue of GH901 (IN 901) FE-Ni-Cr-base superalloys with low segregation. The characteristic specificity is to control the P content below 0.001.
- an analogue of M40 (IN 792) Ni-base superalloy with low segregation.
- the characteristic specificities are (A) to eliminate Zr and reduced P below 0.0005%, and (B) to raise the Al and Ti contents by 1(%).
- an analogue of M38 (IN 738) Ni-base superalloys with low segregation and high Al and Ti contents.
- the characteristics specificities are (A) to eliminate Zr and control P below 0.0005%, (B) to raise the Al and Ti contents by about 1(%).
- an analogue of M 38(IN 738) Ni-base superalloy with low segregation and high Cr content The characteristic specificities are (A) to eliminate Zr and control P content below 0.0005% and (B) to increase the Cr content by about 4(%).
- the service temperature of the exisiting cast superalloys can be raised by 100-300°C. Meanwhile, the invented new method is also very helpful to solve the difficult problem in hog working processing of wrought superatlloys and greatly improve the hot workability of the alloys.
- the new method of the present invention is carried out as follows: Firstly, the P and Si contents of raw materials (Fe and Cr) must be strictly controlled. If the P and Si contents in Fe and/or Ce are a little high, it is necessary that to refine Fe into powder form by wet metallurgy and to purify Cr several times by electrolysis.
- the P content in raw materials of Fe and Cr is below 0.0005%, and Si content is below 0.05%.
- the qualified raw materials are melted in a vacuum induction furnace and the added boron content is controlled at the range from about 0.001 to about 0.015%.
- the alloy is remelted in the vacuum induction furnace with the same melting technology to the ordinary one.
- a superalloy (our name: M17E) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 8.0 to about 10.0% Cr, about 10.0 to about 16.0% Co, about 2.5 to about 3.5% Mo, about 5.5 to about 6.5% Al, about 4.5 to about 5.5% Ti, about 0.005 to about 0.015% B, and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace.
- the melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace.
- the melted alloy was cast into shaped molds to produce parts or specimens.
- a superalloy (our name: M17F) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 8.0 to about 10.0% Cr, about 8.0 to about 10.0% Co, about 3.0 to about 5.0% W, about 1.0 to about 3.5% Mo, about 3.0 to about 5.0% Ta, about 4.5 to about 5.5% Al, about 4.0 to about 5.0% Ti, about 0.005 to about 0.015% B, and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- a superalloy (our name: M40) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 12 to about 14% Cr, about 8 to about 10% Co, about 1.0 to about 3% Mo, about 3.2 to about 4.3% Al, about 4.2 to about 5.3% Ti, about 0.005 to about 0.015% B, about 3 to about 5% W, about 3 to about 5% Ta and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace.
- the melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace.
- the melted alloy was cast into shaped molds to produce parts or specimans.
- a superalloy (our name: M38G) with low segregation for the cast was produced by melting a compositon of about 0.08 to about 0.21% C, about 15 to about 17% Cr, about 7 to about 9% Co, about 2 to about 4% W, about 1 to about 3% Mo, about 1 to about 2.5% Ta, about 3.5 to about 4.5% Al, about 3.3 to about 4.3% Ti, about 0.005 to about 0.015% B,about 0.5 to about 1.5% Nb and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- a superalloy (our name: M36) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 19 to about 21% Cr, about 7 to about 9% Co, about 2 to about 4% W, about 1 to about 3% Mo, about 3.5 to about 4.5% Al, about 3.5 to about 4.5% Ti, about 0.005 to about 0.015% B,about 0.5 to about 1.5% Nb and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace.
- the melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace.
- the melted alloy was cast into shaped molds to produce parts or specimans.
- the most preferred version of the superalloys of the present invention were produced by following compositions of elements in Table I-A.
- the conventional superalloys for the cast containing essentially about 0.004 to about 0.009% P, about 0.03 to about 0.15% Zr, about 0.005 to about 0.02% B, about 0.05 to about 0.3% Si. Because of the segregation, the microstructure of the conventional superalloys are found to have stable laves phase on solidification, to form 3-5% (gamma+gamma′) phase, and to produce delta phase after exposure in the elevated temperatures.
- the nickel-base superalloys in present invention showed improved elevated temperature strength properties over their proir art and these properties were even further improved by use of the preferred heat treatment.
- a superalloy (our name :LSDS738) with low segregatin for the directional solidification was produced by melting a composition of about 0.08% C, about 16% Cr, about 8.5% Co, about 2.6% W, about 1.7% Mo, about 0.7% Nb, about 1.7% Ta, about 3.5% Al, about 3.3% Ti, about 0.008% B, Hf-free and the balance of Ni, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum induction furnace.
- the melted alloy was cast into ceramic molds to form sticks. And cutting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace.
- the melted alloy was cast into shaped molds to produce parts or specimans.
- the conventional superaloys for the directional solidification containing essentially Hf and about 0.08% C, about 0.012% B, about 0.10% Zr, about 0.005% P, about 0.1% Si.
- the very expensive metal Hf have to be added in the said alloy.
- the present invention make it possible that the transverse properties of the directional solidified superalloys can be improved obviously without any addition of Hf. So, the invention benefits to the application of the directional solidification technology and makes it easy to combine with the air-cooling technique.
- the directional solidified superalloys for the cast of the present invention exhibit substantially increased elevated temperature strength and stress Rupture Time, especially increased the transverse properties of the directional solidified suporalloys.
- a superalloy (our name: LSIN901) with low segregation for the wrought was produced by melting a composition of 0.03% C, 12% Cr, 5.7% Mo, 0.2% Al, 3% Ti, 43% Ni, 0.003% B, and the balance of Fe, controlling incidental impurities, such as: ⁇ 0.0005% P, ⁇ 0.05% Si, in a vacuum inductiong furnace.
- the melted alloy was cast into ceramic molds to form slabs.
- the slabs were remelted by vacuum drip melting to form ingot.
- a superalloys (our name:LSA286) with low segregation for the wrought was produced by melting a compositiong of about 0.08% C, about 13.5 to about 16.0% Cr, about 24% to about 27% Ni, about 1.0% to about 1.5% Mo, about 1.9% to about 2.35% Ti, ⁇ 0.35% Al, about 0.1% to about 0.5% V, about 0.001% to about 0.004% B, and the balance of Fe, controlling incidental impurities, such as: ⁇ 0.001% P, ⁇ 0.05% S, in a vacuum induction furnace the malted alloy was cast into ceramic molds to form slabs. The slabs were remelted by vacuum drip melting to form ingot.
- the superalloys of the present invention showed improved elevated temperature strength properties over the prior art and these properties were even further improved by the use of the preferred heat treatment.
- the new method of the present invention is suitable to both Fe-Ni-Cr-base superalloys and Ni-base superalloys. It is obvious that the characteristics of the low segregation superaloys of the present invention lie in: (1) no addition of Zr; (2) P content is below 0.001 or 0.0005%; (3) contents of Al and Ti increased by 1%; (4) Cr content increased by 4%.
- the properties of the superalloys provided by this invention are shown in Table IV, V,VI and VII.
- Table IV shows the comparison of the properties of GH901 (IN901) alloy with those of the low segregation GH90; alloy. It can be seen that the tensile strength at room temperature, stress repture property and incipient temperature of the low segregation GH901 alloy are raised obviously.
- Table V shows the comparison of 100 hour stress repture strength data in the M38 (IN738) and M17(IN100) alloys with those in the corresponding low segregation ones. The properties of the low segregation alloys are obvously higher than those in conventional ones.
- Table VI gives the comparison of the stress rupture life (hour) and hot corrosion resistance in both series of the alloys (M38 & M36 with low segregation M38 & M36 alloys).
- Table VII lists the data of the stress reputre strength at elevated temperatures in both IN 792 and low segregation IN 792 alloys. It is clear that the properties of low segregation superalloys are obviously higher than those of the corresponding conventional ones.
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Abstract
This invention has provided a new technique of improving the properties of superalloys by reducing the segregation of the alloying elements. The characteristic specificity is to reduce the phosphorus content of the alloys to below 0.001 (in wt%) and, in case of Ni-base superalloys, to below 0.0005(wt%). It is needed to eliminate Zr from the superalloys. Meanwhile, it is also needed to control the proper content of B and to reduce the content of Si to below 0.005. The invention has also provided a series of low segregation superalloys.
Description
- The present invention relates to improved superalloys and methods for improving superalloys.
- Superalloys are important materials used as hot components of gas turbines in aeroplanes, warships and industrial and traffic machines. Recently, they have also been widely used in aerospace nuclear reactors and chemical industries, etc. How to improve their resistant ability to oxidation and corrosion, and raise they strength and service temperature are of significant importance. And researches on these problems have been paid much attentions by many metallurgists and designers in the world. Since the late forties, superallloys have been developed rapidly. However, the progress of the development and improvement in composition design of superalloys has been slowed down after 1970's. the main reasons are as follows:
- (1) The compositions of the persent superalloys are extremely complicated. In case of adding more alloying elements, it will lead to the formation of severe solidification segregation in the castings. For instance, on nickel base superalloys more addition of Al and Ti is beneficial to raising their strength at elevated temperature and Cr benefits to increasing their corrosion resistance. However, the excess of the these elements will make the superalloys unusable due to the appearance of brittle phase.
- (2) With increasing the addition of alloying elements, the incipient melting temperature of the superalloys decreases acordingly. For instance, the starting forging temperature of Fe-Ni-Cr-base superalloys must be lower than 1140°C because of the limitation of the incipient melting temperature. Under such a low forging temperature, it is necessary to use huge forging machine and special technique to manufacture the gas turbine disks with tese superalloys due to the large deformation resistance. Therefore the production costs are increased correspondingly.
- (3) In most cases, it is difficult to overcome the contradictions of the service properties at elevated temperature with the machinig and welding properties through adjustments of alloy composition. The aim of this invention is to advance new superalloys with the incipient melting temperature raised, the segration of alloying elements being reduced, precitation of harmful phases being eliminated and eventually the technological properties of the superalloys being improved effectively, and new methods for improving the properties of superalloys.
- The alloys of the present invention contain at least about 25% nickel (all percents expressed herein and in the claims are by weight unless otherwise specified) and up to about 0.001% phosphorus, for nickel-base superalloys the phosphorus content should be lower than 0.0005%, up to about 0.05% silicon, about 0.001 to about 0.015% boron. The balance of the alloy will consist of other elements which are conventionally alloyed with nickel to form superalloys such as elements selected from the group consisting of chromium, iron, cobalt, molybdenum, titanium, tantalum, tungsten, aluminum, niobium, carbon, vitriol and combinations thereof. These alloys will be zirconium-free.
- Generally, the alloy for the cast consists essentially of about 6.0% to about 22.0% chromium, up to about 16.0% cobalt, up to about 8% molybdenum, about 2% to about 5.5% titanium, about 2% to about 6.5 aluminum, up to about 12.0% tungsten, about 10 to about 150 ppm boron, up to about 4.0 niobium, up to about 12.0% tantalum, and about 0.02% to about 0.22% carbon, up to about 0.0005% phosphorus, up to about 0.05 silicon, hafnium-free, zirconium-free and the balance nickel.
- Generally the alloy for the wrought consists essentially of about 25 to 55% nickel, about 0.01 to 0.1% carbon, about 0.1 to about 0.5% vitriol, about 10 to 22% chromium, up to about 3% tungsten, up to about 7% molybdenum, up to about 6% niobium, up to about 6% tantalum, about 0.1 to about 3% aluminum, about 0.5 to about 3% titanium, about 0.001 to about 0.01% boron, up to about 0.001% phosphorus, up to about 0.05% silicon, zirconium-free and the balance iron.
- The invention provides a new method of raising the incipient temperature, reducing the segregation, eliminating technological properties of the superalloys effectively by means of strictly controlling the contents of P and B and eliminating Zr. The key points are: the P content in the present superalloys must be reduced below 0.001 ( in wt%); for nickel-base superalloys the P content should be lower than 0.0005 (wt%); for the existing superalloys using Zr as the grain boundary strengthening element, besides reducing the P content less than 0.0005, it is also necessary to eliminate the Zr from the superalloys. By using this invention, the inventors developed a series of low segregration superalloys with excellent properties. For example, by using this new method the incipient melting temperature of Fe-Ni-Cr-base wrought superalloy GH901 (Namely Alloy IN 901) can be raised from 1140°C to 1260°C and the starting forging temperature can be raised to 1190-1225°C accordingly. At such temperature, the precision mould forging technology can be used very easily and the materials can be utilized very savingly without any loss in tensile and stress rupture properties, for cast superalloys the contents of Al and Ti can be added by 1% more without any loss in hot corrosion resistance and formation of harmful phases.
- The comparison of 100h stress reupture strength data shows that the mechanical properties of the superalloys are greatly improved. What is more, the Cr content can be increased by 4% more in the low P content cast Ni-base superalloys, thus the resistance to oxidation and corrosion at elevated temperature of the alloys can be enhanced obviously.
- This invention also provides the composition of new superalloy modified by the new method mentioned above. They are as follows: (1) an analogue of GH901 (IN 901) FE-Ni-Cr-base superalloys with low segregation. The characteristic specificity is to control the P content below 0.001. The composition of the alloy is: Ni 40-45%, Cr 11-14%, Mo 5.0-6.5%, Al</=0.3%, Ti 2.8-3.1%, B 0.001-0.004%, C 0.02-0.6%, P</=0.001% and Fe balance. (2) an analogue of M17(IN 100) Ni-base superalloy with low segregation. The characteristic specificity is to eliminate Zr and control P below 0.0005%. The composition is: Cr 8.0-10.0%, Co 8.0-10.0%, W 2.0-5.0%, Mo 1.0-3.0%, Ta 2.0-5.0%, Al 3.5-5.5%, Ti 3.5-5.0%, C 0.1-0.22%, P</=0.0005%, B 0.003-0.010%, Si</=0.05%, Fe</=0.3% and Ni balance. (3) an analogue of M40 (IN 792) Ni-base superalloy with low segregation. The characteristic specificities are (A) to eliminate Zr and reduced P below 0.0005%, and (B) to raise the Al and Ti contents by 1(%). The composition is: Cr 11.0-14.0%, Co 8.0-10.0%, W 2.0-5.0%, Mo 1.0-3.0%, Ta 2.0-5.0%, Al 3.8-4.5%, Ti 4.2-5.4%, C 0.1-0.22%, P</=0.0005%, B 0.003-0.010%, Si</=0.05%, Fe</0.3% and Ni balance. (4) an analogue of M38 (IN 738) Ni-base superalloys with low segregation and high Al and Ti contents. The characteristics specificities are (A) to eliminate Zr and control P below 0.0005%, (B) to raise the Al and Ti contents by about 1(%). The composition is: Cr 15.7-16.3%, Co 8.0-9.0%, W 2.4-2.8%, Mo 1.5-2.0%, Nb 0.6-1.1%, Ta 1.5-2.0%, Al 3.7-5.0%, Ti 3.7-5.0%, C 0.1-0.22%, P</=0.0005%, B 0.005-0.010%, Fe</=0.3%, Si</=0.05% and Ni balance. (5) an analogue of M 38(IN 738) Ni-base superalloy with low segregation and high Cr content. The characteristic specificities are (A) to eliminate Zr and control P content below 0.0005% and (B) to increase the Cr content by about 4(%). The composition is: Cr 18.0-22.0%, Co 7.5-9.5%, W 1.6-4.0%, Mo 2.5-3.0%, Nb 0.3-1.5%, Al 3.7-5.0%, Ti 3.5-5.0%, C 0.08-0.22%, P</=0.0005%, B 0.003-0.010%, Si</=0.05%, Fe</=0.3% and Ni balance.
- It is well known that during the recent two decades the air-cooling technique in cast superalloys has been widely used in many countries and some new techniques, such as directional solidification which can raise the service temperature of cast superalloys by about 20°C, have also been developed. However, the directional solidification technique not only makes the air-cooling difficult to be used, but also results in poorer properties along the transverse direction. To overcome this shortage very expensive metal Hf has to be added in the alloy. The new method based on this invention makes it possible that the transverse properties of the directionally solidified superalloys can be improved obviously without any addition of Hf. So, the invention benefits to the application of the directional solidification technology and makes it easy to combine with the air-cooling technique. By using both of the techniques, the service temperature of the exisiting cast superalloys can be raised by 100-300°C. Meanwhile, the invented new method is also very helpful to solve the difficult problem in hog working processing of wrought superatlloys and greatly improve the hot workability of the alloys.
- The new method of the present invention is carried out as follows: Firstly, the P and Si contents of raw materials (Fe and Cr) must be strictly controlled. If the P and Si contents in Fe and/or Ce are a little high, it is necessary that to refine Fe into powder form by wet metallurgy and to purify Cr several times by electrolysis.
- It is needed that the P content in raw materials of Fe and Cr is below 0.0005%, and Si content is below 0.05%. Secondly, the qualified raw materials are melted in a vacuum induction furnace and the added boron content is controlled at the range from about 0.001 to about 0.015%. Finally, when casting the superalloy blades, the alloy is remelted in the vacuum induction furnace with the same melting technology to the ordinary one.
- I-1. A superalloy (our name: M17E) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 8.0 to about 10.0% Cr, about 10.0 to about 16.0% Co, about 2.5 to about 3.5% Mo, about 5.5 to about 6.5% Al, about 4.5 to about 5.5% Ti, about 0.005 to about 0.015% B, and the balance of Ni, controlling incidental impurities, such as: <0.0005% P, <0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimens.
- I-2. A superalloy (our name: M17F) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 8.0 to about 10.0% Cr, about 8.0 to about 10.0% Co, about 3.0 to about 5.0% W, about 1.0 to about 3.5% Mo, about 3.0 to about 5.0% Ta, about 4.5 to about 5.5% Al, about 4.0 to about 5.0% Ti, about 0.005 to about 0.015% B, and the balance of Ni, controlling incidental impurities,such as: ≦0.0005% P, ≦0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- I-3. A superalloy (our name: M40) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 12 to about 14% Cr, about 8 to about 10% Co, about 1.0 to about 3% Mo, about 3.2 to about 4.3% Al, about 4.2 to about 5.3% Ti, about 0.005 to about 0.015% B, about 3 to about 5% W, about 3 to about 5% Ta and the balance of Ni, controlling incidental impurities, such as: ≦0.0005% P, ≦0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- I-4. A superalloy (our name: M38G) with low segregation for the cast was produced by melting a compositon of about 0.08 to about 0.21% C, about 15 to about 17% Cr, about 7 to about 9% Co, about 2 to about 4% W, about 1 to about 3% Mo, about 1 to about 2.5% Ta, about 3.5 to about 4.5% Al, about 3.3 to about 4.3% Ti, about 0.005 to about 0.015% B,about 0.5 to about 1.5% Nb and the balance of Ni, controlling incidental impurities,such as: ≦0.0005% P, ≦0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- I-5. A superalloy (our name: M36) with low segregation for the cast was produced by melting a composition of about 0.08 to about 0.21% C, about 19 to about 21% Cr, about 7 to about 9% Co, about 2 to about 4% W, about 1 to about 3% Mo, about 3.5 to about 4.5% Al, about 3.5 to about 4.5% Ti, about 0.005 to about 0.015% B,about 0.5 to about 1.5% Nb and the balance of Ni, controlling incidental impurities,such as: ≦0.0005% P, ≦0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cuting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- The most preferred version of the superalloys of the present invention were produced by following compositions of elements in Table I-A.
- The conventional superalloys for the cast containing essentially about 0.004 to about 0.009% P, about 0.03 to about 0.15% Zr, about 0.005 to about 0.02% B, about 0.05 to about 0.3% Si. Because of the segregation, the microstructure of the conventional superalloys are found to have stable laves phase on solidification, to form 3-5% (gamma+gamma′) phase, and to produce delta phase after exposure in the elevated temperatures.
- The suprealloys of the present invention for the cast containing about ≦0.0005% P, eliminating Zr, strictly controlling the contents of B and Si, reducing the segregation, and the microstructures of the said superalloys are found not to have stable laves on solidification.
- Specimens of the said superalloys of Example I were evaluated to determine their mechanical properties at different temperatures.The results are:
- TABLE I-B shows 100-hours stress Rupture strength (MPa) at different temperature and Hot corrosion resistance.
- TABLE I-C shows stress Rupture time (hr)
- As may be noted from Table I-B, Table I-C, the nickel-base superalloys in present invention showed improved elevated temperature strength properties over their proir art and these properties were even further improved by use of the preferred heat treatment.
- II-1. A superalloy (our name :LSDS738) with low segregatin for the directional solidification was produced by melting a composition of about 0.08% C, about 16% Cr, about 8.5% Co, about 2.6% W, about 1.7% Mo, about 0.7% Nb, about 1.7% Ta, about 3.5% Al, about 3.3% Ti, about 0.008% B, Hf-free and the balance of Ni, controlling incidental impurities, such as: ≦0.0005% P, ≦0.05% Si, in a vacuum induction furnace. The melted alloy was cast into ceramic molds to form sticks. And cutting down the ends of the sticks, then remelting the sticks in a vacuum induction furnace. The melted alloy was cast into shaped molds to produce parts or specimans.
- The conventional superaloys for the directional solidification containing essentially Hf and about 0.08% C, about 0.012% B, about 0.10% Zr, about 0.005% P, about 0.1% Si.
- For improving the transverse properties of the directional solidified superalloys, the very expensive metal Hf have to be added in the said alloy.
- The present invention make it possible that the transverse properties of the directional solidified superalloys can be improved obviously without any addition of Hf. So, the invention benefits to the application of the directional solidification technology and makes it easy to combine with the air-cooling technique.
- Specimens of the said superalloys were evaluated to determine their mechanical properties at different temperatures. The results are:
- TABLE II-A shows Stress Rupture Time (hr)
- TABLE II-B shows 100-hour stress Rupture strength (MPa) at different temperature.
- As is evident, the directional solidified superalloys for the cast of the present invention exhibit substantially increased elevated temperature strength and stress Rupture Time, especially increased the transverse properties of the directional solidified suporalloys.
- III-1: A superalloy (our name: LSIN901) with low segregation for the wrought was produced by melting a composition of 0.03% C, 12% Cr, 5.7% Mo, 0.2% Al, 3% Ti, 43% Ni, 0.003% B, and the balance of Fe, controlling incidental impurities, such as: ≦0.0005% P, ≦0.05% Si, in a vacuum inductiong furnace. The melted alloy was cast into ceramic molds to form slabs. The slabs were remelted by vacuum drip melting to form ingot.
- III-2. A superalloys (our name:LSA286) with low segregation for the wrought was produced by melting a compositiong of about 0.08% C, about 13.5 to about 16.0% Cr, about 24% to about 27% Ni, about 1.0% to about 1.5% Mo, about 1.9% to about 2.35% Ti, ≦0.35% Al, about 0.1% to about 0.5% V, about 0.001% to about 0.004% B, and the balance of Fe, controlling incidental impurities, such as:≦0.001% P, ≦0.05% S, in a vacuum induction furnace the malted alloy was cast into ceramic molds to form slabs. The slabs were remelted by vacuum drip melting to form ingot.
- Specimens of the two alloys (LSIN901 and IN901) were evaluated to determin their mechanical properties at both room temperature (20°C) and at elevated temperature (650°C). The results are showed at Table III-A.
- Specimens of the two alloys (LSA286 and A286) were evaluated to determine their mechanical properties their mechanical properties at different temperatures (20°C). The results are showed at Table III-B(1)
- TABLE III-B(2) shows stress Rupture Time (hr) of superalloys (LSA286,A286) in stick shape.
- TABLE III-B(3) shows the mechanical properties of superalloys (LSA286, A286) in flat shape.
- Comparison of the mechanical properties of the superalloys of the present invention (LSIN718) with the prior art (IN718).The results are showed at Table III-C.
- As may be noted from Table III-A, Table III-B, III-C, the superalloys of the present invention (LSIN901, LSA286, LSIN718) showed improved elevated temperature strength properties over the prior art and these properties were even further improved by the use of the preferred heat treatment.
- The new method of the present invention is suitable to both Fe-Ni-Cr-base superalloys and Ni-base superalloys. It is obvious that the characteristics of the low segregation superaloys of the present invention lie in: (1) no addition of Zr; (2) P content is below 0.001 or 0.0005%; (3) contents of Al and Ti increased by 1%; (4) Cr content increased by 4%. The properties of the superalloys provided by this invention are shown in Table IV, V,VI and VII.
- Table IV shows the comparison of the properties of GH901 (IN901) alloy with those of the low segregation GH90; alloy. It can be seen that the tensile strength at room temperature, stress repture property and incipient temperature of the low segregation GH901 alloy are raised obviously. Table V shows the comparison of 100 hour stress repture strength data in the M38 (IN738) and M17(IN100) alloys with those in the corresponding low segregation ones. The properties of the low segregation alloys are obvously higher than those in conventional ones. Table VI gives the comparison of the stress rupture life (hour) and hot corrosion resistance in both series of the alloys (M38 & M36 with low segregation M38 & M36 alloys). Table VII lists the data of the stress reputre strength at elevated temperatures in both IN 792 and low segregation IN 792 alloys. It is clear that the properties of low segregation superalloys are obviously higher than those of the corresponding conventional ones.
- By using the new method provided by this invention, it is quite possible to develop a series of new Fe-base and Ni-base superalloys with excellent properties. It is more important that the properties of the superalloys can be greatly improved by this new method without varying their composition range of the superalloys which are widely used and have stable properties. As well known, it takes very long time to develop kind of new superalloy since it can not be put into production until the stable property data is obtained by long-term and systematic tests, such as stress rupture and creep property tests Therefore, it is of significant importance that to improve obviously the properties of the superalloys only by means of controlling the content of one or two elements without varying their composition ranges. In summary, the invention provides a new technique which is easy to perform and has fantastic benefits to the improvement of the properties of superalloys. Its wide application in indusry will certainly bring about huge economic benefit.
TABLE I-A ALLOYS COMPOSITION (w%) Superalloys Ni C Cr Co W Mo Nb Ta Al Ti B P Si M17E balance 0.17 9.0 15.0 - 3.0 - - 6.0 5.0 0.008 <0.0005 <0.05 M17F balance 0.17 9.0 9.0 3.9 2.0 - 3.9 5.0 4.5 0.008 <0.0005 <0.05 M40G balance 0.18 12.7 9.0 3.9 2.0 - 3.9 3.8 4.8 0.008 <0.0005 <0.05 M38G balance 0.17 16.0 8.5 2.6 1.7 0.7 1.7 4.0 3.8 0.008 <0.0005 <0.05 TABLEI-B 100-hours Stress Rupture Strength (MPa) at different temperature and Hot Corrosion Resistance Superalloys 750°C 800°C 850 900°C 950°C 1000°C Hot Corrosion resistance IN100 686 540 421 312 206 147 bad M17E 706 569 466 333 235 157 bad M17F 745 608 480 349 255 176 bad IN792 686 540 421 312 206 142 good M40 696 573 451 343 245 162 good N738 598 451 363 255 176 118 good M38G 666 529 402 299 206 135 good M36 627 500 363 260 186 123 excelent TABLE I-C Stress Rupture Time (hr) Superaeloys 815°C 932 °C 51 (Kg/mm²) 39 (Kg/mm²) 155 (Kg/mm²) IN792 100 1000 100 M40 300 2500 300 TABLE II-A Stress Rupture Time (hr) 815°C 43Kg/mm² alloys IN738 DS 738 LSDS738 Vertical Vertical transverse Time (hr) 100∼120 80∼100 300 200 TABLE II-B 100-hour Stress Rupture Strength (mpa) at different T. alloys 750°C 800°C 850°C 900°C 950°C 1000°C IN738 598 451 363 255 176 118 LSM38G 666 529 402 299 206 135 LSDS 38G Vertical 710 570 456 335 235 142 Transverse 670 540 430 TABLE III-A Alloys 20°C 650°C/617MPa σb (mpa) σ0.2 (mpa) δ (%) ψ (%) Stress Rupture Time (hr) smotr with gap LSIN901 1340 1000 22 27 131 617 IN901 1226 821 19 20 64 63 TABLE III-B (1) Alloys 20°C σb (mpa) σ0.2 (mpa) δ (%) ψ (%) LSA286 stick 1150 803 24 43 flat 1049 706 29 54 A286 stick 892 676 28 43 flat 891 675 28 44 Alloys 550°C σb (mpa) σ0.2 (mpa) δ (%) ψ (%) LSA286 stick 933 686 20 50 flat A286 stick 853 633 22 50 flat Alloys 550°C/666 (MPa) 650°C451 (MPa) Stress Rupture Time (hr) smoth with gap smoth with gap LSA286 stick 6545 >984 flat 243 332 A286 stick 66 84 flat 64 67 TABLE III-B (2) Stress Rupture Time (hr) of Superalloys (LSA286, A286) in stick shape Alloys Begining T. of wrought (°C) 550°C, 68Kg/mm² Time (hr) 650°C, 46Kg/mm² Time (hr) 700 °C, 32Kg/ mm² Time (hr) smoth with gap smoth with gap smoth with gap LSA286 1240 652 >984 475 >650 304 659 >985 287 A286 1120 53 64 67 67 68.7 TABLE III-B (3) The mechanical properties of superalloys (LSA286, A286) in flat shape Alloys Begining T. of Wrought (°C) 20°C σb (mpa) σ0.2 (mpa) δ (‰) ψ (‰) LSA286 1180 1068 770 24.6 43.6 (flat) 1070 789 25.4 42.8 LSA286 1220 1053 761 28.2 50.8 (flat) 1055 807 24.7 47.2 A286 1120 1066 707 24.4 56.8 (flat) Alloys Begining T. of Wrought (°C) 650°C σb (mpa) σ0.2 (mpa) δ (‰) ψ (‰) LSA286 1180 832 669 27.2 50.9 (flat) 837 634 27.1 52.6 LSA286 1220 837 687 24.6 47.6 (flatwt) 835 699 26.6 45.6 A286 1120 (flat) Alloys Begining T. of Wrought (°C) 650°C, 40Kg/mm² Crystal size τ (hr) δ/ψ (%) LSA286 1180 2007 15.2/25.5 4∼6 (flat) 1335 13.1/19.6 LSA286 1220 1971 8.6/21.9 4∼6 (flat) 2078 8.3/22.8 A286 1120 187 7.6/15.7 5∼8 (flat) 261 8.3/13.1 TABLE III-C Alloys 20°C 650°C σb (mpa) σ0.2 (mpa) δ (%) ψ (%) σb (mpa) σ0.2 (mpa) δ (%) ψ (%) IN718 1553 1393 13.5 22.3 1233 1083 28.4 56.5 LSIN718 1517 1325 14.2 21.7 1232 1087 28.2 55.6 Alloys 650°C Stress Rupture Time (hr) Stress (mpa) Stress rupture Time (hr) δ (%) stress rupture Time (hr) (the specimens With gap) IN718 686 37.3 38.8 231 53.6 30.8 450 62.5 28.3 421 64.0 32.0 493 LSIN718 700 114.2 16.8 168 111.3 16.8 >261 68.7 27.6 >261 Table IV The Properties of The Alloys (Tensile properties at room temperature) Alloys σ0.2 (kg/mm²) σb (kg/mm²) δ (%) ψ (%) αk (kg/mm²) 650°C, 63Kg/mm² time (hours) Incipient MeltingPoint (°C) GH901 120/130 84/94 17/21 18/22 5.5/5.6 56/72 1140 LSGH901 134/136 100/101 16/18 31/32 7.5/8.0 109/136 1260 Table V 100hour Stress Rupture Strength (Kg/mm²) at Different Temperature Alloys 700°C 800°C 850°C 900°C 950°C 1000°C M38 61 46 37 26 18 12 LSM38 68 54 41 30.5 21 13.8 M17(In100) 70 56 43 32 21 15 LSM17F 76 62 49 36 26 18 Table VI Stress Rupture Time(h) and Hot Crrosion Resistance Alloys 900C, 26Kg/mm² 850°C, 37Kg/mm² 750°C, 60Kg/mm² hot corrosion resistance M38 100 100 100 good LSM38 300 300 400 good (M38G) LSM36 77 155/176 excellent Table VII Stress Rupture Time(h) Alloys 815°C 932°C 51 (kg/mm²) 39(kg/mm²) 15.5 (kg/mm²) IN-792 100 1000 100 LSIN-792(M40) 300 2500 300 LS: low segregation.
Claims (15)
1. An alloy which comprises nickel, up to about 0.001% phosphorus up to about 0.05% silicon, about 0.001 to about 0.015% boron, no zirconium.
2. The alloy of claim 1 wherein the balance of the alloy comprises one or more elements selected from the group comprising of carbon, iron, chromium, cobact, tungsten, molybdenum, titanium niobium, aluminum and tantalum.
3. An alloy which consists essentially of about 0.02 to about 0.22% carbon, about 6 to about 22% chromium, up to about 8% molybdenum, up to about 4% niobium, up to about 12% tantalum, about 2 to about 6.5% aluminum, about 2 to about 5.5% titanium, about 0.003 to about 0.015% boron, up to about 0.0005% phosphorus, up to about 0.05% silicon zirconium-free and the balance nickel.
4. The alloy of claim 3 wherein if the alloy is to be directional solidified,carbon is about 0.05 to about 0.13% and no hafnium is added, if the alloy is to be casted, carbon is about 0.17% to about 0.18%.
5. An alloy which consists essentially of about 0.08 to 0.21% carbon, about 8 to about 10% chromium, about 10 to about 16% cobalt, about 2.5 to about 3.5% molybdenum, about 5.5 to about 6.5% aluminum, about 4.5 to about 5.5% titanium, about 0.005 to about 0.015 boron, up to about 0.0005% phosphorus, up to about 0.05% silicon, zirconium-free and the balance nickel.
6. An alloy which consists essentially of about 0.08 to about 0.21% carbon, about 8 to about 10% chromium, about 8 to about 10% cobalt, about 3 to about 5% tungsten, about 1 to about 3% molybdenum, about 3 to about 5% tantalum, about 4.5% to about 5.5% aluminum, about 4 to about 5% titanium, about 0.005 to about 0.015% boron, phosphorus</=0.0005%, silicon</=0.05%, zirconium-free and the balance nickel.
7. An alloy which consists essentially of about 0.08 to about 0.21% carbon, about 12 to about 14% chromium, about 8 to about 10% cobalt, about 3 to about 5% tungsten, about 1 to about 3% molybdenum, about 3 to about 5% tantalum, about 3.2 to about 4.3% aluminum, about 4.2 to about 5.3% titanium,about 0.005 to about 0.015% boron, phosphorus</=0,0005% silicon</=0.05%, zirconium-free and the balance nickel.
8. An alloy which consists essentially of about 0.08 to about 0.21% carbon, about 15 to about 17% chromium, about 7 to about 9% cobalt, about 2 to about 4% tungsten, about 1 to about 3% molybdenum, about 0.5 to about 1.5% niobium, about 1 to about 2.5% tantalum, about 3.5 to about 4.5% aluminum, about 3.3 to about 4.3% titanium, about 0.005 to about 0.015% boron, phosphorus</=0.0005%, silican<=0.05%, zirconum-free and the balance nickel.
9. An alloy which consists essentially of about 0.08 to about 0.21% carbon, about 19 to about 21% chromium, about 7 to about 9% cobalt, about 2 to about 4% tungsten, about 1 to about 3% molybdenum, about 0.5 to about 1.5% niobium, about 3.5 to about 4.5% aluminum, about 3.5 to about 4.5% titanium, about 0.005 to about 0.015% boron, phosphorus</=0.0005%, silicon</=0.05%m, zirconium-free and the balance nickel.
10. The alloy of claims 5 to 9 wherein hafnium is free.
11. An alloy which consists essentially of about 0.01 to about 0.05% carbon, about 11 to about 13% chromium, about 5.3 to about 6.3% molybdenum, about 0.1 to about 0.5% aluminum, about 2.5 to about 3.5% titanium, about 40 to about 45% nickel, about 0.001 to about 0.005% boron, phosphorus</=0.001%, silicon</=0.05% and the balance iron.
12. An alloy which consists essentially of about 0.01 to about 0.05% carbon, about 14 to about 16% chromium, about 0.1 to about 0.5% aluminum, about 1.8 to about 3% titanium, about 24 to about 28% nickel, about 0.001 to about 0.005% boron, phosphors</=0.001%, silicon</=0.05% and the balance iron.
13. A method for making an improved superalloy comprising steps of:
(a) controlling phosphorus content in iron and chromium of raw materials, said phosphorus content in iron and chromium is less than 0.0005%,
(b) melting the raw materials with added boron in the range from about 0.001 to about 0.015% and eliminating zirconium.
14. The method of claim 13 wherein silicon content in iron and chromium is less than about 0.05%.
15. An alloy made by the method of claim 13 or 14.
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CN89105034 | 1989-03-15 | ||
CN 89105034 CN1045607A (en) | 1989-03-15 | 1989-03-15 | A kind of method that improves the superalloy performance |
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Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0561179A2 (en) * | 1992-03-18 | 1993-09-22 | Westinghouse Electric Corporation | Gas turbine blade alloy |
WO1999067435A1 (en) * | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
EP1961830A1 (en) * | 2005-11-09 | 2008-08-27 | Japan Science and Technology Agency | Iron-based alloy having shape-memory property and superelasticity and method for manufacture thereof |
JP2014005528A (en) * | 2012-05-29 | 2014-01-16 | Toshiba Corp | Ni-BASED HEAT-RESISTANT ALLOY AND TURBINE COMPONENT |
EP2703507A1 (en) * | 2012-08-30 | 2014-03-05 | Hitachi Ltd. | Ni base alloy and gas turbine blade and gas turbine utilizing the same |
US9856553B2 (en) | 2008-02-13 | 2018-01-02 | The Japan Steel Works, Ltd. | Ni-based superalloy with excellent unsusceptibility to segregation |
CN112779385A (en) * | 2020-12-24 | 2021-05-11 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of GH901 turbine disc forging |
CN114250375A (en) * | 2021-06-02 | 2022-03-29 | 中航上大高温合金材料股份有限公司 | Method for producing GH738 alloy by using reclaimed materials |
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Publication number | Priority date | Publication date | Assignee | Title |
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US11214852B2 (en) | 2017-02-08 | 2022-01-04 | Borgwarner Inc. | Alloys for turbocharger components |
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Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3385698A (en) * | 1965-04-09 | 1968-05-28 | Carpenter Steel Co | Nickel base alloy |
US3667938A (en) * | 1970-05-05 | 1972-06-06 | Special Metals Corp | Nickel base alloy |
GB2075057A (en) * | 1980-05-01 | 1981-11-11 | Rolls Royce | Nickel base superalloy |
EP0045563A1 (en) * | 1980-07-25 | 1982-02-10 | The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and | Nickel-base alloy for single crystal casting |
GB2106138A (en) * | 1981-09-19 | 1983-04-07 | Rolls Royce | Single crystal nickel alloy casting |
EP0194391A1 (en) * | 1985-03-13 | 1986-09-17 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
EP0214080A2 (en) * | 1985-08-16 | 1987-03-11 | United Technologies Corporation | Reduction of twinning in directional recrystallization of nickel base superalloys |
EP0237378A1 (en) * | 1986-02-06 | 1987-09-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Superalloy having a nickel base matrix, manufactured by powder-metallurgical processing, and gas turbine discs made from this alloy |
-
1989
- 1989-03-15 CN CN 89105034 patent/CN1045607A/en active Pending
-
1990
- 1990-03-14 EP EP19900250070 patent/EP0387976A3/en not_active Withdrawn
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3385698A (en) * | 1965-04-09 | 1968-05-28 | Carpenter Steel Co | Nickel base alloy |
US3667938A (en) * | 1970-05-05 | 1972-06-06 | Special Metals Corp | Nickel base alloy |
GB2075057A (en) * | 1980-05-01 | 1981-11-11 | Rolls Royce | Nickel base superalloy |
EP0045563A1 (en) * | 1980-07-25 | 1982-02-10 | The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and | Nickel-base alloy for single crystal casting |
GB2106138A (en) * | 1981-09-19 | 1983-04-07 | Rolls Royce | Single crystal nickel alloy casting |
EP0194391A1 (en) * | 1985-03-13 | 1986-09-17 | General Electric Company | Yttrium and yttrium-silicon bearing nickel-base superalloys especially useful as compatible coatings for advanced superalloys |
EP0214080A2 (en) * | 1985-08-16 | 1987-03-11 | United Technologies Corporation | Reduction of twinning in directional recrystallization of nickel base superalloys |
EP0237378A1 (en) * | 1986-02-06 | 1987-09-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Superalloy having a nickel base matrix, manufactured by powder-metallurgical processing, and gas turbine discs made from this alloy |
Non-Patent Citations (2)
Title |
---|
G.W. MEETHAM: "Development of Gas Turbine Materials", 1981, Applied Science Publishers Ltd., London, GB, pages 93, 296-298, page 93, second paragraph; page 297, Alloy C1023. * |
Metal Progress, Vol. 129, No. 4, March 1986, pages 39-42, Metals Park, Ohio, US; Y. MINGGAO et al.: "Overview: investment casting alloys for aircraft parts". * |
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EP0561179A2 (en) * | 1992-03-18 | 1993-09-22 | Westinghouse Electric Corporation | Gas turbine blade alloy |
EP0561179A3 (en) * | 1992-03-18 | 1993-11-10 | Westinghouse Electric Corp | Gas turbine blade alloy |
WO1999067435A1 (en) * | 1998-06-23 | 1999-12-29 | Siemens Aktiengesellschaft | Directionally solidified casting with improved transverse stress rupture strength |
EP1961830A1 (en) * | 2005-11-09 | 2008-08-27 | Japan Science and Technology Agency | Iron-based alloy having shape-memory property and superelasticity and method for manufacture thereof |
EP1961830A4 (en) * | 2005-11-09 | 2008-12-31 | Japan Science & Tech Agency | Iron-based alloy having shape-memory property and superelasticity and method for manufacture thereof |
US8083990B2 (en) | 2005-11-09 | 2011-12-27 | Japan Science And Technology Agency | Iron-based alloy having shape memory properties and superelasticity and its production method |
US9856553B2 (en) | 2008-02-13 | 2018-01-02 | The Japan Steel Works, Ltd. | Ni-based superalloy with excellent unsusceptibility to segregation |
US10221473B2 (en) | 2008-02-13 | 2019-03-05 | The Japan Steel Works, Ltd. | Ni-based superalloy with excellent unsusceptibility to segregation |
JP2014005528A (en) * | 2012-05-29 | 2014-01-16 | Toshiba Corp | Ni-BASED HEAT-RESISTANT ALLOY AND TURBINE COMPONENT |
EP2703507A1 (en) * | 2012-08-30 | 2014-03-05 | Hitachi Ltd. | Ni base alloy and gas turbine blade and gas turbine utilizing the same |
EP2703507B1 (en) | 2012-08-30 | 2016-01-20 | Mitsubishi Hitachi Power Systems, Ltd. | Ni base alloy and gas turbine blade and gas turbine utilizing the same |
CN112779385A (en) * | 2020-12-24 | 2021-05-11 | 陕西宏远航空锻造有限责任公司 | Heat treatment method of GH901 turbine disc forging |
CN114250375A (en) * | 2021-06-02 | 2022-03-29 | 中航上大高温合金材料股份有限公司 | Method for producing GH738 alloy by using reclaimed materials |
Also Published As
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EP0387976A3 (en) | 1990-11-07 |
CN1045607A (en) | 1990-09-26 |
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