Hollow multi-chamber radial impeller for pressurization system
By designing an optimized radial impeller, using the specific structure of the rotation axis and hub part and the arrangement of multiple chambers, the problems of the weight and inertia characteristics of the radial impeller in the boosting system affect performance and manufacturing costs, achieving performance improvement and cost reduction.
Patent Information
- Application Number
- CN202380078562.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2022-12-09
- Filing Date
- 2023-12-07
- Publication Date
- 2025-06-20
AI Technical Summary
The weight and inertial properties of radial impellers in booster systems affect performance and manufacturing costs, and additive manufacturing does not have advantages in manufacturing large components.
An optimized radial impeller is designed which improves the stability and stiffness of the impeller by a specific structure of the axis of rotation and the arrangement of the hub part and the arrangement of multiple chambers, partially withstand forces through the axial structural elements and the radial structural elements.
By reducing the weight and inertia characteristics of the radial impeller, the performance of the boost system is enhanced and the manufacturing cost is reduced, and the boost system is suitable for industrial applications.
Smart Images
Figure CN120187935A_ABST
Abstract
Description
Technical Field
[0001] Embodiments of the present disclosure relate to a radial impeller for a supercharging system. Further, embodiments of the present disclosure relate to a supercharging system having such a radial impeller. Background Art
[0002] A supercharging system, particularly a turbocharger, can be used to increase the output of an internal combustion engine. Generally, a turbine impeller can be arranged in the exhaust path of the internal combustion engine, and a compressor impeller can be arranged upstream of the internal combustion engine. The exhaust gas generated by the internal combustion engine expands within the turbine impeller. The extracted energy can be transmitted through a shaft to the compressor impeller, which can compress the air supplied to the engine. By utilizing the energy of the exhaust gas to compress the air supplied to the combustion process in the internal combustion engine, the combustion process and efficiency of the internal combustion engine can be optimized.
[0003] Generally, the compressor impeller and / or the turbine impeller of a supercharging system are implemented as radial impellers. A radial impeller according to the present disclosure also means an impeller having an axial flow component, commonly referred to as a mixed-flow impeller. A radial impeller can include multiple layers of blades, resulting in a complex external geometry.
[0004] The radial compressor impeller and turbine impeller of a supercharging system can be loaded with high centrifugal forces. The performance characteristics of a supercharging system can be affected by the weight and inertia characteristics of the compressor impeller and the turbine impeller. The lifespan and fatigue limit of a radial impeller can depend on the stability and stiffness of the radial impeller.
[0005] Additive manufacturing can be used to manufacture the compressor impeller and / or the turbine impeller. A negative factor in additive manufacturing of radial impellers is the poor trade-off between the manufacturing-associated costs (e.g., material and printing time per part) and the component advantages, especially when printing component structures originally designed and optimized for traditional manufacturing methods. Further, for large components, additive manufacturing is generally less advantageous. Summary of the Invention
[0006] Aspects and advantages of the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the present disclosure.
[0007] The present disclosure provides a radial impeller for a supercharging system and a supercharging system having such a radial impeller for enhancing the performance of the supercharging system and / or reducing the manufacturing cost by reducing the weight and inertia characteristics of the radial impeller.
[0008] In one aspect, the present disclosure provides a radial impeller for a supercharging system. The radial impeller has a rotational axis and a hub portion, and the hub portion has an outer hub surface defining a gas flow passage. The outer hub surface is curved for radial gas flow such that a root end portion of the outer hub surface axially located on the root side is arranged more radially outward than a nose end portion of the outer hub surface axially located on the nose side. Further, the radial impeller includes an internal structure and a plurality of blades radially extending outward from the hub portion into the gas flow passage. The internal structure has a plurality of chambers including a first chamber and a second chamber. A radial structural element of the internal structure is axially arranged between the first chamber and the second chamber and radially extends outward through the hub portion. The internal structure further includes at least one structural element axially extending from the radial structural element through the first chamber.
[0009] In another aspect, the present disclosure provides a supercharging system having a radial impeller as disclosed herein.
[0010] Details of one or more aspects of the present disclosure are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description, drawings, and claims. BRIEF DESCRIPTION OF THE DRAWINGS
[0011] Reference is made to the accompanying drawings, in which a complete and enabling disclosure of the present disclosure is set forth, in which:
[0012] Figure 1 is a schematic cross-sectional view of a radial impeller according to an embodiment.
[0013] Figure 2 is Figure 1 a perspective view of cross-section A - A of the radial impeller of
[0014] Figure 3 is a schematic cross-sectional view of a radial impeller according to some embodiments.
[0015] Figure 4 is a schematic cross-sectional view of an embodiment of a radial impeller. DETAILED DESCRIPTION
[0016] The present disclosure generally relates to a radial impeller for a supercharging system, particularly a turbocharger, specifically a radial compressor impeller and / or a radial turbine impeller, which provides favorable weight and inertia characteristics through an optimized internal structure. The radial impeller according to the present disclosure partially bears axial forces through axial structural elements and partially bears radial forces and centrifugal forces through radial structural elements, such that the radial impeller can be capable of withstanding high rotational speeds as well as high thermal loads and high structural loads. In some examples, the radial impeller has hollow blades.
[0017] Embodiments of the radial impeller according to the present disclosure are particularly suitable for use as compressor impellers in industrial applications, particularly in supercharging systems for industrial applications. Some embodiments of the radial impeller according to the present disclosure may be particularly suitable for use as compressor impellers and / or turbine impellers of turbochargers. Embodiments of the supercharging system and / or radial impeller according to the present disclosure may be applicable to the power generation industry, large off-highway vehicles, the railway industry, and / or the marine industry, etc.
[0018] Generally, the present disclosure describes a radial impeller for a supercharging system, the radial impeller having a rotational axis and a hub portion, the hub portion having an outer hub surface defining a gas flow passage. Generally, the hub portion is arranged rotationally symmetrically about the rotational axis. As used herein, the rotational axis corresponds to the axis about which the radial impeller rotates. The term "axially" refers to the direction along the rotational axis, and the term "radially" refers to the direction perpendicular to the axial direction. The term "radially inward" refers to a position closer to the rotational axis than the position "radially outward". The outer hub surface may be curved for the radial gas flow. As used herein, the term "radial gas flow" includes a mixed flow having a radial flow component and an axial flow component. The root end portion of the outer hub surface is axially located on the root side and is arranged and inclined more radially outward than the nose end portion of the outer hub surface axially located on the nose side.
[0019] Although the root end portion of the compressor impeller is generally arranged upstream along the gas flow path of the supercharging system compared to the nose end portion, the root end portion of the turbine impeller is generally arranged downstream along the gas flow path of the supercharging system compared to the nose end portion.
[0020] A plurality of blades extend radially outward from the hub portion into the gas flow passage. The hub portion of the radial impeller according to the present disclosure further includes an internal structure. The internal structure has a plurality of chambers, particularly a plurality of hollow chambers. As used herein, the term "chamber" refers to a substantially hollow portion within the hub portion that can be bounded by wall portions in all directions, wherein the wall portions may have one or more openings. The one or more openings may be for manufacturing purposes and / or for further reducing the weight of the radial impeller. The one or more openings may be arranged in a rotationally symmetric manner.
[0021] The internal structure further includes a radial structural element and an axial structural element. As used herein, the term "radial structural element" refers to a structural element that extends between any two points on the outer hub surface and passes through the axis of rotation, wherein the radial structural element extends at least partially and / or in segments in the radial direction. The radial structural element can be axially disposed between the first chamber and the second chamber. The radial structural element can extend radially outward, through the entire hub portion and out to the outer hub surface, and through the axis of rotation of the radial impeller. The radial structural element can extend substantially perpendicular to the axis of rotation and / or be at least partially angled and / or curved relative to the radial direction. The upper surface of the radial structural element can extend in a different manner from the lower surface of the radial structural element. As used herein, the term "upper surface" refers to the lower wall portion of the upper chamber that defines the chamber on the root side. Similarly, the term "lower surface" refers to the upper wall portion of the lower chamber that defines the chamber on the nose side. For example, the upper surface can extend substantially perpendicular to the axis of rotation through the hub portion, while the lower surface can be curved, or the lower surface can extend substantially perpendicular to the axis of rotation through the hub portion, while the upper surface can be curved. In an embodiment, the thickness of the radial structural element can be constant or can vary in part. In particular, the thickness of the radial structural element can depend on the radial position. The term "thickness" as used herein can refer to the axial distance between the upper surface and the lower surface, at a position where the upper surface is axially disposed towards the nose of the lower surface. The mid-plane can be defined by a plane disposed equidistant from the upper surface and the lower surface. The mid-plane can extend through the axis of rotation.
[0022] The axial structural element can extend from the radial structural element and through the entire axial extent of the first chamber. The axial structural element can extend substantially axially and / or be at least partially angled or curved relative to the axis of rotation. Preferably, at least one axial structural element can extend from the radial structural element through the first chamber within a cylindrical region, the diameter of which is equal to or less than the minimum diameter of the outer hub surface. The axial structural element can include a plurality of sub-elements.
[0023] As used herein, the term "through the entire axial / radial extent" refers to the extent between any two points that are substantially positioned opposite each other in the axial / radial direction, wherein the term "substantially" refers to an extent that can be angled with respect to the axial / radial direction such that the two points can be offset from each other with respect to their respective directions.
[0024] A plurality of chambers arranged in the hub portion may be arranged in an axially stacked manner. For high rotational speeds and high structural loads acting on a radial impeller, it may be appropriate to provide a greater number of chambers. A greater number of substantially radially arranged structural elements may be provided for subdividing the hollow space into, for example, two axially stacked chambers. Radially arranged structural elements, such as radial structural elements, may be adapted to withstand centrifugal forces and provide stiffness.
[0025] The internal structure may be formed such that the principal axis of inertia corresponds to the axis of rotation of the radial impeller. In particular, each element, such as a radial structural element and an axial structural element, may be formed such that the principal axis of inertia corresponds to the axis of rotation of the radial impeller. In an embodiment, a discrete rotationally symmetric arrangement of independent elements of the internal structure may be formed such that the principal axis of inertia corresponds to the axis of rotation of the radial impeller. According to an embodiment, different elements of the internal structure may have a principal axis of inertia corresponding to the axis of rotation of the radial impeller with respect to each other, while each of these different elements does not necessarily have a principal axis of inertia corresponding to the axis of rotation of the radial impeller.
[0026] In an embodiment, independent elements of the internal structure, such as radial structural elements and / or axial structural elements, may be formed according to the number of blades arranged on the hub portion. For example, a plurality of blades may include 8 blades extending radially outward from the hub portion such that the independent elements and / or sub-elements of the internal structure may be arranged at discrete angles that are integer multiples or integer fractions of 45°. In some embodiments, the plurality of blades may include 9 blades extending radially outward from the hub portion such that the independent elements and / or sub-elements of the internal structure may be arranged at discrete angles that are integer multiples of 40°. Such embodiments may enhance the running smoothness of the radial impeller. In some embodiments, it may be advantageous to avoid such a dependence with respect to vibration modes.
[0027] According to an embodiment, a radial structural element may, for example, continuously extend through the hub portion between two circumferential positions opposite each other in at least one cross-section containing the axis of rotation. Preferably, the radial structural element may extend between any two circumferential positions opposite each other in a plurality of cross-sections containing the axis of rotation. Particularly preferably, the radial structural element may extend between any two circumferential positions opposite each other in any cross-section containing the axis of rotation. This design may enable the radial impeller to withstand high rotational speeds. As used herein, the term "continuously extend" refers to a structure along a continuous path between circumferential positions opposite each other (e.g., through the radial structural element). Preferably, in a cross-section containing the axis of rotation and the corresponding circumferential positions opposite each other.
[0028] In an embodiment, the plurality of chambers of the internal structure may include at least one chamber disposed within at least one of the plurality of blades of the radial impeller. Providing substantially hollow blades can improve the inertial characteristics of the radial impeller.
[0029] According to some embodiments, a lattice structure may be disposed within at least one of the plurality of chambers. In particular, the lattice structure may occupy at least 60%, preferably at least 70%, particularly preferably at least 80% of the volume of the corresponding chamber. As used herein, a lattice structure that occupies at least 60% of the volume of the corresponding chamber is defined by 60% of the internal volume of the corresponding chamber, with the internal volume of the corresponding chamber spaced from the lattice structure by at most a characteristic length. The characteristic length may be defined by the lattice constant of the lattice structure. The lattice structure may reduce, for example, the wall thickness of axial structural elements and / or radial structural members. The lattice structure may reduce the weight of the radial impeller and improve inertial characteristics. The lattice structure may be used as a support structure.
[0030] In some embodiments, a third chamber may be axially disposed on the root side of the first and second chambers and / or a fourth chamber may be axially disposed on the nose side of the first and second chambers. Subdividing the hollow hub portion into a plurality of axially stacked chambers can enable the radial impeller to withstand higher centrifugal forces while reducing weight and improving inertial characteristics.
[0031] According to an embodiment, at least one of the plurality of chambers may be connected to another of the plurality of chambers. In an embodiment, each of the plurality of chambers may be connected to each other. As used herein, the term "connected" refers to a connection of a path between two locations through which powder (e.g., powder for additive manufacturing) can pass, either directly or indirectly. For example, a first chamber may be indirectly connected to a fourth chamber through a direct connection of the first chamber to a second chamber and another direct connection of the second chamber to the fourth chamber, and vice versa. The plurality of chambers may be connected to each other, for example, through one or more openings in the surrounding wall portion. Such an embodiment facilitates the manufacture of the radial impeller.
[0032] In some embodiments, the internal structure may have a plurality of radial spokes that can connect the nose side of the radial structural element to the radially outer surface of the chamber. In particular, the radial spokes may extend radially outward and axially toward the nose from the nose side of the radial structural element. In an embodiment, the radial structural element may be directly connected to the outer hub surface at an axial position closer to the root end than the plurality of radial spokes. In some embodiments, the plurality of spokes may include a plurality of spokes, and the number of spokes may be an integer multiple or an integer fraction of the number of blades extending radially outward from the hub portion. The plurality of radial spokes may withstand centrifugal force and / or may partially direct the centrifugal force to the radial structural element, which acts at an axial position closer to the nose end than the axial position of the nose side of the radial structural element. The plurality of radial spokes may increase the stability and stiffness of the radial impeller.
[0033] According to an embodiment, the first chamber may be substantially disposed at the axial level of the widest radius of the hub portion, and / or the second chamber may be disposed closer to the nose side than the first chamber. As used herein, the term "axial level of the widest radius of the hub portion" refers to the widest radius segment on the axis of rotation, which may have the maximum radial distance to the hub portion. The widest radius segment may include a center point or may be a point on the axis of rotation. The term "substantially at the axial level of the widest radius of the hub portion" may refer to an extended segment extending on the axis of rotation compared to the widest radius segment. The extended segment may have the same center point as the widest radius segment and may extend from the center point, or alternatively start from that point, and extend on the axis of rotation in each of the two directions by at most 10% of the axial extension of the hub portion more than the widest radius segment. As used herein, the term "the first chamber may be substantially disposed at the axial level of the widest radius of the hub portion" refers to a design in which any part of the first chamber may be disposed within the radially extended area of the extended segment. Such an embodiment may improve the inertial characteristics of the radial impeller while providing high stability and stiffness.
[0034] In some embodiments, the radial structural element may have a non-planar lower surface. The upper surface of the radial structural element may be non-planar. In particular, the lower surface and / or the upper surface may be formed to bend toward the root side in the direction from radially inward to radially outward and / or may protrude toward the nose in the radially inner portion.
[0035] In an embodiment, a radial structural element may be formed based on a ratio between two parameters. For example, the thickness of the radial structural element may be formed according to an upper thickness-diameter ratio or a lower thickness-diameter ratio. As used herein, the "diameter" in the upper thickness-diameter ratio may be defined by the maximum radial extension of the upper surface of the radial structural element. Similarly, the "diameter" in the lower thickness-diameter ratio may be defined by the maximum radial extension of the lower surface of the radial structural element. The upper thickness-diameter ratio and / or the lower thickness-diameter ratio may be from 0.01 to 0.40, preferably from 0.05 to 0.22, and particularly preferably from 0.01 to 0.18.
[0036] According to an embodiment, at least one sub-element of the axial structural element may be rotationally symmetrically formed about the axis of rotation. In an embodiment, the axial structural element may be symmetric only about discrete angles of rotation (e.g., integer multiples of about 30°), preferably the discrete angles depending on the number of blades radially extending outward from the hub portion.
[0037] In some embodiments, the axial structural element may be supported on its root side to withstand axial loads (e.g., tensile loads and / or compressive loads).
[0038] According to an embodiment, the material ratio of the radial impeller may be from 30% to 70%, preferably from 40% to 60%, and particularly preferably from 45% to 55%. As used herein, the term "material ratio" refers to the percentage of material disposed within a predetermined volume. For example, a solid solid may have a material ratio of 100%.
[0039] In an embodiment, the radial impeller may be integrally formed by a layer-by-layer process. In particular, the radial impeller may be integrally formed from one or more powders (e.g., one or more types of metal powders) by a layer-by-layer process.
[0040] According to an embodiment, the radial impeller may be a radial compressor impeller. In some embodiments, the radial impeller may be an open impeller, i.e., a radial impeller that does not include a shroud. In an embodiment, the blades may be attached to the hub through the blade base but are not connected in the remaining parts, and in particular, are not connected to each other through the shroud.
[0041] Now, embodiments of the present disclosure will be described in detail. Some examples of the present disclosure are shown in the drawings. Each example is provided as an explanation of the present disclosure, not a limitation of the present disclosure. For example, features shown or described as part of an embodiment may be used with other embodiments to produce more embodiments. The drawings may not be drawn to scale.
[0042] Figure 1Fig. shows a schematic cross-sectional view of a radial impeller 100 according to an embodiment of the present disclosure. The radial impeller 100 can be a radial compressor impeller or a radial turbine impeller.
[0043] The radial impeller 100 can be used in a supercharging system, particularly for a turbocharger. According to an embodiment, the radial impeller 100 can include connecting means located on the root side 103 for mounting the radial impeller 100 on the shaft of the supercharging system. In an embodiment, the radial impeller 100 can have a shaft. In an embodiment, a tube that rotates about the rotational axis 101 of the radial impeller 100 can be partially disposed through the radial impeller 100 for mounting the radial impeller 100 on the shaft by means of fixing means or the like. The tube can be included in the radial impeller 100.
[0044] The radial impeller 100 can have a hub portion 110 including an outer hub surface 114. The gas flow passage 116 can be defined by the outer hub surface 114. The diameter of the hub portion 110 at the root side 103 of the radial impeller can be larger than that at the nose side 102. The outer hub surface 114 can be curved for radial gas flow and / or diagonal gas flow.
[0045] The radial impeller 100 can include a plurality of blades 120, and the plurality of blades 120 can be arranged on the outer hub surface 114. The plurality of blades 120 can extend radially outward from the hub portion 110 into the gas flow passage 116. The radial impeller 100 can be an open impeller, so the radial impeller 100 does not include a shroud.
[0046] In an embodiment, the radial impeller 100 has a partially hollow internal structure 130. Preferably, the internal structure 130 can be substantially hollow. For example, compared with a solid radial impeller having the same external geometry, due to the partially hollow internal structure 130, the radial impeller 100 can have a material ratio of less than 60%, preferably less than 55%, and particularly preferably less than 50%.
[0047] The internal structure 130 can be defined by a plurality of chambers, for example, defined by a first hollow chamber 131 and a second hollow chamber 132. The chambers can be bounded by wall portions in all directions. The space bounded by one or more wall portions can be hollow. The plurality of chambers can be formed in different designs (e.g., cuboid, sphere or any other design). For example, one or more chambers can be at least partially bounded by wall portions with a uniform wall thickness of the hub portion 110, such that the design of one or more chambers can at least partially depend on the geometry of the outer hub surface 114. In an embodiment, the wall portions can have one or more openings.
[0048] The internal structure 130 may include a third chamber 133 and a fourth chamber 134. The third chamber 133 may be axially arranged at the root side 103 of the first chamber 131. The fourth chamber 134 may be axially arranged at the nose side 102 of the second chamber 132.
[0049] The plurality of blades 120 may further include at least one blade chamber 121. The blade chamber 121 may be arranged in the blade 122. In an embodiment, the blade chamber 121 may be formed at least partially according to the geometry of the blade 122, particularly such that the blade 122 may resemble a shell with a uniform wall thickness.
[0050] In an embodiment, the wall portion defining one or more of the plurality of chambers may have an opening. In particular, as Figure 1 shown, the second chamber 132 and the fourth chamber 134 may be defined by the same wall portion. The wall portion axially arranged between the second chamber 132 and the fourth chamber 134 may have one or more openings such that the second chamber 132 and the fourth chamber 134 may be directly connected. According to an embodiment, any one of the plurality of chambers may be connected to any other of the plurality of chambers. Such connection may be direct or indirect. In particular, the first chamber 131 may be indirectly connected to the fourth chamber 134 by being directly connected to the second chamber (the second chamber is directly connected to the fourth chamber 134).
[0051] The internal structure may further include additional chambers. For example, the fourth chamber may be divided into two or more chambers by a wall portion. By providing additional chambers, the material ratio of the radial impeller 100 will have a higher percentage value than when providing a smaller number of chambers. Although a higher percentage value of the material ratio may increase the stiffness of the radial impeller and enable it to withstand more forces, during the operation of the radial impeller 100, more material may have to be accelerated, which may result in more forces and / or more unfavorable inertial characteristics.
[0052] A radial structural element 141 may be axially arranged between the first chamber 131 and the second chamber 132. The radial structural element 141 may extend substantially perpendicular to the rotation axis 101. In an embodiment, the radial structural element 141 may extend radially outward through the hub portion 110 and through the rotation axis 101. The radial structural element 141 may withstand circumferential forces during the operation of the radial impeller 100.
[0053] The radial structural element 141 can continuously extend between two circumferential positions opposite to each other in a plurality of cross-sections containing the rotational axis 101 through the hub portion 110. The plurality of cross-sections containing the rotational axis 101 can be at angles that are integer multiples of 15° relative to each other. Preferably, the radial structural element 141 can extend between any two corresponding circumferential positions in any cross-section containing the rotational axis 101.
[0054] In an embodiment, the radial structural element 141 can be formed according to an upper thickness-diameter ratio and / or a lower thickness-diameter ratio. The upper thickness-diameter ratio and / or the lower thickness-diameter ratio can be from 0.01 to 0.40, preferably from 0.05 to 0.22, and particularly preferably from 0.01 to 0.18. The thickness of the radial structural element 141 can be selected according to the axial position and / or depending on the radial extension of the radial structural element 141.
[0055] According to an embodiment, the first chamber 131 can be substantially arranged at the axial position of the widest radius of the hub portion 110. Since the radial structural element 141 can be arranged at the nose side 102 of the first chamber 131, the radial structural element 141 can be in an advantageous position to withstand a large amount of circumferential force.
[0056] The radial structural element 141 can have a non-planar lower surface. In particular, the radial structural element 141 can bend as the radial position moves from the rotational axis towards the root side 103. The upper surface of the radial structural element 141 can be formed as non-planar. In particular, the upper surface of the radial structural element 141 can be formed to bend towards the nose from radially inwards to radially outwards.
[0057] As Figure 1 shown, the axial structural element 142 can extend substantially axially through the first chamber 131. The axial structural element 142 can be designed as one or more columns. For example, each column represents a sub-element of the axial structural element such as a cylinder. During operation, the axial structural element 142 can withstand the axial force acting on the radial impeller 100. In an embodiment, the axial structural element 142 can extend in segments in the radial direction. Preferably, the axial structural element 142 can be designed to be rotationally symmetric about the rotational axis 101. In an embodiment, a plurality of sub-elements of the axial structural element 142 can also form a discrete rotationally symmetric design, for example in integer multiples of 30°.
[0058] For example, in order to withstand a large amount of tensile and / or compressive axial force, it may be advantageous to provide support at the root side of the axial structural element 142.
[0059] Figure 1 The shown radial impeller 100 can be integrally formed by a layer-by-layer process. In particular, the radial impeller 100 can be formed from powder. The powder can be metal powder. For example, if forming a radial compressor impeller, titanium alloy powder and / or aluminum alloy powder can be used. When forming a turbine impeller, nickel alloy powder can generally be used. For example, the radial impeller 100 can be manufactured by processes such as selective laser melting process.
[0060] In some embodiments, the radial impeller 100 can be integrally formed from multiple materials by a layer-by-layer process. For example, compared with the low-stress regions of the radial impeller 100, different materials (such as high-strength metal alloys) can be used to print the high-stress regions of the radial impeller 100. In some embodiments, the materials can be selected at least in part according to the radial position and / or the axial position. For example, a high thermal conductivity material (such as copper) can be selected for the regions of the elements of the internal structure 130 and / or the sub-elements of the internal structure 130 that are close to the rotational axis 101.
[0061] In an embodiment, a support structure can be used to print the radial impeller 100. According to an embodiment, the lattice structure 160 can be used as the support structure. The lattice structure 160 can be arranged in one or more of a plurality of chambers. In particular, the lattice structure 160 can occupy at least 80% of the volume of the corresponding chamber. The internal volume of the corresponding chamber is spaced from the lattice by at most the characteristic length of the lattice structure 160.
[0062] Figure 2 is shown Figure 1 A schematic perspective view of a cross-section A-A of the radial impeller 100. Figure 2 A plurality of blades 120 that can radially extend outward from the outer hub surface 114 are shown. In addition, the second chamber 132 is shown in a three-dimensional cross-sectional view. The wall portion that defines the second chamber at the root side 103 can be the upper surface of the radial structural element 141.
[0063] According to an embodiment, a plurality of radial spokes 150 can be arranged in the second chamber 132. The plurality of radial spokes 150 can connect the radial structural element 141 to the radially outer surface of the second chamber 132. As Figure 2Exemplarily shown, for example, the radial spokes 150 may extend radially outward from the nose side of the radial structural element 141 and axially toward the nose side 102. Similarly, a plurality of radial spokes 150 may additionally or alternatively be arranged in any other of the plurality of chambers. Further, a plurality of radial spokes 150 may additionally and / or alternatively be arranged between the first chamber 131 and the third chamber 133 and / or between the second chamber 132 and the fourth chamber 134 such that an opening may be provided between any two of the plurality of radial spokes 150, which opening may directly connect two corresponding chambers to each other.
[0064] Figure 3 A cross-sectional schematic view of a radial impeller 100 according to some embodiments is shown. The radial impeller 100 may have a hub portion 110 and a plurality of blades 120 that rotate about a rotational axis 101. The hub portion 110 may include an internal structure 130, which internal structure 130 may include a plurality of chambers. Figure 3 The internal structure 130 of the radial impeller 100 in includes a first chamber 131, a second chamber 132, and a plurality of blade chambers 121.
[0065] The radial structural element 141 may be axially arranged between the first chamber 131 and the second chamber 132. The extension of the radial structural element 141 in the axial direction may be less than its extension in the radial direction. The lower surface 143 of the radial structural element 141 may be curved such that the radial structural element 141 may extend to the widest diameter of the hub portion 110. The radial structural element 141 may include an opening. In particular, the radial structural element 141 may include a plurality of rods arranged at an angle to each other. For example, each of the plurality of rods may extend through the entire hub portion 110. An opening may be formed between every two rods. Each of the plurality of rods may extend between a first position and a second position. The second position may correspond to the position after the first position is rotated 180° about the rotational axis 101. In some embodiments, the radial structural element 141 may be formed continuously without any openings.
[0066] The cylindrical axial structural element 142 may be arranged to extend within a cylindrical region from the radial structural element 141 through the first chamber 131, the diameter of which cylindrical region may be equal to or less than the minimum diameter of the outer hub surface 114. In some embodiments, a plurality of sub-elements of the axial structural element 142 may be arranged in a discrete rotational symmetry manner. In particular, in an annular pattern, one sub-element of the axial structural element 142 may be arranged every 15° or an integer multiple of 15°. The sub-elements may have a circular cross-section.
[0067] The lattice structure 160 can be disposed in the second chamber 132. The lattice structure 160 can cause the hollow chamber (e.g., the second chamber 132) to expand in size. Since the wall thickness of the hub portion 110 can be reduced and the forces that would otherwise have to be borne by the outer wall of the hub portion 110 can be borne by the lattice structure 160 at a radial position closer to the axis of rotation 101, the lattice structure 160 can improve the inertial characteristics of the radial impeller.
[0068] Figure 4 A cross-sectional schematic view of an embodiment of a radial impeller 100 is shown. The radial impeller 100 can have an internal structure 130 that includes a first chamber 131, a second chamber 132, a third chamber 133, a fourth chamber 134, and blade chambers 121 in each of a plurality of blades 120 that extend radially outward from the hub portion 110 of the radial impeller.
[0069] Figure 4 The internal structure 130 shown can include radial structural elements 141. Additionally, the internal structure 130 can include axial structural elements 142 having a plurality of sub-elements. A first sub-element 142a can be formed as a column that extends along the axis of rotation 101 through the entire first chamber 131, third chamber 133, and second chamber 132 from the radial structural element 141. A cylindrical second sub-element 142b can be formed to pass through the first chamber 131 around the axis of rotation 101.
[0070] The lattice structure 160 can be formed in the fourth chamber 134 and / or in any other of the plurality of chambers. The lattice structure 160 can be used as a support structure integrally formed with the radial impeller 100. For example, the radial impeller 100 can be formed by layer-by-layer printing with a 3D printer. The lattice structure 160 can serve as a support structure and can remain in the chamber during operation of the radial impeller 100.
[0071] According to the present disclosure, any of the embodiments of the radial impeller can be used in a supercharging system, e.g., a radial compressor impeller and / or a turbine impeller.
[0072] Thus, with reference to specific examples, the radial impeller has been introduced in the foregoing description. It should be understood that the various aspects disclosed herein can be combined in different specific combinations than those presented in the figures. It should be understood that various modifications can be made to the reference examples without departing from the scope of the present disclosure and the appended claims.
[0073] List of Reference Numerals
[0074] 100 Radial impeller
[0075] 101 Axis of rotation
[0076] 102 Nose side
[0077] 103 Root side
[0078] 110 Hub portion
[0079] 114 Outer hub surface
[0080] 116 Gas flow channel
[0081] 120 Multiple blades
[0082] 121 Blade chamber
[0083] 122 Blade
[0084] 130 Internal structure
[0085] 131 First chamber
[0086] 132 Second chamber
[0087] 133 Third chamber
[0088] 134 Fourth chamber
[0089] 141 Radial structural element
[0090] 142 Axial structural element
[0091] 142a First sub - element
[0092] 142b Second sub - element
[0093] 143 Lower surface
[0094] 150 Multiple radial spokes
[0095] 160 Lattice structure
Claims
1. A radial impeller (100) for a supercharging system, the radial impeller (100) having a rotational axis (101) and comprising: A hub portion (110) having an outer hub surface (114) defining a gas flow passage (116), the outer hub surface (114) being curved for radial gas flow such that a root end portion of the outer hub surface (114) axially located on the root side (103) is arranged more radially outward than a nose end portion of the outer hub surface (114) axially located on the nose side (102); A plurality of vanes (120) extending radially outward from the hub portion (110) into the gas flow passage (116); And An internal structure (130) comprising: A plurality of chambers including a first chamber (131) and a second chamber (132); A radial structural element (141) axially arranged between the first chamber (131) and the second chamber (132) and extending radially outward from the axis of rotation (101) through the hub portion (110); and An axial structural element (142) axially extending from the radial structural element (141) through the first chamber (131).
2. The radial impeller (100) according to claim 1, wherein, The radial structural element (141) continuously extends through the hub portion (110) between two circumferential positions opposite to each other in at least one cross-section containing the axis of rotation (101).
3. The radial impeller (100) according to any one of the preceding claims, wherein, The plurality of chambers further includes a vane chamber (121) arranged in at least one of the vanes (122).
4. The radial impeller (100) according to any one of the preceding claims, wherein, The internal structure (130) further includes a lattice structure (160) in at least one of the plurality of chambers.
5. The radial impeller (100) according to any one of the preceding claims, wherein, The plurality of chambers further includes a third chamber (133) axially arranged on the root side (103) between the first chamber (131) and the second chamber (132), and / or a fourth chamber (134) axially arranged on the nose side (102) between the first chamber (131) and the second chamber (132).
6. The radial impeller (100) according to any one of the preceding claims, wherein, At least one of the plurality of chambers is connected to another of the plurality of chambers, in particular, each of the plurality of chambers is connected to each other.
7. The radial impeller (100) according to any one of the preceding claims, wherein, The internal structure (130) further includes a plurality of radial spokes (150) connecting the nose side of the radial structural element (141) to the radially outer surface of the second chamber (132), in particular, the radial spokes (150) extend radially outward and axially towards the nose from the nose side of the radial structural element (141).
8. The radial impeller (100) according to any one of the preceding claims, wherein, The first chamber (131) is substantially arranged at the axial position of the widest radius of the hub portion (110), and / or wherein the second chamber (132) is arranged closer to the nose side (102) than the first chamber (131).
9. The radial impeller (100) according to any one of the preceding claims, wherein, The radial structural element (141) includes a non-planar lower surface (143).
10. The radial impeller (100) according to any one of the preceding claims, wherein, The axial structural element (142) is rotationally symmetrically formed about the axis of rotation (101).
11. The radial impeller (100) according to any one of the preceding claims, wherein, The axial structural element (142) is supported on its root side to withstand axial loads.
12. The radial impeller (100) according to any one of the preceding claims, wherein, The radial impeller (100) comprises a material ratio of 30% to 70%, preferably the material ratio is 40% to 60%, and particularly preferably the material ratio is 45% to 55%.
13. The radial impeller (100) according to any one of the preceding claims, wherein, The radial impeller (100) is integrally formed by a layer-by-layer process, in particular by one or more types of powder formation.
14. The radial impeller (100) according to any one of the preceding claims, wherein, The radial impeller (100) is a radial compressor impeller.
15. A supercharging system having a radial impeller (100) according to any one of the preceding claims.