Nozzle ring for radial turbine, exhaust turbine and turbocharger
By designing a nozzle ring with convex curved end, the problem of insufficient material between the nozzle ring and the turbine impeller in the radial turbine is solved, flow improvement and manufacturing limitations are achieved, and the stability and flow of the turbine housing are ensured. performance.
Patent Information
- Application Number
- CN202380029167.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2022-03-22
- Filing Date
- 2023-03-08
- Publication Date
- 2024-12-17
AI Technical Summary
During casting of a runoff turbine, the core gap between the nozzle ring and the turbine impeller cannot be produced from available blanks, resulting in insufficient material and manufacturing limitations, affecting the formation of the flow profile.
A nozzle ring is designed, including a plurality of guide blades between the first annular element and the second annular element, the second annular element extending inwardly in the radial direction and having a convex curve in the end region, To replace or bridge missing materials, overcome manufacturing-related limitations and improve flow characteristics.
The nozzle ring can at least partially or completely overcome the material shortage in the casting process, achieve flow improvements, and ensure stable connection and flow guidance of the turbine housing.
Smart Images
Figure CN119156484A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the field of turbochargers including exhaust gas turbines, in particular radial turbines. In particular, the present invention relates to a nozzle ring for a radial turbine. Background Art
[0002] In order to increase the performance of internal combustion engines, turbochargers are currently used as standard, which include a turbine in the exhaust system of the internal combustion engine and a compressor upstream of the internal combustion engine. In this arrangement, the exhaust gases of the internal combustion engine are decompressed in the turbine. The work thus generated is transmitted via 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 in the internal combustion engine, the combustion process and efficiency of the internal combustion engine can be optimized.
[0003] The kinetic and thermal energy of the exhaust gases is used to drive the rotor of the turbocharger. In order to be able to ensure safe operation, the exhaust gas flow must be directed in a targeted manner onto the turbine shaft. For this purpose, and in order to allow the thermodynamics of the turbocharger to be adapted to different applications, in the case of radial turbine stages, a nozzle ring is installed at the outlet of the flow duct, upstream of the turbine shaft. The exhaust gas is supplied to the turbine via a nozzle ring connected upstream of the turbine. The arrangement of the nozzle ring blades influences the characteristics of the turbocharger. Different nozzle rings are used for different applications.
[0004] The turbine housing or gas inlet housing is usually a casting produced in the sand casting process. In this process, the flow duct inside the housing is represented by means of a so-called core in the casting mold. This core is connected to the outer contour of the casting mold. This connection is called the core gap. In the component, the core gap is located at the location of the nozzle ring arranged in the turbocharger. For technical reasons, the core gap must have a minimum cross section to ensure a sufficiently stable connection to the outer mold.
[0005] It has been found that in the case of small turbine blades (cut edges), flow profiles are required in the region between the nozzle ring and the turbine wheel, i.e. in the region of the core gap of the casting mold, which flow profiles cannot be produced from the available blank, since the blank does not provide sufficient material. For casting-related reasons, the blank cannot be adjusted, since such an adjustment would reduce the core gap to a cross-section that can no longer be used to produce the housing.
[0006] The object of the present invention is to provide a solution to the above problems. Summary of the invention
[0007] In order to solve the above-mentioned problems, a nozzle ring and an exhaust gas turbine as described in the independent claims are provided. In addition, a turbocharger comprising an exhaust gas turbine according to the embodiments described herein is provided. Other aspects, advantages and features of the invention can be found in the dependent claims, the description and the drawings. According to one aspect of the invention, a nozzle ring for a radial flow turbine is provided. The nozzle ring comprises a first annular element, a second annular element and a plurality of guide vanes arranged between the first annular element and the second annular element. The second annular element comprises an end region extending inwardly only in the radial direction, the end region having a convex curvature on a side facing the first annular element.
[0008] Thus, advantageously, a nozzle ring is provided, by means of which the manufacturing-related disadvantages mentioned at the beginning during the casting of the housing can be at least partially or even completely overcome. In particular, a nozzle ring is advantageously provided, by means of which material missing from the turbine housing due to manufacturing-related limitations can be replaced or bridged. In particular, the second ring element of the nozzle ring is advantageously configured in such a way that casting-related disadvantages and limitations for producing radial turbines with small turbine blades can be overcome and improvements in terms of flow can be achieved.
[0009] A second aspect of the present invention relates to an exhaust gas turbine, in particular to a radial flow turbine. The exhaust gas turbine comprises a turbine housing having a gas inlet housing, a radial gas inflow duct arranged in the gas inlet housing, and a nozzle ring arranged in the radial gas inflow duct. The nozzle ring comprises a first annular element, a second annular element, and a plurality of guide vanes arranged between the first annular element and the second annular element. The second annular element comprises an end region extending inwardly only in the radial direction, the end region having a convex curvature on the side facing the first annular element. In particular, the convex curvature extends to the radial inner end of the second annular element. There is an axial gap between the side of the second annular element facing away from the first annular element and the opposite side of the gas inlet housing.
[0010] Advantageously, an exhaust gas turbine is thus provided which is improved compared to the prior art. In particular, an exhaust gas turbine is provided, by means of which the manufacturing-related disadvantages mentioned at the outset in the process of casting the housing can be at least partially or even completely overcome.
[0011] A third aspect of the invention relates to a turbocharger comprising an exhaust gas turbine according to the embodiments described herein, so that advantageously an improved turbocharger with respect to the prior art is provided. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] In the following, the invention will be explained with reference to the exemplary embodiments shown in the accompanying drawings, and further advantages and modifications will be derived therefrom. In the drawings:
[0013] Figure 1 is a schematic cross-sectional view of a nozzle ring according to an embodiment described herein;
[0014] Figure 2 is a schematic cross-sectional view of a nozzle ring according to further embodiments described herein;
[0015] Figure 3 is a schematic cross-sectional view of an exhaust gas turbine including a nozzle ring according to an embodiment described herein; and
[0016] Figure 4 Shows Figure 3 An enlarged area of FIG. 1 is shown in which an installed nozzle ring according to an embodiment described herein is shown. DETAILED DESCRIPTION
[0017] Various embodiments are described below, wherein one or more examples are shown in each figure. Each example is for illustrative purposes only and should not be construed as limiting. For example, a feature shown or described as part of an embodiment can be used on or in combination with each different embodiment to obtain another embodiment. The present disclosure is intended to include such modifications and variations.
[0018] In the following description of the drawings, the same reference numerals refer to the same or similar parts. Generally speaking, only the differences related to each embodiment are described. Unless otherwise stated, the description of a part or aspect in one embodiment can also refer to the corresponding part or corresponding aspect in another embodiment.
[0019] Reference Figures 1 to 4 , a nozzle ring 10 for a radial flow turbine is described according to an embodiment of the present disclosure.
[0020] According to one embodiment, which can be combined with other embodiments described herein, Figure 1 As shown in the figure, the nozzle ring 10 comprises a first ring element 11, a second ring element 12 and a plurality of guide vanes 13. The guide vanes 13 are arranged between the first ring element 11 and the second ring element 12. Typically, the flow duct 17 is located between the first ring element 11 and the second ring element 12. In other words, the intermediate space between the first ring element 11 and the second ring element 12 provides the flow duct 17. The first ring element 11 typically defines the flow duct 17 on the bearing housing side. Figure 3, an exemplary embodiment of a nozzle ring 10 is shown when installed, wherein a turbine housing 21 and a bearing housing 22 are shown. The second annular element 12 usually defines a flow duct 17 on the turbine housing side. The second annular element 12 comprises an end region 12E extending only inwardly in the radial direction. The radial direction r and the axial direction x are in the Figures 1 to 4 As shown in the figure, the end region 12E that only extends inward in the radial direction is the end region on the outflow side. Figure 1 and Figure 2 Typically, the length of the end region is less than or equal to 50% of the total radial extent of the second annular element 12. The side 121 of the radially inner end region 12E of the second annular element 12 facing the first annular element 11 has a convex curvature 141. Figure 1 , Figure 2 and Figure 3 As can be clearly seen in FIG. 1 , the side 121 facing the first ring element 11 is typically the side of the nozzle ring 10 defining the flow duct 17. In particular, the convex curvature 141 extends to the radially inner end of the second ring element 12. Typically, the convex curvature 141 is continuous in curvature.
[0021] Thus, advantageously, a nozzle ring is provided, by means of which the casting-related disadvantages in the production of the turbine housing mentioned at the beginning can be at least partially or even completely overcome. In particular, the embodiments of the nozzle ring described herein allow replacing or bridging material missing from the turbine housing due to manufacturing-related limitations. In particular, the second annular element of the nozzle ring is advantageously configured in such a way that casting-related disadvantages and limitations for the production of radial turbines with small turbine blades can be overcome and improvements in terms of flow can be achieved.
[0022] According to one embodiment, which can be combined with other embodiments described herein, the first annular element 11 is a support ring for the nozzle ring 10. The second annular element 12 can be a cover ring for the nozzle ring 10. In addition to the bearing housing-side definition of the flow duct 17, the first annular element 11, in particular the support ring, can also be configured to provide a radial and / or axial positioning function for the nozzle ring. Furthermore, the first annular element 11, in particular the support ring, can be configured to provide a centering function in the turbine housing. Furthermore, the first annular element 11, in particular the support ring, can be configured to provide a flow guide profile in the direction of the turbine wheel after the flow guide blades 13.
[0023] According to one embodiment, which can be combined with other embodiments described herein, Figure 2, the second ring element 12 comprises an extension 14 which, compared to the first ring element 11, extends only inwardly in the radial direction. Thus, material missing from the turbine housing due to manufacturing-related restrictions can advantageously be replaced or bridged by the extension 14. Advantageously, the extension 14 extends beyond the flow duct 17 of the nozzle ring 10. Furthermore, the extension 14 can advantageously be used to compensate for casting tolerances in the turbine housing in the transition region from the turbine housing to the nozzle ring. Figure 2 As shown exemplarily in FIG. 1 , the extension 14 generally comprises a convex curvature 141. In particular, the convex curvature 141 extends to the radially inner end of the extension 14. Thus, an improved flow guidance can be provided in the direction of the turbine wheel.
[0024] According to one embodiment, which can be combined with other embodiments described herein, the extension 14 has a length L V , the length L V is the radial extent R of the first annular element 11 11 At least 10% of Figure 2 Alternatively, the length L V The radial extent R of the first annular element 11 can be 11 For example, the length L V The radial extent R of the first annular element 11 can be 11 at least 30%.
[0025] according to Figure 2 In the exemplary embodiment shown, which can be combined with other embodiments described herein, the second annular element 12 further comprises an axial extension 15. The axial extension 15 is configured to be inserted into an axial receiving portion 212 of the gas inlet housing 21E of the turbine housing 21, such as Figure 4 Typically, the axial extension 15 is arranged in the region of the inflow side of the second ring element 12. According to an embodiment not explicitly shown, the axial extension 15 can be arranged in the region of the outflow side of the ring element 12.
[0026] According to one embodiment, which can be combined with other embodiments described herein, the axial extension 15 comprises a receiving portion 151 for the sealing element 16, such as Figure 2 and Figure 4 Typically, the receiving portion 151 for the sealing element 16 is arranged in the radially inner region of the axial extension 15. According to an embodiment not explicitly shown, the receiving portion 151 for the sealing element 16 can be arranged in the radially outer region of the axial extension 15.
[0027] Reference Figure 3 and Figure 4According to an embodiment of the present disclosure, an exhaust gas turbine 20, in particular a radial turbine, is described. According to an embodiment that can be combined with other embodiments described herein, the exhaust gas turbine 20 includes a turbine housing 21 having a gas inlet housing 21E. The exhaust gas turbine can be understood as a turbine stage. In the gas inlet housing 21E, a radial gas inflow duct 211 is arranged. The exhaust gas turbine generally includes a turbine wheel 23 arranged on a shaft 24, which is mounted in a bearing housing 22 and has a rotation center axis 25. In addition, the exhaust gas turbine 20 includes a nozzle ring 10, which is arranged in the radial gas inflow duct 211. The nozzle ring 10 includes a first annular element 11, a second annular element 12 and a plurality of guide vanes 13. The guide vanes 13 are arranged between the first annular element 11 and the second annular element 12. The second annular element 12 includes an end region 12E that extends inwardly only in the radial direction. The end region 12E has a convex curvature 141 on the side 121 facing the first annular element 11. In particular, the convex curvature 141 extends to the radially inner end of the second ring element 12. An axial gap S1 is located between a side 122 of the second ring element 12 facing away from the first ring element 11 and an opposite side 214 of the gas inlet housing 21E.
[0028] Advantageously, an exhaust gas turbine is thus provided which is improved with respect to the prior art. In particular, a gas turbine is provided, with the aid of which the manufacturing-related disadvantages mentioned at the outset in the process of casting the housing can be at least partially or even completely overcome. In particular, an exhaust gas turbine is provided, with the aid of which casting-related disadvantages and limitations for producing radial turbines with small turbine blades can be overcome and improvements in terms of flow can be achieved.
[0029] As reference Figure 2 and Figure 4 As described, the second annular element 12 has an extension 14 which extends only inwardly in the radial direction compared to the first annular element 11. Furthermore, the second annular element 12 can include an axial extension 15 which is at least partially arranged in the axial receiving portion 212 of the gas inlet housing 21E, as shown in FIG. Figure 4 As shown in the example.
[0030] According to one embodiment, which can be combined with other embodiments described herein, the axial extension 15 comprises a receiving portion 151 for a sealing element 16, in which the sealing element 16 is arranged. Typically, the sealing element 16 provides a seal between the nozzle ring 10 and the gas inlet housing 21E. The sealing element 16 can be, for example, a metal foil sealing ring.
[0031] According to one embodiment, which can be combined with other embodiments described herein, the axial receiving portion 212 of the gas inlet housing 21E comprises a chamfer 213 or a rounded corner, such as Figure 4 Typically, the chamfer or fillet is arranged in the radially inner region of the axial receiving portion 212. Providing the chamfer facilitates inserting the axial extension 15 together with the sealing element 16 into the axial receiving portion 212 of the gas inlet housing 21E.
[0032] According to one embodiment, which can be combined with other embodiments described herein, there is an axial gap S2 between the end face of the axial extension 15 and the axial receiving portion 212 of the gas inlet housing 21E.
[0033] According to one embodiment, which can be combined with other embodiments described herein, there is a radial gap S3 between the radially outer side of the axial extension 15 and the axial receiving portion 212 of the gas inlet housing 21E.
[0034] The provision of the gaps S1 , S2 and S3 described herein can particularly advantageously minimize material stresses due to temperature-related material expansions, in particular of the nozzle ring.
[0035] It should be noted that the exhaust gas turbine 20 typically comprises a nozzle ring 10 according to one of the embodiments described herein. It should also be noted that according to the embodiments described herein a turbocharger comprising an exhaust gas turbine according to the embodiments described herein can advantageously be provided.
[0036] Reference numerals list
[0037] 10 Nozzle ring
[0038] 11 First annular element / support ring
[0039] 12 Second annular element / cover ring
[0040] 121 A side of the second annular element facing the first annular element
[0041] 122 A side of the second annular element facing away from the first annular element
[0042] 13 Guide blades
[0043] 14 Extension extending inward in the radial direction
[0044] 12E Radially inwardly directed end region of the second annular element
[0045] 141 Convex bend
[0046] 15 Axial extension
[0047] 151 Receiving portion for sealing element
[0048] 16 Sealing element
[0049] 17 Flow Pipe
[0050] 20 Exhaust gas turbine
[0051] 21 Turbine housing
[0052] 21E Gas Inlet Housing
[0053] 211 Radial gas inflow duct
[0054] 212 Axial receiving portion for axial extension in gas inlet housing
[0055] 213 bevel
[0056] 214 A side of the gas inlet housing opposite to the side of the second annular element facing away from the first annular element
[0057] 22 Bearing housing
[0058] 23 Turbine impeller
[0059] 24 Axis
[0060] 25 Rotation center axis
[0061] S1 Axial clearance between radial extension and gas inlet housing
[0062] S2 Axial clearance between the axial extension and the axial receiving portion of the gas inlet housing
[0063] S3 Radial clearance between the axial extension and the axial receiving portion of the gas inlet housing
[0064] r Radial direction
[0065] x-axis direction
[0066] S Flow direction
[0067] L v Length of radial extension of the second annular element / cover ring
[0068] R 11 The radial extent of the first annular element
Claims
1. A nozzle ring (10) for a radial turbine, wherein: The nozzle ring (10) comprises a first annular element (11), a second annular element (12) and a plurality of guide vanes (13) arranged between the first annular element (11) and the second annular element (12), wherein the second annular element (12) comprises an end region (12E) extending inwardly only in a radial direction, the end region having a convex curvature (141) on a side (121) facing the first annular element (11).
2. The nozzle ring (10) according to claim 1, wherein: The convexly curved portion (141) extends to the radially inner end of the second annular element (12).
3. The nozzle ring (10) according to claim 1 or 2, wherein: Compared to the first annular element (11), the second annular element (12) has an extension (14) extending inwardly only in the radial direction.
4. The nozzle ring (10) according to claim 3, wherein: The extension (14) has a length L V , the length is the radial extent R of the first annular element (11) 11 At least 10% of, in particular, wherein the length L V is the radial extent R of the first annular element (11) 11 at least 30%.
5. The nozzle ring (10) according to any one of claims 1 to 4, wherein: The second annular element (12) further comprises an axial extension (15) for insertion into an axial receiving portion (212) of a gas inlet housing (21E) of a turbine housing (21).
6. The nozzle ring (10) according to claim 5, wherein: The axial extension (15) comprises a receiving portion (151) for a sealing element (16), in particular, wherein the receiving portion (151) for the sealing element (16) is arranged in a radially inner region or a radially outer region of the axial extension (15).
7. An exhaust gas turbine (20), in particular a radial turbine, comprising: - a turbine housing (21) having a gas inlet housing (21E), - a radial gas inflow duct (211) arranged in said gas inlet housing (21E), and - A nozzle ring (10) according to any one of claims 1 to 6, arranged in the radial gas inflow duct (211).
8. The exhaust gas turbine (20) according to claim 7, wherein: An axial gap (S1) exists between a side (122) of the second annular element (12) facing away from the first annular element (11) and an opposite side (214) of the gas inlet housing (21E).
9. The exhaust gas turbine (20) according to claim 7 or 8 in combination with claim 5, wherein: The axial extension (15) is at least partially arranged in an axial receiving portion (212) of the gas inlet housing (21E).
10. The exhaust gas turbine (20) according to any one of claims 7 to 9 in combination with claim 6, wherein: A sealing element (16) is arranged in the receiving portion (151) for the sealing element (16), which provides a seal between the nozzle ring (10) and the gas inlet housing (21E), in particular wherein the sealing element (16) is a foil sealing ring.
11. The exhaust gas turbine (20) according to claim 9 or 10, wherein: The axial receiving portion (212) of the gas inlet housing (21E) includes a chamfer (213) or a rounded corner.
12. The exhaust gas turbine (20) according to claim 11, wherein: The chamfer (213) or the rounded corner is arranged in a radially inner region of the axial receiving portion (212).
13. The exhaust gas turbine (20) according to any one of claims 9 to 12, wherein: An axial gap (S2) exists between the end surface of the axially extending portion (15) and the axial receiving portion (212) of the gas inlet housing (21E).
14. The exhaust gas turbine (20) according to any one of claims 9 to 13, wherein: A radial gap (S3) exists between the radially outer side of the axially extending portion (15) and the axially receiving portion (212) of the gas inlet housing (21E).
15. A turbocharger comprising an exhaust gas turbine (20) according to any one of claims 7 to 14.