Turbine housing comprising a turbine insert part

Abstract

The invention relates to a turbine-housing assembly (100) for a turbomachine, in particular a turbocharger. The turbine-housing assembly (100) comprises: a spiral casing (110) having at least one flow channel (111) for conducting a working fluid from an upstream flow-channel inlet (115) of the spiral casing (110) to a downstream turbine-chamber inlet (112); wherein the flow channel (111) joins, at a tongue region (113), a flow path (114) at the turbine-chamber inlet (112), which flow path lies radially inward with respect to the flow channel (111); and a turbine insert part (120) having a cross-section which decreases substantially in a flow direction (116); wherein the turbine insert part (120) is located in the tongue region (113). The invention also relates to a turbine insert part of this kind, to a turbomachine, and to a method for assembling a turbine-housing assembly (100) of this kind.

Description

Description TURBINE HOUSING WITH TURBINE INSERT TECHNICAL FIELD

[0001] The present disclosure relates to a turbine housing assembly for a turbomachine, in particular a turbocharger, preferably a radial turbocharger, a turbine insert, a turbomachine, in particular a turbocharger, preferably a radial turbocharger, having such a turbine housing assembly, and a method for assembling a turbine housing assembly. TECHNICAL BACKGROUND

[0002] Turbomachinery, especially turbochargers, is used, for example, to increase the performance and / or efficiency of internal combustion engines. Some engines incorporate a turbine. The turbine converts energy from a working fluid into kinetic energy. The working fluid is typically at high temperatures and thus heats components of the turbomachinery, especially turbine components. The heated components are subjected to high thermal stress.

[0003] Turbomachinery startups and shutdowns, especially in large numbers, can lead to thermomechanical fatigue phenomena in components, typically resulting in cracks. These cracks can lead to bursting in turbomachinery.

[0004] Certain components and / or component parts can be more susceptible to thermomechanical fatigue phenomena. For example, a volute casing of a turbine housing assembly can be affected. Volute casings are usually cast components that typically have at least one flow channel, also called a "volute" or "volute," which crosses itself in at least one section. This section is also called the "tongue region." The tongue region is often characterized by large differences in wall thickness. The region subject to high thermal stress in the tongue region is also referred to as the "tongue." BRIEF DESCRIPTION OF THE INVENTION

[0005] Aspects and advantages of the disclosure will be set forth in part in the description which follows, or may be obvious from the description itself, or may be learned by practice of the present disclosure.

[0006] The present disclosure provides a turbine housing assembly for a turbomachine, in particular a turbocharger, as well as a turbine insert, a turbomachine, in particular a turbocharger, with such a turbine housing assembly and a method for assembling a turbine housing assembly, which prevent cracks in the tongue area due to thermomechanical fatigue phenomena.

[0007] According to one aspect of the present disclosure, a turbine housing assembly for a turbomachine, in particular for a turbocharger, preferably for a radial turbocharger, is provided. The turbine housing assembly comprises a spiral casing with at least one flow channel for conducting a working fluid from an upstream flow channel inlet of the spiral casing to a downstream turbine chamber inlet, wherein the flow channel meets, at a tongue region, a flow path at the turbine chamber inlet that is radially inward relative to the flow channel. The turbine housing assembly further comprises a turbine insert part with a cross-section that decreases in a flow direction, wherein the turbine insert part is arranged in the tongue region.

[0008] In another aspect of the present disclosure, a turbine insert having a cross-section decreasing in a flow direction is provided for use in a turbine housing assembly according to embodiments of the present disclosure.

[0009] According to a further aspect of the present disclosure, a turbomachine, in particular a turbocharger, preferably a radial turbocharger, is provided with a turbine housing assembly according to embodiments of the present disclosure.

[0010] In a further aspect of the present disclosure, a method for assembling a turbine housing assembly for a turbomachine, in particular for a turbocharger, is provided. The method comprises assembling a Spiral casing with at least one flow channel for conducting a working fluid from an upstream flow channel inlet of the spiral casing to a downstream turbine chamber inlet, on a bearing housing assembly, wherein the flow channel meets in a tongue region with a flow path at the turbine chamber inlet, which flow path is radially inward with respect to the flow channel, and mounting a turbine insert part with a cross-section decreasing in a flow direction in the tongue region.

[0011] The details of one or more aspects of the disclosure are set forth in the accompanying figures and the following description. Other features, objects, and advantages of the principles described in this disclosure will be apparent from the description and drawings, as well as from the claims. BRIEF DESCRIPTION OF THE CHARACTERS

[0012] The invention is explained in more detail below using embodiments, without these being intended to limit the scope of protection defined by the claims.

[0013] The accompanying drawings illustrate embodiments and, together with the description, serve to explain the principles of the invention. The elements of the drawings are relative to one another and are not necessarily to scale. Like reference numerals designate similar parts.

[0014] Fig. 1 schematically shows a turbomachine according to embodiments of the present disclosure.

[0015] Fig. 2 shows schematically a prior art turbine housing assembly sectioned along the plane AA.

[0016] Fig. 3 schematically shows in a perspective view a turbine housing assembly according to embodiments of the present disclosure.

[0017] Fig. 4 schematically shows a section of a turbine housing assembly cut at surface AA according to embodiments of the present disclosure.

[0018] Fig. 5 schematically shows a sectional view of a turbine housing assembly according to embodiments of the present disclosure with a groove in a volute casing.

[0019] Fig. 6 schematically shows a sectional view of a turbine housing assembly according to embodiments of the present disclosure with a groove in a housing part.

[0020] Fig. 7 schematically shows a sectional view of a turbine housing assembly according to embodiments of the present disclosure with a groove in a volute and a housing part.

[0021] Fig. 8 schematically shows a perspective view of turbine inserts according to embodiments of the present disclosure. DETAILED DESCRIPTION

[0022] The principles described in this disclosure relate to a crack-preventing design of a turbine housing assembly. This is achieved at least in part by designing a tongue region such that less pronounced wall thickness changes are provided. For this purpose, a turbine insert is arranged in this region. The turbine insert can, for example, be easily and cost-effectively replaced during maintenance. The turbine insert can be less susceptible to thermomechanical fatigue phenomena. In some embodiments, the turbine insert can be used to secure another housing part, in particular a nozzle ring, against rotation. Such embodiments can save costs during assembly and / or maintenance of the turbomachine.

[0023] Embodiments of the present disclosure may be particularly suitable for use in turbomachinery in industrial applications, in particular for turbochargers, preferably radial turbochargers, for industrial applications. Embodiments of the present disclosure may be suitable, for example, for use in power generation, large work machines, rail vehicles, the marine industry, and / or the like.

[0024] This disclosure describes a turbine housing assembly for a turbomachine, in particular for a turbocharger, preferably for a radial turbocharger. In this context, "turbine housing assembly" may refer to an assembly and / or an integrally manufactured component, wherein the turbine housing assembly is substantially stationary during operation of the turbomachine. The turbine housing assembly is arranged at least partially around a rotor. The rotor rotates during operation of the turbomachine.

[0025] The turbine housing assembly comprises a volute casing. The volute casing has at least one flow channel. In some embodiments, the volute casing may have two or more flow channels. The flow channel guides a working fluid from an upstream flow channel inlet of the volute casing to a downstream turbine chamber inlet. The working fluid may, for example, be exhaust gas from an internal combustion engine. The volute casing typically guides the working fluid in a spiral shape to the turbine chamber inlet. Immediately downstream of the turbine chamber inlet, the working fluid may, for example, encounter a housing part, in particular a nozzle ring. A rotor configured to convert energy from the working fluid into rotational energy may be arranged in a turbine chamber. The rotor may, for example, be a turbine wheel, in particular a radial turbine wheel.The radial turbine wheel may be a turbine wheel with a flow path extending substantially radially. For example, the flow path may be inclined substantially by at least 45° to the rotation axis.

[0026] The flow channel meets a flow path at the turbine chamber inlet in a tongue region, which is located radially inward relative to the flow channel. "Radially inward" in this context can refer to a distance in the radial direction starting from a rotational axis of the rotor, i.e., transverse to the rotational axis. Spiral casings are typically characterized by a flow channel meeting itself at a point. For the purposes of this disclosure, the flow path can therefore originate from the flow channel and / or be considered a continuation of the flow channel. In particular, the spiral casing can divide the flow of the working fluid into several circumferentially and radially inwardly directed partial flows, with the flow channel and the flow path each being provided for one of these partial flows. The partial flows can be rejoined in the tongue region, more precisely at a tip of the tongue.

[0027] The turbine housing assembly further comprises a turbine insert. The turbine insert has a cross-section that substantially decreases in the direction of flow. "Substantially decreasing cross-section" in this context means that the turbine insert, for example a base body of the Turbine insert part, can have a larger cross-section on the upstream side than on the downstream side. The base body can be configured to guide the working fluid in the flow direction. In some embodiments, the cross-section of the turbine insert part decreases monotonically in the flow direction. According to some embodiments, the cross-section of the turbine insert part decreases strictly monotonically in the flow direction.

[0028] The flow direction can be curved, for example, particularly within the spiral casing. The turbine insert part is arranged in the tongue region. The turbine insert part can form a tongue. The turbine insert part can at least partially separate the flow channel from the flow path, for example, in the radial direction. The turbine insert part according to the present disclosure is therefore arranged in the tongue region, around which, due to the spiral-shaped flow channel and / or flow path, essentially tapered walls are usually provided. The geometries of the spiral casing in the tongue region can be very complex. The spiral casing regularly has uneven wall thicknesses around the tongue region.

[0029] The turbine insert can, for example, be welded, soldered, screwed, and / or pressed to the spiral casing and / or another component of the turbine casing assembly. Preferably, the turbine insert is detachably and non-destructively attached to the turbine casing assembly.

[0030] In some embodiments, the turbine insert part can have at least one fastening element. The fastening element can be designed to fasten the turbine insert part to the spiral casing and / or other components of the turbine housing assembly. The fastening element can, for example, have a snap mechanism. The snap mechanism can, for example, comprise elastic deformation of the fastening element. The snap mechanism can comprise clipping. The snap mechanism can comprise an opening and a clip-in tab for clipping into the opening. The opening can be provided in the turbine housing assembly (e.g., in the spiral casing and / or in the housing part) and the clip-in tab on the turbine insert part, or vice versa. The opening can, for example, be a groove. Such embodiments enable simplified assembly and more cost-effective production with little play in the turbine insert part.

[0031] According to some embodiments, the turbine insert part can have at least two fastening elements offset in the axial direction and / or at least two fastening elements offset in the flow direction. The at least two fastening elements can be spaced apart such that a resonant frequency of the turbine insert part and / or one or more fastening elements lies outside frequency ranges that can occur during operation of the turbomachine.

[0032] In some embodiments, the turbine insert part can have at least two fastening elements, wherein a first fastening element can have a smaller radial distance from the rotational axis of the turbomachine than a second fastening element. In particular, the first fastening element can be arranged, for example, on the compressor side. The term "compressor side" refers, for example, to a compressor side of a turbomachine with a compressor. In contrast, the term "turbine side" refers, for example, to a turbine side of the turbomachine. Alternatively, the compressor side can also be referred to, for example, as the root side, referring, for example, to the root side of the rotor, the compressor side, and / or the cold side. In the course of this disclosure, the term "compressor side" is also used for turbomachines without a compressor to simplify the description.Alternatively, the turbine side may also be referred to, for example, as the nose side, referring to the nose side of the rotor, and / or the hot side. Descriptions of the sides of a component within this disclosure may be described as relative side designations with respect to the component itself in its installed position.

[0033] According to some embodiments, the turbine insert part can have at least one fastening element exclusively on one side, in particular on the turbine side. Such embodiments enable simplified assembly of the turbine insert part and / or reduced production costs and / or assembly costs for the turbine housing assembly.

[0034] In some embodiments, the turbine housing assembly may include at least one groove, wherein the groove may be configured to receive the fastener of the turbine insert. For example, the turbine housing assembly may include at least two grooves, wherein the grooves may be configured to individually or collectively receive the one or more fasteners.

[0035] The at least one groove may be configured to receive the fastener with the snap mechanism.

[0036] According to some embodiments, the groove can be arranged at least partially in the spiral casing. In some embodiments, the groove can be arranged at least partially in a housing part. The housing part can be a nozzle ring. Such embodiments can be particularly advantageous because the turbine insert part can be used to secure the housing part against rotation. This eliminates the need for locking pins, as in the prior art, and in particular, complex and expensive assembly and disassembly can be avoided. Furthermore, stress peaks in the area of ​​the locking pins can be avoided.

[0037] The spiral casing and the casing part and / or the spiral casing together with the casing part can form and / or have one or more grooves.

[0038] The turbine insert may comprise steel. For example, the turbine insert may comprise a high-temperature material. In some embodiments, the turbine insert may comprise a nickel-based alloy and / or ceramic. The turbine insert may be substantially fatigue-resistant with respect to thermomechanical fatigue phenomena, such as cracking.

[0039] According to some embodiments, a turbine insert thermal expansion coefficient may be greater than a volute casing thermal expansion coefficient. In embodiments that include the casing part, the turbine insert thermal expansion coefficient may be greater than a casing part thermal expansion coefficient. Such embodiments enable at least partial sealing of possible manufacturing-related gaps in the tongue area.

[0040] In some embodiments, the turbine insert part can be manufactured via precision casting and / or sintering, in particular via additive manufacturing processes, e.g. selective laser melting or similar.

[0041] In particular, reference is made below to embodiments of the disclosure, some examples of which are illustrated in the figures. Each example is intended to illustrate the disclosure, not to limit it. For example, features illustrated or described as part of embodiments be used with other embodiments to yield further embodiments.

[0042] Fig. 1 schematically shows a turbomachine according to embodiments of the present disclosure. The turbomachine in Fig. 1 is embodied, by way of example, as a radial turbocharger. However, the turbomachine can also be embodied as a turbine, in particular as a radial turbine or similar.

[0043] The turbomachine has a turbine 10 on a turbine side 12. The turbine 10 comprises a turbine housing assembly 100. The turbine housing assembly 100 can, for example, be mounted on a bearing housing assembly 200. The turbine housing assembly 100 encloses a rotor 101. The rotor 101 has turbine blades 102. The rotor 101 rotates about a rotational axis 11. The turbine housing group 100 comprises a spiral casing 110 with at least one flow channel 111. The flow channel 111 conducts a working fluid, in the example of the radial turbocharger, typically an exhaust gas from an internal combustion engine, from an upstream flow channel inlet 115 of the spiral casing 110 to a downstream turbine chamber inlet 112. There, energy can be extracted from the working fluid, which can be converted into mechanical rotational energy.For example, a compressor 300 on a compressor side 13, in particular a compressor wheel 301, can be driven. In some embodiments, a generator can be driven by the turbine 10.

[0044] The turbine housing assembly 100 may be integral or formed from more than one component.

[0045] Fig. 2 schematically shows a prior art turbine housing assembly 100, sectioned along area AA of Fig. 1. The turbine housing assembly 100 comprises a spiral casing 110. Furthermore, a rotor 101 and a housing part 140 are shown. The housing part 140 is designed as a nozzle ring. The spiral casing 110 comprises a flow channel 111. The spiral casing 110 can have at least two flow channels 111. The flow channel 111 is configured to conduct a working fluid from an upstream flow channel inlet 115 of the spiral casing 110 to a downstream turbine chamber inlet 112. At the turbine chamber inlet 112, the working fluid can, for example, first encounter the nozzle ring.

[0046] From the turbine chamber inlet 112 onward, the flow channel 111 may be referred to as flow path 114 throughout the present disclosure. This serves to simplify explanation. However, as can also be seen from Fig. 2, the flow channel 111 meets itself at the turbine chamber inlet 112, particularly at a tongue region 113, due to the spiral shape of the spiral casing 110. However, the term flow path 114 will be used below for ease of explanation.

[0047] As shown in Fig. 2, the spiral casing 110 has uneven wall thicknesses in the tongue area 113. The uneven wall thicknesses can lead to increased stresses in the spiral casing 110, particularly during start-up or shutdown of the turbomachine. In particular, thin wall thicknesses can lead to more rapid heating of the material, and thus to expansion, than is the case with thicker walls. If the wall thickness increases or decreases significantly within a short distance, this leads to increased stresses. The increased stresses can lead to thermomechanical fatigue phenomena, particularly cracks in the spiral casing 110, particularly during numerous temperature changes.

[0048] Fig. 3 schematically shows a perspective view of a turbine housing assembly 100 according to embodiments of the present disclosure. The turbine housing assembly 100 comprises a spiral casing 110. The spiral casing 110 has a flow channel 111. The flow channel 111 is configured to conduct a working fluid. The working fluid is conducted from the spiral casing 110 from an upstream flow channel inlet 115 (not shown in Fig. 3) via a turbine insert part 120 to a downstream turbine chamber inlet 112. In a tongue region 113, the flow channel 111 meets a flow path 114 located radially inward with respect to the flow channel 111. The turbine insert part 120 has a cross-section that decreases substantially in a flow direction 116.

[0049] The turbine insert part 120 is arranged in the tongue region 113. Thus, the turbine insert part 120 forms a tongue. The tongue partially separates the flow channel 111 from the flow path 114.

[0050] Fig. 4 schematically shows a section of a turbine housing assembly 100 cut along surface AA according to embodiments of the present disclosure.

[0051] The turbine housing assembly 100 in Fig. 4 is similar to the turbine housing assembly 100 shown in Fig. 3. It comprises a spiral casing 110 with two flow channels 111 (hereinafter, reference is made to one of the two flow channels). It further comprises a casing part 140. The casing part 140 is designed as a nozzle ring. The casing part 140 can also be a spiral casing half or the like.

[0052] At a tongue region 113, the flow channel 111 meets a flow path 114. The flow path 114 can emerge at least partially from the flow channel 111. As shown in Fig. 4, a turbine insert part 120 is arranged in the tongue region 113. The turbine insert part 120 has a cross-section that essentially decreases in a flow direction 116. In particular, the turbine insert part 120 can taper essentially to a point downstream in the flow direction 116. In this way, the efficiency of the turbine 10 can be increased.

[0053] The turbine insert part 120 has a fastening element 121. The fastening element 121 has a snap mechanism. As can be seen in Fig. 4, the turbine insert part 120 has, for example, a recess 123. The fastening element 121 can be elastically deformable, for example, in the direction of the recess 123.

[0054] The turbine housing assembly 100 further includes a groove 130. The groove 130 is configured to receive the fastener 121. The groove 130 is disposed in the volute casing 110.

[0055] Fig. 5 schematically shows a sectional view of a turbine housing assembly 100 according to embodiments of the present disclosure with a groove 130 in a spiral casing 110. A turbine insert part 120 with a fastening element 121, in particular with a first, turbine-side, fastening element 121A and a second, compressor-side, fastening element 121B, is shown in section. The first fastening element 121A is received in a first, turbine-side, groove 130A. The second fastening element 121B is received in a second, compressor-side, groove 130B. The first groove 130A and the second groove 130B are each arranged in the spiral casing 110. The first fastening element 121A has a greater distance in the radial direction from a rotation axis 11 than the second fastening element 121B.

[0056] The spiral casing 110 has a groove 130A, 130B, which provides a stop for the fastening element 121A, 121B, at least in the circumferential direction. The spiral casing 110 has a groove 130A, 130B, which provides a radial stop for the fastening element 121A, 121B. The spiral casing 110 has a groove 130A, 130B, which provides an axial stop for the fastening element 121A, 121B. A radially inner surface of the fastening element 121A, 121B can abut a housing part 140. In some embodiments, the groove 130A, 130B can completely accommodate the fastening element 121A, 121B.

[0057] A first turbine-side contact surface 117A of the volute casing 110 and / or a second compressor-side contact surface 117B of the volute casing 110 can be configured to abut the turbine insert 120 in such a way that substantially no working fluid can flow past the turbine-side side surfaces and / or the compressor-side side surfaces of the turbine insert 120. For this purpose, for example, machining of the first contact surface 117A and / or the second contact surface 117B can be provided.

[0058] In some embodiments, the turbine insert 120 may have a turbine insert thermal expansion coefficient, wherein the turbine insert thermal expansion coefficient is greater than a volute casing thermal expansion coefficient of the volute casing 110. In this way, a seal, for example as described in the above paragraph, can be achieved even more effectively; in particular, the seal can be achieved shortly after the turbomachine is started. Alternatively or additionally, an improved mounting of the turbine insert 120 in the turbine casing assembly 100 can be achieved in this way.

[0059] The turbine insert part 120 can preferably be manufactured via precision casting and / or sintering, in particular via additive manufacturing. In some embodiments, the turbine insert part 120 can be at least partially mechanically reworked. In this way, the seal on the turbine-side side surfaces and / or compressor-side side surfaces of the turbine insert part 120 and / or other surfaces of the turbine insert part, and / or the mounting of the turbine insert part 120 in the turbine housing assembly 100, can be improved.

[0060] Fig. 6 schematically shows a sectional view of a turbine housing assembly 100 according to embodiments of the present disclosure with a groove 130 in a housing part 140, in particular in a nozzle ring.

[0061] The embodiment shown in Fig. 6 differs from the embodiment shown in Fig. 5 essentially in that a groove 130 is arranged in a housing part 140. In the illustrated embodiment, the housing part 140 is a nozzle ring. A turbine insert part 120 has a fastening element 121. The fastening element 121 is arranged on the turbine side of the turbine insert part 120. On the compressor side, the turbine insert part 120 rests against a compressor-side contact surface 117B of the spiral casing 110.

[0062] The housing part 140 has a groove 130, at least in the circumferential direction, as a stop for the fastening element 121. The housing part 140 has a groove 130, a radial stop for the fastening element 121. The housing part 140 has a groove 130, an axial stop for the fastening element 121. A radially outer surface of the fastening element 121 can bear against the spiral casing 110. In some embodiments, the groove 130 can completely accommodate the fastening element 121.

[0063] Typically, at least one positioning means is provided on the turbine housing assembly 100 for orienting a housing part 140, in particular a nozzle ring, relative to other components of the turbine housing assembly 100, for example, the spiral casing 110, in the circumferential direction. A turbine insert part 120 with a fastening element 121 for receiving by a groove 130, which is at least partially arranged in the housing part 140 or at least partially formed by the housing part 140, can establish the orientation relative to the other components of the turbine housing group 100, for example, the spiral casing 110, in the circumferential direction. Thus, the positioning means can be omitted.

[0064] In some embodiments, the turbine insert part 120 may have a turbine insert part thermal expansion coefficient, wherein the turbine insert part thermal expansion coefficient is greater than a spiral casing thermal expansion coefficient of the spiral casing 110 and / or than a casing part thermal expansion coefficient of the casing part 140. In this way, a seal, for example as described above in connection with Fig. 5, can be achieved even more effectively. In particular, the seal can be reached shortly after the turbomachine has started up. In this way, an improved mounting of the turbine insert 120 in the turbine housing assembly 100 can be achieved, alternatively or additionally.

[0065] Fig. 7 schematically shows a sectional view of a turbine housing assembly 100 according to embodiments of the present disclosure with a groove 130 in a volute casing 110 and a housing part 140.

[0066] The embodiment shown in Fig. 7 differs from the embodiments shown in Fig. 5 and Fig. 6 essentially in that a first groove 130A is formed by a housing part 140 and a spiral casing 110. In the illustrated embodiment, the housing part 140 is a nozzle ring. A turbine insert part 120 has a first fastening element 121A. The fastening element 121A is arranged on the turbine side of the turbine insert part 120. The turbine insert part 120 has a second fastening element 121B. The fastening element 121B is arranged on the compressor side of the turbine insert part 120.

[0067] The second fastening element 121B is received in a second groove 130B. The second groove 130B is formed by the volute casing 110. In some embodiments, the second groove 130B may be formed by the casing part 140 or by the casing part 140 and the volute casing 110.

[0068] A rotation lock of the housing part 140 as described in connection with Fig. 6 is also achieved by the embodiment in Fig. 7.

[0069] Fig. 8 schematically shows a perspective view of turbine inserts 120 according to embodiments of the present disclosure.

[0070] The turbine insert part 120 may, for example, comprise steel. The turbine insert part 120 may, for example, comprise a nickel-based alloy. The turbine insert part 120 may, for example, comprise ceramic. The turbine insert part 120 may be designed to be substantially fatigue-resistant with respect to thermomechanical fatigue phenomena, such as cracks. The turbine insert part 120 may have a turbine insert thermal expansion coefficient that is greater than one or more thermal expansion coefficients of one or more components of a turbine housing assembly 100, in particular greater than one or more Thermal expansion coefficients of one or more components adjacent to the turbine insert 120.

[0071] The turbine insert part 120 can be manufactured, for example, via precision casting and / or sintering, in particular via additive manufacturing processes.

[0072] The turbine insert 120 has a cross-section that decreases in the flow direction 116. The cross-section can, for example, decrease monotonically or strictly monotonically in the flow direction 116. The cross-section can relate to a current-carrying base body 122 such that a fastening element 121 and / or design elements associated with the fastening element 121, such as a recess 123 for producing a snap mechanism or the like, are not taken into account in the decreasing cross-section.

[0073] The turbine insert part 120 in Fig. 4A has a first turbine-side fastening element 121A and a second compressor-side fastening element 121B. The first fastening element 121A has a smaller radial extension from the base body 122 than the second fastening element 121B.

[0074] The turbine insert part 120 further has a recess 123 for producing a snap mechanism.

[0075] The first fastening element 121A and / or the second fastening element 121B may be configured such that vibrations occurring during operation of the turbomachine substantially do not result in resonance of the fastening elements 121A, 121B.

[0076] The turbine insert part 120 in Fig. 4B has a first turbine-side fastening element 121A and a second compressor-side fastening element 121B. The first fastening element 121A has a smaller radial extension from the base body 122 than the second fastening element 121B.

[0077] The first fastening element 121A and / or the second fastening element 121B may be configured such that vibrations occurring during operation of the turbomachine substantially do not result in resonance of the fastening elements 121A, 121B.

[0078] The turbine insert part 120 in Fig. 4C has a turbine-side fastening element 121. The turbine insert part 120 further has a recess 123 for producing a snap mechanism.

[0079] The fastening element 121 may be configured such that vibrations occurring during operation of the turbomachine substantially do not result in resonance of the fastening element 121.

[0080] In connection with Fig. 1 to Fig. 8, a method for assembling a turbine housing assembly 100 for a turbomachine 10, in particular for a turbocharger, is described below.

[0081] A volute casing 110 having at least one flow channel 111 for conducting a working fluid from an upstream flow channel inlet 115 of the volute casing 110 to a downstream turbine chamber inlet 112 is mounted on a bearing housing assembly 200.

[0082] The flow channel 111 meets in a tongue region 113 with a flow path 114, which is located radially inward with respect to the flow channel 111, at the turbine chamber inlet 112.

[0083] A turbine insert part 120 with a cross-section decreasing in a flow direction 116 is arranged in the tongue region 113, for example via screwing, soldering and / or welding.

[0084] The turbine insert part 120 can be mounted using at least one fastening element 121. For this purpose, the fastening element 121 can, for example, be clipped and / or inserted in such a way that the fastening element 121 snaps into place.

[0085] The fastening element 121 can, for example, be arranged in at least one groove 130 of the turbine housing assembly 100. The groove 130 can, for example, be arranged at least partially in the spiral housing 110 and / or a housing part 140.

[0086] The housing part 140, in particular a nozzle ring, can be mounted on the bearing housing assembly 200, the turbine housing assembly 100, and / or the spiral casing 110, and the turbine insert part 120. For example, such that the housing part 140 at least partially forms the at least one groove 130, which receives and / or fixes the at least one fastening element 121 of the turbine insert part 120. In this way, an additional anti-rotation lock of the housing part 140 with respect to, for example, the spiral casing 110 is achieved.

[0087] In the above description, a turbine housing assembly for a turbomachine, in particular a turbocharger, preferably a radial turbocharger, a turbine insert, a turbomachine, in particular a turbocharger, preferably a radial turbocharger, with such a turbine housing assembly, and a method for assembling a turbine housing assembly were presented with reference to specific examples. It should be noted that various aspects and embodiments disclosed herein may be combined in combinations other than the specific combinations illustrated in the figures. It is understood that various modifications may be made to the aforementioned embodiments without departing from the scope of the disclosure and the following claims. LIST OF REFERENCE SYMBOLS 10 turbines 11 Rotation axis 12 Turbine side 13 Compressor side 100 Turbine housing assembly 101 Rotor 102 turbine blades 110 spiral casing 111 Flow channel 112 Turbine room entrance 113 Tongue area 114 Flow path 115 Flow channel inlet 116 Flow direction 117 contact surface 120 Turbine insert 121 Fastener 122 basic bodies 123 Recess 130 groove 140 Housing part 200 Bearing housing assembly 300 compressor 301 Compressor wheel

Claims

Claims 1.Turbine housing assembly (100) for a turbomachine, in particular a turbocharger, comprising: a spiral housing (110) with at least one flow channel (111) for conducting a working fluid from an upstream flow channel inlet (115) of the spiral housing (110) to a downstream turbine chamber inlet (112); wherein the flow channel (111) meets at a tongue region (113) with a flow path (114) at the turbine chamber inlet (112), which flow path is radially inward with respect to the flow channel (111); a turbine insert part (120) with a cross-section that decreases substantially in a flow direction (116); wherein the turbine insert part (120) is arranged in the tongue region (113); wherein the turbine insert part (120) has at least one fastening element (121); and wherein the turbine housing assembly has at least one groove (130), the groove (130) being configured to receive the fastening element (121) of the turbine insert part (120).

2. Turbine housing assembly (100) according to claim 1, wherein the fastening element (121) has a snap mechanism.

3. Turbine housing assembly (100) according to one of the preceding claims, wherein the groove (130) is at least partially arranged in the spiral casing (110).

4. Turbine housing assembly (100) according to one of the preceding claims, wherein the turbine housing further comprises a housing part (140), in particular a nozzle ring, and wherein the groove (130) is at least partially arranged in the housing part (140).

5. Turbine housing assembly (100) according to one of the preceding claims, wherein the turbine insert part (120) comprises steel, a nickel-based alloy and / or ceramic.

6. Turbine housing assembly (100) according to one of the preceding claims, wherein a turbine insert thermal expansion coefficient is greater than a volute casing thermal expansion coefficient and / or a casing part thermal expansion coefficient.

7. Turbine housing assembly (100) according to one of the preceding claims, wherein the turbine insert part (120) is manufactured via precision casting and / or sintering, in particular via additive manufacturing.

8. Turbine insert part (120) with a cross-section decreasing in a flow direction (116) for use in a turbine housing assembly (100) according to one of the preceding claims.

9. Turbomachine, in particular turbocharger, with a turbine housing assembly (100) according to one of the preceding claims 1 - 7.

10. A method for assembling a turbine housing assembly (100) for a turbomachine, in particular for a turbocharger, comprising: - Mounting a spiral casing (110) with at least one flow channel (111) for conducting a working fluid from a upstream flow channel inlet (115) of the spiral casing (110) to a downstream turbine chamber inlet (112), on a bearing housing assembly; wherein the flow channel (111) meets in a tongue region (113) with a flow path (114) at the turbine chamber inlet (112) which is radially inward with respect to the flow channel (111); and - Mounting a turbine insert part (120) with a cross-section decreasing in a flow direction (116) in the tongue region (113); wherein the turbine insert part (120) is mounted by means of at least one fastening element (121); and wherein the fastening element (121) is arranged in at least one groove (130) of the turbine housing group.

11. A method of assembling a turbine housing assembly (100) according to claim 10, wherein the fastening element (121) is inserted such that the fastening element (121) snaps into place.

12. A method of assembling a turbine housing assembly (100) according to any one of claims 10-11, wherein the groove (130) is at least partially disposed in the spiral casing (110).

13. A method of assembling a turbine housing assembly (100) according to any one of claims 10-12, the method further comprising: - Mounting a housing part (140), in particular a nozzle ring, on the bearing housing assembly, the turbine housing assembly (100), and / or the spiral casing (110), and the turbine insert part (120) such that the housing part (140) at least partially forms the at least one groove (130) which receives the at least one fastening element (121) of the turbine insert part (120).

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