US20210102275A1 - High oxidation-resistant alloy and gas turbine applications using the same - Google Patents
High oxidation-resistant alloy and gas turbine applications using the same Download PDFInfo
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- US20210102275A1 US20210102275A1 US16/924,893 US202016924893A US2021102275A1 US 20210102275 A1 US20210102275 A1 US 20210102275A1 US 202016924893 A US202016924893 A US 202016924893A US 2021102275 A1 US2021102275 A1 US 2021102275A1
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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%
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y70/00—Materials specially adapted for additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/0433—Nickel- or cobalt-based alloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Combustion & Propulsion (AREA)
- Powder Metallurgy (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.
Description
- This application is a continuation of U.S. application Ser. No. 16/080,364, filed Aug. 28, 2018. U.S. application Ser. No. 16/080,364 is the U.S. National Stage of International Application No. PCT/EP2017/055666, filed Mar. 10, 2017. International Application No. PCT/EP2017/055666 claims the benefit of IT 102016000025497, filed Mar. 10, 2016. Each of these applications is incorporated by reference in their entirety.
- Embodiments of the subject matter disclosed herein relate primarily to a high oxidation-resistant alloy and gas turbine applications using the same.
- For gas turbine applications (buckets, nozzles, shrouds, combustion chambers) nickel-base superalloys are used.
- However, in this field, nickel-base superalloys encounter one fundamental limitation, i.e. their oxidation resistance.
- In this regard, it should be considered that creep damage in gas turbine components is associated with grain boundary precipitates. These particles provide favourable nucleation sites for grain boundary cavities and micro-cracks. The formation of HfC and M23C6 carbides as grain boundary precipitates can also lead to grain boundary metal depleted zones which are susceptible to corrosive attack.
- Therefore, there is a general need for materials suitable for gas turbine applications, which show good properties in terms of thermal fatigue at the operating conditions, low density, flexural resistance, creep properties and fracture toughness, as well as an improved oxidation resistance.
- An important idea is to provide an alloy wherein the selected elements in selected ranges allows to significantly increase the oxidation resistance by reducing the undesired formation of Hafnium carbide and precipitation of M23C6 carbides. This avoids the additional cost and process step of antioxidant coatings.
- This alloy can be produced by conventional processes such as Powder Metallurgy and Investment Casting, as well as innovative Additive Manufacturing technologies (e.g. Direct Metal Laser Melting processes).
- First embodiments of the subject matter disclosed herein correspond to a high oxidation-resistant alloy having a nominal composition consisting of:
- Co 9.00-9.50 wt % W 9.30-9.70 wt % Cr 8.00-8.70 wt % Al 4.00-15.50 wt % Ti 0.60-0.90 wt % Ta 2.80-3.30 wt % Mo 0.40-0.60 wt % Hf up to 1.20 wt % Mn up to 0.05 wt % Si up to 0.02 wt % C up to 0.065 wt % Re 0.00-4.00 wt % Mg, B, Zr, Fe, O, N, S, or a up to 0.287 wt % mixture thereof Ni balance based on the alloy weight.
- In general, said alloy shows remarkably improved oxidation resistance properties with respect to conventional Ni super-alloys.
- Second embodiments of the subject matter disclosed herein correspond to a gas turbine component, such as a bucket, nozzle, shroud, and combustion chambers, made of the above alloy.
- The accompanying drawings, which are incorporated herein and constitute a part of the specification, illustrate exemplary embodiments of the present subject matter and, together with the detailed description, explain these embodiments. In the drawings:
-
FIG. 1 shows a micrograph taken by Optical Microscope of the oxidation surface of a conventional alloy ‘Mar M247 LC’, after 1000 h at 980° C.; -
FIG. 2 shows a micrograph taken by Optical Microscope of the oxidation surface of the alloy of Example 1, after 1000 h at 980° C.; and -
FIG. 3 shows the affected metal thickness at 980° C. after different times (from 1000 to 4000 hours) for the alloy Mar M247 LC and the alloy of Example 1. The thickness is normalized with respect to the maximum affected thickness in the alloy MarM 247 LC. - The following description of exemplary embodiments refers to the accompanying drawings.
- The following description does not limit embodiments of the invention. Instead, the scope of embodiments of the invention is defined by the appended claims.
- Reference throughout the specification to “one embodiment” or “an embodiment” means that a particular feature, structure, or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrases “in one embodiment” or “in an embodiment” in various places throughout the specification is not necessarily referring to the same embodiment. Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.
- First embodiments of the subject matter disclosed herein correspond to a high oxidation-resistant alloy having a nominal composition consisting of:
- Co 9.00-9.50 wt % W 9.30-9.70 wt % Cr 8.00-8.70 wt % Al 4.00-15.50 wt % Ti 0.60-0.90 wt % Ta 2.80-3.30 wt % Mo 0.40-0.60 wt % Hf up to 1.20 wt % Mn up to 0.05 wt % Si up to 0.02 wt % C up to 0.065 wt % Re 0.00-4.00 wt % Mg, B, Zr, Fe, O, N, S, or a up to 0.287 wt % mixture thereof Ni balance based on the alloy weight.
- It should be appreciated that the alloy above encompasses reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as it will be demonstrated in the following working examples. Furthermore, the above alloy has an improved oxidation resistance due to the specific ranges of W and Cr.
- In some embodiments of the high oxidation-resistant alloy, Al is present in an amount of 4.00-10.50 wt %.
- In other embodiments of the high oxidation-resistant alloy, Mg is present in an amount of up to 0.008 wt %, and Mo, B, Zr, Fe, O, N, S, or a mixture thereof in an amount of up to 0.879 wt %.
- In other embodiments of the high oxidation-resistant alloy, Mo is present in an amount of up to 0.60 wt %, in one embodiment 0.40-0.60 wt %, and Mg, B, Zr, Fe, O, N, S, or a mixture thereof in an amount of up to 0.287 wt %.
- In other embodiments of the high oxidation-resistant alloy, B is present in an amount of up to 0.015 wt %, in one embodiment 0.005-0.015 wt %, and Mg, Mo, Zr, Fe, O, N, S, or a mixture thereof in an amount of up to 0.872 wt %.
- In other embodiments of the high oxidation-resistant alloy, Zr is present in an amount of up to 0.015 wt %, in one embodiment 0.005-0.015 wt %, and Mg, Mo, B, Fe, O, N, S, or a mixture thereof in an amount of up to 0.872 wt %.
- In other embodiments of the high oxidation-resistant alloy, Fe is present in an amount of up to 0.20 wt %, and Mg, Mo, B, Zr, O, N, S, or a mixture thereof in an amount of up to 0.687 wt %.
- In other embodiments of the high oxidation-resistant alloy, 0 is present in an amount of up to 0.02 wt %, and Mg, Mo, B, Zr, Fe, N, S, or a mixture thereof in an amount of up to 0.867 wt %.
- In other embodiments of the high oxidation-resistant alloy, N is present in an amount of up to 0.005 wt %, and Mg, Mo, B, Zr, Fe, 0, S, or a mixture thereof in an amount of up to 0.882 wt %.
- In other embodiments of the high oxidation-resistant alloy, S is present in an amount of up to 0.004 wt %, and Mg, Mo, B, Zr, Fe, 0, N, or a mixture thereof in an amount of up to 0.883 wt %.
- In embodiments, the high oxidation-resistant alloy has a nominal composition consisting of:
- Co 9.00-9.50 wt % W 9.30-9.70 wt % Cr 8.00-8.70 wt % Al 4.00-10.50 wt % Ti 0.60-0.90 wt % Ta 2.80-3.30 wt % Hf up to 1.20 wt % Mn up to 0.05 wt % Mg up to 0.008 wt % Mo up to 0.60 wt % Si up to 0.02 wt % B up to 0.015 wt % Zr up to 0.015 wt % Fe up to 0.20 wt % O up to 0.020 wt % N up to 0.0050 wt % S up to 0.0040 wt % C up to 0.065 wt % Re 0.0-0.4 wt % Ni balance based on the alloy weight.
- In embodiments of the high oxidation-resistant alloy, Al is present in an amount of 5.25-5.75 wt %.
- In other embodiments of the high oxidation-resistant alloy, Hf is present in an amount of 1.00-1.20 wt %.
- In other embodiments of the high oxidation-resistant alloy, Re is present in an amount of 0.0-3.0 wt %.
- An embodiment corresponds to a high oxidation-resistant alloy having a nominal composition consisting of:
- Co 9.07 wt % W 9.36 wt % Cr 8.43 wt % Al 5.73 wt % Ti 0.65 wt % Ta 2.93 wt % Mo 0.51 wt % Hf 1.02 wt % Mn up to 0.001 wt % Mg up to 0.060 wt % Si 0.06 wt % B 0.010 wt % Zr 0.012 wt % Fe 0.035 wt % O 0.014 wt % N 0.002 wt % S up to 0.010 wt % C 0.043 wt % Re 0.0 wt % Ni balance based on the alloy weight.
- With reference to
FIG. 1 , the observed oxidation damage of conventional alloy ‘MarM 247 LC’ is characterized by spiking oxidation attack. The EDS analysis of the internal oxidation reveals that the Al2O3 is in one embodiment present along with Hf and Ta oxides. One possible explanation of this type of oxidation is that Hf carbides have greater affinity for oxygen than the matrix metal. Some literature studies show that HfO2 particles act as short circuit diffusion paths for oxygen transportation, due to the fact that the diffusivity of oxygen in HfO2 is several orders of magnitude higher than in Al2O3. This leads to in one embodiment localize scale thickening in the neighborhood of these particles, thus causing a deep penetration of the formed HfO2 scales into the substrate. The oxygen transported through this short circuit diffusion path reacts with Al atoms in the surrounding areas to form Al2O3 scales. Therefore, HfO2 ‘pegs’ scales surrounded by Al2O3 scales are formed. - Conversely, with reference with
FIG. 2 , the alloy herein disclosed shows a homogeneous oxide layer without in one embodiment localized scale thickening, but with a total affected layer that resulted half of that of conventional alloy ‘Mar M 247 LC’. - Oxidation tests performed on the herein disclosed alloy demonstrated that its oxidation resistance is increased with respect to conventional alloy ‘
Mar M 247 LC’, i.e. a comparative Ni-based superalloy, as shownFIG. 3 . - The alloy herein disclosed can be obtained by processes known in the art, such as Powder Metallurgy, Investment Casting, Direct Metal Laser Melting (DMLM), Selective Laser Melting (SLM), Selective Laser Sintering (SLS), Laser Metal Forming (LMF) or Electron Beam Melting (EBM).
- In general, the process of production of the alloy can be carried out until a desired thickness and shape of the alloy is achieved.
- However, in one embodiment of the processes, the alloy is obtained by Direct Metal Laser Melting (DMLM), followed by a Hot Isostatic Press (HIP) process. The resulting alloy solution is then heat treated and allowed to cool and harden.
- In some embodiments, the alloy is obtained by DMLM, wherein the power source has an energy power of 150-370 W, more particularly in one embodiment of about 350 W.
- In other embodiments, the resulting powder layer thickness is, in an embodiment, lower than 0.06 mm (i.e. 60 microns). Particularly in one embodiment a layer thickness of about 0.04 mm.
- The power source scan spacing is, in an embodiment, arranged in order to provide substantial overlapping of adjacent scan lines. An overlapping scan by the power source enables stress reduction to be provided by the subsequent adjacent scan, and may effectively provide a continuously heat treated material.
- A Hot Isostatic Press (HIP) process is then performed in order to obtain the alloy with the desired characteristics. Good results have been obtained from 4 hours on, at 140 MPa and 1260° C. with heat up and cool down rates of 8-15° C./min.
- The resulting alloy solution is then heat treated and allowed to cool and harden.
- Second embodiments of the subject matter disclosed herein correspond to a gas turbine component, such as a bucket, nozzle, combustion chambers, and shroud, made of the above alloy.
- It should be also understood that all the combinations of aspects of the alloy, and process of production, as well as their uses in gas turbine applications, as above reported, are to be deemed as hereby disclosed.
- While the disclosed embodiments of the subject matter described herein have been fully described above with particularity and detail in connection with several exemplary embodiments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without materially departing from the novel teachings, the principles and concepts set forth herein, and advantages of the subject matter recited in the appended claims. Hence, the proper scope of the disclosed innovations should be determined only by the broadest interpretation of the appended claims so as to encompass all such modifications, changes, and omissions. In addition, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments.
- An alloy has been prepared having the following nominal composition:
- Co 9.07 wt % W 9.36 wt % Cr 8.43 wt % Al 5.73 wt % Ti 0.65 wt % Ta 2.93 wt % Mo 0.51 wt % Hf 1.02 wt % Mn up to 0.001 wt % Mg up to 0.060 wt % Si 0.06 wt % B 0.010 wt % Zr 0.012 wt % Fe 0.035 wt % O 0.014 wt % N 0.002 wt % S up to 0.010 wt % C 0.043 wt % Re 0.0 wt % Ni balance based on the alloy weight.
- The alloy was obtained by DMLM, wherein the power source had an energy power of about 350 W. The resulting powder layer thickness was of about 0.04 mm.
- The power source scan spacing was, in an embodiment, arranged in order to provide substantial overlapping of adjacent scan lines. An overlapping scan by the power source enabled stress reduction to be provided by the subsequent adjacent scan, and may effectively provide a continuously heat treated material.
- A Hot Isostatic Press (HIP) process was then performed from 4 hours on, at 140 MPa and 1260° C. with heat up and cool down rates of 8-15° C./min.
- The resulting alloy solution was then heat treated and allowed to cool and harden.
- Oxidation resistance of the alloy of Example 1 has been evaluated by carrying out static oxidation tests at 870° C. up to 4000 hours.
- Tests were carried out on dish samples with a diameter of 25 mm and a thickness of 3 mm.
- Oxidated samples were cut in two parts and conventionally prepared for metallographic observation of their thickness. They were observed by Optical Microscope and the total affected layer by oxidation was measured.
- OM microstructures for conventional Mar M247 LC (
FIG. 1 ) and the alloy of Example 1 (FIG. 2 ) are reported. In particular, the oxidation damage of conventional Mar M247 LC characterized by spiking oxidation attacks due to Hafnium Carbides is well recognizable inFIG. 1 . On the other hand, the alloy of Example 1 is characterized by a homogeneous oxidation layer. -
FIG. 3 shows the affected metal thickness at 980° C. after different times (from 1000 to 4000 hours) for conventional Mar M247 LC and the alloy of Example 1. The thickness is normalized with respect to the maximum affected thickness inMar M 247 LC. It is well visible the better oxidation behavior of the alloy of Example 1 for which the affected metal thickness is halved with respect to conventional Mar M247 LC. - This written description uses examples to disclose the invention, including the preferred embodiments, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (18)
1. A high oxidation-resistant alloy having a nominal composition comprising:
Co 9.00-9.50 wt %;
W 9.30-9.70 wt %;
Cr 8.00-8.70 wt %;
Al 4.00-15.50 wt %;
Ti 0.60-0.90 wt %;
Ta 2.80-3.30 wt %;
Mo 0.40-0.60 wt %;
Hf up to 1.20 wt %;
Ni;
based on the alloy weight.
2. The high oxidation-resistant alloy of claim 1 , wherein Al is present in an amount of 7-10.50 wt %.
3. The high oxidation-resistant alloy of claim 1 , wherein Hf is present in an amount of 1.00-1.20 wt %.
4. The high oxidation-resistant alloy of claim 1 , further comprising Re in a non-zero amount of up to 4.0 wt %.
5. The high oxidation-resistant alloy of claim 1 , further comprising C in a non-zero amount up to 0.065 wt %.
6. The high oxidation-resistant alloy of claim 1 , further comprising Mg in a non-zero amount of up to 0.008 wt %, and Mo, B, Zr, Fe, O, N, S, or a mixture thereof, in an amount of up to 0.879 wt %.
7. The high oxidation-resistant alloy of claim 1 , further comprising Mg, B, Zr, Fe, O, N, S, or a mixture thereof, in an amount of up to 0.287 wt %.
8. The high oxidation-resistant alloy of claim 1 , further comprising B in a non-zero amount of up to 0.015 wt %, and Mg, Mo, Zr, Fe, O, N, S, or a mixture thereof, in an amount of up to 0.872 wt %.
9. The high oxidation-resistant alloy of claim 1 , further comprising Zr in a non-zero amount of up to 0.015 wt %, and Mg, Mo, B, Fe, O, N, S, or a mixture thereof, in an amount of up to 0.872 wt %.
10. The high oxidation-resistant alloy of claim 1 , further comprising Fe in a non-zero amount of up to 0.20 wt %, and Mg, Mo, B, Zr, O, N, S, or a mixture thereof, in an amount of up to 0.687 wt %.
11. The high oxidation-resistant alloy of claim 1 , further comprising O in a non-zero amount of up to 0.02 wt %, and Mg, Mo, B, Zr, Fe, N, S, or a mixture thereof, in an amount of up to 0.867 wt %.
12. The high oxidation-resistant alloy of claim 1 , further comprising N in a non-zero amount of up to 0.005 wt %, and Mg, Mo, B, Zr, Fe, O, S, or a mixture thereof, in an amount of up to 0.882 wt %.
13. The high oxidation-resistant alloy of claim 1 , further comprising S in a non-zero amount of up to 0.004 wt %, and Mg, Mo, B, Zr, Fe, O, N, or a mixture thereof in an amount of up to 0.883 wt %.
14. The high oxidation-resistant alloy of claim 1 , having a nominal composition consisting of:
Co 9.00-9.50 wt %;
W 9.30-9.70 wt %;
Cr 8.00-8.70 wt %;
Al 4.00-10.50 wt %;
Ti 0.60-0.90 wt %;
Ta 2.80-3.30 wt %;
Hf up to 1.20 wt %;
Mn up to 0.05 wt %;
Mg up to 0.008 wt %;
Mo up to 0.60 wt %;
Si up to 0.02 wt %;
B up to 0.015 wt %;
Zr up to 0.015 wt %;
Fe up to 0.20 wt %;
O up to 0.020 wt %;
N up to 0.0050 wt %;
S up to 0.0040 wt %;
C up to 0.065 wt %;
Re up to 0.4 wt %;
Ni balance;
based on the alloy weight.
15. The high oxidation-resistant alloy of claim 14 , having a nominal composition consisting of:
Co 9.07 wt %;
W 9.36 wt %;
Cr 8.43 wt %;
Al 5.73 wt %;
Ti 0.65 wt %;
Ta 2.93 wt %;
Mo 0.51 wt %;
Hf 1.02 wt %;
Mn up to 0.001 wt %;
Mg up to 0.060 wt %;
Si 0.06 wt %;
B 0.010 wt %;
Zr 0.012 wt %;
Fe 0.035 wt %;
O 0.014 wt %;
N 0.002 wt %;
S up to 0.010 wt %;
C 0.043 wt %;
Re 0.00 wt %;
Ni balance;
based on the alloy weight.
16. The high oxidation-resistant alloy of claim 1 , obtainable by Powder Metallurgy, Investment Casting, Direct Metal Laser Melting (DMLM), Selective Laser Melting (SLM), Selective Laser Sintering (SLS), Laser Metal Forming (LMF) or Electron Beam Melting (EBM).
17. A method for producing a turbomachine component, comprising producing the component by additive manufacturing technologies employing a high oxidation-resistant alloy according to claim 1 .
18. A gas turbine component, the component being a bucket, nozzle, combustion chamber or shroud, made of the alloy of claim 1 .
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ITUA2016A001551A ITUA20161551A1 (en) | 2016-03-10 | 2016-03-10 | LEAGUE HAVING HIGH RESISTANCE TO OXIDATION AND APPLICATIONS OF GAS TURBINES THAT USE IT |
PCT/EP2017/055666 WO2017153573A1 (en) | 2016-03-10 | 2017-03-10 | High oxidation-resistant alloy and gas turbine applications using the same |
US201816080364A | 2018-08-28 | 2018-08-28 | |
US16/924,893 US20210102275A1 (en) | 2016-03-10 | 2020-07-09 | High oxidation-resistant alloy and gas turbine applications using the same |
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KR (2) | KR20220051855A (en) |
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2017
- 2017-03-10 RU RU2018130865A patent/RU2729477C2/en active
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EP3426811A1 (en) | 2019-01-16 |
KR20220051855A (en) | 2022-04-26 |
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US10724122B2 (en) | 2020-07-28 |
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