• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A rotor manufacturing process comprising manufacturing a hub using a traditional manufacturing process and manufacturing an aerodynamic profile using an additional layer-by-layer manufacturing process. A rotor includes a hub that has been manufactured using a traditional manufacturing process and an aerodynamic profile that has been manufactured on the hub using an additional layer-by-layer manufacturing process.
    公开号:FR3023499A1
    申请号:FR1556114
    申请日:2015-06-30
    公开日:2016-01-15
    发明作者:Changsheng Guo
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION [0001] The present invention relates to the manufacture of rotors, and in particular to a hybrid manufacturing process for manufacturing rotors. Rotors are rotating elements that can be used to circulate a fluid through a system. Rotors, also referred to as turbine wheels or impellers, comprise a hub portion that forms a rotor support structure and aerodynamic profiles attached to the hub portion that are used to circulate air through the rotor. Rotors are typically manufactured using traditional manufacturing processes such as machining, forging and pouring. These traditional manufacturing processes make it possible to manufacture the hub and the aerodynamic profiles at the same time and from the same material. The use of traditional manufacturing processes to manufacture rotors presents constraints. First, the design of aerodynamic profiles is limited due to the constraints of traditional manufacturing processes. The restrictive design of the aerodynamic profiles can affect the efficiency and performance of the rotors, since complex aerodynamic profile designs can not be manufactured using traditional manufacturing processes. Second, the use of traditional manufacturing processes to make rotors can be costly and time consuming. The manufacture of aerodynamic profiles on the rotor can be difficult using traditional manufacturing processes; therefore, these processes need to be done slowly and with great care. Thirdly, it is often desirable to manufacture rotors from nickel or titanium alloys in view of the fact that these materials exhibit high strength and are capable of withstanding high temperatures. Nickel and titanium alloys can be difficult to machine with traditional manufacturing processes, making it difficult to accurately manufacture rotors made from nickel and titanium alloys using traditional manufacturing processes. [0003] The rotors can also be manufactured using additive manufacturing processes. The additive manufacturing processes are partly based on a layer-by-layer principle. The use of an additive manufacturing process to manufacture a hub portion and the aerodynamic profiles of a rotor also presents constraints. First, the additive manufacturing processes can be extremely slow processes when a large amount of material is needed to make the part. Rotors require a large amount of material; therefore, the manufacture of a rotor through an additive manufacturing process can be extremely time-consuming. Secondly, when parts with thick, thin sections are manufactured through additive manufacturing processes, deformation of the parts may occur and affect the properties of the part. Rotors have thick, thin sections; therefore, rotors manufactured through additive manufacturing processes may be deformed and unusable due to deformation. Third, additive manufacturing processes can be extremely expensive when large parts are manufactured. The material used in additive manufacturing processes is limited in size; therefore, it can be expensive to make large pieces when only one piece or a few pieces can be made at the same time.
    [0002] SUMMARY [0004] A rotor manufacturing process includes manufacturing a hub using a traditional manufacturing process and manufacturing an airfoil on the hub using a process. additive manufacturing layer by layer. The traditional manufacturing process may be a process selected from the group consisting of machining, forging, milling or combinations thereof. The additional layer-by-layer manufacturing process may be a process selected from the group consisting of cold spraying, thermal spraying, selective laser sintering, direct metal laser sintering, electron beam melting, laser selective melting and the combinations of these. The manufacture of the hub may include the manufacture of the hub using a first material. The manufacture of the aerodynamic profile may comprise the manufacture of the aerodynamic profile using a second material. The manufacture of the aerodynamic profile may comprise the manufacture of a first portion of the airfoil using a first material of the airfoil and the manufacture of a second portion of the airfoil using a second material of the aerodynamic profile. aerodynamic profile. The process may further include fabricating a plurality of airfoils on the hub using an additional layer-by-layer manufacturing process. The plurality of airfoils can be manufactured simultaneously. The plurality of aerodynamic profiles can be manufactured one at a time. The process may further include treating the hub and the airfoil to create a final portion. The treatment of the hub and aerodynamic profile may include the use of a process selected from the group consisting of milling, grinding, machining, finishing and combinations thereof. [0005] A rotor comprises a hub which has been manufactured by means of a traditional manufacturing process and an aerodynamic profile which has been manufactured on the hub thanks to an additive manufacturing process layer by layer. The hub may be made of a first material and the aerodynamic profile is made of a second material. The first part of the aerodynamic profile may consist of a first material of the aerodynamic profile and a second part consists of the second material of the aerodynamic profile. The first aerodynamic profile material may be a material that is capable of withstanding high stresses, and wherein the second material of the aerodynamic profile is a material that is capable of withstanding high temperatures. The rotor may further include: a plurality of airfoils that have been manufactured on the hub using an additional layer-by-layer manufacturing process. BRIEF DESCRIPTION OF THE DRAWINGS [0006] FIG. 1 is a flowchart illustrating the steps of manufacturing a rotor. [0007] Figure 2 is a side view of a hub that has been manufactured through a traditional manufacturing process. Figure 3 is a side view of an aerodynamic profile which is additively produced by a projection process on the hub. Figure 4 is a side view of an aerodynamic profile that is additively manufactured by laser melting or a sintering process on the hub. DETAILED DESCRIPTION [0010] In general, the present description relates to the use of a hybrid manufacturing process for manufacturing a rotor. The rotors comprise turin wheels and impellers that have a hub and a plurality of airfoils attached to the hub. The hybrid manufacturing process involves the use of a traditional manufacturing process 3 to manufacture a rotor hub and the use of a layer-by-layer additive manufacturing process to produce aerodynamic profiles on the rotor hub. Traditional manufacturing processes may include forging, casting or machining. Layer-by-layer additive manufacturing processes may include direct laser metal sintering, laser selective sintering, electron beam melting, laser selective melting, cold splashing, or hot splashing. The use of the hybrid manufacturing process to manufacture rotors makes it possible to manufacture the rotors more quickly and economically. In addition, aerodynamic profile design on the rotor may be more complex when aerodynamic profiles are manufactured using a layer-by-layer additive manufacturing process, which improves rotor efficiency and performance. The aerodynamic profiles can also be made from several materials so that the aerodynamic parts can be made from materials with different properties. Thus, each aerodynamic profile has portions that have a high wear resistance and parts that have a high strength, for example. Figure 1 is a flow chart illustrating the steps of manufacturing a rotor. Figure 1 includes steps 10 to 14. Step 10 includes making a hub using a traditional manufacturing process. Step 12 includes manufacturing a plurality of airfoils on the hub using a layer-by-layer additive manufacturing process. Step 14 includes the transformation of the hub and aerodynamic profiles to produce a final piece. [0012] Step 10 includes making a hub using a traditional manufacturing process. The hub forms a support structure of a rotor on which the aerodynamic profiles are fixed. The hub generally includes a base portion and a shaft portion extending perpendicular to the base portion. Traditional manufacturing processes can include any manufacturing process that is able to work a material to form a part. This may include, for example, forging, casting or machining, among others. Forging uses compressive forces to shape a metallic material and can be performed at different temperatures. Pouring comprises pouring a molten material into a mold, wherein the molten material can cure in the mold to form a workpiece. Machining involves removing the material from a starting piece until a final piece is obtained. Machining processes can also be called subtractive manufacturing processes. The hub has a simple geometry and requires a large amount of material. The use of a traditional manufacturing process to manufacture the hub makes it possible to manufacture the hub quickly and inexpensively. The hub may also be made from a material having desirable properties for a rotor hub, including materials that exhibit high strength and materials that are capable of withstanding high temperatures. Step 12 comprises manufacturing a plurality of airfoils on the hub using a layer-by-layer additive manufacturing process. The plurality of aerodynamic profiles is manufactured and fixed on the hub. Each aerodynamic profile will have a first side that is attached to the base portion of the hub and a second side that is attached to the hub shaft portion. Interstices remain between the plurality of airfoils so that fluid can flow between the plurality of airfoils when the rotor is in use. The plurality of airfoils may be manufactured on the hub either all at the same time or one by one. In addition, the plurality of airfoils may be made from the same material at the hub or the plurality of airfoils may be made from a different material. Each aerodynamic profile can also be made from multiple materials when additive manufacturing processes are used. [0016] Layer-by-layer additive manufacturing processes include any manufacturing process that produces a layer-by-layer element. This may include, for example, direct laser metal sintering, laser selective sintering, electron beam melting, laser selective melting, cold splashing, or hot splashing. Direct laser metal sintering and laser selective sintering both sinter a selected portion of a layer of powdered material with a laser. Electron beam melting and laser selective melting both melt a selected portion of a layer of powdered material with a laser. Cold spraying involves spraying a material in powder form on a surface, in which the powder particles undergo plastic deformation when they strike the surface. Hot spraying comprises projecting onto a surface a material in the form of molten or heated powder. All of these processes will form a new layer over the previous layer to produce aerodynamic profiles that have been fabricated layer by layer. The shape of each layer is defined by a data file (such as an STL file), which is used to control the additive manufacturing process. In prior art processes, the plurality of airfoils and the hub were manufactured together using a traditional manufacturing process. This limited the design of the plurality of aerodynamic profiles, since traditional manufacturing processes are limited in terms of design complexity and manufacturing accuracy. In addition, the manufacture of the plurality of airfoils through a traditional manufacturing process was time consuming and expensive because of the complex shape of the plurality of airfoils. The hub and plurality of airfoils also had to be made from the same material using traditional manufacturing processes. The use of an additive manufacturing process layer by layer to manufacture the plurality of aerodynamic profiles provides greater flexibility in the design of aerodynamic profiles. Forms and geometries that were previously impossible with traditional manufacturing processes can be achieved using layer-by-layer additive manufacturing processes. In addition, the use of traditional manufacturing processes to manufacture the plurality of aerodynamic profiles could be time-consuming and expensive, since each aerodynamic profile had to be manufactured slowly and carefully. The use of a layer-by-layer additive manufacturing process to manufacture the plurality of aerodynamic profiles is faster and less expensive, since the additive manufacturing processes can more easily produce the shape and geometry required for the plurality of aerodynamic profiles. . In addition, the plurality of aerodynamic profiles requires only a small amount of material. The use of a layer-by-layer additive manufacturing process is advantageous in that these processes save more material than traditional manufacturing processes. In addition, the hub may be made from a first material and the plurality of airfoils may be made from a second material which is different from the first material. This makes it possible to select both the hub material and the material of the aerodynamic profiles depending on the material properties that are desired in the hub as in the aerodynamic profiles. For example, the hub may be made from a first material that has significant strength and the airfoils may be made from a second material that is capable of withstanding high temperatures. Materials that can be used to make the hub and airfoils may include titanium alloys, nickel alloys, aluminum alloys, ceramic materials, or any other suitable material. Different grades of titanium alloys and different grades of nickel alloys can also be used. The hub can for example be manufactured from a first grade of titanium alloy and the aerodynamic profiles can be made from a second grade of titanium alloy. The hub may also be made of titanium alloy and the aerodynamic profiles may be nickel alloy, or vice versa. This makes it possible to manufacture the hub and the aerodynamic profiles from a material made to measure to withstand the stresses and the temperatures present in the hub like in the aerodynamic profiles. In addition, a first portion of an airfoil may be made from a first aerodynamic profile material and a second portion of the aerodynamic profile may be made from a second aerodynamic profile material which is different from the first aerodynamic profile material. This makes it possible to accurately design each aerodynamic profile according to the part of the aerodynamic profile that must be able to withstand significant stresses and the part of the aerodynamic profiles that must be able to withstand high temperatures. For example, the first part of the aerodynamic profile can be made from a first aerodynamic profile material which has a high resistance and the second part of the aerodynamic profile can be made from a second aerodynamic profile material which is able to withstand high temperatures. Materials that can be used to make the airfoils may include titanium alloys, nickel alloys, aluminum alloys, ceramic materials, or any other suitable material. Different grades of titanium alloys and different grades of nickel alloys can also be used. For example, a first portion of the airfoil can be made from a first grade of titanium alloy and a second portion of the airfoil can be made from a second grade of titanium alloy. On the other hand, a first portion of the airfoil may be made from a titanium alloy and a second portion of the airfoil may be made from a nickel alloy, or vice versa. This makes it possible to manufacture each part of the aerodynamic profile from a custom-made material to withstand the stresses and temperatures present in this part. In addition, a thermal insulation layer (for example zirconia) and / or a wear-resistant layer (for example ceramic materials) can be added to an outer surface of the airfoils using a additive manufacturing process layer by layer. The use of a layer-by-layer additive manufacturing process provides greater flexibility in rotor design, making the rotor stronger, more heat-resistant and ultimately more efficient. Step 14 includes the treatment of the hub and aerodynamic profiles to produce a final piece. After the plurality of airfoils has been made on the hub, the plurality of airfoils and the hub can be processed to obtain a final piece. This may include the use of any number of methods to ensure that the plurality of airfoils and the hub have the desired material properties and mechanical shape. In some cases, the aerodynamic profiles can also be processed during their manufacture. Some surfaces of an aerodynamic profile having a complex structure may be inaccessible once the aerodynamic profile has been fully fabricated. Treating the aerodynamic profile during manufacture allows all surfaces of the airfoil to be completed when the aerodynamic profile is manufactured. Examples of methods that can be used to produce a final part are given below. It is also possible to use other methods. First, the plurality of airfoils and the hub may be heated to fully sinter and solidify the plurality of airfoils and the hub to form a final piece. Then, the plurality of airfoils can undergo a finishing process to achieve a better finish on an outer surface of each airfoil. These methods may include multi-axis milling, super-abrasive machining, grinding or finishing by mass-engineering processes, such as abrasive flow. The plurality of aerodynamic profiles can also undergo these finishing processes during their manufacture using additive manufacturing processes, in layers. [0023] Using steps 10 to 14 to make a rotor is advantageous. The hub has a simple geometry, which makes it possible to use traditional manufacturing processes quickly and cost-effectively to manufacture the hub. Each aerodynamic profile of the plurality of airfoils has a complex geometry, making the use of additive, layer-wise, cost-effective and time-efficient manufacturing processes for manufacturing the plurality of airfoils. In addition, the plurality of aerodynamic profiles can be designed with more complex shapes than was previously possible with traditional manufacturing processes. The hybrid manufacturing process discussed in steps 10-14 exploits both the advantages of traditional manufacturing processes and layered additive manufacturing processes to make a rotor that is more efficient and effective than was possible before. Figure 2 is a side view of the hub 20 which has been manufactured through a traditional manufacturing process. The hub 20 comprises a base portion 22 and a shaft portion 24. The hub 20 is used as a support structure of a rotor. A plurality of airfoils may be attached to the hub 20 to form a final rotor. The hub 20 comprises the base portion 22 and the shaft portion 14. The base portion 22 is a cylindrical piece with a first diameter. The shaft portion 24 is a cylindrical piece with a second diameter. The first diameter of the base portion 22 is larger than the second diameter of the shaft portion 24. The shaft portion 24 extends perpendicularly to the base portion 22. In other embodiments, the Hub 20 may have a different shape for other rotor designs. The base portion 22 and the shaft portion 24 form a single monolithic piece that is formed using a traditional manufacturing process. As mentioned above with reference to Figure 1, traditional manufacturing processes may include forging, casting or machining. [0026] Using a traditional manufacturing process to make the hub 20 is advantageous. The hub 20 has a simple design that facilitates its manufacture. Traditional manufacturing processes can be used to quickly build the hub 20 at a lower cost. Figure 3 is a side view of the airfoil 30 which is further manufactured through a sputtering process on the hub 20. The hub 20 includes the base portion 22 and the shaft portion 24. The profile aerodynamic 30 includes the previously formed portion 32 and the layer 34. FIG. 3 also shows the sprayer 40 and the particles 42. The hub 20 includes the base portion 22 and the extending shaft portion 24. perpendicular to the base portion 22. The airfoil 30 is manufactured on the hub 20 in FIG. 3 using a sputtering process. A first layer of the airfoil 30 is made on the base portion 22, the shaft portion 24, or the base portion 22 and the shaft portion 24 at the same time. The aerodynamic profile 30 includes the previously formed portion 32 and the layer 34. The previously formed portion 32 is a portion of the airfoil 30 that has already been manufactured using a sputtering process. The layer 34 is an outer layer of the airfoil 30 which has just been applied to the airfoil 30 during manufacture using the spraying process. The spraying process may include cold spraying processes and thermal spraying processes. The spraying process comprises the sprayer 40. The sprayer 40 sprays the particles 42 on an outer surface of the airfoil 30 to form the layer 34. If the spraying process is a cold spraying process, the particles 42 will be particles of powder that will undergo plastic deformation and adhere to the outer surface of the airfoil 30 when in contact with the outer surface of the airfoil. If the spraying process is a thermal spraying process, the particles 42 will be melted or heated powder particles. Once the layer 34 of the airfoil 30 has been fully applied, the layer 34 will be part of the previously formed portion 32 of the airfoil 30. Since the particles 42 are sprayed on the portion 32 formed previously, the particles 42 will be bonded by mechanically bonding to the previously formed portion 32 to form the layer 34. Once the layer 34 is fully formed, a heat treatment process may be used to chemically bond the particles 42 of the layer 34 to the previously formed portion 32. Layer 34 becomes a new outer layer of portion 32 previously formed at this stage. The sprayer 40 can then spray a new layer of particles 42 on the airfoil 30. This process can be continued layer by layer until the airfoil is fully manufactured. The spraying process may use different equipment in relation to those shown in Figure 3 and may include additional steps if necessary. For example, several sprayers can be used at the same time to quickly create the airfoil 30 or a plurality of airfoils 30 on the hub 20. Making the airfoil 30 using a spraying process is advantageous since the Aerodynamic profile 30 may have more complex designs and geometries than before with traditional manufacturing processes. In addition, the aerodynamic profile 30 can be made from a material different from that of the hub 20. This allows the hub 20 and the airfoil 30 to be made from a material having properties that are better adapted. for the hub 20 and the airfoil 30. Different parts of the airfoil 30 can also be made from different materials. For example, a first portion of the airfoil 30 may be made from a material that exhibits high temperature resistance and a second portion of the airfoil 30 may be made from a material capable of withstanding high stresses. Materials that can be used include nickel alloys, titanium alloys, ceramic materials and other suitable materials. In addition, an outer surface of the airfoil 30 may be covered with a thermal barrier material (e.g., zirconia) or a wear resistant material (e.g. ceramic material). This allows the aerodynamic profile to be accurately fabricated according to the most suitable material properties for each part of the airfoil 30. FIG. 4 is a side view of an aerodynamic profile 30 'which is manufactured so further through a process of sintering or laser melting on the hub 20. The hub 20 comprises the base portion 22 and the shaft portion 24. The airfoil 30 'comprises the previously formed portion 32' and the diaper 34 . The figure also shows the laser 50, the beam 52 and the powder 54. The hub 20 comprises the base portion 22 and the shaft portion 24 which extends perpendicularly to the base portion 22. The aerodynamic profile 30 'is manufactured on the hub 20 in FIG. 4 using a sintering or laser melting process. A first layer of the airfoil 30 'is made on the base portion 22, the shaft portion 24, or on the base portion 22 and the shaft portion 24 at the same time. The aerodynamic profile 30 'comprises the previously formed portion 32' and the layer 34 '. The previously formed portion 32 'is a portion of the airfoil 30' that has already been fabricated using a sintering or laser melting process. The layer 34 'is an outer layer 11 of the aerodynamic profile 30' which has just been applied to the aerodynamic profile 30 'during manufacture by means of the sintering or melting process.
    [0003] The sintering or melting process may include direct metal laser sintering, selective laser sintering, electron beam melting, and selective laser melting. The sintering or laser melting process comprises the laser 50. The laser 50 has the beam 52 which can be directed to the airfoil 30 '. To form the layer 34 'on an outer surface of the airfoil 30', a layer of the powder 54 must be spread over the outer surface of the airfoil 30 '. The laser 50 can then direct the beam 52 onto the powder 54 and either fuse or sinter the powder 54 to form the layer 34 'of the airfoil 30'. The layer 34 'will then be part of the portion 32' previously formed of the airfoil 30 '. The laser 50 will fuse or sinter the particles 54 and an outer surface of the previously formed portion 32 '. Since the particles 54 and the outer surface of the previously formed portion 32 'solidify, they will be chemically bonded together. The layer 34 'becomes a new outer layer of the portion 32 formed previously at this stage. Another layer of powder can then be applied to the outer surface of the aerodynamic profile 30 'and fused or sintered with the beam 52 of the laser 50. This process can be continued layer by layer with additional layers of powder 54 placed on the upper part of the previously formed portion 32 'of the airfoil 30' until the airfoil 30 'is fully manufactured.
    [0004] 100341 The sintering or laser melting process may use different equipment from those mentioned in Figure 4 and may include additional steps if necessary. For example, the equipment may include a scanning head that is used to move the laser across an entire surface of the rotor. Manufacturing the aerodynamic profile 30 'using a sintering or laser melting process is advantageous since the aerodynamic profile 30' may have more complex designs and geometries than before with traditional manufacturing processes. In addition, the airfoil 30 can be made from a material different from those used for the hub 20. This allows the hub 20 and the airfoil 30 'to be made from a material having properties respectively better adapted to the hub 20 and the aerodynamic profile 30 '. Different parts of the aerodynamic profile 30 'can also be made from different materials. For example, a first portion of the aerodynamic profile 30 'can be made from a material that has high temperature resistance and a second portion of the airfoil 30' can be made from a material capable of withstanding the stresses high. Materials that can be used include nickel alloys, titanium alloys, ceramic materials and other suitable materials. In addition, an outer surface of the airfoil 30 'may be covered with a thermal barrier material (for example zirconia) or a wear resistant material (for example a ceramic material). This allows the aerodynamic profile 30 'to be accurately manufactured according to the properties of the material most suitable for each part of the aerodynamic profile 30'. While the invention has been described by mentioning one or more embodiment (s) of embodiment by way of example, those skilled in the art will understand that several modifications can be made and that equivalents can be replaced by elements that derive from it while remaining within the scope of the invention. In addition, many modifications can be made to adapt a situation or a particular material to the teachings of the invention without departing from the essential field of application thereof. Therefore, it is intended that the invention not be limited to the particular embodiment (s) disclosed. 13
    权利要求:
    Claims (6)
    [0001]
    CLAIMS: 1. A process for manufacturing a rotor, the rotor comprising: manufacturing a hub using a traditional manufacturing process; and manufacturing an airfoil on the hub using an additional layer-by-layer manufacturing process.
    [0002]
    The process of claim 1 wherein the traditional manufacturing process is a process selected from the group consisting of machining, forging, milling or combinations thereof.
    [0003]
    The process of claim 1 or 2, wherein the additional layer-by-layer manufacturing process is a process selected from the group consisting of cold spraying, thermal spraying, selective laser sintering, direct metal laser sintering, smelting by electron beam, laser selective fusion and combinations thereof.
    [0004]
    The process according to any one of claims 1 to 3, wherein the manufacture of the hub comprises the manufacture of the hub using a first material, and wherein the manufacture of the airfoil comprises the manufacture of the airfoil at using a second material.
    [0005]
    The process according to any one of claims 1 to 4, wherein the manufacture of the airfoil comprises manufacturing a first portion of the airfoil using a first material of the airfoil and manufacturing a second part of the aerodynamic profile using a second material of the aerodynamic profile. 25
    [0006]
    The process of any one of claims 1 to 5, and further comprising: manufacturing a plurality of airfoils on the hub using an additional layer-by-layer manufacturing process. The process of claim 6, wherein the plurality of airfoils are manufactured simultaneously. The process of claim 6 or 7, wherein the plurality of airfoils are manufactured one at a time. The process of any one of claims 1 to 8, and further comprising: treating the hub and the airfoil to create a final portion. The process of claim 9, wherein the treatment of the hub and the airfoil comprises the use of a process selected from the group consisting of milling, grinding, machining, finishing and combinations thereof. A rotor comprising: a hub that has been manufactured using a traditional manufacturing process; and an aerodynamic profile that has been manufactured on the hub using an additional layer-by-layer manufacturing process. 12. Rotor according to claim 11, wherein the hub is made of a first material and the aerodynamic profile is made of a second material. The rotor of claim 11 or 12, wherein the first portion of the airfoil comprises a first material of the airfoil and a second portion is the second material of the airfoil. The rotor of claim 13, wherein the first material of the airfoil is a material that is capable of withstanding high stresses, and wherein the second material of the airfoil is a material that is capable of withstanding high temperatures. The rotor according to any one of claims 11 to 14, wherein the rotor further comprises: a plurality of airfoils that have been manufactured on the hub using an additional layer-by-layer manufacturing process. 16
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    同族专利:
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    法律状态:
    2016-05-24| PLFP| Fee payment|Year of fee payment: 2 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 3 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/329,298|US20160010469A1|2014-07-11|2014-07-11|Hybrid manufacturing for rotors|
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