Turbo component with energy absorption struts

Abstract

The invention relates to a turbo component (100, 200) for a turbomachine, comprising an impeller (130, 230) mounted on a shaft (120). The shaft (120) defines the rotor axis (RA). The turbo component further comprises a first housing wall portion (143, 243), which defines a first spiral housing portion (150, 251), and a second housing wall portion (145, 245), which is arranged at least partially within the first housing wall portion (143, 243). The turbo component further comprises a plurality of transverse struts (147, 247), which extend substantially transversally to the rotor axis (RA) and each connect the first housing wall portion (143, 243) to the second housing wall portion (145, 245).

Description

TURBO COMPONENT WITH ENERGY ABSORPTION STRUTS TECHNICAL FIELD

[0001] The invention relates to a turbo component for a turbomachine, in particular for an exhaust gas turbocharger, and a turbomachine, in particular an exhaust gas turbocharger. TECHNICAL BACKGROUND

[0002] To increase the performance of an internal combustion engine (combustion engine), exhaust gas turbochargers are now standard equipment. They consist of a compressor that supplies air to the combustion chamber for the combustion process, and an exhaust gas turbine in the engine's exhaust tract. Turbocharging increases the amount of air and fuel in the cylinders, resulting in a noticeable increase in engine power. The exhaust gas turbocharger used for this purpose typically consists of a rotor, a compressor wheel, and a turbine wheel, as well as the shaft bearings, the flow-carrying housing components (compressor housing, turbine housing), and the bearing housing.

[0003] When the internal combustion engine is operated at full load, and the exhaust turbine of the exhaust turbocharger is subjected to a correspondingly large exhaust gas flow, very high circumferential speeds are reached at the blade tips of the turbine and compressor wheels. The maximum permissible rotor speed of a turbocharger is a function of the wheel size, the geometry, and the strength values ​​of the materials used. In general, the rotating components are subject to very high centrifugal loads and thus high material stresses. Defects in the Material structures can, under certain circumstances, lead to the bursting of the compressor or turbine wheel, with unpredictable consequences for the adjacent housings.

[0004] The initial failure pattern of a compressor wheel can be described as a blade fracture or a multi-part hub burst. In a blade burst, the blades fail in the compressor's root area, leaving the wheel hub intact. In a multi-part hub burst, the hub area usually breaks into two to four fragments. The most critical compressor burst case is a three-part hub fracture with three roughly equal-sized fragments (3 x 120° sectors).

[0005] The burst protection concept (containment concept) of an exhaust gas turbocharger must be designed to ensure that, in the event of a multi-part hub burst, all fragments are contained within the outer casing at a specified burst speed. Thus, during the design of the exhaust gas turbocharger, care is taken to ensure that the kinetic energy of the compressor is already dissipated in the inner, rotor-like casing sections through plastic deformation, so that the remaining kinetic energy of the radially propelled fragments is insufficient to penetrate the outer casing or cause the external casing connections (e.g., bolts) to fail.

[0006] Various measures to reduce the load on the housing in the event of a bursting compressor wheel are known, for example from EP 2 216 516 Al, EP 2 194 277 Al, or DE 10 2010 064 025 Al.

[0007] The design variants known from the state of the art have various disadvantages. Some design variants lead to flow restrictions in a recirculator channel and / or have insufficient energy absorption capacity in the event of a compressor burst. or turbine wheel and / or have other design disadvantages, such as the fact that too large a construction volume is required for implementation or that the production is very time-consuming and costly. BRIEF DESCRIPTION OF THE INVENTION

[0008] The object of the present invention is to provide a turbo component which is improved with respect to at least one of the disadvantages known from the prior art.

[0009] To achieve the above-mentioned object, a turbo component for a turbomachine according to claim 1 and a turbomachine according to claim 15 are provided.

[0010] According to one aspect of the invention, a turbo component for a turbomachine, in particular for an exhaust gas turbocharger, is provided. The turbo component comprises an impeller mounted on a shaft. The shaft defines a rotor axis. The turbo component further comprises a first housing wall section defining a first spiral housing section and a second housing wall section arranged at least partially within the first housing wall section. Furthermore, the turbo component has a plurality of cross struts extending substantially transversely to the rotor axis and each connecting the first housing wall section to the second housing wall section.

[0011] The turbo component is preferably a compressor or a radial turbine.

[0012] The first housing wall section defines the first volute section, and thus at least a portion of the volute. In some embodiments, the first housing wall section may completely define the volute. The volute defines a spiral-shaped collecting chamber of the turbo component.

[0013] The first housing wall section and / or the second housing wall section can be axially extended and can be completely or substantially completely continuous or continuous in the circumferential direction. The first housing wall section and / or the second housing wall section can be substantially cylindrical at its first axial end section. If the turbo component is a compressor, the first housing wall section and / or the second housing wall section can be substantially cylindrical at its upstream end section. If the turbo component is a radial turbine, the first housing wall section and / or the second housing wall section can be substantially cylindrical at its downstream end section.

[0014] The first housing wall section and / or the second housing wall section are preferably arranged radially spaced from one another at their first axial end section and / or are not adjacent or contiguous to one another at their first axial end section. The second housing wall section can be arranged entirely within the first housing wall section.

[0015] At the second end section, which is opposite in the axial direction, the first housing wall section and / or the second housing wall section can have a shape that deviates from a cylindrical shape. For example, the first housing wall section can define the first spiral housing section at the second end section. If the turbo component is a compressor, the second end section can be a downstream end section. If the turbo component is a radial turbine, the second end section can be an upstream end section.

[0016] A cross brace is a connecting piece, which connects the first to the second housing wall section and is designed to absorb forces. Furthermore, the cross strut extends in the circumferential direction only over part of the circumference of the first or second housing wall section. The cross strut has a length perpendicular to the rotor axis which is greater than a thickness along the rotor axis. Preferably, an angle between the cross strut and a radial plane is less than 30°, more preferably less than 10°, and most preferably the cross strut is exactly transverse to the rotor axis. The radial plane (or transverse plane) is a plane perpendicular to the rotor axis which intersects the cross strut.

[0017] Thus, a turbo component is advantageously provided which enables a slim design, i.e., it does not require a larger, or at least not significantly larger, construction volume for implementation. The turbo component, comprising the plurality of cross struts, enables high energy absorption capacity and no, or at least only a minimal, need for additional containment measures in the event of a bursting impeller. The cross struts are designed to be less rigid in the axial direction and are therefore particularly suitable for absorbing axial forces in the event of a bursting impeller. Thus, the cross struts described herein have a particularly high energy absorption capacity, making additional containment measures unnecessary.Turbo components known from the prior art with differently designed struts (particularly longitudinal struts) are significantly stiffer in the axial direction and thus have a lower energy absorption capacity, requiring additional containment measures, which leads to a larger construction volume and / or more time- and cost-intensive production. Axial forces can be absorbed by bending the transverse struts, whereas stiffer longitudinal struts are less suitable for this purpose. When using stiffer struts, energy absorption can be achieved via a screw connection (e.g., a bolted connection). a screw connection between a wall insert and an outer housing of the turbo component), which can break more easily. Furthermore, the turbo components described herein allow for flow restrictions to be kept to a minimum, for example, if the second housing wall section at least partially defines a flow channel.

[0018] In one embodiment, the ratio of the length of the cross strut perpendicular to the rotor axis to the thickness of the cross strut along the rotor axis is greater than 2. Preferably, the ratio can be greater than 3, greater than 4, or even greater than 5. If the length or thickness of the cross strut is not uniform across its length or thickness, the maximum length or thickness is used for the determination. A larger ratio between the length and thickness of the cross strut enables a less rigid design of the cross strut in the axial direction, thereby achieving greater energy absorption capacity in the event of a burst impeller.

[0019] In one embodiment, the ratio of the arc length of the cross strut to the thickness of the cross strut is greater than 3, and preferably greater than 4. The arc length is determined at a mean length of the cross strut, i.e., at half the length of the cross strut. A larger ratio between the arc length and the thickness of the cross strut allows for a less rigid design of the cross strut in the axial direction, thereby achieving greater energy absorption capacity in the event of a burst impeller.

[0020] The plurality of cross struts are preferably arranged spaced apart from one another in the circumferential direction. For example, the turbo component can have three cross struts. The cross struts can be evenly distributed (ie, with three cross struts, adjacent cross struts form an angle of 120°) or unevenly distributed over the circumference. However, the turbo component can have any number of cross struts other than three. number of cross braces, such as four or five cross braces.

[0021] In one embodiment, a radially inner end of each cross strut of the plurality of cross struts is connected to the second housing wall section. The cross struts can end radially inward on the second housing wall section. Flow restrictions can advantageously be minimized if the cross struts do not extend radially further inward than the second housing wall section. For example, if a flow channel (such as a recirculation channel) is provided radially inward from the second housing wall section, the cross struts do not protrude into this flow channel and create fewer flow restrictions in the flow channel. Furthermore, a radially outer end of each cross strut of the plurality of cross struts can be connected to the first housing wall section. The cross struts can end radially outward on the first housing wall section.

[0022] The first and second housing wall sections can together define a channel or a cavity. The cavity can be axially extended and be completely or substantially completely continuous in the circumferential direction. The cross struts can bridge the cavity between the first and second housing wall sections at the first end section. Preferably, the channel or cavity is provided as a hollow space and not as a flow channel.

[0023] According to this disclosure, embodiments are provided in which the first housing wall section defines the volute, as well as embodiments in which the volute has a plurality of volute sections and the volute is defined by a plurality of housing wall components.

[0024] In one embodiment, the first housing wall section defines the spiral housing. The spiral housing has the first spiral casing section. In this embodiment, the spiral casing is preferably completely or substantially completely defined by the spiral casing. The first casing wall section can define the outer contour of the casing of the turbo component. The first casing wall section can be detachably connectable to a bearing housing of the turbomachine.

[0025] The first and second housing wall sections can be formed integrally with one another. The first and second housing wall sections can be materially connected to one another via a connecting section. The connecting section is preferably arranged at the second end section. The connecting section is provided in addition to the cross struts. The connecting section can extend in the circumferential direction over a majority or even over the entire circumference of the second housing wall section. Typically, the connecting section is designed to be rather rigid and / or is only suitable to a limited extent for absorbing axial forces in the event of a bursting impeller, which can cause the turbo component to break at the connecting section. Advantageously, the cross struts are designed to be less rigid and can absorb the axial force in this case.Integral can mean that the component was initially manufactured as a single piece, or that it is a component made up of components that are joined together in a material-to-material manner.

[0026] In a further embodiment, the turbo component has an outer housing. The outer housing has a second spiral housing section. The first spiral housing section, together with the second spiral housing section, defines the spiral housing. The turbo component further has a wall insert, which comprises the first housing wall section and the second housing wall section. The first housing wall section is preferably an outer wall of the wall insert.

[0027] The wall insert is arranged (radially viewed) at least partially within the outer housing and detachably fastened to the outer housing. For example, the first housing wall section and the outer housing can each have a flange section. The wall insert can be detachably connected to the outer housing by means of fastening means that detachably connect the two flange sections to one another. The wall insert, and in particular the first housing wall section, can at least partially adjoin or bear against the outer housing (radially viewed) at its first axial end section.

[0028] The outer casing is preferably axially extended and completely or substantially completely continuous or continuous in the circumferential direction. The outer casing may be substantially cylindrical at its first axial end portion. If the turbo component is a compressor, the outer casing may be substantially cylindrical at the upstream end portion. If the turbo component is a radial turbine, the outer casing may be substantially cylindrical at the downstream end portion.

[0029] The first and second housing wall sections can be formed integrally with one another. Preferably, the wall insert is an integrally formed component. The first and second housing wall sections can be materially connected to one another via a connecting section. The connecting section is preferably arranged at the second end section. The connecting section is provided in addition to the cross struts. The connecting section can extend in the circumferential direction over a majority or even over the entire circumference of the second housing wall section. Typically, the connecting section is rather rigid and / or is only limitedly suitable for absorbing axial forces in the event of a bursting impeller, which can cause the turbo component to fracture at the connecting section. Advantageously, the cross struts are less stiff and can absorb the axial force in this case.

[0030] Furthermore, the turbo component can have additional housing parts, such as a radially outwardly arranged second outer housing, which is detachably connected to the (first) outer housing. The second outer housing can be connectable to the bearing housing of the turbomachine or connectable to a muffler and / or an intake manifold of the turbomachine.

[0031] According to one embodiment, the second housing wall section delimits a flow channel for the impeller. In this embodiment, the second housing wall section can be regarded as the inner wall of the housing of the turbo component. The second housing wall section can define an inner wall of the wall insert. This embodiment is particularly advantageous when the turbo component is a radial turbine. The first and second housing wall sections can together define the cavity. The cavity can define a flow channel. If the turbo component is a radial turbine, the cavity is typically not provided as a flow channel.

[0032] According to another embodiment, the turbo component has a third housing wall section. The third housing wall section defines a flow channel for the impeller. In this embodiment, the third housing wall section can be considered the inner wall of the housing of the turbo component. The third housing wall section can define an inner wall of the wall insert. The second housing wall section can be considered an intermediate wall in this embodiment.

[0033] The third housing wall section can be axially extended and completely or substantially completely continuous in the circumferential direction or be continuous. The third housing wall section can be substantially cylindrical at a first axial end section. If the turbo component is a compressor, the third housing wall section can be substantially cylindrical at the upstream end section. If the turbo component is a radial turbine, the third housing wall section can be substantially cylindrical at the downstream end section.

[0034] The third housing wall section is (seen radially) arranged at least partially within the second housing wall section.

[0035] The first and third and / or the second and third housing wall sections can be formed integrally with one another. Preferably, the wall insert is an integrally formed component comprising the first, second and third housing wall sections. The third housing wall section can be materially connected to the first and / or second housing wall section via the connecting section. Alternatively, the third housing wall section can be materially connected to the second housing wall section via a second connecting section. The connecting section and / or the second connecting section is preferably arranged at the second end section. The second connecting section can extend in the circumferential direction over a majority or even over the entire circumference of the second housing wall section.

[0036] The third housing wall section and the second housing wall section are preferably arranged radially spaced from one another at their first axial end section and / or are not adjacent or abutting one another at their first axial end section. The second housing wall section and the third housing wall section can define a channel. The channel can be a flow channel. In one embodiment, the second housing wall section and the third housing wall section define a recirculation channel. This embodiment is particularly advantageous when the turbo component is a compressor. Preferably, the radially inner end of each cross strut of the plurality of cross struts is connected to the second housing wall section. The cross struts can thus end radially inward on the second housing wall section. In other words, the second housing wall section is preferably not connected to the third housing wall section via cross struts. Advantageously, in this case, the cross struts do not protrude into the flow channel, in particular the recirculation channel, and thus create fewer or no flow restrictions in the flow channel. Furthermore, by providing the second and third housing wall sections, a width (length perpendicular to the rotor axis) of the recirculation channel can be arbitrarily determined.In particular, this enables a narrow recirculation channel and thus a slimmer design.

[0037] In one embodiment, the third housing wall section has at least one, preferably two, recirculation opening(s). The at least one recirculation opening can be an inlet opening and / or an outlet opening. The recirculation opening can be formed as a slot extending in the circumferential direction. The slot can have various cross-sections. For example, the slot can have a rectangular cross-section or a conically tapered cross-section. The outlet opening can be arranged upstream of the inlet opening.

[0038] In another embodiment, the second housing wall section defines the flow channel for the impeller. In this embodiment, the second housing wall section can have at least one recirculation opening.

[0039] According to one embodiment, the turbo component further comprises a plurality of ribs arranged between the second and third housing wall sections. The ribs are provided in addition to the cross struts. The ribs can be part of the wall insert. The ribs can divide the recirculation channel into a plurality of axially extending channel sections. Two adjacent ribs can each define a channel section, in particular together with the inlet opening and the outlet opening.

[0040] The ribs can be formed integrally with the second and third housing wall sections. In particular, the ribs can be formed integrally with the wall insert. Preferably, the ribs are not cross struts. Typically, the ribs are narrow in the circumferential direction and axially extended. The ribs can have a length perpendicular to the rotor axis that is less than a thickness along the rotor axis. The ribs can each extend along the rotor axis over a majority of the axial extent of the first housing wall section, in particular of the wall insert. Preferably, the ribs each extend along the rotor axis over at least 80% of the axial extent of the first housing wall section, in particular of the wall insert.

[0041] A narrow circumferential configuration of the ribs advantageously reduces flow restrictions in the flow channel. For example, the turbo component can have eleven ribs, but any number of ribs other than eleven is also possible. The ribs can be distributed over the circumference of the third housing wall section, for example, evenly spaced from one another in the circumferential direction. A radially inner end of each of the plurality of ribs can be connected to the third housing wall section; a radially outer end of each of the plurality of ribs can be connected to the second housing wall section.

[0042] In one embodiment, the ribs are longitudinal struts. The longitudinal struts can extend substantially along the rotor axis. The longitudinal struts can have a length perpendicular to the rotor axis that is at least as long as a length of the third housing wall section perpendicular to the rotor axis. Preferably, the ribs, in particular the longitudinal struts, each connect the second housing wall section to the third housing wall section. The ribs can connect the second housing wall section to the third housing wall section over their entire axial length. The ribs result in a particularly stable connection between the second and third housing wall sections, so that in the event of the impeller bursting, a break in the connection between the second and third housing wall sections is not to be expected.The ribs can also have a shape that differs from the shape of longitudinal struts, as long as the flow channel, especially the recirculation channel, is not blocked in the axial direction and the flow restrictions in the flow channel are as minimal as possible. For example, the ribs can be slightly inclined.

[0043] The plurality of ribs are preferably designed to be stiffer in the axial direction than the plurality of cross struts. The plurality of ribs typically have a low energy absorption capacity in the axial direction. In the event of an impeller burst, the connecting section, which can connect the first and second casing wall sections, can break. The plurality of cross struts can be designed to absorb an axial force in the event of an impeller burst. The plurality of cross struts thus enables containment of the turbo component in the event of an impeller burst, without the need for further precautions for the burst protection concept (containment concept).

[0044] According to one embodiment, the turbo component is a compressor. The impeller is a compressor wheel. The optional outer casing is an outer compressor casing. The first end portion of the The first end section of the housing components described herein is an upstream end section. The second end section of the housing components described herein is a downstream end section. The cross struts are arranged at the upstream end section of the first housing wall section, in particular the wall insert. The first housing wall section and the second housing wall section can be spaced apart from each other at least at the upstream end section.

[0045] In this embodiment, the first housing wall section can completely define the spiral casing, or the spiral casing has a plurality of spiral casing sections and the spiral casing is defined by a plurality of housing wall components, preferably by the first housing wall section and the outer compressor casing. Preferably, the compressor has the third housing wall section, which together with a hub of the compressor wheel can delimit the flow channel for the impeller. The first and the second housing wall section can define the cavity, which is designed as a hollow space and is preferably not a flow channel. The second and the third housing wall section can define the recirculation channel. Preferably, the compressor has the wall insert, which has the first, second housing wall section and optionally the third housing wall section. The wall insert can be formed integrally.The first housing wall section and the second housing wall section can be integrally connected to one another at the downstream end section via a connecting section. The outer compressor housing can also be detachably connected to a silencer and / or an intake manifold. The silencer and / or the intake manifold can delimit the recirculation channel and / or the cavity at the upstream end section.

[0046] According to a further embodiment, the turbo component is a radial turbine. The impeller is a turbine wheel. The optional outer casing is an outer turbine casing. The first end portion of the turbine component The first end portion of the housing components described herein is a downstream end portion. The second end portion of the housing components described herein is an upstream end portion. The cross struts are arranged at the downstream end portion of the first housing wall portion, in particular the wall insert. The first housing wall portion and the second housing wall portion can be spaced apart from each other at least at the downstream end portion.

[0047] In this embodiment, the first housing wall section can completely define the spiral casing, or the spiral casing has a plurality of spiral casing sections and the spiral casing is defined by a plurality of housing wall components, preferably by the first housing wall section and the outer turbine casing. Preferably, the second housing wall section, together with a hub of the turbine wheel, defines the flow channel for the turbine wheel. The first and second housing wall sections can define the cavity, which is configured as a hollow space and is preferably not a flow channel. Preferably, the radial turbine has the wall insert, which has the first and second housing wall sections. The wall insert can be integrally formed. The first housing wall section and the second housing wall section can be materially connected to one another at the upstream end section via a connecting section.

[0048] According to a further aspect of the invention, a turbomachine, in particular an exhaust gas turbocharger, is provided. The turbomachine comprises the turbo component according to one of the embodiments described herein. The turbo component can be a compressor, and the impeller can be a compressor wheel. Alternatively, the turbo component can be a radial turbine, and the impeller can be a turbine wheel. BRIEF DESCRIPTION OF THE CHARACTERS

[0049] The invention will be explained below with reference to exemplary embodiments illustrated in the figures, from which further advantages and modifications emerge. Herein: Figure 1 is a schematic view of a turbo component according to embodiments described herein; Figure 2 is a simplified schematic view of the turbo component shown in Figure 1; Figure 3 is a schematic sectional view of the turbo component from Figure 1; Figure 4 shows a further schematic sectional view of the turbo component from Figure 1; Figure 5 is a schematic sectional view of a turbo component according to another embodiment described herein; Figure 6 is another schematic sectional view of the turbo component shown in Figure 5; Figure 7 is a schematic view of the turbo component shown in Figures 5 and 6. DETAILED DESCRIPTION OF THE FIGURES

[0050] The following will now discuss in detail the various embodiments, one or more examples of which are shown in each figure. Each example is provided for illustrative purposes and is not intended to be limiting. For example, features shown or described as part of one embodiment may be used on or in conjunction with any other embodiment to obtain a further embodiment. The present disclosure is intended to encompass such modifications and variations.

[0051] In the following description of the drawings, the same reference numbers refer to the same or similar components. Generally, only the differences between the individual embodiments are described. Unless otherwise noted, the description of a part or aspect in one embodiment may also refer to a corresponding part or aspect in another embodiment.

[0052] With reference to Figures 1 to 4, various views of a turbo component 100 according to the present disclosure are described. The turbo component 100 is a compressor. Figure 1 shows a schematic view of the compressor. Figure 2 shows a simplified schematic view of the compressor shown in Figure 1, in which some of the components from Figure 1 are omitted for clarity. Figures 3 and 4 each show different schematic sectional views of the compressor from Figure 1.

[0053] According to one embodiment, which can be combined with other embodiments described herein, the compressor comprises a first housing wall section 143 and a second housing wall section 145. The first and second housing wall sections 143, 145 are connected to one another in the region of their upstream end sections by means of three cross struts 147. Furthermore, the first and second housing wall sections are integrally connected to one another via a connecting section at their downstream end sections. This is best seen in Figure 3. The second housing wall section 145 is arranged within the first housing wall section 143 and is radially spaced from the first housing wall section 143 in the region of the upstream end section. The first and second housing wall sections 143, 145 together define a cavity 149.

[0054] The compressor 100 has a wall insert 140 which first and second housing wall sections 143, 145. Furthermore, the wall insert 140 comprises a third housing wall section 141. The third housing wall section 141 is arranged within the second housing wall section 145 and is radially spaced from the second housing wall section 145 in the region of the upstream end section. The second and third housing wall sections 145, 141 are integrally connected to one another at their downstream end sections. Furthermore, the wall insert 140 has eleven longitudinal struts 148. The longitudinal struts 148 are axially extended and extend substantially over the entire length of the third housing wall section 141. The longitudinal struts 148 connect the second housing wall section 145 to the third housing wall section 141. The second and third housing wall sections 145, 141 together define a recirculation channel 146. The recirculation channel 146 is divided into eleven axially extended channel sections by the eleven longitudinal struts 148.Furthermore, the third housing wall section 141 has a recirculation opening 142 (best seen in Figure 3). The recirculation opening 142 is formed as a slot extending in the circumferential direction. The recirculation opening 142 shown in Figure 3 is an inlet opening.

[0055] The first housing wall section 143 defines a first scroll casing section 150. The compressor 100 further comprises an outer casing 110. The outer casing 110 comprises a second scroll casing section 111. The first and second scroll casing sections 150, 111 together define a scroll casing. The first Housing wall section 143, and in particular the wall insert 140, is arranged within the outer housing 110. The wall insert 140 is detachably connected to the outer housing 110. The wall insert 140 has a flange section 144, which is detachably secured to a flange section of the outer housing 110 by means of fastening means (for example, screws or bolts). Figure 2 shows the wall insert 140. The The outer casing 110 has been omitted for clarity. Figure 1 schematically shows the outer casing 110 and the detachable connection to the wall insert 140 by means of screws. Furthermore, the radial position of a shaft is indicated in Figure 1 by reference symbol 120. The compressor has a hub connected to the shaft. The compressor further has an impeller 130 connected to the hub.

[0056] With reference to Figures 5 to 7, various views of a turbo component 200 according to another embodiment of the present disclosure are described. The turbo component 200 is a compressor. Figures 5 and 6 each show different schematic sectional views of the compressor 200. Figure 7 shows a simplified schematic view of the compressor 200 shown in Figures 5 and 6. Figure 6 illustrates a section along line AA in Figure 7.

[0057] The compressor 200 is similar to the compressor 100 in many aspects. The differences are highlighted below.

[0058] The compressor 200 has a volute casing 253. The volute casing 253 is completely defined by the first casing wall section 243. The casing wall section 253 thus defines a first volute casing section 251 and a second volute casing section 252. The first casing wall section 243 forms an outer casing of the compressor 200. The first casing wall section 243 can be connectable to a muffler and / or an intake manifold of the turbomachine at its upstream end section (not shown in Figures 5-7). At a downstream end section, the first casing wall section 243 can be connectable to a bearing housing of the turbomachine (not shown in Figures 5-7).

[0059] In one embodiment, a ratio of the length h r the cross strut 247 perpendicular to the rotor axis RA and the thickness L A the cross brace 247 along the rotor axis RA greater than 2. Figure 6 illustrates the length h r and the thickness L Ä as well as the position of the rotor axis RA. Preferably, the ratio can be greater than 3, greater than 4, or even greater than 5.

[0060] In one embodiment, a ratio of an arc length L B the cross member and the thickness L A of the cross brace 247 greater than 3, and preferably greater than 4. Figure 7 illustrates the arc length L B . The arc length L B is carried out on a medium length h r / 2 of the cross brace 247, ie at half the length of the cross brace. Figure 7 illustrates the average length h r / 2 of the cross brace 247.

[0061] The compressor 200 has a hub 231 connected to a shaft. The compressor 200 further has an impeller 230 connected to the hub 231.

[0062] Furthermore, the first and second housing wall sections 243, 245 are integrally connected to each other via a connecting section 254 at their downstream end portion. This is best seen in Figure 5. LIST OF REFERENCE SYMBOLS 100, 200 turbo component 110 outer casing 150, 251 first spiral casing section 120 wave 130, 230 wheel 231 Hub 140 wall insert 141, 241 third housing wall section 142, 242 Recirculation opening 143, 243 first housing wall section 144 Flange section 145, 245 second housing wall section 146. 246 Recirculation channel 147. 247 Cross brace 148. 248 Longitudinal strut 149. 249 Cavity 111, 252 second spiral casing section 253 Spiral casing 254 Connecting section RA rotor axis

Claims

CLAIMS 1. Turbo component (100, 200) for a turbomachine, in particular for an exhaust gas turbocharger, comprising: an impeller (130, 230) mounted on a shaft (120), wherein the shaft (120) defines a rotor axis (RA); a first housing wall section (143, 243) defining a first spiral housing section (150, 251), a second housing wall section (145, 245) arranged at least partially within the first housing wall section (143, 243), and a plurality of cross struts (147, 247) extending substantially transversely to the rotor axis (RA) and each connecting the first housing wall section (143, 243) to the second Housing wall section (145, 245), wherein the cross strut has a length (hr) perpendicular to the rotor axis which is greater than a thickness (LA) along the rotor axis.

2. Turbo component (100, 200) according to claim 1, wherein a ratio of the length (hr) of the cross strut (147, 247) perpendicular to the rotor axis and the thickness (LA) of the cross strut (147, 247) along the rotor axis is greater than 2, preferably greater than 3.

3. Turbo component (100, 200) according to one of the preceding claims, wherein a ratio of an arc length (LB) of the cross strut (147, 247) and the thickness (LA) of the cross strut (147, 247) is greater than 3, preferably greater than 4.

4. Turbo component according to one of the preceding claims, wherein the first housing wall portion (243) defines a spiral casing (253) and is formed integrally with the second housing wall portion (245).

5. Turbo component according to one of claims 1 to 3, further comprising: a wall insert (140) comprising the first housing wall section (143) and the second housing wall section (145), and an outer housing (HO) comprising a second spiral housing section (111) which, together with the first spiral housing section (150) of the first housing wall section (143), defines a spiral housing; and wherein the wall insert (140) is at least partially disposed within the housing (110) and releasably secured to the housing (110).

6. Turbo component according to one of the preceding claims, wherein a radially inner end of each cross strut of the plurality of cross struts (147, 247) is connected to the second housing wall section (145, 245).

7. Turbo component according to one of the preceding claims, wherein the second housing wall section (145, 245) defines a flow channel for the impeller.

8. Turbo component according to one of claims 1 to 6, further comprising a third housing wall section (141, 241) which is arranged at least partially within the second housing wall section (145, 245) and delimits a flow channel for the impeller (130).

9. Turbo component according to claim 8, wherein the third housing wall section (141, 241) has a recirculation opening (142, 242); and in particular wherein the recirculation opening (142, 242) is formed as a circumferentially extending slot and / or wherein the at least one recirculation opening (142, 242) has an inlet opening or an outlet opening.

10. Turbo component (100, 200) according to one of claims 8 to 9, wherein the second housing wall section (145, 245) and the third housing wall section (141, 241) define a recirculation channel (146, 246).

11. Turbo component (100, 200) according to one of claims 8 to 10, further comprising a plurality of ribs arranged between the second and third housing wall sections, in particular wherein the ribs are longitudinal struts (148) which extend substantially along the rotor axis and each connect the second housing wall section to the third housing wall section.

12. Turbo component (100, 200) according to one of claims 8 to 11, wherein the plurality of ribs (148) are stiffer than the plurality of cross struts (147, 247).

13. Turbo component (100, 200) according to one of the preceding claims, wherein the plurality of cross struts (147, 247) are designed to absorb an axial force in the event of a bursting of the impeller (130).

14. Turbo component according to one of the preceding claims, wherein the turbo component is a compressor (100, 200) and the impeller (130) is a compressor wheel, and optionally wherein the outer casing (110) is a compressor casing.

15. Turbomachine, in particular an exhaust gas turbocharger, comprising the turbo component (100, 200) according to one of the preceding claims, in particular wherein the turbo component (100, 200) is a compressor and the impeller (130) is a compressor wheel.

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