Axial turbine for turbomachine, associated disassembly method and use
By improving the axial turbine design and utilizing the fastening devices and clamping sections of the nozzle ring and cover ring, the efficiency and vibration issues in the nozzle ring design are resolved, the disassembly and assembly process is simplified, and costs and time are reduced.
Patent Information
- Application Number
- CN202480032812.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2023-06-01
- Filing Date
- 2024-05-24
- Publication Date
- 2025-12-12
AI Technical Summary
The nozzle ring design of existing turbochargers results in poor efficiency and vibration characteristics, and the disassembly and assembly work is complicated, increasing costs and maintenance time.
The axial turbine design, through the fastening device of the lug and lug receiver between the nozzle ring and the cover ring, combined with the clamping section and fastening element, enables the detachable connection of the nozzle ring, allowing assembly and disassembly from the cold and hot sides, reducing threaded connections and production steps.
It simplifies the assembly and disassembly process of the nozzle ring, reduces production steps, lowers efficiency loss and blade vibration risk, and reduces maintenance costs and time.
Smart Images
Figure CN121127665A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present disclosure relates to an axial turbine for a turbomachine, a turbomachine and a method for dismounting a nozzle ring. BACKGROUND
[0002] To improve the performance of an internal combustion engine, exhaust gas turbochargers are now standard, which have a turbine on the exhaust gas side of the internal combustion engine and have a compressor upstream of the internal combustion engine. The exhaust gases of the internal combustion engine expand in the turbine, the work generated thereby being transmitted by a shaft to the compressor, which compresses the air supplied to the internal combustion engine. By using the energy of the exhaust gases to compress the air supplied to the combustion process of the internal combustion engine, the performance, the combustion process and the efficiency of the internal combustion engine can be improved.
[0003] The nozzle ring of a turbocharger axial turbine is usually fastened to the intake housing or the exhaust housing by a threaded connection. The threaded connection of the nozzle ring can be realized inside or outside the nozzle ring.
[0004] Alternatively, the nozzle ring can also be held in place by a clamping connection, for example between the intake housing and the exhaust housing. In this case, the dome of the intake housing is usually connected to the outer portion of the intake housing by a strut. It has now been found that the strut between the dome and the outer portion of the intake housing has a disadvantageous effect on the turbine efficiency and the vibration behavior of the turbine rotor blades in the flow channel.
[0005] The above-mentioned design variants result in a non-optimal structural design in terms of efficiency and vibration behavior and require considerable dismounting and assembly effort, ultimately resulting in an increase in costs and time required for maintenance. SUMMARY
[0006] It is an object of the present invention to provide an axial turbine which improves at least one of the disadvantages known from the prior art.
[0007] To achieve the above-mentioned object, an axial turbine for a turbomachine and a method for dismounting a nozzle ring are provided according to the independent claims. Further embodiments, modifications and improvements will become apparent from the following description and the appended claims.
[0008] According to one embodiment, an axial turbine for a turbine, particularly for an exhaust gas turbocharger, is provided. The axial turbine includes: a turbine housing; a turbine impeller disposed within the turbine housing and mounted on a shaft; and a nozzle ring disposed within the turbine housing and at least partially upstream of the turbine impeller, wherein the nozzle ring has an outer ring. Furthermore, the axial turbine includes: a cover ring disposed within the turbine housing and downstream of the nozzle ring; and a fastening device that axially detachably connects the outer ring to the cover ring from a radially outer side. The downstream end portion of the outer ring has a radially outwardly projecting nozzle ring lug, and the upstream end portion of the cover ring has a cover ring lug receiving portion. The nozzle ring lug engages in the cover ring lug receiving portion.
[0009] The axial and radial directions are defined by the shaft of the axial turbine. The fastening device connecting the outer ring to the cover ring "on the radially outer side" can be understood as: the fastening device is arranged in the radially outer region of the outer ring and / or the cover ring, specifically, the fastening device is arranged at the radial end of the outer ring and / or the cover ring, or in the radially outer end portion of the outer ring and / or the cover ring.
[0010] The term "axial" is preferably understood to mean that the fastening device extends substantially in the axial direction.
[0011] The “downstream end portion” includes the downstream end and a portion of the downstream end region, and the “upstream end portion” includes the upstream end and a portion of the upstream end region.
[0012] In this disclosure, "nozzle ring, which is at least partially arranged upstream of the turbine impeller" should be understood to mean that a portion of the nozzle ring may not be arranged upstream of the turbine impeller. However, "nozzle ring, which is at least partially arranged upstream of the turbine impeller" can also be understood to mean that the nozzle ring is completely arranged upstream of the turbine impeller.
[0013] Therefore, an axial turbine is advantageously provided, which improves assembly and disassembly, particularly during maintenance. Specifically, the embodiments of the axial turbine described herein reduce the time required for assembly and disassembly, which has a positive impact on cost. Another advantage is that the nozzle ring lug and cover ring lug receiving portion can be manufactured through simple turning and milling operations, making it advantageous to reduce the number of production steps compared to the prior art for the embodiments described herein. Furthermore, the embodiments described herein minimize threaded connections. Additionally, the embodiments described herein advantageously minimize potential efficiency losses and reduce the risk of turbine impeller blade vibration.
[0014] The turbine housing may have an inlet housing and an exhaust housing. The inlet housing may be detachably connected to the exhaust housing by means of fastening devices (e.g., threaded connections). The turbine impeller, nozzle ring, cover ring, and in particular the diffuser may be arranged within the turbine housing. The shaft may be arranged at least partially within the turbine housing. Preferably, the cover ring and / or the turbine diffuser are arranged within the exhaust housing.
[0015] The nozzle ring can be disposed within the exhaust housing. Typically, the nozzle ring is disposed within both the intake and exhaust housings. In addition to securing the nozzle ring to the cover ring, the nozzle ring can also be held in place by a clamping connection (e.g., through the intake housing) or by a clamping connection between the intake and exhaust housings.
[0016] The nozzle ring typically has multiple guide vanes formed within an outer ring. The nozzle ring may also have an inner ring, which can be formed within the guide vanes. The inner ring and guide vanes are preferably arranged upstream of the turbine impeller. The outer ring, guide vanes, and inner ring, and particularly the entire nozzle ring, can be integrally formed. For example, the outer ring, guide vanes, and inner ring can be bonded together, or they can be manufactured from a single piece.
[0017] The axial turbine, and particularly the inlet housing, may also have a dome. The dome may be disposed on the upstream end portion of the nozzle ring and / or in a region of the inlet housing. Typically, the dome is not fixed to the turbine housing. The dome is preferably not connected to struts or the like on the turbine housing. Therefore, the dome is preferably neither adhesively attached to the turbine housing nor threadedly attached to it. In a preferred embodiment, the dome is integrally formed with the nozzle ring, particularly with the inner ring of the nozzle ring. For example, the inner ring and the dome may be adhesively connected to each other, or they may be manufactured from a single piece. In an alternative embodiment, the dome is only fastened to the inner ring of the nozzle ring.
[0018] Omitting the connection between the dome and the turbine casing helps reduce potential efficiency losses and the risk of turbine impeller blade vibration. Furthermore, omitting the adhesive connection between the dome and the turbine casing—that is, omitting, for example, the struts—allows access to the “internal” components of the axial turbine from the turbine side, or in other words, access from the “hot” side. This possible access will be described in more detail below.
[0019] The cover ring can be disposed within the exhaust casing and can also be disposed in the region of the turbine impeller. The cover ring can surround at least a portion of the turbine impeller. The cover ring can radially outwardly surround a portion of the turbine impeller and radially outwardly define a flow path in the region of the impeller blades. Therefore, fluid (e.g., exhaust gas) can be prevented from bypassing the turbine impeller of the axial turbine, and in particular, the impeller blades of the turbine impeller. The cover ring is typically not directly fastened to the turbine casing.
[0020] In one embodiment, the axial turbine further includes a turbine diffuser disposed at least partially downstream of the turbine impeller. The turbine diffuser may be connected (e.g., via a threaded connection) to the turbine housing, particularly to the exhaust housing.
[0021] In one embodiment, the turbine diffuser is integrally formed with the cover ring. For example, the cover ring and the turbine diffuser can be glued together or manufactured from a single part. The turbine diffuser includes the cover ring at its upstream end portion and the diffuser portion at its downstream end. This embodiment allows for a simpler structural design with fewer connections.
[0022] In an alternative embodiment, the cover ring is detachably connected to the turbine diffuser. In this case, the downstream end portion of the cover ring is detachably fastened to the upstream end portion of the turbine diffuser. Preferably, the axial turbine has one or more (e.g., four or six) fastening elements connecting the turbine diffuser to the cover ring. The fastening elements preferably axially connect the outer ring to the cover ring on the radially outer side. At least one fastening element may be spaced apart from the fastening device (which detachably connects the outer ring and the cover ring) and optional clamping sections when viewed in the circumferential direction. The axial turbine can be designed to allow for insertion and / or release and removal of the fastening elements via turbine-side access (or from the hot side). This possible access is described in more detail below. This allows for removal or removal of the cover ring via turbine-side access.
[0023] For example, the fastening element may extend along the insertion opening or through hole of the cover ring. Furthermore, the fastening element may engage with threads in the turbine diffuser. The fastening element may be a pin (particularly a pin with internal threads), a bolt (particularly a bolt with internal threads), or a screw.
[0024] In one embodiment, the outer ring has a clamping section, wherein a fastening device extends through an insertion opening in the clamping section. Furthermore, the fastening device can engage with threads in the cover ring.
[0025] The outer ring of the nozzle ring has radially outwardly projecting nozzle ring lugs and optionally has a clamping section. Typically, the outer ring is integrally connected with the clamping section and the nozzle ring lugs.
[0026] The nozzle ring lug can be flattened perpendicular to the axial direction. The nozzle ring lug can also be in the form of a tongue. The axial extension of the nozzle ring lug can be significantly less than the radial extension and / or circumferential extension. The nozzle ring lug can be a radial protrusion extending from the radial end or a portion of the radial end of the outer ring.
[0027] The clamping segment may be flattened perpendicular to the axial direction. The axial extension of the clamping segment may be significantly less than the radial extension and / or circumferential extension. The clamping segment may be a radial protrusion extending from the radial end or a portion of the radial end of the outer ring.
[0028] The clamping section can be arranged on the downstream end portion of the outer ring, and in particular, can protrude radially from the downstream end portion of the outer ring. The clamping section can be arranged near the nozzle ring lug in both the axial and circumferential directions. The clamping section is preferably arranged upstream of and spaced apart from the nozzle ring lug. For example, the clamping section can be installed a few millimeters upstream of the nozzle ring lug.
[0029] Additionally or alternatively, the clamping section may at least partially overlap with the nozzle ring lug when viewed in the circumferential direction. The clamping section may have a greater extension than the nozzle ring lug when viewed in the circumferential direction. For example, the nozzle ring lug may extend entirely within the clamping section when viewed in the circumferential direction.
[0030] In one embodiment, the clamping section has two insertion openings or through holes. The axial turbine may also have at least two fastening devices by which the outer ring is detachably connected to the cover ring. The cover ring may have at least two threads. Each of the at least two fastening devices may extend through one of the insertion openings in the clamping section. Furthermore, the at least two fastening devices may engage in one of the threads in the cover ring. The fastening devices may also extend through a guide hole in the cover ring. The threads may be arranged downstream of the guide hole.
[0031] When viewed circumferentially, the nozzle ring lug can be positioned between two insertion openings or through holes in the clamping section. Therefore, at least two insertion openings can each be spaced circumferentially from the nozzle ring lug. For example, one of the two insertion openings can be spaced circumferentially clockwise from the nozzle ring lug, while the other of the two insertion openings can be spaced circumferentially counterclockwise from the nozzle ring lug.
[0032] The upstream end portion of the cover ring has a cover ring lug receiving portion or groove. To secure the nozzle ring to the cover ring, the nozzle ring can be aligned (rotated) so that the nozzle ring lug can descend into the cover ring lug receiving portion. The lug engaging in the lug receiving portion forms a tangential contact surface. This allows for the centering of the nozzle ring and defines its position when viewed in the circumferential direction. Furthermore, the tangential contact surface between the nozzle ring lug and the cover ring lug receiving portion allows for more reliable torque transmission. The lug receiving portion can have dimensions corresponding to the nozzle ring lug. For example, the lug receiving portion can have a slightly larger dimension than the lug in the circumferential direction. This form of torque transmission between the lug and the lug receiving portion allows the nozzle ring to expand radially during operation, which improves thermomechanical fatigue characteristics.
[0033] According to an embodiment that can be combined with other embodiments described herein, the lug receiver has radially extending, relatively positioned, and circumferentially spaced sidewalls for securing the nozzle ring lug of the nozzle ring in the circumferential direction. Typically, the circumferential spacing between the two sidewalls is chosen such that there is no gap between the nozzle ring lug and the lug receiver.
[0034] According to one embodiment, the cover ring has a clamping protrusion for receiving a clamping section. The clamping protrusion may have one or more receiving portions, which are flattened, and the clamping section may be supported on or pressed against the receiving portion. The clamping protrusion may have at least one thread in the cover ring. A cover ring lug receiving portion may be arranged within the clamping protrusion when viewed in the circumferential direction. Additionally or alternatively, the cover ring lug receiving portion may be arranged downstream of the clamping protrusion when viewed axially. The clamping protrusion may have two receiving portions. For example, one receiving portion may be spaced clockwise from the lug receiving portion when viewed in the circumferential direction, while another receiving portion may be spaced counterclockwise from the lug receiving portion in the circumferential direction.
[0035] The fastening device, preferably together with the clamping section (and optionally the clamping protrusion), allows for axial fixation between the nozzle ring and the cover ring. In this case, the fastening device allows the clamping section to press against the cover ring (optionally against the clamping protrusion), and the clamping section can press the lug into the lug receiving portion. In other words, axially fastening the outer ring to the cover ring by at least one fastening device allows the nozzle ring lug to be pressed into the cover ring lug receiving portion. In particular, it is also possible to press the clamping section against the clamping protrusion. The combination of the lug and the lug receiving portion (on one hand) and the combination of the fastening device and the clamping section (on the other hand) allow for simultaneous centering and axial fastening of the nozzle ring.
[0036] According to embodiments that can be combined with other embodiments described herein, the fastening device has internal threads. Fastening devices with internal threads facilitate removal during disassembly using tools with corresponding external threads. The fastening device can be a pin (particularly a pin with internal threads), a bolt (particularly a bolt with internal threads), or a screw.
[0037] Pressing the clamping section against the cover ring using a fastening device can also create a contact surface between the clamping section and the nozzle ring lug. In this case, pressing can either push the clamping section axially upstream of the nozzle ring lug or cause the nozzle ring lug to axially protrude into the clamping section. The clamping section can be bent by the nozzle ring lug, and an axial clamping force can be elastically applied to the nozzle ring lug.
[0038] In one embodiment, the axial turbine is configured such that it is axially fastened to the cover ring by means of an outer ring via a fastening device, and the nozzle ring lug causes at least a portion of the clamping section to move axially upstream by at least 0.05 mm, preferably at least 0.1 mm, more preferably at least 0.2 mm, and most preferably at least 0.3 mm. Alternatively or additionally, the axial turbine may be configured such that it is axially fastened to the cover ring by means of an outer ring via a fastening device, and the nozzle ring lug protrudes into the clamping section by at least 0.05 mm, preferably at least 0.1 mm, more preferably at least 0.2 mm, and most preferably at least 0.3 mm.
[0039] The cover ring, particularly the lug receiving portion, may have threads for accommodating a guide rail. In this case, the nozzle ring lug may have a through-hole through which the guide rail extends. Additionally or alternatively, the clamping section may have a through-hole through which the guide rail can extend (in addition to the insertion opening), the guide rail facilitating the assembly of the cover ring and the nozzle ring.
[0040] The nozzle ring lugs and cover ring lug receptacles can also be considered as lug-lug receptacle pairs. In one embodiment, the axial turbine has multiple lug-lug receptacle pairs spaced apart from each other in the circumferential direction of the outer ring. For each lug-lug receptacle pair, the axial turbine preferably has at least one (e.g., two) fastening device that axially and detachably connects the outer ring to the cover ring in the region of the associated lug-lug receptacle pair. Additionally or alternatively, for each lug-lug receptacle pair, the axial turbine may have a clamping section that applies an axial force specifically to the associated lug-lug receptacle pair. Optionally, the axial turbine may have clamping protrusions for each lug-lug receptacle pair. Thus, additional lug-lug receptacle pairs and / or additional clamping section-clamping protrusion pairs arranged on the axial turbine can be designed according to the above description.
[0041] In the embodiments, each lug-lug receiving pair differs in geometric design. For example, each lug-lug receiving pair may differ from the others in its length along the circumferential direction. Thus, it is possible for a lug to engage only with a specific lug receiving portion. Therefore, it is advantageously ensured that the nozzle ring is assembled in a specific, desired orientation.
[0042] In one exemplary embodiment, the axial turbine has three lug-lug receiving pairs and three clamping section-clamping protrusion pairs. Each of the three clamping section-clamping protrusion pairs may have two insertion openings or through holes. The nozzle ring can be removably fastened to the cover ring by six fastening devices.
[0043] The axial turbine described herein advantageously allows for the assembly and disassembly of various components from both the "cold" side (compressor side) and the "hot" side (turbine side).
[0044] Axial turbines can be designed based on a "box concept." The "box" can include a shaft and a turbine impeller mounted on the shaft. After removing the box, other components of the axial turbine (such as the diffuser, cover ring, and nozzle ring) can be accessed. The nozzle ring and / or cover ring can be designed for axial removal from the compressor side (from the "cold" side). Removing the nozzle ring or cover ring from the "cold" side, while time-consuming, is particularly wise when major repairs or maintenance (rather than repairs or replacements of the nozzle ring or cover ring) are required.
[0045] Furthermore, the nozzle ring and / or cover ring can be designed to be axially removed from the turbine side (from the "hot" side). For this purpose, at least the outer portion of the intake housing can be disassembled. In particular, this embodiment can reduce the time required for assembly and disassembly, which has a positive impact on maintenance costs. If only the nozzle ring and / or cover ring need to be repaired or replaced, it can be accessed via the turbine side within the required short time.
[0046] According to one embodiment, the axial turbine has an intermediate space between the outer ring of the nozzle ring (and optionally the cover ring) and the exhaust housing of the turbine housing. This intermediate space allows axial access to the fastening device (especially after a portion of the intake housing has been removed). This means the fastening device can be loosened, allowing the nozzle ring to be disassembled and removed from the hot side.
[0047] In another embodiment, the intermediate space allows axial access to the fastening elements (especially after a portion of the intake housing has been removed). This means the fastening elements can be loosened, allowing the cover ring to be removed from the hot side. In this case, by sequentially loosening the fastening devices and fastening elements, the nozzle ring can be removed first on the turbine side, followed by the cover ring. Alternatively, only the fastening elements can be loosened, and then the cover ring and nozzle ring can be removed together on the turbine side.
[0048] According to another embodiment, a turbine, particularly an exhaust turbocharger, is provided. The turbine has an axial turbine according to any embodiment described herein, and a compressor connected to the shaft.
[0049] According to another embodiment, a method for disassembling a nozzle ring is provided. The nozzle ring is mounted in an axial turbine and disposed within the turbine housing of the axial turbine. The axial turbine includes a fastening device that axially and detachably connects the outer ring of the nozzle ring to a cover ring of the axial turbine on the radially outer side. The axial turbine may also have a fastening element that axially and detachably connects the cover ring to a turbine diffuser of the axial turbine on the radially outer side. The turbine housing and the nozzle ring are shaped such that an intermediate space is provided between the outer ring of the nozzle ring and the turbine housing.
[0050] In one embodiment, the method includes the steps of: removing the outer portion of the intake housing of the turbine housing of an axial turbine; removing the fastening device by means of axial approach in the intermediate space; and axially removing the nozzle ring from the turbine housing on the turbine side.
[0051] The method may also optionally include the following steps: removing the fastening element by means of axial approach in the intermediate space; and axially removing the cover ring from the turbine housing on the turbine side.
[0052] In another embodiment, the method includes the following steps: removing the outer portion of the intake housing of the turbine housing of the axial turbine; removing fastening elements by means of axial approach in the intermediate space; and axially removing the nozzle ring and cover ring from the turbine housing on the turbine side.
[0053] Specifically, the method may include removing the nozzle ring and cover ring together axially from the turbine housing on the turbine side.
[0054] The axial turbine and / or nozzle ring and / or cover ring can be designed according to any of the embodiments described herein.
[0055] In another embodiment, the use of an assembly comprising a nozzle ring and a cover ring is described for mounting to and / or removal from an axial turbine of a turbine on the turbine side. The assembly has a nozzle ring with an outer ring. The nozzle ring is designed to be mounted into the turbine housing of the axial turbine and is at least partially disposed upstream of the turbine impeller of the axial turbine. Furthermore, the assembly includes a cover ring designed to be mounted into the turbine housing and disposed downstream of the nozzle ring. The assembly includes a fastening device that axially and detachably connects the outer ring to the cover ring radially outward. The downstream end portion of the outer ring has a radially outwardly projecting nozzle ring lug, and the upstream end portion of the cover ring has a cover ring lug receiving portion. The nozzle ring lug engages in the cover ring lug receiving portion.
[0056] The outer ring may have a clamping section, wherein the fastening device extends through an insertion opening in the clamping section. Optionally, the fastening device may engage with threads in the cover ring.
[0057] In another embodiment, an assembly comprising a nozzle ring and a cover ring is provided, particularly for mounting to and / or removing from an axial turbine of a turbine on the turbine side. The assembly has a nozzle ring having an outer ring. The nozzle ring is designed to be mounted into the turbine housing of the axial turbine and is at least partially disposed upstream of the turbine impeller of the axial turbine. Furthermore, the assembly includes a cover ring designed to be mounted into the turbine housing and disposed downstream of the nozzle ring. The assembly includes a fastening device that axially detachably connects the outer ring to the cover ring radially outward. The downstream end portion of the outer ring has a radially outwardly projecting nozzle ring lug, and the upstream end portion of the cover ring has a cover ring lug receiving portion. The nozzle ring lug engages in the cover ring lug receiving portion.
[0058] The outer ring may have a clamping section, wherein the fastening device extends through an insertion opening in the clamping section. Optionally, the fastening device may engage with threads in the cover ring. BRIEF DESCRIPTION OF DRAWINGS
[0059] The invention will now be discussed in more detail based on embodiments, but these embodiments are not intended to limit the scope of protection defined by the claims.
[0060] The accompanying drawings illustrate embodiments and, together with the description, serve to explain the principles of the invention. Elements in the drawings are relative and not necessarily drawn to scale. The same reference numerals are used to denote corresponding similar parts.
[0061] In the attached diagram:
[0062] Figure 1 An exploded view shows an axial turbine according to an embodiment.
[0063] Figure 2 A portion of an axial turbine according to an embodiment is shown.
[0064] Figure 3 A portion of an axial turbine according to an embodiment is shown.
[0065] Figure 4 It shows Figure 3 A magnified view of the area.
[0066] Figure 5 An axial turbine according to an embodiment is shown. DETAILED DESCRIPTION
[0067] The following detailed description will be given with reference to the accompanying drawings, which illustrate a portion of the invention and show specific embodiments in which the invention can be implemented. It should be understood that other embodiments may be used, and structural or logical changes may be made, without departing from the scope of the invention. Therefore, the following detailed description should not be interpreted in a limiting manner, and the scope of the invention is defined by the appended claims. The described embodiments use specific language, which should not be construed as limiting the scope of the appended claims.
[0068] Figure 1 and Figure 2 A portion of an axial turbine 100 for a turbine according to an embodiment is shown. For better overview, some components of the axial turbine 100 are not shown. Specifically, the axial turbine 100 has a turbine housing, a shaft 170, and a turbine impeller 180 disposed in the turbine housing and mounted on the shaft 170. Figure 1 It is presented in exploded view form. Therefore, the components of the axial turbine 100 are shown in an unassembled state.
[0069] The axial turbine 100 has a nozzle ring 110. The nozzle ring 110 has an outer ring 112, an inner ring 114, and a guide vane 113 disposed between the outer ring 112 and the inner ring 114. The turbine housing has a dome 111 connected to the nozzle ring 110. In this case, the outer ring 112, the guide vane 113, the inner ring 114, and the dome 111 are all integrally formed. The nozzle ring 110 is disposed within the turbine housing (not shown).
[0070] In addition, the axial turbine 100 has a cover ring 120. The cover ring is disposed within the turbine housing (not shown) and downstream of the nozzle ring 110.
[0071] The axial turbine 100 has six fastening devices 140 that detachably connect the outer ring 112 to the cover ring 120 radially outward. In this configuration, the outer ring 112 has three clamping sections 116, and the cover ring 120 has three clamping protrusions 122 (in...). Figure 1 Only the two clamping sections 116 and two clamping protrusions 122 are shown in full. The two fastening devices 140 respectively connect the clamping sections 116 to the outer ring 112.
[0072] Furthermore, the outer ring 112 has three nozzle ring lugs 115, and the cover ring 120 has three corresponding lug receiving portions 121 (in Figure 1 In the image, only one nozzle ring lug 115 and one lug receiving portion 121 are fully shown.
[0073] The axial turbine 100 also includes a turbine diffuser or diffuser 130. The diffuser 130 and the cover ring 120 are each formed as separate components and are connected to each other by fastening elements 150. The cover ring 120 has a plurality of insertion openings 125, and the turbine diffuser 130 has a corresponding number of threads 131 for receiving the fastening elements 150. Each fastening element 150 extends through one of the insertion openings 125 and engages with one of the threads 131 in the diffuser 130.
[0074] Figure 2 and Figure 3 Cross-sectional views of the axial turbine 100 according to an embodiment are shown. Figure 2 and Figure 3 The area shown illustrates the connection between the nozzle ring 110 and the cover ring 120.
[0075] The nozzle ring lug 115 of the nozzle ring 110 abuts against the corresponding lug receiving portion 121 of the cover ring 120. The clamping section 116 of the nozzle ring 110 abuts against the clamping protrusion of the cover ring 120.
[0076] By fastening the two fastening devices 140 shown, the clamping section 116 presses against the clamping protrusion 122. The pressing of the clamping section 116 against the clamping protrusion 122 causes the nozzle ring lug 115 to press against the lug receiving portion 121. Although an axial gap may exist between the nozzle ring lug 115 and the clamping section 121 in the unassembled state, due to the connection between the nozzle ring 110 and the cover ring 120, the nozzle ring lug 115 and the clamping section 121 come into contact with each other, thereby creating a contact surface between the nozzle ring lug 115 and the clamping section 121. In this case, pressing can cause the nozzle ring lug 115 to push the clamping section 121 axially upward or cause the nozzle ring lug 115 to protrude axially into the clamping section 121. The nozzle ring lug 115 protruding into the clamping section 121... Figure 3 The middle is indicated by a thick black line, and in Figure 4 The enlarged image shows it more clearly.
[0077] The cover ring 120 may have threads 124 for receiving a guide rail. In this case, the nozzle ring lug 115 may have a through-hole through which the guide rail extends. Additionally or alternatively, the clamping section 121 may have a through-hole through which the guide rail can extend (in addition to the insertion opening 117). The guide rail makes it easier to assemble the cover ring 120 with the nozzle ring 110.
[0078] Figure 5 An axial turbine 100 is shown, having a nozzle ring 110, a cover ring 120, and a diffuser 130. The axial turbine 100 has a turbine housing 160. The turbine housing includes an intake housing 161 and an exhaust housing 162. The diffuser 130 and the cover ring 120 are disposed within the exhaust housing 162. The nozzle ring 110 is partially disposed within the intake housing 161 and partially disposed within the exhaust housing 162. The nozzle ring 110 and the exhaust housing 162 are shaped to form an intermediate space 163. The intermediate space 163 allows axial access to the nozzle ring 110 after at least partial removal of the intake housing 161. This allows access to a fastening device 140. After the fastening device 140 is loosened and removed, the nozzle ring 110 can be removed from the turbine side.
[0079] In this case, shaft 170 defines the longitudinal axis 190 or the axial and radial directions. Figure 5 The longitudinal axis 190 is shown by a dashed line.
[0080] Furthermore, the intermediate space 163 allows access to the fastening element 150. After the fastening element 150 is loosened and removed, the cover ring 120 can be removed from the turbine side.
[0081] Although specific embodiments have been shown and described herein, appropriate combinations or modifications of the shown embodiments without departing from the scope of protection of this invention also fall within the scope of this invention.
[0082] List of reference numerals
[0083] 100 Axial Turbine
[0084] 110 Nozzle Ring
[0085] 111 Dome
[0086] 112 Outer Ring
[0087] 113 (Nozzle ring) Guide vane
[0088] 114 (Inner ring of nozzle ring)
[0089] 115 Nozzle ring lug
[0090] 116 Clamping Section
[0091] 117 Insertion opening
[0092] 120 cap ring
[0093] 121 Lug Receiving Section
[0094] 122 Clamping protrusion
[0095] 123 Guide hole
[0096] 124 Thread for accommodating guide rails
[0097] 125 Insertion opening in the cover ring
[0098] 130 Turbine Diffuser
[0099] 131 Threads in a turbine diffuser (for accommodating fastening elements)
[0100] 140 Fastening device
[0101] 150 Fastening Components
[0102] 160 Turbine Housing
[0103] 161 Intake Housing
[0104] 162 Exhaust housing
[0105] 163 Intermediate Space
[0106] 170 axis
[0107] 180 turbine impeller
[0108] 190 Longitudinal axis
Claims
1. An axial turbine (100) for a turbine, particularly for an exhaust gas turbocharger, comprising: - Turbine housing (160); - A turbine impeller (180), which is arranged in the turbine housing (160) and mounted on a shaft (170); - A nozzle ring (110) disposed in the turbine housing (160) and at least partially disposed upstream of the turbine impeller (180), wherein the nozzle ring has an outer ring (112). - A cover ring (120), which is arranged in the turbine housing (160) and downstream of the nozzle ring (110), - Fastening device (140) which axially and detachably connects the outer ring (112) to the cover ring (120) on the radially outer side. The outer ring (112) has a nozzle ring lug (115) that protrudes radially outward, and the cap ring (120) has a cap ring lug receiving portion (121) at its upstream end, wherein the nozzle ring lug (115) is engaged in the cap ring lug receiving portion (121).
2. The axial turbine of claim 1, further comprising a dome (111) disposed on the upstream end portion of the nozzle ring, wherein, The dome (111) is fastened only to the inner ring (114) of the nozzle ring (110), or wherein the dome (111) is integrally formed with the nozzle ring (110), particularly with the inner ring (114) of the nozzle ring (110).
3. The axial turbine (100) according to any one of the preceding claims, wherein, The outer ring (112) has a clamping section (116) in which the fastening device (140) extends through an insertion opening (117) in the clamping section (116); and wherein, optionally, the fastening device (140) engages in a thread in the cover ring (120).
4. The axial turbine (100) according to claim 3, wherein, The nozzle ring lug (115) protrudes into the clamping section (116) by at least 0.05 mm, preferably at least 0.1 mm, more preferably at least 0.2 mm, and most preferably at least 0.3 mm.
5. The axial turbine (100) according to claim 3 or 4, wherein, The clamping section (116) has two insertion openings (117), wherein the nozzle annular lug (115) is arranged between the two insertion openings when viewed in the circumferential direction.
6. The axial turbine (100) according to any one of claims 3 to 5, wherein, The clamping section (116) is arranged upstream of and spaced apart from the nozzle ring lug (115); and / or wherein, The clamping section (116) overlaps at least partially with the nozzle ring lug (115) when viewed in the circumferential direction.
7. The axial turbine (100) according to any one of claims 3 to 6, wherein, The cover ring (120) has a clamping protrusion (122) for receiving the clamping segment (116).
8. The axial turbine (100) according to any one of the preceding claims, wherein, The axial turbine is configured such that it is axially fastened to the cover ring (120) by means of the outer ring (112) via the fastening device (140), the nozzle ring lug (115) is pressed into the cover ring lug receiving portion (121), and in particular the clamping section (116) presses against the clamping protrusion (122).
9. The axial turbine (100) according to any one of the preceding claims further includes a turbine diffuser (130) disposed at least partially downstream of the turbine impeller (180).
10. The axial turbine (100) according to claim 9, wherein, The turbine diffuser (130) is integrally formed with the cover ring (120).
11. The axial turbine (100) according to claim 9, wherein, The downstream end portion of the cover ring (120) is fastened to the upstream end portion of the turbine diffuser (130); wherein, in particular, the turbine diffuser (130) is detachably connected to the cover ring (120) by a fastening element (150), wherein the fastening element (150) extends along the insertion opening (125) of the cover ring (120) and engages in the threads (131) in the turbine diffuser (130).
12. The axial turbine (100) according to any one of the preceding claims, wherein, The nozzle ring lug (115) and the cover ring lug receiving portion (121) form a lug-lug receiving portion pair, and the axial turbine (100) has at least three lug-lug receiving portion pairs spaced apart from each other in the circumferential direction of the outer ring (112).
13. The axial turbine (100) according to any one of the preceding claims, wherein, The nozzle ring (110) and / or the cover ring (120) are designed to be axially removed on the turbine side.
14. A method for removing a nozzle ring (110) mounted in an axial turbine (100) and disposed in a turbine housing (160) of the axial turbine, in, The axial turbine (100) has a fastening device (140) that axially and detachably connects the outer ring (112) of the nozzle ring (110) to the cover ring (120) of the axial turbine (100) on the radially outer side; and optionally, the axial turbine (100) has a fastening element (150) that axially and detachably connects the cover ring (120) to the turbine diffuser (130) of the axial turbine (100) on the radially outer side. The turbine housing (160) and the nozzle ring (110) are shaped such that an intermediate space (163) is disposed between the outer ring (112) of the nozzle ring (110) and the turbine housing, the method comprising: - Remove the outer portion of the intake casing (161) of the turbine housing (160) of the axial turbine (100); - Remove the fastening device (140) by means of axial approach in the intermediate space (163); and remove the nozzle ring (110) axially from the turbine housing (160) on the turbine side; or - The fastening element (150) is removed by means of axial approach in the intermediate space (163); and the nozzle ring (110) and the cover ring (120) are axially removed from the turbine housing (160) on the turbine side.
15. Use of an assembly comprising a nozzle ring (110) and a cover ring (120) for mounting to and / or removal from an axial turbine (100) of a turbine on the turbine side, said assembly comprising: - Nozzle ring (110), having an outer ring (112) and designed to be mounted in the turbine housing (160) of the axial turbine (100) and arranged at least partially upstream of the turbine impeller (180) of the axial turbine (100); - A cover ring (120), which is designed to be installed in the turbine housing (160) and arranged downstream of the nozzle ring (110), - Fastening device (140) which axially and detachably connects the outer ring (112) to the cover ring (120) on the radially outer side. The outer ring (112) has a nozzle ring lug (115) that protrudes radially outward, and the cap ring (120) has a cap ring lug receiving portion (121) at its upstream end, wherein the nozzle ring lug (115) is engaged in the cap ring lug receiving portion (121).