Martensitic alloy components and methods for forming martensitic alloy components

Abstract

The martensitic alloy component comprises, by weight, 0.25% to 0.31% carbon (C), 2.1% to 3.0% manganese (Mn), 0.22% to 0.28% silicon (Si), 2.0% to 2.2% chromium (Cr), 0.45% to 0.55% molybdenum (Mo), and 0.08% to 0.12% vanadium (V), with the balance being iron (Fe) and occasional impurities. The manganese-chromium martensitic alloy component has hardenability corresponding to an ideal diameter of about 15 inches to about 30 inches or larger.

Description

Technical Field

[0001] This invention relates to martensitic alloys, articles comprising martensitic alloys, and methods for forming alloys. More specifically, this invention relates to manganese-chromium martensitic alloys and methods for forming manganese-chromium martensitic alloys. Background Technology

[0002] Turbines are exposed to significant operating stresses from heat and rotational forces. As turbines increase their output, the size and desired properties of turbine rotor shafts increase. Forged / hardened steels (e.g., NiCrMoV alloys) are the material of choice for rotor shafts, which are typically machined from steel forgings. The material for rotor shafts is usually a quenched-tempered high-strength low-alloy steel with critical fatigue properties. Currently, NiCrMoV alloys used for these rotor shafts incorporate nickel, chromium, and molybdenum to provide the alloy's required hardenability. While NiCrMoV performs well in smaller rotor shafts, it does not provide the required hardenability and fracture appearance transition temperature (FATT) in larger rotor shafts. With the trend towards larger gas turbines and larger compressor rotor assemblies (e.g., wheels and front short shafts), current materials such as NiCrMoV steels cannot achieve the required properties, particularly deep-cut impact toughness. The large cross-sections of these components make it difficult for manufacturers to meet FATT requirements, especially in deep-cut locations where cooling rates are slowest during the quenching and tempering heat treatment process. Invention Summary

[0003] On one hand, the martensitic alloy components, by weight, include:

[0004] 0.25% to 0.31%C;

[0005] 2.1% to 3.0% Mn;

[0006] 0.22% to 0.28% Si;

[0007] 2.0% to 2.2% Cr;

[0008] 0.45% to 0.55%Mo;

[0009] 0.08% to 0.12% V; and

[0010] The remaining iron and occasional impurities; and

[0011] The component described therein has hardenability corresponding to an ideal diameter of about 15 inches to about 30 inches or larger.

[0012] On the other hand, the turbine shaft is made of a martensitic alloy, and the martensitic alloy comprises, by weight:

[0013] 0.25% to 0.31%C;

[0014] 2.1% to 3.0% Mn;

[0015] 0.22% to 0.28% Si;

[0016] 2.0% to 2.2% Cr;

[0017] 0.45% to 0.55%Mo;

[0018] 0.08% to 0.12% V; and

[0019] The remaining iron and occasional impurities; and

[0020] The martensitic alloy described therein has hardenability corresponding to an ideal diameter of about 20 inches to about 30 inches or larger.

[0021] In another aspect, a method of forming a manganese-chromium martensitic alloy component includes forging the alloy component, said alloy component comprising, by weight:

[0022] 0.25% to 0.31%C;

[0023] 2.1% to 3.0% Mn;

[0024] 0.22% to 0.28% Si;

[0025] 2.0% to 2.2% Cr;

[0026] 0.45% to 0.55%Mo;

[0027] 0.08% to 0.12% V;

[0028] The remaining amount of iron and occasional impurities;

[0029] To austenitize the forged alloy;

[0030] Quenching the austenitized alloy;

[0031] The tempered alloy; and

[0032] The component described therein has hardenability corresponding to an ideal diameter of 20 to 30 inches or larger.

[0033] Following forging, the manganese-chromium martensitic alloy assembly is austenitized, quenched, and tempered. The tempered forged alloy has hardenability corresponding to an ideal diameter of approximately 20 inches to approximately 30 inches or larger.

[0034] Other features and advantages of the invention will become apparent from the following more detailed description of preferred embodiments, taken in conjunction with the accompanying drawings, which illustrate the principles of the invention by way of example. Invention Details

[0035] Exemplary manganese-chromium alloy components with predetermined properties are provided, along with methods for forming such components. Compared to methods and products that do not utilize one or more features disclosed herein, aspects of this disclosure reduce or eliminate the nickel percentage, increase the chromium percentage, increase the manganese percentage, reduce material costs, increase the martensite percentage, decrease and improve the fracture appearance transformation temperature (FATT), and increase the desired diameter (D). i ), or combinations thereof.

[0036] In one aspect, this disclosure includes a method for producing turbine shafts (e.g., turbine rotor shafts or compressor rotor shafts) from martensitic alloys. This method can also be used to produce wind turbine main shafts from martensitic alloys, but it should be understood that the invention is also well-suited for producing various components from martensitic alloy compositions. Other non-limiting examples include motor components, such as electric machine shafts, wheel axles, and various other components used in the energy, automotive, rail, construction, mining, and agricultural industries. These components are well known in the art and therefore do not require further description.

[0037] refer to Figure 1 Shaft 100 is indicated as having a generally cylindrical shape, with an optional flange formed at one end, but it is understood that... Figure 1 This is merely a schematic diagram, and different configurations of shaft 100 are also within the scope of this invention. Although Figure 1 The shaft 100 shown comprises multiple segments, but it can also be formed from a single piece. The shaft 100 can be solid, hollow, or a combination of solid and hollow components. The shaft 100 has an axisymmetric geometry relative to its longitudinal axis of rotation. The shaft 100 can be used in wind turbines or turbines, and it can have an outer diameter well over 20 inches (approximately 50 cm), and more typically over 24 inches (approximately 60 cm), with a typical range of approximately 25 to 60 inches (approximately 63 to approximately 152 cm), although smaller and larger diameters are also foreseeable. Other aspects of the shaft 100, including its installation in turbines or wind turbines and its operation, are otherwise known in the art and will therefore not be discussed in detail here.

[0038] The martensitic alloys according to this disclosure include the compositions shown in Table 1.

[0039] Table 1

[0040]

[0041] Components formed from the compositions according to this disclosure include an ideal diameter (D) corresponding to 20 inches (50.8 cm) to 30 inches (76.2 cm) or greater. iThe hardenability of the component is defined as follows: In one embodiment, the component has a hardenability corresponding to an ideal diameter of about 30 inches (76.2 cm). In another embodiment, the component has a hardenability corresponding to an ideal diameter of about 40 inches (101.6 cm) or greater. As used herein, hardenability corresponding to an ideal diameter is the ability of the material, component, and heat treatment (e.g., after ideal quenching from the austenitizing temperature) to form at least 50% martensite at the center of a solid cylinder. While the above definition of hardenability corresponding to an ideal diameter is based on a solid component, those skilled in the art will understand that the geometry is not limited to a solid cylinder and may include other geometries and / or hollow components. For example, the hardenability of a hollow component corresponds to a corresponding center depth within the material (e.g., the center of the wall), where at least 50% martensite is formed after heat treatment.

[0042] One problem with alloying with manganese (Mn) is its strong influence on lowering the martensite initiation (Ms) and martensite completion (Mf) temperatures. If the temperature drops too low, this can introduce retained austenite into the microstructure. The Ms and Mf temperatures for the nominal NiCrMoV composition are expected to be 552℉ and 165℉, respectively. In contrast, the Ms and Mf temperatures for the nominal composition alloys given in Table 1 are estimated to be 497℉ and 110℉, respectively. Therefore, the alloys of the present invention in Table 1 undergo transformation above room temperature during quenching, which will prevent problems associated with retained austenite or quench cracking.

[0043] Compared to other alloys (e.g., NiCrMoV), the martensitic microstructure provides increased material toughness. Increasing the percentage of martensite in the material's microstructure will decrease the material's fracture toughness and damage tolerance (FATT). Increasing the ideal diameter of the material in a thicker cross-section increases the amount of martensite, thus reducing the FATT. At temperatures below the FATT, the material will exhibit low fracture toughness and low damage tolerance. To form a damage-tolerant assembly, the assembly's operating temperature should be above the FATT.

[0044] In one embodiment, the component formed from the composition according to the present disclosure includes a FATT of less than -40℉ (-40°C), less than -50℉ (-45.6°C), or less than -60℉ (-51.1°C) at its surface. Additionally, the component includes a FATT of less than 86℉ (30°C), less than 80℉ (26.7°C), or less than 75℉ (23.9°C) at its maximum thickness.

[0045] In addition to increasing the ideal diameter (D) iIn addition to the above, the properties of materials that reduce FATT include, but are not limited to, increasing the percentage of martensite, decreasing the grain size, decreasing the yield strength, or a combination thereof. In one embodiment, the desired yield strength of the material is 650 MPa or greater, or about 650 MPa to about 1000 MPa, and the tensile strength is about 800 to about 1000 MPa. In another embodiment, the average grain size of the material is formed during material processing and is maintained at about 62 μm or less or about 50 μm or less. The FATT of materials having defined yield strength and grain size ranges is adjusted by modifying the microstructure. In one embodiment, the microstructure is adjusted by increasing and / or decreasing the concentration of alloying elements. Alloying elements include, but are not limited to, carbon, silicon, manganese, nickel (0% to trace), chromium, molybdenum, vanadium, sulfur (optional), phosphorus (optional), copper (optional), or a combination thereof. Trace is defined as 0.02% or less, and trace amounts of nickel are sometimes present in various metals or steels. In addition to regulating the microstructure, increasing and / or decreasing the concentration of alloying elements also regulates the material's strength, toughness, ductility, grain size, or combinations thereof.

[0046] In one implementation, the manganese and chromium concentrations are increased. The hardenability of a material is affected by the amount of each element present in the material. Hardenability is the ease with which a material forms a martensitic structure during quenching from the austenitizing temperature. Increasing the manganese and chromium concentrations improves the hardenability of the material. Increasing the hardenability of the material increases the ideal diameter, which increases the formation of the martensitic structure and reduces the FATT in thick cross-sections, thereby providing increased damage tolerance.

[0047] Exemplary methods for forming the component include forging the component. Following forging, the component is heat-treated by methods including, but not limited to, austenitization, quenching, tempering, or combinations thereof. Austenitization is a method of holding a martensitic alloy forging above a critical temperature for a sufficient period of time to ensure complete transformation of the matrix into austenite. To produce a single-phase matrix microstructure (austenite) with a uniform carbon distribution, austenitization involves holding the forging at a temperature greater than about 870°C (1,598℉) for a period of time sufficient to completely transform the matrix of the thickest section into austenite. Quenching from the austenitization temperature forms the martensitic microstructure and can be done using any suitable quenching method known in the art. The quenching rate must be high enough to reduce or eliminate the formation of ferrite / pearlite or bainite. Tempering is provided to increase toughness and reduce the brittleness of the component. Suitable tempering temperatures include, but are not limited to, about 550°C (1,022°F) to about 650°C (1,202°F), about 580°C (1,076°F) to about 620°C (1,148°F), or about 600°C (1,112°F), or any combination, subcombination, range or subrange thereof.

[0048] This disclosure also includes the following implementation schemes:

[0049] 1. A martensitic alloy component comprising, by weight:

[0050] 0.25% to 0.31%C;

[0051] 2.1% to 3.0% Mn;

[0052] 0.22% to 0.28% Si;

[0053] 2.0% to 2.2% Cr;

[0054] 0.45% to 0.55%Mo;

[0055] 0.08% to 0.12% V; and

[0056] The remaining iron and occasional impurities; and

[0057] The component described therein has hardenability corresponding to an ideal diameter of about 15 inches to about 30 inches or larger.

[0058] 2. The martensitic alloy component of embodiment 1, wherein the component contains 2.2% to 3.0% Mn.

[0059] 3. The martensitic alloy component of embodiment 1, wherein the component contains 2.3% to 3.0% Mn.

[0060] 4. The martensitic alloy component of embodiment 1, wherein the component contains 2.4% to 3.0% Mn.

[0061] 5. The martensitic alloy component of embodiment 1, wherein the component contains 2.5% to 3.0% Mn.

[0062] 6. The martensitic alloy component of embodiment 1, wherein the component contains 2.6% to 3.0% Mn.

[0063] 7. The martensitic alloy component of embodiment 1, wherein the component contains 2.1% to 2.2% Cr.

[0064] 8. The martensitic alloy assembly of embodiment 1, wherein the assembly has hardenability corresponding to an ideal diameter of 20 inches to 30 inches.

[0065] 9. The martensitic alloy component of embodiment 1, wherein the component has hardenability corresponding to an ideal diameter of about 30 inches.

[0066] 10. The martensitic alloy assembly of embodiment 1, wherein the assembly is a turbine rotor shaft.

[0067] 11. The martensitic alloy assembly of embodiment 1, wherein the assembly is a turbine component.

[0068] 12. The martensitic alloy component of embodiment 1, wherein the component is a wind turbine part.

[0069] 13. A turbine shaft comprising a martensitic alloy, said martensitic alloy comprising, by weight:

[0070] 0.25% to 0.31%C;

[0071] 2.1% to 3.0% Mn;

[0072] 0.22% to 0.28% Si;

[0073] 2.0% to 2.2% Cr;

[0074] 0.45% to 0.55%Mo;

[0075] 0.08% to 0.12% V;

[0076] The remaining iron and occasional impurities; and

[0077] The martensitic alloy described therein has hardenability corresponding to an ideal diameter of about 20 inches to about 30 inches or larger.

[0078] 14. The turbine shaft of embodiment 13, wherein the martensitic alloy comprises 2.2% to 3.0% Mn.

[0079] 15. The turbine shaft of embodiment 13, wherein the martensitic alloy comprises 2.3% to 3.0% Mn.

[0080] 16. The turbine shaft of embodiment 13, wherein the martensitic alloy comprises 2.5% to 3.0% Mn.

[0081] 17. The turbine shaft of embodiment 13, wherein the martensitic alloy comprises 2.6% to 3.0% Mn.

[0082] 18. A method for forming a martensitic alloy component, the method comprising:

[0083] Forging alloy, said alloy comprising, by weight:

[0084] 0.25% to 0.31%C;

[0085] 2.1% to 3.0% Mn;

[0086] 0.22% to 0.28% Si;

[0087] 2.0% to 2.2% Cr;

[0088] 0.45% to 0.55%Mo;

[0089] 0.08% to 0.12% V;

[0090] The remaining amount of iron and occasional impurities;

[0091] To austenitize the forged alloy;

[0092] Quenching the austenitized alloy;

[0093] The tempered alloy; and

[0094] The component described therein has hardenability corresponding to an ideal diameter of 20 to 30 inches or larger.

[0095] 19. The method of implementation scheme 18, wherein the component has a thickness greater than 20 inches.

[0096] 20. The method of embodiment 18, wherein the component is a turbine shaft or a wind turbine shaft. Example

[0097] Comparative Example 1

[0098] Comparative Example 1: The known composition of NiCrMoV steel (a material known for the manufacture of turbine shafts) is shown below:

[0099]

[0100] The nominal composition of Comparative Example 1 corresponds to hardenability for an ideal diameter of 14 inches, an estimated martensite initiation (Ms) temperature of 552℉ and an estimated martensite completion (Mf) temperature of 165℉.

[0101] Example 1

[0102] Example 1: A martensitic alloy composition having the following composition:

[0103]

[0104] The component shown in Example 1 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 1 has an estimated hardenability corresponding to an ideal diameter of 30 inches, an estimated martensite start (Ms) temperature of 497℉, and an estimated martensite finish (Mf) temperature of 110℉.

[0105] Example 2

[0106] Example 2: A martensitic alloy composition having the following composition:

[0107]

[0108] The component shown in Example 2 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 2 has an estimated hardenability corresponding to an ideal diameter of 24.7 inches, an estimated martensite start (Ms) temperature of 521℉, and an estimated martensite finish (Mf) temperature of 134℉.

[0109] Example 3

[0110] Example 3: A martensitic alloy composition having the following composition:

[0111]

[0112] The component shown in Example 3 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 3 has an estimated hardenability corresponding to an ideal diameter of 25.8 inches, an estimated martensite start (Ms) temperature of 515℉, and an estimated martensite finish (Mf) temperature of 128℉.

[0113] Example 4

[0114] Example 4: A martensitic alloy composition having the following composition:

[0115]

[0116] The component shown in Example 4 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 4 has an estimated hardenability corresponding to an ideal diameter of 26.9 inches, an estimated martensite start (Ms) temperature of 509℉, and an estimated martensite finish (Mf) temperature of 122℉.

[0117] Example 5

[0118] Example 5: A martensitic alloy composition having the following composition:

[0119]

[0120] The component shown in Example 5 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 5 has an estimated hardenability corresponding to an ideal diameter of 28 inches, an estimated martensite start (Ms) temperature of 503℉, and an estimated martensite finish (Mf) temperature of 116℉.

[0121] Example 6

[0122] Example 6: A martensitic alloy composition having the following composition:

[0123]

[0124] The component shown in Example 6 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 6 has an estimated hardenability corresponding to an ideal diameter of 30.2 inches, an estimated martensite start (Ms) temperature of 491℉, and an estimated martensite finish (Mf) temperature of 104℉.

[0125] Example 7

[0126] Example 7: A martensitic alloy composition having the following composition:

[0127]

[0128] The component shown in Example 7 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 7 has an estimated hardenability corresponding to an ideal diameter of 31.3 inches, an estimated martensite initiation (Ms) temperature of 485℉, and an estimated martensite completion (Mf) temperature of 98℉.

[0129] Example 8

[0130] Example 8: A martensitic alloy composition having the following composition:

[0131]

[0132] The component shown in Example 8 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 8 has an estimated hardenability corresponding to an ideal diameter of 32.3 inches, an estimated martensite start (Ms) temperature of 479℉, and an estimated martensite finish (Mf) temperature of 92℉.

[0133] Example 9

[0134] Example 9: A martensitic alloy composition having the following composition:

[0135]

[0136] The component shown in Example 9 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 9 has an estimated hardenability corresponding to an ideal diameter of 33.4 inches, an estimated martensite start (Ms) temperature of 473℉, and an estimated martensite finish (Mf) temperature of 86℉.

[0137] Example 10

[0138] Example 10: A martensitic alloy composition having the following composition:

[0139]

[0140] The component shown in Example 10 is formed from an exemplary composition according to this disclosure. The nominal composition of Example 10 has an estimated hardenability corresponding to an ideal diameter of 34.5 inches, an estimated martensite start (Ms) temperature of 467℉, and an estimated martensite finish (Mf) temperature of 80℉.

[0141] The technical advantage of the manganese-chromium martensitic alloy described herein lies in the fact that, by utilizing the strong hardenability of manganese and chromium, the new material will be able to form the desired martensitic microstructure in deeper locations more easily than NiCrMoV (or similar alloys). Nickel has a negligible effect on hardenability compared to both Mn and Cr. This difference can be illustrated by comparing the ideal diameter multiplication factors for a 1.0% addition of the three elements. For a 1.0% addition of Ni, the multiplication factor is 1.363, for Mn it is 4.333, and for Cr it is 3.160. These figures clearly show that both Mn and Cr have a much greater effect on hardenability than Ni, with Mn having the strongest effect. Another technical advantage of the manganese-chromium martensitic alloy described herein is the significantly increased hardenability without causing problems related to retained austenite and quenching cracks (as indicated by the martensitic initiation (Ms) and martensitic completion (Mf) temperatures). The Ms and Mf temperatures for the manganese-chromium martensitic alloy are estimated at 497°F and 110°F, respectively. Therefore, the new alloy will transform during heat treatment above room temperature, which will prevent and / or reduce problems associated with retained austenite or quenching cracking. The commercial advantage of the manganese-chromium martensitic alloy lies in its lower cost compared to NiCrMoV, as it will utilize low-cost Mn and Cr as the main alloying elements instead of the more expensive Ni, and this will drive down the net cost of energy equipment and thus energy production.

[0142] This written description uses examples to disclose the invention, including the best mode, and also enables those skilled in the art to practice the invention, including preparing and using any device or system and performing any combined methods. The patentable scope of the invention is defined by the claims, but may include other examples that would 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 are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A martensitic alloy component comprising, by weight: 0.25% to 0.31% C; 2.1% to 3.0% Mn; 0.22% to 0.28% Si; 2.0% to 2.2% Cr; 0.45% to 0.55% Mo; 0.08% to 0.12% V; and the balance of iron and incidental impurities; wherein the component has hardenability corresponding to a desired diameter of 15 inches to 30 inches; and wherein the method of forming the martensitic alloy component comprises: forging an alloy comprising, by weight: 0.25% to 0.31% C; 2.1% to 3.0% Mn; 0.22% to 0.28% Si; 2.0% to 2.2% Cr; 0.45% to 0.55% Mo; 0.08% to 0.12% V; the balance of iron and incidental impurities; austenitizing the forged alloy, including holding the forging at a temperature greater than 870°C; quenching the austenitized alloy; tempering the quenched alloy at a temperature of 550°C to 650°C.

2. The martensitic alloy component of claim 1, wherein the component comprises 2.2% to 3.0% Mn.

3. The martensitic alloy component of claim 1, wherein the component comprises 2.3% to 3.0% Mn.

4. The martensitic alloy component of claim 1, wherein the component comprises 2.4% to 3.0% Mn.

5. The martensitic alloy component of claim 1, wherein the component comprises 2.5% to 3.0% Mn.

6. The martensitic alloy component of claim 1, wherein the component comprises 2.6% to 3.0% Mn.

7. The martensitic alloy component of claim 1, wherein the component comprises 2.1% to 2.2% Cr.

8. The martensitic alloy component of claim 1, wherein the component has hardenability corresponding to a desired diameter of 20 inches to 30 inches.

9. The martensitic alloy component of claim 1, wherein the component has hardenability corresponding to a desired diameter of 30 inches.

10. The martensitic alloy component of claim 1, wherein the component is a turbine rotor shaft.

11. The martensitic alloy component of claim 1, wherein the component is a turbine component.

12. The martensitic alloy component of claim 1, wherein the component is a wind turbine component.

13. A turbine shaft comprising a martensitic alloy, the martensitic alloy comprising, by weight: 0.25% to 0.31% C; 2.1% to 3.0% Mn; 0.22% to 0.28% Si; 2.0% to 2.2% Cr; 0.45% to 0.55% Mo; 0.08% to 0.12% V; the balance of iron and incidental impurities; and wherein the martensitic alloy has hardenability corresponding to a desired diameter of 20 inches to 30 inches, and wherein the method of forming the turbine shaft comprising a martensitic alloy comprises: forging an alloy comprising, by weight: 0.25% to 0.31% C; 2.1% to 3.0% Mn; 0.22% to 0.28% Si; 2.0% to 2.2% Cr; 0.45% to 0.55% Mo; 0.08% to 0.12% V; the balance of iron and incidental impurities. the balance iron and incidental impurities; austenitizing the forged alloy, including holding the forge piece at a temperature greater than 870 °C; quenching the austenitized alloy; tempering the quenched alloy at a temperature of 550 °C to 650 °C.

14. The turbine shaft of claim 13, wherein the martensitic alloy includes 2.2% to 3.0% Mn.

15. The turbine shaft of claim 13, wherein the martensitic alloy includes 2.3% to 3.0% Mn.

16. The turbine shaft of claim 13, wherein the martensitic alloy includes 2.5% to 3.0% Mn.

17. The turbine shaft of claim 13, wherein the martensitic alloy includes 2.6% to 3.0% Mn.

18. A method of forming a martensitic alloy component, the method comprising: forging an alloy, the alloy comprising by weight: 0.25% to 0.31% C; 2.1% to 3.0% Mn; 0.22% to 0.28% Si; 2.0% to 2.2% Cr; 0.45% to 0.55% Mo; 0.08% to 0.12% V; the balance iron and incidental impurities; austenitizing the forged alloy, including holding the forge piece at a temperature greater than 870 °C; quenching the austenitized alloy; tempering the quenched alloy at a temperature of 550 °C to 650 °C; and wherein the component has hardenability corresponding to a desired diameter of 20 inches to 30 inches.

19. The method of claim 18, wherein the component has a thickness greater than 20 inches.

20. The method of claim 18, wherein the component is a turbine shaft or a wind turbine shaft.

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