• 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 turbo-machine impeller (120) is described, comprising a plurality of solidified layers formed by solidified powder material. The impeller comprises at least one portion made of a lattice structure (L) surrounded by a solid skin structure (S).
    公开号:AU2013224120A1
    申请号:U2013224120
    申请日:2013-02-20
    公开日:2014-08-28
    发明作者:Lacopo Giovannetti；Andrea Massini；Pierluigi TOZZI
    申请人:Nuovo Pignone SRL；
    IPC主号:B22F3-105
    专利说明:
    WO 2013/124314 PCT/EP2013/053373 TURBO-MACHINE IMPELLER MANUFACTURING DESCRIPTION FIELD OF THE INVENTION The present disclosure relates generally to manufacturing of turbo-machine impellers, 5 such as impellers for centrifugal compressors, centrifugal pumps or turboexpanders. The disclosure more specifically concerns manufacturing of turbo-machine impellers by additive-manufacturing-type production processes. DESCRIPTION OF THE RELATED ART Turbo-machine impellers, for centrifugal compressors or centrifugal pumps for 10 example, are components of complex geometry. Fig. 1 illustrates a perspective view of an exemplary centrifugal compressor impeller. Fig. 2 shows an exemplary cross-section along a radial plane of a portion of a shrouded compressor impeller. The impeller, designated 1 as a whole, comprises an inlet 2 and outlet 3. The flow passage for the gas to be compressed extending from the inlet 2 to the outlet 3 is 15 formed between a hub 4 and a shroud 5. Blades 6 are arranged between the hub 4 and the shroud 5. Between adjacent blades 6 flow vanes 7 are formed, extending from the gas inlet 2 to the gas outlet 3. The impeller 1 has a central hole through which the compressor shaft, not shown, passes. The portion of the impeller hub 4 surrounding the central hole is named the "impeller foot" and is designated with reference number 20 8. The impellers provided with the shroud 5 as the one shown in Fig. 1 are particularly complex to manufacture. In particular tridimensional blades require the use of manufacturing processes such as electrical discharge machining or electrical-chemical machining. Shrouded impellers further require the shroud to be welded on the hub 25 once the blades have been machined or to be machined by full milling, using a 5-axes numerically controlled machine tool, starting from a solid metal piece. - 1 - WO 2013/124314 PCT/EP2013/053373 In order to achieve more efficient and less expensive manufacturing of this kind of components, in recent times additive-manufacturing-type production processes have been investigated. One of these processes is the so called electron beam layer melting process. This manufacturing process provides for a layer-by-layer construction of 5 complex components. The component is manufactured by distributing sequentially layers of powder material, which is melted and subsequently solidified. Each layer is melted and solidified along a portion of the layer which is defined by the boundaries of the cross-section of the article to be manufactured at the level of the relevant layer. Turbo-machine impellers are subject to high dynamic mechanical stresses and are 10 sometimes required to work in a particularly difficult environment, for example when acid gas or wet gas is processed by the compressors. Moreover, there is a constant need for reducing the weight of the impeller maintaining at the same time the required mechanical and chemical-physical resistance. SUMMARY OF THE INVENTION 15 A reduction of the weight of a turbo-machine impeller manufactured by an additive manufacturing-type production process is achieved by controlling the high energy source used for melting or sintering the powder material such that the bulk portions of the turbo-machine impeller are formed with an interior lattice structure, surrounded by a solid structure, i.e. by a sort of a skin which provides for a solid, continuous outer 20 surface. Lattice structures can be obtained by suitably controlling the energy delivered by the high energy source, such that the powder material is melted spot-wise, and individual volumes of melted powder material will solidify and adhere one to the other leaving volumes there between, where the powder material is not melted and will subsequently be removed leaving an empty space within the solidified material forming 25 the lattice structure. According to one embodiment, a method of manufacturing a turbo-machine impeller layer by layer is provided, using powder material. The powder material is irradiated and melted with a high energy source and solidifies to form the impeller. The high energy source is controlled such that at least one bulky portion of the turbo-machine -2- WO 2013/124314 PCT/EP2013/053373 impeller is irradiated such that the powder material solidifies in a lattice structure surrounded by a solid skin structure enclosing the lattice structure. In particularly advantageous embodiments, an electron-beam source is used. The electron beam generated by an electron-beam gun locally melts the powder material. 5 Subsequent cooling of the melted material generates the final structure of each layer of the turbo-machine impeller. Although the following detailed description will refer specifically to electron-beam sources, the method disclosed herein can be carried out also using different high energy sources. The selection of the high energy source can depend e.g. upon the kind of 10 material used. For example, laser sources can be used instead of electron-beam guns. In other embodiments electric energy can be applied to the powder material to be solidified, e.g. using suitably arranged and controlled electrode(s). The term "solidify" and "solidification" as used herein shall be in general understood as any action or process transforming the loose powder material in a hard body having a 15 given shape. In some embodiments, the powder material is melted and then solidified. In other embodiments, however, the powder material can undergo a different solidification process, e.g. a sintering process, rather than a melting and subsequent solidification process. In some embodiments, the method comprises the following steps: 20 - depositing a first layer of powder material onto a target surface; - irradiating a first portion of said first layer of powder material with said high energy source and solidifying said first portion of powder material, said first portion corresponding to a first cross-sectional region of said turbo-machine impeller; - depositing a second layer of powder material onto the first portion; 25 - irradiating a second portion of said second layer of powder material with said high energy source and solidifying said second portion of powder material, said second -3 - WO 2013/124314 PCT/EP2013/053373 portion corresponding to a second cross-sectional region of said turbo-machine impeller, the first portion and the second portion being joined to one another; - depositing successive layers of powder material onto the previous portion and irradiating a portion of each successive layer to produce said turbo-machine impeller 5 comprising a plurality of solidified layer portions, each layer portion corresponding to a cross-sectional region of said turbo-machine impeller. At least some of the successive solidified layer portions have at least one inner part formed by a lattice structure surrounded by an outer solid skin structure portion. Each layer can be deposited on the previous layer when the latter is solidified, or only partly 10 solidified, or still in the melted state. The lattice structure is located at least in the bulky, i.e. massive portion of the impeller, namely at least in the radially inner portion of the hub, i.e. the impeller foot, surrounding the central hole of the impeller. Shrouded impellers may include a lattice structure in the interior of the thicker portion of the shroud, i.e. the impeller eye. 15 Advantageously the lattice structure develops circumferentially around the axis of the impeller. Additive-manufacturing processes have been used for manufacturing turbomachine components such as blades of axial turbines. These components are relatively small components having a narrow cross section. The interior of the blades are usually 20 hollow, for cooling purposes. The additive-manufacturing process has also been used to provide an additional lattice structure in the interior of turbine blades, to improve the mechanical strength of the blades (DE-A-102009048665). Additive-manufacturing processes have little or no applications for manufacturing massive metallic components. Thermal stresses generated in the bulky structure of 25 massive components causes deformations of the individual layers formed during the manufacturing process. In the case of large massive components the deformation caused by thermal stress during melting and subsequent solidification of one layer of powder material can be so extensive as to negatively affect or even hindering the -4- WO 2013/124314 PCT/EP2013/053373 deposition of the subsequent powder layer, as the lower solidified and deformed layer obstructs the movement of the rack used to distribute the subsequent powder layer. By solidifying the powder material to form a lattice structure, rather than a solid structure, in the bulky portion of the impeller, improves heat dissipation and prevents 5 or reduces thermal stresses and deformations, thus making additive-manufacturing of massive impellers feasible. Less thermal energy is required to generate a lattice versus a solid structure. Thus, the total amount of heat that has to be dissipated is reduced. Additionally, free space remains in the non-melted portions of the layer, where heat dissipation is made easier and faster. Both factors contribute to the reduction of 10 thermal deformations. The term "irradiating" as used herein shall be understood as any action of applying energy from a high energy source to a the powder material. According to some embodiments, the layers of powder material are deposited in a heated confinement structure. The temperature of the impeller can thus be controlled. 15 Residual stresses in the final product can be prevented or reduced by controlling the temperature vs. time curve, e.g. as a function of the material used, the shape of the product, the kind of high energy source used, or other process parameters. In general, any portion of the impeller can be manufactured with a lattice structure. Since an outer solid, impervious skin structure is usually provided around an inner, 20 lattice structure, the latter is preferably formed in the bulkier portions of the impeller, typically the bulkier portions of the hub, e.g those nearer the rotation axis of the hub and/or of the shroud, if present. The lattice structure is sufficiently strong to resist mechanical and thermal stresses, but has a specific weight lower than the solid material forming the remaining portions of 25 the impeller, thus reducing the overall impeller weight. The un-solidified powder material remaining in the lattice structure can be removed e.g. by blowing or sucking. To facilitate removal of the residual un-solidified powder material, one or more apertures can be provided in the solid skin structure surrounding the lattice structure. -5 - WO 2013/124314 PCT/EP2013/053373 The apertures can be generated during the layer by layer manufacturing process. In other embodiments the apertures can be machined in the finished impeller. The present disclosure also specifically refers to a turbo-machine impeller having at least a hub and a plurality of blades, wherein at least one portion of the inner volume of 5 said impeller comprises a lattice structure surrounded by a solid skin structure. The lattice structure and the solid skin structure surrounding the lattice structure are made of the same material forming the remaining parts of the impeller. Advantageously, the solid skin structure surrounding the lattice structure forms an integral body with the remaining solid parts of the impeller. This can be achieved by means of an additive 10 manufacturing-type-production process. In general terms, the impeller can comprise more than one inner volume portion comprised of a lattice structure. Thus, the present disclosure also relates to a turbo-machine impeller comprising a plurality of solidified layers formed by solidified powder material, wherein at least one 15 portion of the turbo-machine impeller has a lattice structure surrounded by a solid skin structure. In some embodiments the radially most inward part of the hub includes a lattice structure, surrounded by a solid skin structure. Typically the impeller foot will include a lattice structure. 20 The impeller can comprise an impeller shroud with an impeller eye. In advantageous embodiments, at least one inner portion of the shroud has a lattice structure surrounded by said solid skin structure. The lattice structure of the shroud is preferably located in the impeller eye. In some embodiments, the powder material can comprise a titanium alloy. A suitable 25 titanium alloy is Ti-6Al-4V. In other embodiments cobalt-chromium alloys, such as stellite, can be used. In other embodiments an austenitic nickel-chromium-based super-alloy can be used. -6- WO 2013/124314 PCT/EP2013/053373 Examples of suitable super-alloys of this kind are Inconel@ 625 and Inconel@ 718. According to yet further embodiments, steel such as stainless steel, steel 17-4 or other steels suitable for the manufacturing of turbo-machinery components can be used. Features and embodiments are disclosed here below and are further set forth in the 5 appended claims, which form an integral part of the present description. The above brief description sets forth features of the various embodiments of the present invention in order that the detailed description that follows may be better understood and in order that the present contributions to the art may be better appreciated. There are, of course, other features of the invention that will be described hereinafter and 10 which will be set forth in the appended claims. In this respect, before explaining several embodiments of the invention in details, it is understood that the various embodiments of the invention are not limited in their application to the details of the construction and to the arrangements of the components set forth in the following description or illustrated in the drawings. The invention is capable of other embodiments and of being 15 practiced and carried out in various ways. Also, it is to be understood that the phraseology and terminology employed herein are for the purpose of description and should not be regarded as limiting. As such, those skilled in the art will appreciate that the conception, upon which the disclosure is based, may readily be utilized as a basis for designing other structures, 20 methods, and/or systems for carrying out the several purposes of the present invention. It is important, therefore, that the claims be regarded as including such equivalent constructions insofar as they do not depart from the spirit and scope of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS 25 A more complete appreciation of the disclosed embodiments of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein: -7- WO 2013/124314 PCT/EP2013/053373 Fig. 1 illustrates a perspective view of a shrouded impeller according to the state of the art; Fig. 2 illustrates a schematic cross section of a shrouded impeller according to the state of the art; 5 Fig. 3 illustrates a schematic of an electron-beam melting machine; Fig. 4 illustrates a cross-section of a shrouded impeller according to the present disclosure; Figs. 5A, 5B and 5C schematically represent alternative lattice structures which can be formed in the bulky areas of the impeller. 10 DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION The following detailed description of the exemplary embodiments refers to the accompanying drawings. The same reference numbers in different drawings identify the same or similar elements. Additionally, the drawings are not necessarily drawn to scale. Also, the following detailed description does not limit the invention. Instead, the scope 15 of the invention is defined by the appended claims. Reference throughout the specification to "one embodiment" or "an embodiment" or "some embodiments" means that the particular feature, structure or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrase "in one embodiment" 20 or "in an embodiment" or "in some embodiments" in various places throughout the specification is not necessarily referring to the same embodiment(s). Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments. Fig. 3 illustrates an electron-beam melting machine designated 100 as a whole. The 25 structure and operation of the electron-beam melting machine are known per se and will not be described in great detail herein. The electron-beam melting machine 100 -8- WO 2013/124314 PCT/EP2013/053373 includes an electron-beam gun 101 comprising an electron emitter 103 which generates an electron beam EB. The electron beam EB is directed towards a target surface TS, arranged under the electron-beam gun 101. Along the electron-beam path a focusing coil 105 and a deflection coil 107 are arranged. The focusing coil 105 focuses the 5 electron beam on the target surface TS and the deflection coil 107 controls the movement of the electron beam EB along a pattern according to which a powder material has to be melted and solidified. A computer device 109 controls the deflection coil 107 and the movement of the electron beam EB. The movement of the electron beam EB is controlled by the computer device 109 based on data from a file 10 representing the three-dimensional product to be manufactured. Under the electron-beam gun 101 a confinement structure 111 is arranged. The confinement structure 111 can be combined to temperature control means, for example comprising a heater shown schematically at 113, e.g. an electrical heater. A movable table 115 can be arranged in the confinement structure 111. The movable table 115 can 15 be controlled to move vertically according to double arrow fl 15. The vertical movement of the movable table 115 can be controlled by the computer device109. A powder material container 117 is arranged above the target surface TS and is controlled to move horizontally according to double arrow fl 17, for example under the control of the computer device 109. 20 The manufacturing process performed by the electron-beam melting machine 100 can be summarized as follows. A first layer of powder material from the powder container 117 is distributed on the movable table 115 by moving the powder material container 117 according to arrow fl 17 one or more times along the movable table 115 which is placed at the height of the target surface TS. Once the first layer of powder material 25 has been distributed, the electron-beam gun 101 is activated and the electron beam EB is controlled by the deflection coil 107 such as to locally melt the powder material in a restricted portion of the layer, corresponding to a cross-section of the product to be manufactured. After melting, the powder material is allowed to cool and solidify. Powder material outside the boundaries of the cross-section of the product to be 30 manufactured remains in the powder form. Once the first layer has been processed as -9- WO 2013/124314 PCT/EP2013/053373 described above, the movable table 115 is lowered and a subsequent layer of powder material is distributed on top of the first layer. The second layer of powder material is in turn selectively melted and subsequently allowed to cool and solidify. Melting and solidifying are performed such that each layer portion will adhere to the previously 5 formed payer portion. The process is repeated stepwise, until the entire product is formed, by subsequently adding one powder material layer after the other and selectively melting and solidifying layer portions corresponding to subsequent cross sections of the product. Once the product has been completed, the powder material which has not been melted 10 and solidified can be removed and recycled. The product thus obtained can be subjected to further processing if required, such as surface finishing processes or machining. The above described process can be carried out under controlled temperature conditions by means of the heater 113. The temperature within the confinement 15 structure 111 is controlled such that the entire process is performed at high temperature and virtually no residual stresses remain in the product at the complexion of the manufacturing cycle. After the construction process has been completed, the product can be allowed to cool down from a processing temperature to an environment temperature following a cooling curve which prevents residual stresses in the final 20 product. Preferably the interior of the confinement structure 111 is maintained under hard vacuum conditions, such that oxygen absorption by the powder material and the melted material is prevented. In the representation of Fig. 3 an impeller 120 is schematically shown in an 25 intermediate step of the above summarized additive-manufacturing-type manufacturing process. By suitably controlling the electron beam emission a complete melting and subsequent solidification of the powder material is possible, thus obtaining a final compact and - 10 - WO 2013/124314 PCT/EP2013/053373 solid structure. Alternatively, it is also possible to control the electron beam emission such that the powder material is melted and subsequently solidified only in limited volumes, i.e. in a factional manner. By so doing, restricted volumes of powder material are melted and subsequently solidified, said volumes being arranged one adjacent to the 5 other, such that they will connect to one another forming a lattice structure. The lattice structure obtained will be immersed in a bed of powder material which has not been melted. This residual powder material can be subsequently removed, leaving an empty lattice structure. According to the present disclosure, a mixed arrangement is suggested, comprising 10 solid portions and lattice-structured portions, which together form the final product, e.g. a turbo-machine impeller. In Fig. 4 a cross-sectional view of an impeller for a centrifugal turbo-machine manufactured using the layer-by-layer manufacturing process described above is shown. The impeller 120 comprises a hub 121, a shroud 123, blades 125 extending 15 inside the volume between the hub 121 and the shroud 123. Vanes 126 are defined between adjacent blades 125. The impeller 120 comprises a central hole 129 for a shaft (not shown). The hole 129 is surrounded by a bulky portion 131 of the hub 121 of the impeller 120, commonly named "impeller foot". 20 As can be appreciated from the sectional view of Fig. 4, the thickness of the material forming the various parts of the impeller 120 differs from one portion of the impeller to the other. For example, the blades 125 have a relatively thin cross-section, similarly to the radially outer part of the hub 121, i.e. the portion labeled 121A of the hub 121. The radially inner part of the hub 121 forms the above mentioned impeller foot 131, the 25 thickness of which, is remarkably larger than the remaining part of the hub 121. Also the shroud 123 has a radially outer portion 123B which is thinner than the radially inner portion 123A. - 11 - WO 2013/124314 PCT/EP2013/053373 In the exemplary embodiment shown in Fig.4, the interior of the bulkier portions of the impeller 120 and more specifically the interior of the impeller foot 131 as well as the bulkier portion 123A of the shroud 123, commonly named "impeller eye" are manufactured with a lattice structure labeled L. The lattice structure L can be produced 5 as mentioned above, by suitably controlling the electron beam EB. The lattice structure L is surrounded by a solid skin structure or portion S, which is fluid impervious and compact. In the exemplary embodiment shown in Fig. 4 the impeller has only two areas formed by a lattice structure. Those skilled in the art will however understand that a different 10 arrangement of lattice structure portions can be provided, depending upon the design of the impeller. For example, if the shroud has a limited thickness, it can be manufactured as a single compact and solid part, without a lattice structure inside. Similarly, un-shrouded impellers can be provided with a lattice structure only in the impeller hub, and preferably in the impeller foot, which has a bulkier structure than the 15 remaining parts of the hub. The radial extension of the lattice structure in both the hub and the shroud (if present) depends upon the shape of the cross section of the impeller in a radial plane. Providing lattice-structured blades or blade portions is also not excluded, if allowed by the cross-sectional dimensions and shape of the blades. In general, each lattice-structured part of the impeller will be surrounded and 20 encapsulated in a solid skin structure, which forms a fluid impervious barrier, preventing gas or liquid from penetrating the internal lattice structure and providing a smooth outer flow surface for the fluid being processed by the turbo-machine. The solid skin structure can be machined in the same way as any other solid part of the impeller, e.g. for surface finishing purposes. 25 The entire outer surface of the impeller 120 is therefore formed by a continuous solid structure, with no porosity, while the lattice structure L is confined inside said solid skin structure and does not surface on the outside of the impeller 120. As shortly discussed above, both the lattice structure L and the solid parts, including the solid skin structure S, of the turbo-machine impeller can be manufactured layer-by - 12 - WO 2013/124314 PCT/EP2013/053373 layer by suitably controlling the electron-beam emission. Along the same layer of powder material the electron beam EB can be controlled such as to provoke a complete melting of the powder material along those portions of the layer which are intended to form the solid structure, including the solid skin structure S surrounding 5 the lattice structure L. In the areas of the layer where a lattice structure L is required, such as in the impeller foot, the electron beam can be for example pulsed, i.e. choppered, and moved such that the powder material is melted spot-wise, each spot of melted material contacting the adjacent spots of melted material and solidifying in the required lattice structure L. 10 In order to more easily remove the loose powder material which remains trapped between the melted and solidified spots of the lattice structure L, according to some embodiments one or more apertures are provided in the solid skin structure S surrounding each lattice structure L formed in the inner volume of the impeller. In Fig. 4 two apertures A are shown by way of example in the solid skin structure S 15 surrounding the lattice structure L of the impeller foot 131. The apertures A can be used to blow air or suck air through the lattice structure L thus removing the unsolidified powder material therefrom. Preferably the apertures are positioned on the outer surface of the impeller such as not to negatively affect the flow of the fluid being processed by the impeller, as shown in the example illustrated in the drawings. 20 Figs. 5A to 5C schematically illustrate possible lattice structures obtained by electron beam local melting. As can be appreciated from these figures, the lattice structure contains large empty volumes, which reduce the overall amount of material forming the impeller and reducing therefore the weight of the impeller. While the disclosed embodiments of the subject matter described herein have been 25 shown in the drawings and fully described above with particularity and detail in connection with several exemplary embodiments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without materially departing from the novel teachings, the principles and concepts set forth herein, and advantages of the subject matter recited in the appended claims. - 13 - WO 2013/124314 PCT/EP2013/053373 Hence, the proper scope of the disclosed innovations should be determined only by the broadest interpretation of the appended claims so as to encompass all such modifications, changes, and omissions. In addition, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative 5 embodiments. -14-
    权利要求:
    Claims (26)
    [1] 1. A method of manufacturing a turbo-machine impeller comprising a hub and a plurality of blades, using powder material in an additive-manufacturing process; said method comprising: applying energy to said powder material by means of a high energy source; and solidifying said powder material, wherein at least one bulky portion of said hub is irradiated such that the powder material solidifies in a lattice structure surrounded by a solid skin structure enclosing said lattice structure.
    [2] 2. Method according to claim 1, comprising the following steps: depositing a first layer of powder material onto a target surface; irradiating a first portion of said first layer of powder material with said high energy source and solidifying said first portion of powder material; said first portion corresponding to a first cross-sectional region of said turbo-machine impeller; depositing a second layer of powder material onto the first portion; irradiating a second portion of said second layer of powder material with said high energy source and solidifying said second portion of powder material, said second portion corresponding to a second cross-sectional region of said turbo-machine impeller, the first portion and the second portion being joined to one another; depositing successive layers of powder material onto the previous portion and irradiating a portion of each successive layer to produce said turbo-machine impeller comprising a plurality of solidified layer portions, each layer portion corresponding to a cross-sectional region of said turbo-machine impeller; wherein at least some of said successive solidified layer portions have at least one inner part formed by a lattice structure surrounded by an outer solid skin structure portion, said lattice structure forming at least said bulky portion of the impeller hub.
    [3] 3. Method according to claim 1 or 2, wherein said high energy source comprises an electronic beam generator. - 15 - WO 2013/124314 PCT/EP2013/053373
    [4] 4. Method according to any preceding claim, wherein said high energy source comprises a laser source.
    [5] 5. Method according to one or more of the preceding claims, wherein said layers of powder material are deposited in a heated confinement structure.
    [6] 6. Method according to one or more of the preceding claims, comprising the step of controlling the temperature of the turbo-machine impeller after formation of said layer portions avoiding high temperature gradients in the turbo-machine impeller and thus minimizing the residual stresses.
    [7] 7. Method according to one or more of the preceding claims, wherein said powder material is melted and solidified.
    [8] 8. Method according to one or more of the preceding claims, wherein said powder material is solidified by sintering.
    [9] 9. Method according to one or more of the preceding claims, wherein said high energy source is pulsed to generate said lattice structure.
    [10] 10. Method according to one or more of the preceding claims, comprising the step of forming a lattice structure in an inner volume of a hub of said turbo-machine impeller.
    [11] 11. Method according to any preceding claim, wherein said lattice structure is formed in an impeller foot.
    [12] 12. Method according to one or more of the preceding claims, comprising the step of forming an impeller shroud.
    [13] 13. Method according to claim 12, comprising the step of forming a lattice structure in an inner volume of said impeller shroud.
    [14] 14. Method according to claim 13, wherein said lattice structure is formed in an impeller eye.
    [15] 15. Method according to one or more of the preceding claims, comprising the step of - 16 - WO 2013/124314 PCT/EP2013/053373 forming at least one aperture through said solid skin portion for removing un-solidified powder material from the lattice structure surrounded by said skin portion.
    [16] 16. Method according to one or more of the preceding claims, comprising the step of removing un-solidified powder material from the lattice structure after all the layers of the turbo-machine impeller have been completely formed.
    [17] 17. Method according to claim 16, wherein said un-solidified powder material is removed by blowing or sucking a gaseous flow through said lattice structure.
    [18] 18. A turbo-machine impeller comprising a plurality of solidified layers formed by solidified powder material, wherein at least one inner portion of a hub of said turbo machine impeller has a lattice structure surrounded by a solid skin structure.
    [19] 19. Turbo-machine impeller according to claim 18, wherein said lattice structure is located in an impeller foot of said hub.
    [20] 20. Turbo-machine impeller according to claim 18 or 19, comprising an impeller shroud and wherein at least one inner portion of said impeller shroud has a lattice structure and is surrounded by said solid skin structure.
    [21] 21. Turbo-machine impeller according to claim 20, wherein said lattice structure is located in an impeller eye.
    [22] 22. Turbo-machine impeller according to one or more of claims 18 to 21, wherein said solid skin structure has at least one aperture, the lattice structure being in fluid communication with the outer surface of said turbo-machine impeller through said aperture.
    [23] 23. Turbo-machine impeller according to claim 22, wherein said solid skin structure comprises two apertures, the lattice structure surrounded by said solid skin structure being in fluid communication with the outer surface of said turbo-machine impeller through said two apertures.
    [24] 24. Turbo-machine impeller according to one or more of claims 18 to 23, made of a - 17 - WO 2013/124314 PCT/EP2013/053373 material selected from the group comprising: titanium alloys, stellite, steel, stainless steel, austenitic nickel-chromium-based super-alloys, steel 17-4.
    [25] 25. Turbo-machine impeller according to one or more of clams 18 to 24, made of Ti6Al4V.
    [26] 26. A turbo-machine including an impeller according to one or more of claims 18 to 25. - 18 -
    类似技术:
    公开号 | 公开日 | 专利标题
    US10865647B2|2020-12-15|Turbo-machine impeller manufacturing
    EP2957380B1|2018-08-01|Method for making an integrally bladed rotor with hollow blades
    US8691333B2|2014-04-08|Methods for manufacturing engine components with structural bridge devices
    EP3148731B1|2021-11-03|Method for manufacturing a turbomachine component
    US9175568B2|2015-11-03|Methods for manufacturing turbine components
    EP3702069B1|2022-02-23|Titanium aluminide components from articles formed by consolidation processes
    US20110052412A1|2011-03-03|High-pressure turbine rotor, and method for the production thereof
    JP6871425B2|2021-05-12|Parts and parts manufacturing methods using composite additive manufacturing technology
    Gebisa et al.2018|Additive manufacturing for the manufacture of gas turbine engine components: literature review and future perspectives
    Tan et al.2014|Application of electron beam melting | in additive manufacturing of an impeller
    US11168566B2|2021-11-09|Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
    Magerramova et al.2018|Peculiarities of additive technologies application in the production of gas turbine engine parts
    US20190176273A1|2019-06-13|Component and method of forming a component
    JP2017190688A|2017-10-19|Turbine member, axial flow turbine and method for manufacturing turbine member
    EP3663878A1|2020-06-10|Method of designing an intermediate product, computer pro-gram product, method of additive manufacturing, method of manufacturing a component and a corresponding component
    同族专利:
    公开号 | 公开日
    RU2014133205A|2016-04-10|
    US10865647B2|2020-12-15|
    MX2014010166A|2015-01-19|
    RU2630139C2|2017-09-05|
    JP6118350B2|2017-04-19|
    WO2013124314A1|2013-08-29|
    KR20140130136A|2014-11-07|
    US9903207B2|2018-02-27|
    JP2015510979A|2015-04-13|
    ES2825056T3|2021-05-14|
    ITFI20120035A1|2013-08-24|
    EP2817117B1|2020-08-05|
    US20180209276A1|2018-07-26|
    US20150017013A1|2015-01-15|
    EP2817117A1|2014-12-31|
    CA2864617A1|2013-08-29|
    CN104284746B|2018-06-19|
    CN104284746A|2015-01-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2643851A|1948-05-27|1953-06-30|Gen Electric|Turbo-machine rotor with cooling means|
    JPS5458147A|1977-10-19|1979-05-10|Hitachi Ltd|Hydraulic machinery|
    JPS5470102U|1977-10-28|1979-05-18|||
    JPS62203721A|1986-03-03|1987-09-08|Inoue Japax Res Inc|Turbopump|
    FR2774931B1|1998-02-19|2000-04-28|Arnaud Hory|METHOD OF RAPID PROTOTYPING BY LASER POWDER SINTERING AND ASSOCIATED DEVICE|
    US6811744B2|1999-07-07|2004-11-02|Optomec Design Company|Forming structures from CAD solid models|
    JP2003129862A|2001-10-23|2003-05-08|Toshiba Corp|Turbine blade production method|
    JP3997123B2|2002-08-12|2007-10-24|株式会社神戸製鋼所|Iron-based powder material for forming iron-based sintered body and method for producing iron-based sintered body|
    EP2302170A1|2004-11-12|2011-03-30|Board of Trustees of Michigan State University|Turbomachine system and method of operation|
    CN2761319Y|2004-12-15|2006-03-01|华中科技大学|Fast shaping system for direct manufacturing metal parts|
    US7281901B2|2004-12-29|2007-10-16|Caterpillar Inc.|Free-form welded power system component|
    JP2007000964A|2005-06-23|2007-01-11|Tohoku Univ|Method for manufacturing resin-made micromachine component|
    AT544548T|2006-07-14|2012-02-15|Avioprop S R L|METHOD OF MASS PRODUCTION THREE-DIMENSIONAL OBJECTS OF INTERMETALLIC CONNECTIONS|
    US20080075618A1|2006-09-19|2008-03-27|Schlumberger Technology Corporation|Metal Powder Layered Apparatus for Downhole Use|
    JP4901413B2|2006-10-13|2012-03-21|株式会社東芝|Erosion prevention method and member with erosion prevention part|
    US20100034647A1|2006-12-07|2010-02-11|General Electric Company|Processes for the formation of positive features on shroud components, and related articles|
    US8691329B2|2007-01-31|2014-04-08|General Electric Company|Laser net shape manufacturing using an adaptive toolpath deposition method|
    US20090193656A1|2008-02-04|2009-08-06|General Electric Company|Steam turbine bucket with erosion durability|
    RU2386517C1|2008-08-07|2010-04-20|Российская Федерация, от имени которой выступает государственный заказчик - Министерство промышленности и торговли Российской Федерации |Method for sintering in laser layer powder synthesis of volume parts|
    JP2010228332A|2009-03-27|2010-10-14|Panasonic Corp|Production process of shaped article|
    IT1394295B1|2009-05-08|2012-06-06|Nuovo Pignone Spa|CENTRIFUGAL IMPELLER OF THE CLOSED TYPE FOR TURBOMACCHINE, COMPONENT FOR SUCH A IMPELLER, TURBOMACCHINA PROVIDED WITH THAT IMPELLER AND METHOD OF REALIZING SUCH A IMPELLER|
    JP2011021218A|2009-07-14|2011-02-03|Kinki Univ|Powder material for laminate molding, and powder laminate molding method|
    DE102009048665A1|2009-09-28|2011-03-31|Siemens Aktiengesellschaft|Turbine blade and method for its production|
    IT1397058B1|2009-11-23|2012-12-28|Nuovo Pignone Spa|CENTRIFUGAL IMPELLER MOLD, MOLD INSERTS AND METHOD TO BUILD A CENTRIFUGAL IMPELLER|
    US8727729B2|2010-06-29|2014-05-20|Turbocam, Inc.|Method for producing a shrouded impeller from two or more components|
    JP5612530B2|2011-04-19|2014-10-22|パナソニック株式会社|Manufacturing method of three-dimensional shaped object|
    US11000899B2|2012-01-29|2021-05-11|Raytheon Technologies Corporation|Hollow airfoil construction utilizing functionally graded materials|DE102011108957B4|2011-07-29|2013-07-04|Mtu Aero Engines Gmbh|A method for producing, repairing and / or replacing a housing, in particular an engine housing, and a corresponding housing|
    US20140169971A1|2012-12-18|2014-06-19|Hamilton Sundstrand Corporation|Additively manufactured impeller|
    DE102014200381A1|2014-01-13|2015-07-16|Robert Bosch Gmbh|Method of generatively producing a turbine wheel with a shroud|
    US9868155B2|2014-03-20|2018-01-16|Ingersoll-Rand Company|Monolithic shrouded impeller|
    US10004292B2|2014-04-09|2018-06-26|Nike, Inc.|Selectively applied adhesive particulate on nonmetallic substrates|
    EP3148731B1|2014-05-26|2021-11-03|Nuovo Pignone S.r.l.|Method for manufacturing a turbomachine component|
    US9399256B2|2014-06-20|2016-07-26|Velo3D, Inc.|Apparatuses, systems and methods for three-dimensional printing|
    JP6726627B2|2014-07-04|2020-07-22|ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ．|Manufacturing turbomachinery impellers by assembling multiple tubular parts|
    DE102014215089A1|2014-07-31|2016-02-04|Ksb Aktiengesellschaft|Flow guiding component|
    US11098728B2|2015-02-09|2021-08-24|Atlas Copco Airpower, Naamloze Vennootschap|Impeller and method for producing such an impeller|
    DE102015202417A1|2015-02-11|2016-08-11|Ksb Aktiengesellschaft|Stömungsführendes component|
    BE1023131B1|2015-03-26|2016-11-25|Atlas Copco Airpower, Naamloze Vennootschap|Method for manufacturing a centrifugal paddle wheel and centrifugal paddle wheel obtained with such a method.|
    WO2016149774A1|2015-03-26|2016-09-29|Atlas Copco Airpower, Naamloze Vennootschap|Method for manufacturing a centrifugal metal impeller and a centrifugal impeller obtained with such a method|
    GB201507130D0|2015-04-27|2015-06-10|Alcon Components Ltd|Brake caliper body and method of manufacture of a brake caliper body|
    US10449606B2|2015-06-19|2019-10-22|General Electric Company|Additive manufacturing apparatus and method for large components|
    US10634153B1|2015-07-14|2020-04-28|Florida Turbine Technologies, Inc.|Apparatus and process for manufacturing a centrifugal pump with a rotor within a single piece housing|
    BE1023309B1|2015-07-29|2017-01-31|Atlas Copco Airpower Naamloze Vennootschap|Centrifugal paddle wheel, centrifugal machine equipped with such paddle wheel and method for cooling a centrifugal machine|
    ITUB20153620A1|2015-09-15|2017-03-15|Nuovo Pignone Tecnologie Srl|IMPELLER FOR TURBOMACCHINA WITH HIGH RIGIDITY, TURBOMACCHINA INCLUDING THAT IMPELLER AND PRODUCTION METHOD|
    US10281053B2|2015-10-12|2019-05-07|Emerson Process Management Regulator Technologies, Inc.|Lattice structure valve/regulator body|
    GB2543305A|2015-10-14|2017-04-19|Rolls Royce Plc|Apparatus for building a component|
    EP3370948A4|2015-11-06|2019-07-24|Velo3d Inc.|Adept three-dimensional printing|
    KR102234977B1|2015-12-09|2021-04-01|아틀라스 캅코 에어파워, 남로체 벤누트삽|Shrouded impeller manufactured by additive manufacturing and having cavities in the hub and shroud|
    BE1023667B1|2015-12-09|2017-06-12|Atlas Copco Airpower Naamloze Vennootschap|A METHOD FOR PRODUCING CLOSED SHEEP BOOTS|
    US9962767B2|2015-12-10|2018-05-08|Velo3D, Inc.|Apparatuses for three-dimensional printing|
    CN108883575A|2016-02-18|2018-11-23|维洛3D公司|Accurate 3 D-printing|
    FR3048629B1|2016-03-14|2018-04-06|Centre National De La Recherche Scientifique|PROCESS FOR MANUFACTURING A TURBINE RING FOR TURBOMACHINE|
    WO2017158837A1|2016-03-18|2017-09-21|三菱重工業株式会社|Rotating machine and method for manufacturing casing for rotating machine|
    JP2017180178A|2016-03-29|2017-10-05|三菱重工コンプレッサ株式会社|Impeller manufacturing method with thermofusion laminate molding and mechanical polishing|
    JP2017180177A|2016-03-29|2017-10-05|三菱重工コンプレッサ株式会社|Impeller manufacturing method according to thermofusion lamination forming using dissimilar material and impeller|
    EP3251787A1|2016-05-31|2017-12-06|Sulzer Management AG|Method for producing a component of a rotary machine and component produced according to such a method|
    GB201609856D0|2016-06-06|2016-07-20|Renishaw Plc|A particle size sensor for metallic powders|
    US10252336B2|2016-06-29|2019-04-09|Velo3D, Inc.|Three-dimensional printing and three-dimensional printers|
    US20180001384A1|2016-07-01|2018-01-04|General Electric Company|Methods and multi-purpose powder removal features for additive manufacturing|
    CN106077643B|2016-07-26|2018-06-01|西安航天发动机厂|A kind of integral manufacturing method of S-04 high strength stainless steels or S-08 high strength stainless steel three-dimensional closed impellers|
    DE102016217110A1|2016-09-08|2018-03-08|KSB SE & Co. KGaA|rotary pump|
    WO2018058097A1|2016-09-26|2018-03-29|Fluid Handling Llc|Multi-stage impeller produced via additive manufacturing|
    DE102016120480A1|2016-10-27|2018-05-03|Man Diesel & Turbo Se|Method for producing a turbomachine wheel|
    US20180126460A1|2016-11-07|2018-05-10|Velo3D, Inc.|Gas flow in three-dimensional printing|
    US20180186081A1|2017-01-05|2018-07-05|Velo3D, Inc.|Optics in three-dimensional printing|
    EP3364040A1|2017-02-15|2018-08-22|Siemens Aktiengesellschaft|Rotor component, method for producing same|
    US20190358705A1|2017-02-24|2019-11-28|Mitsubishi Heavy Industries Compressor Corporation|Additive manufacturing method and additive manufacturing device|
    WO2018154730A1|2017-02-24|2018-08-30|三菱重工コンプレッサ株式会社|Impeller manufacturing method and impeller flow path elongation jig|
    US10369629B2|2017-03-02|2019-08-06|Veo3D, Inc.|Three-dimensional printing of three-dimensional objects|
    US20180281284A1|2017-03-28|2018-10-04|Velo3D, Inc.|Material manipulation in three-dimensional printing|
    USD871468S1|2017-03-28|2019-12-31|General Electric Company|Flow ingestion discourager with ridged pattern for a turbomachine shroud|
    CN108724023A|2017-04-21|2018-11-02|株式会社不二制作所|The impeller of jet processing apparatus, the manufacturing method of impeller and jet processing apparatus|
    CN107253025A|2017-06-14|2017-10-17|南京辉锐光电科技有限公司|A kind of impeller manufacture method|
    CN107377886B|2017-08-01|2019-06-04|浙江博星工贸有限公司|The casting grilled mold technique of engine cam|
    JP6738789B2|2017-11-29|2020-08-12|株式会社神戸製鋼所|Laminated object design method, manufacturing method, manufacturing apparatus, and program|
    US10272525B1|2017-12-27|2019-04-30|Velo3D, Inc.|Three-dimensional printing systems and methods of their use|
    WO2019138497A1|2018-01-11|2019-07-18|三菱重工エンジン＆ターボチャージャ株式会社|Turbine rotor blade, turbo charger, and turbine rotor blade manufacturing method|
    US10144176B1|2018-01-15|2018-12-04|Velo3D, Inc.|Three-dimensional printing systems and methods of their use|
    RU182168U1|2018-03-16|2018-08-06|Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова"|Axial Turbomachine Disc|
    RU2675735C1|2018-03-16|2018-12-24|Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова"|Method of manufacturing axial turbomachine disk|
    CN108960811B|2018-05-29|2021-01-15|创新先进技术有限公司|Payment method and client|
    RU2682734C1|2018-06-25|2019-03-21|Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова"|Hollow disk of turbine rotor and method of its manufacture|
    RU2672989C1|2018-07-20|2018-11-22|Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова"|Method of manufacturing hollow disk of gas turbine engine|
    US11130174B2|2018-08-03|2021-09-28|General Electric Company|Support structure and methods for additively manufacturing impellers|
    CN108994298B|2018-08-08|2019-11-12|南京航空航天大学|A kind of production method of surface totally enclosed type internal porous gap lightweight metalwork|
    FR3088582B1|2018-11-20|2020-11-20|Commissariat Energie Atomique|Single-portion structured rim|
    US10907497B2|2018-12-13|2021-02-02|Transportation Ip Holdings, Llc|Method and systems for a variable geometry turbocharger for an engine|
    BE1026931B1|2018-12-27|2020-07-27|Atlas Copco Airpower Nv|Impeller and turbocharger equipped with such impeller|
    IT201900007758A1|2019-05-31|2020-12-01|Nuovo Pignone Tecnologie Srl|IMPELLER RING REINFORCED BY COLD DEPOSITION|
    法律状态:
    2018-03-15| MK5| Application lapsed section 142(2)(e) - patent request and compl. specification not accepted|
    优先权:
    申请号 | 申请日 | 专利标题
    IT000035A|ITFI20120035A1|2012-02-23|2012-02-23|"IMPELLER PRODUCTION FOR TURBO-MACHINES"|
    ITFI2012A000035||2012-02-23||
    PCT/EP2013/053373|WO2013124314A1|2012-02-23|2013-02-20|Turbo-machine impeller manufacturing|
    [返回顶部]