Component for a turbomachine and method for manufacturing same

Abstract

The invention relates to a component for a turbomachine, in particular for an aircraft propulsion system, wherein the component (1, 2, 3) is manufactured from alloy powder and has a first region (11) and at least one second region (12, 13, 14). The invention also relates to a material for a component (1, 2, 3) for a turbomachine, in particular for an aircraft propulsion system, as well as to a method for manufacturing such a component.

Description

[0001] Component for a turbomachine and manufacturing process for it

[0002] The invention relates to a component for a turbomachine, in particular for an aircraft engine, a material for a component for a turbomachine and a manufacturing method for a component for a turbomachine.

[0003] Various components of turbomachinery, particularly in the hot section of high-pressure compressors (HPCs), utilize high-alloy disc materials manufactured through costly forging processes. In some cases, special powder metallurgy (PM) processes are employed for the forging material to produce components of the required quality. This involves the use of difficult-to-machine conventional materials such as Udimet720Li, Waspaloy, or Rene65, or powder metallurgy materials such as ME16, Rene88, or RR1000, to ensure sufficient strength and oxidation resistance even at the high operating temperatures of the rear HPC stages.

[0004] Due to the component loads, the rear stages of high-pressure compressors are not always designed as blisks, but rather as a disc with attached impeller blades. The impeller and guide vanes used in this area must also exhibit high temperature resistance and are therefore made of high-temperature forged materials.

[0005] Furthermore, the rotor and guide vanes must meet a wide variety of requirements. The base material is typically selected based on thermal and mechanical loads. For additional functions in particularly exposed areas of the blade, local coatings are often used to provide, for example, wear, corrosion, or erosion protection. Applying such a coating locally using conventional coating processes, such as thermal spraying, electrochemical deposition, or vapor deposition, requires masking and is usually very complex. Manufacturing blades using the same process as PM discs would be very expensive and therefore not economically competitive with conventional wrought materials. Materials for PM rotors are only produced for individual, highly stressed components with limited service life.This means that, for example, in the production of turbine blades, the only remaining option is currently to pair PM discs with conventional blades made of a different material.

[0006] At very high temperatures, especially in the final stages of the high-pressure compressor, it is advantageous to use optimized materials for components such as the blades used there. Furthermore, under such conditions, it can be beneficial to provide additional protective measures such as blade tip armor or wear protection at the blade root, since, in addition to impacts and erosion, wear and run-in are frequent causes of blade repairs.

[0007] Starting from this premise, it is an object of the present invention to provide a component for a turbomachine, in particular for an aircraft propulsion system, and in particular also to propose a material and a manufacturing method for this component. This is achieved according to the invention by the teachings of the independent claims. Advantageous embodiments of the invention are the subject of the dependent claims.

[0008] To solve the problem, a component for a turbomachine, in particular for an aircraft propulsion system, is proposed in a first aspect of the invention, wherein the component is made of alloy powder and has a first region and at least one second region, wherein a) the first region consists of a first alloy; b) the (at least one) second region consists of a second alloy different from the first alloy; and c) the first region and the (at least one) second region have a metallic bond, so that an integral component is formed.

[0009] Preferably, neither the first region nor the (at least one) second region contains a ceramic, and in particular no ceramic additive. The first region and the at least one second region of the component according to the invention for a turbomachine are connected to each other by a metallic bond, so that an integral component is formed. The proposed component for a turbomachine is an integral component that has locally different compositions in order to better withstand locally varying loads. The component has at least one alloy that is particularly well suited for use at high temperatures.

[0010] The proposed component is integrally designed with at least two areas made of different materials with correspondingly different properties. This allows for the provision of components with different areas particularly suited to various functions, such as an area with higher wear resistance, for example, at the base or hook of a blade, or on the blade tip armor.

[0011] In one embodiment, the first area of ​​the component is the base body, i.e., the area that forms the largest volume of the component.

[0012] In one embodiment of the component, the second area(s) are, in particular, functional areas of the component, i.e., areas that occupy a smaller volume than the base body of the component and, in particular, constitute areas of the component that are subject to particularly high stress and / or are exposed. In the case of a high-temperature compressor blade, this could, for example, be the blade tip, the blade root, or the hooks of a static guide vane. In particular, the second area(s) can be located near the surface and thus replace a costly coating. Specifically, the component has at least two second areas, wherein the at least two second areas consist of at least two different alloys, distinct from the first alloy.

[0013] In DE 10 2016 208 761 Al, a method is described for producing a 2-component

[0014] The aim is to produce an injection-molded part. Specifically, an adjustable guide vane made of Ti64 is to be manufactured and made wear-resistant by applying tungsten carbide or other hard ceramic materials. The injection molding process is implemented in such a way that the manufactured component consists of several components with a graded transition between them. The process-related production of this transition zone is described in detail. Due to the significant differences in properties when joining titanium and ceramic, this transition zone is necessary. Wear protection is achieved through the high wear resistance of the feedstock and the resulting high hardness of the material.

[0015] The current invention, however, does not target the front compressor stages, where adjustable titanium guide vanes are used, but rather the rear, hot sections of the compressor. These sections typically use static guide vanes and impeller blades made of high-alloy nickel alloys. The wear protection provided by the second component is not achieved through high hardness and is not yet pronounced in the feedstock. Instead, under typical operating conditions, the second material forms lubricating oxides or a so-called "glaze layer" of compacted, largely amorphous oxides on its surface, or undergoes phase transformations. These wear protection mechanisms are exhibited particularly, but not exclusively, by metallic alloys with high cobalt and molybdenum content. When combining, for example,When a cobalt alloy is used as wear protection on a high-alloy nickel alloy as the base material, a metallic bond forms during sintering through diffusion, thus eliminating the need for a transition zone created during spraying, such as between metal and ceramic.

[0016] According to a further embodiment of the invention, the first region comprises a nickel-based alloy and at least one second region comprises a different nickel-based alloy. Preferably, the at least one second region consists of this other nickel-based alloy.

[0017] According to a further embodiment of the invention, the first region comprises a nickel-based alloy and at least a second region comprises a cobalt-based alloy. Preferably, the at least second region consists of this cobalt-based alloy. According to a further embodiment of the invention, the first region comprises a nickel-based alloy and at least a second region comprises an iron-based alloy. Preferably, the at least second region consists of this iron-based alloy.

[0018] According to a further embodiment of the invention, the first region comprises an iron-based alloy and at least a second region comprises a different iron-based alloy. Preferably, the at least one second region consists of this other iron-based alloy.

[0019] According to a further embodiment of the invention, the first region comprises an iron-based alloy and at least one second region comprises a nickel-based alloy. Preferably, the at least one second region consists of this nickel-based alloy.

[0020] According to a further embodiment of the invention, the first region comprises an iron-based alloy and at least a second region comprises a cobalt-based alloy. Preferably, the at least one second region consists of this cobalt-based alloy.

[0021] According to a further embodiment of the invention, the first region comprises an intermetallic TiAl alloy and at least a second region comprises an Fe-based alloy. Preferably, the at least one second region consists of this Fe-based alloy.

[0022] According to a further embodiment of the invention, the first region comprises an intermetallic TiAl alloy and at least a second region comprises a Ni-based alloy. Preferably, the at least one second region consists of this Ni-based alloy.

[0023] According to a further embodiment of the invention, the first region comprises an intermetallic TiAl alloy and at least a second region comprises a cobalt-based alloy. Preferably, the at least one second region consists of this cobalt-based alloy.

[0024] According to a further preferred embodiment of the invention, both the first region and the at least one second region consist of the specified alloys. According to one embodiment of the present invention, the first region comprises the following nickel alloy according to a further aspect of the invention. According to a further preferred embodiment, the first region consists of this nickel alloy.

[0025] Another aspect of the invention relates to a nickel alloy, in particular for the production of a previously described component for a turbomachine, especially for an aircraft engine. The nickel alloy is produced by powder metallurgy. It is provided that the nickel alloy has a specific alloy composition characterized by predetermined mass fractions of the alloying elements.The alloy composition comprises chromium with a mass fraction of 12% to 15% inclusive; cobalt with a mass fraction of 17% to 22% inclusive; molybdenum with a mass fraction of 3% to 5.5% inclusive; tungsten with a mass fraction of up to 2.5% inclusive; niobium with a mass fraction of less than 1%; aluminum with a mass fraction of 3% to 4% inclusive; titanium with a mass fraction of 3.5% to 4.5% inclusive; hafnium with a mass fraction of up to 0.3% inclusive; tantalum with a mass fraction of 1.7% to 3% inclusive; carbon with a mass fraction of less than 0.05%; boron with a mass fraction of less than 0.04%; and zirconium with a mass fraction of less than 0.05%. A residual portion is nickel, which may include unavoidable impurities.

[0026] In particular, the alloy composition comprises chromium in a mass fraction of 12% to 15% inclusive; cobalt in a mass fraction of 17% to 22% inclusive; molybdenum in a mass fraction of 3% to 5.5% inclusive; tungsten in a mass fraction of 1.7% to 2.5% inclusive; niobium in a mass fraction of less than 1%; aluminum in a mass fraction of 3% to 4% inclusive; titanium in a mass fraction of 3.5% to 4.5% inclusive; tantalum in a mass fraction of 2% to 3% inclusive; carbon in a mass fraction of less than 0.05%; boron in a mass fraction of less than 0.04%; and zirconium in a mass fraction of less than 0.05%. A remaining proportion is nickel, which may include unavoidable impurities.Another aspect of the invention relates to an alloy powder (particularly for the production of a previously proposed nickel alloy). The alloy powder is specifically intended for the production of the nickel alloy by means of a powder metallurgy process and has a predetermined composition. It is provided that the alloy powder has a specific powder composition characterized by predetermined mass fractions of the powder elements.The powder composition comprises chromium with a mass fraction of 12% to 15% inclusive; cobalt with a mass fraction of 17% to 22% inclusive; molybdenum with a mass fraction of 3% to 5.5% inclusive; tungsten with a mass fraction of up to 2.5% inclusive; niobium with a mass fraction of less than 1%; aluminum with a mass fraction of 3% to 4% inclusive; titanium with a mass fraction of 3.5% to 4.5% inclusive; hafnium with a mass fraction of up to 0.3% inclusive; tantalum with a mass fraction of 1.7% to 3% inclusive; carbon with a mass fraction of less than 0.05%; boron with a mass fraction of less than 0.04%; and zirconium with a mass fraction of less than 0.05%. The remaining portion is nickel.

[0027] In particular, the powder composition comprises chromium with a mass fraction of 12% to 15% inclusive; cobalt with a mass fraction of 17% to 22% inclusive; molybdenum with a mass fraction of 3% to 5.5% inclusive; tungsten with a mass fraction of 1.7% to 2.5% inclusive; niobium with a mass fraction of less than 1%; aluminum with a mass fraction of 3% to 4% inclusive; titanium with a mass fraction of 3.5% to 4.5% inclusive; tantalum with a mass fraction of 2% to 3% inclusive; carbon with a mass fraction of less than 0.05%; boron with a mass fraction of less than 0.04%; and zirconium with a mass fraction of less than 0.05%. The remaining fraction is nickel.

[0028] The alloy powder can be produced, for example, by the following process: The process comprises at least one step of combining the elements of the alloy powder. In a further step, these elements are melted to form a master melt. The master melt is either poured into an electrode and fed to an atomization process or atomized directly, for example, by gas atomization, plasma atomization, or centrifugal processes. The atomization of the alloy is preferably carried out under a protective atmosphere. The atomization produces a metallic powder with the desired alloy composition. Subsequently, the powder is preferably sieved and classified to a particle size distribution of 325 mesh and finer. Furthermore, the alloy powder is provided, in particular, with a particle size distribution of D50 in the range of 8 pm to 12 pm inclusive, which is typical for metal injection molding (MIM).

[0029] One aspect of the invention relates to a component for a turbomachine, in particular for an aircraft engine, which incorporates at least a locally proposed nickel alloy. The component can be manufactured using powder metallurgy from a previously described alloy powder.

[0030] The component, which is manufactured from the proposed alloy powder, exhibits a fatigue strength of IxlO, particularly at maximum operating temperature. 7 Load cycles of greater than 400 MPa.

[0031] In particular, the proposed component for a turbomachine is a component for an aircraft propulsion system, specifically a static or rotating high-pressure compressor blade.

[0032] In particular, the proposed component for a turbomachine is a guide vane or guide vane segment with a more wear-resistant area at the hook (see Fig. 1, 50) or a running vane with a more wear-resistant area at the blade root (Fig. 3, 60) or armor at the blade tip (Fig. 3, 30).

[0033] According to a further aspect of the invention, the proposed component is manufactured by the method described below. Method for manufacturing a component for a turbomachine, in particular for an aircraft engine, wherein the component comprises a first region and at least one second region, comprising the following process steps: a) providing a first alloy powder and at least one second alloy powder by vacuum or inert gas atomization; b) mixing the first alloy powder with at least one binder to obtain a first mixture; c) mixing the at least one second alloy powder with at least one binder to obtain at least one second mixture; d) injection molding the first mixture into a cavity to obtain a green part with a first region;e) Fitting the cavity and injection molding the at least one second mixture into the cavity with the green part to obtain a green part with a first and at least one second region; f) Debinding the green part to obtain a debound component; and g) Sintering the debound component.

[0034] In the first step, the first alloy powder and at least one second alloy powder are produced by vacuum, inert gas, or plasma atomization in a suitable composition (analogous to PM discs or other high-temperature resistant materials). The selection of the at least one second alloy powder ensures the properties of the desired functional layer(s) on the final component.

[0035] The manufacturing process underlying the proposed method is known as metal injection molding (MIM). In steps b) and c), a first and at least a second alloy powder, respectively, are mixed with at least one binder, which in particular comprises thermoplastics and additives. This yields a first and at least a second mixture of alloy powder and binder.

[0036] In step d), the first mixture obtained in step b) is injected into a cavity of an injection mold in an injection molding machine, particularly under increased pressure and temperature. The mixture cools, causing the raw part to solidify. In step e), the cavity is adjusted, and the second mixture obtained in step c) is injected into at least one area of ​​the part obtained in step d) and cools. This step e) can be repeated multiple times, depending on the design of the component, particularly in conjunction with the number of second alloy powders or the number of second areas produced. This creates a green part with at least two areas of defined, different alloy composition. This process yields a green part of the final component.The proposed method thus offers a high degree of design freedom for the at least two areas of the component, which are formed by a first or at least a second mixture.

[0037] In a further step (f), the binder is removed from the green part to obtain a debound component. Depending on the binder used, debinding can be catalytic, thermal, or solvent-based. The debound component can also be referred to as the brown part, which is sintered in a further step (g) of the proposed process. In this step, the debound component is exposed to a temperature just below the melting point of the at least two alloy powders. The interfaces between the two mixtures also sinter and, through thermally activated diffusion processes, form a stable, metallurgical bond, resulting in an integral component that cannot be separated after sintering. In particular, these interfaces establish connections between the first and at least one second region.During this sintering process, the component shrinks to its intended final size and can acquire further properties and / or features through potentially planned post-processing. Additional process and / or machining steps can take place between steps a) to g).

[0038] Furthermore, the proposed method allows for the use of additional second mixtures (in particular, a third, fourth, fifth, or further mixtures) obtained by mixing additional alloy powders with at least one binder. By incorporating different mixtures analogously to step e) and prior to step f), further functional areas of the component with, in particular, additional properties can be created. The proposed method allows the component to be integrally formed with at least two areas, each containing different materials with correspondingly different properties. This enables the creation of components with different areas particularly suited to various functions, such as an area with higher wear resistance, for example, at a blade root or hook, a blade tip armor, or with higher erosion resistance at the leading edges.

[0039] In one embodiment of the method, the first region of the component produced according to the invention is the base body, i.e., the region which in particular forms the largest volume of the component.

[0040] The component according to the invention of the first aspect of the invention is preferably produced by the method according to the invention.

[0041] In one embodiment of the component manufactured using the proposed method, the second area(s) of the component are, in particular, functional areas of the component, i.e., areas that occupy a smaller volume than the base body of the component and, in particular, constitute areas of the component that are subject to particularly high stress and / or are exposed. In the case of a high-temperature compressor blade, this could, for example, be the leading edge of the blade, the blade tip, the blade root, or the hooks of a static guide vane. In particular, the second area(s) can be located near the surface and thus replace a costly coating.

[0042] In the proposed process, in addition to the base material of the component, in particular the blade, at least one further functional area is created which has a different chemical composition and is produced via a second injected material and co-sintering.

[0043] The method according to the invention is particularly suitable for the production of blades (rotor blades and guide vanes) for the rear stages of the high-pressure compressor of a turbomachine. In particular, the composition of the base body ensures compatibility with a high-temperature resistant rotor produced by powder metallurgy or conventional methods and guarantees the required high-temperature stability for the blade component. The locally varying composition, especially in areas subject to particularly high stress, allows for optimization with regard to further requirements such as wear or erosion resistance and thereby increases the robustness of the components, especially the blades.

[0044] Further features of the invention will become apparent from the following description in conjunction with the figures. It shows

[0045] Fig. 1 shows a schematic representation of an exemplary static guide vane according to the invention;

[0046] Fig. 2 shows a schematic representation of an exemplary invention.

[0047] V positioning guide vane;

[0048] Fig. 3 shows a schematic representation of an exemplary impeller according to the invention; and

[0049] Fig. 4 shows a schematic representation of a flowchart of an exemplary process for manufacturing a component for a turbomachine.

[0050] Fig. 1 shows a schematic representation of an exemplary static guide vane 1. The guide vane 1 has a base body 10 as its first section, which is made, in particular, of a nickel alloy proposed herein. Furthermore, the guide vane 1 has a second section 12 at its leading edge 20, which is made of a different alloy. This second section 12 is more impact-resistant than the base body 10. The guide vane 1 also has two further second sections 13, which are made of a different alloy than the base body 10 and the first second section 12, and which form the hooks 50. These further second sections 13 are, due to the alloy used for them, more wear-resistant than the base body 10 and less impact-resistant than the second section 12 at the leading edge 20. Fig. 2 shows a schematic representation of an exemplary adjustable guide vane 2.The adjustable guide vane 2 has a base body 10 as its first section 11, which is made, in particular, of a nickel alloy proposed herein. Furthermore, the adjustable guide vane 2 has a second section 12 at its leading edge 20, which is made of a different alloy. This second section 12 is more impact-resistant than the base body. In addition, the adjustable guide vane 2 has a pivot pin 40 at both its upper and lower ends, each forming a further second section 13 and being more wear-resistant than the base body 10. These pivot pins 40 each constitute a further second section 13, which is formed from a third alloy.

[0051] Fig. 3 shows a schematic representation of an exemplary rotor blade 3. The rotor blade 3 has a base body 10 as its first section 11, which is made, in particular, of a nickel alloy proposed herein. Furthermore, the rotor blade 3 has a second section 12 at its leading edge 20, which is made of a different alloy. This second section 12 is more impact-resistant than the base body 10. The rotor blade 3 also has a blade root 60, which is more wear-resistant than the base body 10. Finally, the rotor blade 3 has a further second section 14 at the blade tip 30, which is more erosion-resistant than the base body 10 and the second sections 12 and 13. This blade tip 30 thus represents a further second section 14, which is formed from a fourth alloy.

[0052] Fig. 4 shows a schematic representation of a flow diagram of an exemplary method 100 for manufacturing a component 1, 2, 3 for a turbomachine, in particular an aircraft engine, wherein the component 1, 2, 3 has a first region 11 and at least one second region 12, 23. The proposed method comprises process steps a) to g). In the first step a), the first alloy powder and at least one second alloy powder are provided in a suitable composition by vacuum or inert gas atomization. In steps b) and c), a first or at least one second alloy powder is mixed with at least one binder, which in particular comprises thermoplastics and additives. This yields a first and at least one second mixture of alloy powder and binder.In step d), the first mixture obtained in step b) is injected into a cavity of an injection mold in an injection molding machine, particularly under increased pressure and temperature. The mixture cools, causing the raw part to solidify. In step e), the cavity is adjusted, and at least one second mixture obtained in step c) is injected into at least one area of ​​the part obtained in step d) and cools. This step e) can be repeated multiple times, depending on the design of component 1, 2, 3, particularly in conjunction with the number of second alloy powders or produced second areas 12, 13 of component 1, 2, 3. This produces a green part with at least two areas 11, 12, 13, 14 of defined, different alloy compositions. This process yields a green part of the later component 1, 2, 3.

[0053] In a further step f), the binder is removed from the green part to obtain a debound component 1, 2, 3, which can also be referred to as the brown part. In a further step g) of the proposed process, the component 1, 2, 3 is then sintered. During this process, the interfaces between at least two mixtures also sinter, forming a stable, metallurgical bond. During this sintering process, the component 1, 2, 3 shrinks to its intended final size and can acquire further properties and / or characteristics through any subsequent processing. Additional process and / or machining steps can take place between steps a) to g).

[0054] REFERENCE MARK LIST

[0055] 1 static guide vane

[0056] 2 Adjustable guide vane 3 Running vane

[0057] 10 basic shapes

[0058] 11 first area

[0059] 12 second area

[0060] 13 further second area ch 14 further second area

[0061] 20 front edge of the shovel

[0062] 30 shovel tip

[0063] 40 pivot pins

[0064] 50 hooks 60 shovel feet

Claims

REQUIREMENTS 1. Component (1, 2, 3) for a turbomachine, in particular for an aircraft engine, wherein the component (1, 2, 3) is made of alloy powder and has a first region (11) and at least one second region (12, 13, 14), characterized in that a) the first region (11) consists of a first alloy; b) the at least one second region (12, 13, 14) consists of a second alloy different from the first alloy; and c) the first region (11) and the at least one second region (12, 13, 14) have a metallic bond, such that an integral component (1, 2, 3) is formed.

2. Component (1, 2, 3) according to claim 1, characterized in that neither the first region (11) nor the at least one second region (12, 13, 14) contains a ceramic.

3. Component (1, 2, 3) according to claim 1 or 2, characterized by at least two second areas (12, 13, 14), wherein the at least two second areas (12, 13, 14) consist of at least two different alloys different from the first alloy.

4. Component (1, 2, 3) according to at least one of the preceding claims, characterized in that the first region (11) has a Ni-based alloy and at least one second region (12, 13, 14) has an Fe-based alloy, another Ni-based alloy or a Co-based alloy.

5. Component (1, 2, 3) according to claim 4, characterized in that the Ni-based alloy of the first region (11) has the following mass fractions of the alloy composition: including 12% to 15% chromium, including 17% to 22% cobalt, including 3% to 5.5% molybdenum, including 0% to 2.5% tungsten, less than 1% niobium, including 3% to 4% aluminum, including 3.5% to 4.5% titanium, up to and including 0.3% hafnium, including 2% to 3% tantalum, less than 0.05% carbon, less than 0.04% boron, less than 0.05% zirconium, remainder nickel.

6. Component (1, 2, 3) according to at least one of claims 1 to 3, characterized in that the first region (11) has an Fe-based alloy and at least one second region (12, 13, 14) has another Fe-based alloy, a Ni-based alloy or a Co-based alloy.

7. Component (1, 2, 3) according to at least one of claims 1 to 3, characterized in that the first region (11) has an intermetallic TiAl alloy and at least one second region (12, 13, 14) has an Fe-based alloy, a Ni-based alloy or a Co-based alloy.

8. Component according to at least one of the preceding claims, characterized in that the component is a guide vane (3) or a guide vane (1, 2).

9. Component (1, 2, 3) according to at least one of the preceding claims, characterized in that the component (1, 2, 3) is produced by metal injection molding (MIM) and the first area (11) and the at least one second area (12, 13, 14) are produced by sequential use of different feedstocks (mixtures) in the same mold and a metallic bond is created between the areas (11, 12, 13, 14) by subsequent sintering, so that an integral part is formed.

10. Component (1, 2, 3) according to claim 9, characterized in that the at least one second area forms lubricating oxides or a glaze layer under operating conditions or undergoes phase transformations that protect against wear.

11. Nickel alloy, in particular for the manufacture of a component (1, 2, 3) according to at least one of the preceding claims for a turbomachine, in particular for an aircraft engine, characterized by the following mass fractions of an alloy composition: including 12% to 15% chromium, including 17% to 22% cobalt, including 3% to 5.5% molybdenum, including 0% to 2.5% tungsten, less than 1% niobium, including 3% to 4% aluminum, including 3.5% to 4.5% titanium, up to and including 0.3% hafnium, including 2% to 3% tantalum, less than 0.05% carbon, less than 0.04% boron, less than 0.05% zirconium, balance nickel.

12. Alloy powder for the production of a nickel alloy, in particular according to claim 11, characterized by the following mass fractions of a powder composition: including 12% to 15% chromium, including 17% to 22% cobalt, including 3% to 5.5% molybdenum, including 0% to 2.5% tungsten, less than 1% niobium, including 3% to 4% aluminum, including 3.5% to 4.5% titanium, up to and including 0.3% hafnium. including 2% to 3% tantalum, less than 0.05% carbon, less than 0.04% boron, less than 0.05% zirconium, balance nickel.

13. Component (1, 2, 3) for a turbomachine, in particular for an aircraft propulsion system, comprising, at least locally, a nickel alloy according to claim 11.

14. Use of the alloy powder according to claim 12 for a component (1, 2, 3) according to at least one of claims 1 to 10.

15. Method for manufacturing a component (1, 2, 3) for a turbomachine according to any one of claims 1 to 10, in particular for an aircraft propulsion system, wherein the component (1, 2, 3) comprises a first region (11) and at least one second region (12, 13, 14), characterized in that it comprises the following process steps: a) providing a first alloy powder and at least one second a) alloy powder by vacuum or inert gas atomization; b) mixing the first alloy powder with at least one binder to obtain a first mixture; c) mixing the at least one second alloy powder with at least one binder to obtain at least one second mixture; d) injection molding the first mixture into a cavity to obtain a green part with a first region (11); e) fitting the cavity and injection molding the at least one second mixture into the cavity with the green part to obtain a green part with a first (11) and at least one second region (12, 13, 14); f) debinding the green part to obtain a debound component (1, 2, 3); and g) sintering the debound component (1, 2, 3).

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