Nozzle assembly for a turbocharger and turbocharger having the same

Abstract

A nozzle assembly for a turbocharger includes a housing of a turbine of the turbocharger, a nozzle having a plurality of vanes extending from both sides of a nozzle body, each vane having a profile for guiding a gas flow, and an insert provided at an intermediate body of the turbocharger and independent of the housing and the nozzle, the nozzle being sandwiched between the housing and the insert in an axial direction of the turbocharger, the vanes on both sides of the nozzle body abutting against an insert top surface of the insert and an inner peripheral surface of the housing with respective vane top surfaces. In this assembly, the nozzle, the housing of the turbine and the insert are independent of each other and can be individually manufactured, whereby the machining accuracy of the profile of the vanes of the nozzle for guiding the gas flow is not limited by the housing and different flow specifications of the turbine wheel can be accommodated by replacing only the nozzle, while the housing of the turbine and the insert can be repeatedly used in modular form. A turbocharger having this nozzle assembly is also proposed.

Description

Technical Field

[0001] This invention relates to the technical field of turbochargers. Specifically, this invention relates to a nozzle assembly for a turbocharger, and a turbocharger having the assembly. Background Technology

[0002] In the turbine of a turbocharger, a nozzle is located upstream of the turbine impeller. The nozzle has fixed or movable blades. The blades of the nozzle guide and deflect the exhaust gas flowing into the turbine from upstream, causing it to be sprayed onto the turbine impeller located downstream at a given angle and in a given direction, thereby improving the efficiency of the turbine.

[0003] In existing turbines, there are integrated nozzles, where the nozzle with blades is manufactured integrally with the turbine casing. This structure allows the nozzle blades to be integrally formed within the vortex channels of the turbine casing, thereby creating a fixed flow guide channel upstream of the turbine impeller.

[0004] However, it has been found that because the blades of the integrated nozzle are integrally molded with the turbine casing, the profile of the nozzle blades needs to be machined on the overall structure of the turbine casing. Limited by factors such as the internal structure of the casing, the clamping method, and the machining datum, it is difficult to guarantee the contour, angle, and surface quality of the nozzle blade profile. This reduces the machining accuracy of the blade profile, making it easy for the resulting flow-guiding profile to deviate from the desired aerodynamic state, affecting the airflow matching of the turbine impeller. Furthermore, the integral molding of the blades with the casing means that the blade profile and installation angle cannot be individually replaced or adjusted after molding. Therefore, when turbine impeller specifications or aerodynamic performance requirements change, the entire turbine casing structure must be altered, resulting in poor design flexibility for the turbine and hindering the individual replacement of damaged nozzle blades.

[0005] In existing turbines, there are also separate nozzles, where the bladed nozzle and the turbine casing are manufactured and assembled independently. After assembly, the nozzle is supported by support structures located on both sides of it and by the casing. This structure can also create a defined flow guide upstream of the turbine impeller, directing the flow of exhaust gas flowing into the turbine from upstream.

[0006] However, it has been found that for such separate nozzles, due to the assembly relationship between the nozzle and the turbine housing, the blade profile of one type of nozzle can only correspond to a specific turbine impeller. When the turbine impeller specifications change, the original separate nozzle is no longer applicable and may need to be remanufactured. This makes the nozzle non-universal, reduces flexibility, and increases the overall cost of the turbocharger. Furthermore, for these separate nozzles, sealing rings need to be installed during assembly with the turbine housing to achieve surface sealing, increasing the number of turbocharger parts and assembly steps, raising costs. Moreover, the sealing rings are prone to oxidation, creep, and loosening under the high-temperature exhaust gas environment, leading to a decrease in sealing contact pressure and gas leakage between the turbine housing and the nozzle mating surfaces. The sealing reliability gradually decreases with use, ultimately reducing turbine efficiency.

[0007] Therefore, it is desirable in the art to propose an improved turbocharger that can improve upon or avoid at least one of the defects of the existing turbochargers mentioned above. Summary of the Invention

[0008] The present invention was made in view of the above-mentioned technical problems, and its object is to provide a nozzle assembly for a turbocharger that can improve the versatility of the nozzle, so that the nozzle assembly can be more flexibly applied to turbochargers with turbine impellers that have different flow requirements.

[0009] According to a first aspect of the invention, a nozzle assembly for a turbocharger is provided, the turbocharger including a turbine and an intermediate body, the nozzle assembly including: a housing of the turbine; a nozzle having a plurality of blades extending from both sides of an annular nozzle body, each blade having a profile for guiding gas flow; and an insert disposed at the intermediate body and independent of the housing and the nozzle, wherein the nozzle is sandwiched between the housing and the insert in the axial direction of the turbocharger, such that the blades located on both sides of the nozzle body abut against the insert top surface of the insert and the inner peripheral surface of the housing, respectively.

[0010] In the nozzle assembly according to the invention, the nozzle with fixed blades is an independent component relative to the turbine housing and insert, and can be individually machined, for example, by machining or casting. Therefore, the machining accuracy of the nozzle blade profile is not limited by the clamping of the turbine housing. Furthermore, when the nozzle assembly needs to adapt to turbine impellers of different flow rates, only the nozzle needs to be replaced, while the turbine housing and insert can be reused in a modular manner. This improves the versatility of other components in the nozzle assembly and reduces the overall adaptation cost of the nozzle assembly to turbine impellers of different flow rates.

[0011] Preferably, the nozzle assembly according to the invention further includes an elastic element pre-tensioned between the intermediate body of the turbocharger and the insert, so as to press the insert top surface of the insert against the blade top surface of the nozzle blade in the axial direction of the turbocharger, such that the insert top surface of the insert is sealed against the blade top surface of the nozzle blade.

[0012] Therefore, in the nozzle assembly according to the invention, the preload of the elastic element ensures a contact surface seal between the top surface of the insert and the top surface of the blade, thereby ensuring sealing reliability, reducing the probability of exhaust gas leakage, and ensuring the working efficiency of the turbine.

[0013] Preferably, in the nozzle assembly according to the invention, no seal is provided between the insert and the nozzle, and no seal is provided between the nozzle and the turbine housing.

[0014] Here, the nozzle assembly according to the present invention achieves the assembly of the independent nozzle, insert, and turbine housing without the need for additional seals such as sealing rings, reducing the number of parts in the nozzle assembly, lowering the cost of the nozzle assembly, and simplifying the assembly of the nozzle assembly. Furthermore, by eliminating the use of seals, the risk of leakage caused by the gradual oxidation, creep, and loosening of seals under high-temperature exhaust gas conditions can be avoided.

[0015] Preferably, in the nozzle assembly according to the invention, the insert is designed to be annular, and an insert step is formed on the inner circumferential surface of the insert, wherein the elastic element is pre-tensioned and arranged between the intermediate body and the insert step.

[0016] Here, the aforementioned insert step portion and intermediate body of the insert provide a support interface for the elastic element, thereby enabling the preload of the elastic element to act on the insert, pressing the insert against the nozzle, and making the overall structure of the nozzle assembly compact.

[0017] In a preferred embodiment of the present invention, the elastic element is the cover spring of the turbocharger.

[0018] The cover spring is an existing component of the turbocharger. Using it as the pre-tensioned elastic element will not increase the number of parts in the nozzle assembly and the turbocharger, nor will it increase the assembly complexity of the nozzle assembly. Thus, while ensuring the flexibility and versatility of the nozzle assembly, it can also avoid increasing the cost of the turbocharger using the nozzle assembly according to the present invention.

[0019] In a preferred embodiment of the invention, the nozzle assembly further includes a pin for connecting the insert and the intermediate body. The intermediate body has an insert receiving portion in which the insert is received. An opening is provided at the bottom of the insert receiving portion, and a hole is provided in the bottom surface of the insert opposite to its top surface. The pin is disposed in the opening and the hole of the insert receiving portion.

[0020] Here, by using a pin to achieve a key connection between the insert in the nozzle assembly and the intermediate body of the turbocharger, the rotation of the insert relative to the intermediate body and its axial movement can be restricted, thereby providing stable axial support for the nozzle abutting the insert.

[0021] In a non-limiting embodiment of the present invention, the turbine housing has a vortex section, the housing resting on the intermediate body step portion of the intermediate body, the end face of the vortex section being designed to fit the side face of the intermediate body step portion, and the side face of the vortex section being designed to fit the bottom face of the intermediate body step portion.

[0022] Here, the turbine housing can be positioned axially relative to the intermediate body without the need for additional positioning structures, simplifying the assembly of the turbocharger using the nozzle assembly according to the invention.

[0023] In a non-limiting embodiment of the invention, the insert is received in the insert receiving portion of the intermediate body, and the outer peripheral surface of the insert is in contact with the end face of the vortex section of the turbine housing to form a contact surface.

[0024] Here, in the nozzle assembly according to the invention, a contact surface seal is also formed between the mating surfaces of the turbine housing and the insert, thereby preventing exhaust gas bypass leakage and reducing the turbine's operating efficiency.

[0025] In a non-limiting embodiment of the invention, the turbine housing section of the nozzle assembly has a partition wall. The partition wall divides the vortex section into a first flow channel and a second flow channel that are independent of each other.

[0026] Here, the nozzle assembly according to the invention is particularly suitable for turbines with a twin-vortex configuration.

[0027] Preferably, the partition wall end face of the partition wall of the turbine housing vortex section of the nozzle assembly is in contact with the nozzle outer peripheral surface of the nozzle.

[0028] Here, by ensuring the contact between the outer peripheral surface of the nozzle of the nozzle assembly and the end face of the partition wall of the turbine housing, possible leakage paths between the first and second flow channels in the vortex section of the turbine housing are avoided, thus ensuring the flow distribution accuracy of the dual vortex system. Preferably, the gas in the first and second flow channels of the turbine can be directed to the blades located on both sides of the nozzle body.

[0029] Preferably, in the nozzle assembly according to the invention, the nozzle body has a thickened outer peripheral portion such that the width of the outer peripheral surface of the nozzle is greater than the width of the inner peripheral surface of the nozzle.

[0030] Here, the thickened outer periphery of the nozzle body can improve the circumferential stiffness and deformation resistance of the nozzle, and provide a wider contact surface for the turbine housing part that contacts it, such as the partition wall end face of the partition wall of the vortex section, thereby achieving airtight reliability of the separation between the two flow channels.

[0031] Preferably, in the nozzle assembly according to the invention, the nozzle blades are designed with a slope or a non-planar slope.

[0032] In a non-limiting embodiment of the invention, the blade profiles on both sides of the nozzle body are identical.

[0033] Here, the manufacture and assembly of the nozzle assembly are convenient because the blades have the same design and construction profile.

[0034] Furthermore, the top surfaces of the inserts that provide support to the nozzle on both sides and the inner circumferential surfaces of the turbine housing are also symmetrically formed to be identical.

[0035] Alternatively, in the nozzle assembly according to the invention, the blade profiles on both sides of the nozzle body can be designed to be not entirely identical. For example, two or more different blade profile configurations can be provided among the multiple blades of the nozzle. During nozzle manufacturing, the blade profiles on both sides of the nozzle body are machined accordingly based on the specific turbine impeller flow rate specifications and inlet requirements.

[0036] Advantageously, the blade profile can be selected and customized according to the flow rate requirements and intake angle requirements of the turbine impeller in the turbocharger where the nozzle assembly is used. This allows for the production of fixed-blade nozzles with the corresponding profiles through machining or casting. Advantageously, for blades with different profiles, only the insert needs to be adapted to meet the axial direction of the nozzle assembly in the turbocharger and its width within the turbine, while keeping the turbine housing as universal as possible.

[0037] Preferably, in the nozzle assembly according to the invention, a plurality of blades located on both sides of the nozzle body are arranged circumferentially spaced apart from each other. For each blade, the direction of extension from the leading edge to the trailing edge is at a slope angle to the radial direction at the location of the trailing edge.

[0038] In the nozzle assembly according to the invention, the blades on the individually machined nozzle guide the exhaust gas to the turbine impeller at a suitable angle. The number of blades on the nozzle and the aforementioned slope angle, i.e., the angle between the extension direction of each blade from the leading edge to the trailing edge and the radial direction at the trailing edge, can be customized as needed during nozzle machining to match the flow requirements of different turbine impellers.

[0039] Optionally, multiple blades are evenly arranged in the circumferential direction on both sides of the nozzle body, that is, they are spaced apart by equal intervals to achieve the desired exhaust gas flow guidance effect.

[0040] Alternatively, as needed, multiple blades can be arranged non-uniformly in the circumferential direction on both sides of the nozzle body, that is, the spacing between the blades is not exactly the same.

[0041] Optionally, the slope angle of each blade on both sides of the nozzle body is the same to achieve the desired exhaust gas flow guidance effect and to simplify the manufacture and assembly of the nozzle assembly.

[0042] Alternatively, as needed, multiple blades on both sides of the nozzle body may have two or more different slope angles, especially slope angles of different sizes.

[0043] Preferably, in the nozzle assembly according to the invention, the plurality of blades located on both sides of the nozzle body are arranged in a mirror-symmetric manner with respect to the nozzle body, or the plurality of blades located on both sides of the nozzle body are arranged in a non-mirror-symmetric manner with respect to the nozzle body.

[0044] Here, when the blades on both sides of the nozzle body are arranged in a mirror-symmetric manner, it is advantageous in terms of the efficiency of manufacturing the nozzle and assembling the nozzle assembly, and at a lower cost. As for the case where the blades on both sides of the nozzle body are not mirror-symmetrically arranged, nozzles with this blade arrangement are particularly suitable for turbine casings with a twin-scroll configuration. This allows the blades on both sides of the nozzle to be adapted to different airflow requirements in the twin-scroll, optimizing the guiding efficiency of the nozzle assembly for gas in different flow channels under high gas flow conditions.

[0045] According to a second aspect of the invention, a turbocharger is also provided, comprising: a turbine having a housing; an intermediate body; and a nozzle assembly as described in any of the above embodiments.

[0046] The turbocharger is highly efficient, low-cost, and easy to maintain due to the high versatility of the nozzle assembly according to the invention, the high machining accuracy of the blade profile, and the reliable sealing.

[0047] Additional features and advantages described herein will be set forth in the detailed description below, and will be recognized by those skilled in the art as will be apparent from the following description or from practice of the embodiments described herein, including the detailed description below, the claims, and the accompanying drawings.

[0048] It should be understood that the foregoing general description and the following detailed description illustrate various embodiments and are intended to provide an overview or framework for understanding the nature and characteristics of the claimed subject matter. Drawings are included to provide a further understanding of the various embodiments, and these drawings are incorporated in and form part of this specification. The drawings illustrate the various embodiments described herein and, together with the description, serve to explain the principles and operation of the claimed subject matter. Attached Figure Description

[0049] With reference to the above objectives, the technical features of the present invention are clearly described in the following claims, and its advantages will be apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the invention by way of example, without limiting the scope of the inventive concept.

[0050] Figure 1 A partial assembly schematic diagram of a turbocharger having a nozzle assembly according to the present invention is shown; Figure 2 Enlarged display Figure 1 The nozzle assembly in the middle; Figure 3 Show Figure 1 A perspective view of the nozzle in the nozzle assembly shown; Figure 4 Showing the cross-section Figure 3 A partial schematic diagram of the nozzle blades shown; Figure 5 Showing the cross-section Figure 3 A partial schematic diagram of the non-blade section of the nozzle shown; Figure 6 Showing the cross section viewed from the side Figure 3 A perspective view of the nozzle blades shown; and Figure 7 Show Figure 1 A perspective view of the insert in the nozzle assembly shown.

[0051] List of reference numerals

[0052] 100 Nozzle Assembly

[0053] 10 nozzles

[0054] 11 Nozzle body

[0055] 12 blades

[0056] 13-face

[0057] 14. Nozzle outer circumference

[0058] 15. Nozzle inner circumferential surface

[0059] 16 Blade top surface

[0060] 20 Inserts

[0061] 21 Top surface of the insert

[0062] 22. Bottom surface of the insert

[0063] 23. Insert step section

[0064] 24. Outer periphery of the insert

[0065] 25 holes

[0066] 26 Inner circumferential surface of the insert

[0067] 30 sales

[0068] 200 intermediates

[0069] 210 Intermediate Step Section

[0070] 211 Side of the step

[0071] 212 Bottom surface of the step

[0072] 220 Insert receiving part

[0073] 221 Opening

[0074] 300 turbine

[0075] 310 Housing

[0076] 311 Vortex Section

[0077] 3111 End face of vortex channel section

[0078] 3112 Side of the vortex section

[0079] 312 partition wall

[0080] 3121 Partition wall end face

[0081] 313 First Stream

[0082] 314 Second Flow Channel

[0083] 315 inner peripheral surface

[0084] 320 turbine impeller

[0085] 340 cover spring

[0086] L leading edge end

[0087] T trailing edge end Detailed Implementation

[0088] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims. For ease of interpretation and precise definition in the appended claims, the terms “upper,” “lower,” “inner,” and “outer” are used to describe features with reference to their location in the exemplary embodiments shown in the figures.

[0089] It has been found that for turbochargers, when using an integrated nozzle in the turbine, the machining accuracy of the nozzle blade profile used for flow guidance is limited due to the integration of the nozzle with the turbine housing, thus affecting the nozzle's flow guidance and deflection effects. When using a separate nozzle in the turbine, because the turbine housing and turbine impeller specifications are matched, one nozzle can generally only be used for one type of turbine impeller, making it incompatible with different turbines. Furthermore, the assembly of the separate nozzle with the side support structures requires sealing rings to ensure airtightness, and these sealing rings gradually age with the operation of the turbocharger, leading to a decrease in airtightness and increasing turbine manufacturing costs.

[0090] To this end, the inventors have proposed a modular nozzle assembly for a turbocharger, which will now be described with reference to the accompanying drawings, generally given reference numeral 100.

[0091] like Figure 1 As shown, the turbocharger has an intermediate body 200 and a turbine 300. The turbine 300 has a housing 310.

[0092] The nozzle assembly 100 is located upstream of the turbine impeller 320 of the turbine 300 and includes a turbine housing 310, a nozzle 10, and an insert 20, which are independent of each other. Figure 1As can be seen, the nozzle 10 is sandwiched between the housing 310 and the insert 20, and is located near the vortex section 311 of the housing 310. The nozzle 10 is used to guide the exhaust gas entering the turbine 300 to the turbine impeller 320 to improve the turbine efficiency.

[0093] Figure 1 The turbine 300 shown has a housing 310 with a double-vortex design. In other embodiments not shown, the nozzle assembly 100 may also be adapted to turbines with various housing designs, such as single-vortex or fan-shaped partitioned vortex.

[0094] like Figure 2 As can be seen, the turbine casing 310 rests on the intermediate step portion 210 of the turbocharger intermediate body 200. The end face 3111 of the vortex section 311 of the turbine casing 310 is designed to fit with the side surface 211 of the step portion 210 of the intermediate body 200, and the side surface 3112 of the vortex section 311 of the casing 310 is designed to fit with the bottom surface 212 of the step portion 210 of the intermediate body 200. Therefore, the turbine casing 310 can be placed on the intermediate step portion 210 of the intermediate body 200 without the aid of additional positioning structures, thereby achieving initial axial positioning of the turbine casing 310.

[0095] like Figure 1 As can be seen, the vortex section 311 of the shell 310 has a double vortex design. The partition wall 312 divides the vortex section 311 into a first flow channel 313 and a second flow channel 314 that are independent of each other.

[0096] The nozzle 10, which is sandwiched between the insert 20 and the housing 310 of the turbine 300, is a separate component configured to guide gas flow. The nozzle 10 can be obtained by machining or by a lower-cost machining method, such as casting.

[0097] like Figure 3 As can be seen, the nozzle 10 has an annular nozzle body 11 and a plurality of blades 12 extending from two sides of the nozzle body 11. The blades 12 are integrally formed with the nozzle body 11. The blades 12 on both sides of the nozzle body 11 contact the insert top surface 21 of the insert 20 and the inner peripheral surface 315 of the housing 310 on both sides of the nozzle 10 with their blade top surfaces 16 respectively. Each blade 12 has a profile 13 extending from its respective leading edge end L to its trailing edge end T, that is, the blade surface of the blade 12.

[0098] Furthermore, referring to Figures 4 to 6The multiple blades 12 on both sides of the nozzle body 11 are designed and constructed in a mirror symmetrical manner with respect to the nozzle body 11.

[0099] Since the nozzle 10 is an independent component, the number of blades 12, the slope angle of the blades 12 relative to the nozzle body 11 in the radial direction, and the design and construction of the blade profile 13 can be set according to requirements, thereby adapting to different turbine performance requirements such as flow rate and inlet angle. The blade profile 13 can be planar, inclined, or especially non-planar. When the blade profile 13 adopts an inclined or sloped design or when adjusting the above-mentioned parameter settings, if it is necessary to adapt to the axial dimension requirements of the inclined or sloped profile, there is no need to change the design and construction of the housing 310; only the design and construction of the insert 20 need to be adapted accordingly. This makes the nozzle assembly 100 adaptable to different turbine impeller specifications at a lower cost and with higher flexibility.

[0100] In the illustrated embodiment, the nozzle 10 is an independent machined part made of stainless steel, allowing for precision machining of the blade 12's profile 13 independently. This eliminates the need for integral machining with the turbine housing 310, avoiding the limitations of machining space and reduced machining accuracy associated with one-piece molding, thus ensuring the machining quality of the blade 12's profile 13. In the illustrated embodiment, fifteen blades 12 are mirror-symmetrically arranged on both sides of the nozzle body 11. They are evenly spaced circumferentially on both sides of the nozzle body 11. The extension direction of each blade 12, from its leading edge L to its trailing edge T, forms a slope angle relative to the radial direction of its trailing edge T, thereby guiding the exhaust gas towards the turbine impeller 320 at a suitable angle.

[0101] Since the blade 12 can be machined separately, the profile tolerance and machining accuracy of the blade 12 can be improved compared to the one-piece nozzle mentioned at the beginning of this article, thereby effectively ensuring the aerodynamic performance of the profile 13.

[0102] In embodiments not shown, the number of blades 12 can be adjusted to match turbine impellers 320 with different flow rates, thereby enabling the nozzle assembly 100 to be adapted to turbine impellers 320 with different flow rates at a lower cost. For example, for turbine impellers 320 with small flow rates, the number of blades 12 of the nozzle 10 can be set to be more, while for turbine impellers 320 with large flow rates, the number of blades 12 of the nozzle 10 can be set to be less.

[0103] Furthermore, the following configuration of the blades 12 can be adjusted according to different flow specifications or flow requirements of the turbine impeller 320.

[0104] For example, in an embodiment not shown, for a turbine impeller 320 with a small flow rate, the slope angle between the extension direction of the blade 12 and the radial direction at the position of the trailing edge end T of the blade 12 can be set to a larger value, that is, the extension direction of the blade 12 is relatively flat relative to the horizontal direction. For a turbine impeller 320 with a large flow rate, the slope angle between the extension direction of the blade 12 and the radial direction at the position of the trailing edge end T of the blade 12 can be set to a smaller value, that is, the extension direction of the blade 12 is relatively oblique relative to the horizontal direction.

[0105] For example, in an embodiment not shown, for a turbine impeller 320 with a small flow rate, the profile 13 of the blade 12 can be designed as a flat inclined surface, while for a turbine impeller 320 with a large flow rate, the profile of the blade 12 can be designed as an optimized curved surface profile. In particular, the blades 12 on both sides of the nozzle 10 can also adopt a non-mirror symmetrical structure to optimize the airflow guiding efficiency under high flow rates.

[0106] In other embodiments, for turbine impellers 320 with specific flow characteristics, the profile 13 of blades 12 may also be set as an inclined or sloped surface.

[0107] When the nozzle 10 is modified to adapt to the flow requirements or flow characteristics of different turbine impellers 320, if the axial width of the nozzle 10 remains unchanged, that is, the distance from the blade tip surface 16 of one side blade 12 to the blade tip surface 16 of the other side blade 12 remains unchanged, there is no need to change the design and structure of the insert 20, and the casing 310 of the turbine 300 can remain as unchanged as possible.

[0108] Figure 7 The insert 20 of the nozzle assembly 100 is shown. The insert 20 is also a separate component, designed in a ring shape. The ring-shaped insert 20 is disposed in the insert receiving portion 220 of the intermediate body 200. An opening 221 is provided in the insert receiving portion 220. A hole 25 is provided on the bottom surface 22 of the insert 20, opposite the top surface 21, and it is keyed to the intermediate body 200 by means of a pin 30. The pin 30 is accommodated in the opening 221 of the insert receiving portion 220 and the hole 25 of the insert 20. This achieves positioning of the insert 20 in both the circumferential and axial directions. The keyed engagement of the pin 30 with the intermediate body 200 restricts the rotation of the insert 20 in the circumferential direction and its axial movement, thereby providing axial support for the nozzle 10 in the turbine 300.

[0109] In the illustrated embodiment, the insert top surface 21 of the insert 20, that is, the surface that makes surface contact with the blade top surface 16 of the blade 12 of the nozzle 10, is formed as an inclined surface, gradually rising from the periphery of the insert 20 toward the center of the insert 20.

[0110] Reference Figure 2 and Figure 7 As can be seen, an insertion step 23 is formed at the inner circumferential surface 26 of the annular insertion 20. A pre-tensioned elastic element, such as a cover spring 340, is pre-tensioned and arranged between the intermediate body 200 and the insertion step 23, thereby... Figure 2 In the diagram shown, an axial clamping force is applied to the insert 20, pressing the insert 20, which is located in the insert receiving portion 220, against the blade top surface 16 of the blade 12 of the nozzle 10. This achieves a tight fit between the insert top surface 21 of the insert 20 and the blade top surface 16 of the blade 12, allowing the nozzle assembly 100 to achieve a surface seal between the insert 20 and the nozzle 10 without the need for additional sealing components. This ensures the operating efficiency of the turbine 300. Furthermore, the cover spring 340 is an existing component in the turbocharger and does not increase the assembly complexity or the number of parts in the turbocharger. Since both the blade top surface 16 of the nozzle 10 blade 12 and the insert top surface 21 of the mating insert 20 are precision machined, a contact seal can be achieved by improving the surface machining accuracy of the mating surfaces between the nozzle 10 and the insert 20. Therefore, the airtightness of the contact surface between the nozzle 10 and the insert 20 is guaranteed by the tight fit of the high-precision mating surfaces. Because the contact surface is close to the flow path of the exhaust gas in the turbine 300, the reliability requirements for its sealing are high.

[0111] It is conceivable that other pre-tensioned elastic elements could also be provided to maintain the fit between the insert 20 and the nozzle 10, such as disc springs, wave springs or other elastic elements that can provide axial preload.

[0112] The outer peripheral surface 24 of the insert 20, received in the insert receiving portion 220, and the end face 3111 of the vortex section 311 of the housing 310 form a contact surface. Ideally, this contact surface is arranged in a planar structure to achieve a contact-type surface seal. The material of the insert 20 is selected such that its coefficient of thermal expansion matches that of the material of the housing 310 of the turbine 300. This avoids changes in the gap between the mating surfaces of the vortex section end face 3111 of the housing 310 and the outer peripheral surface 24 of the insert 20 under high-temperature exhaust gas conditions due to the difference in thermal expansion between the insert 20 and the housing 310, which would affect the sealing of the nozzle assembly 100 and the positioning accuracy of the insert 20. This, in turn, would adversely affect the positioning of the nozzle 10 and the airflow guiding efficiency of its blades 12. The sealing reliability requirement at this location is lower than the sealing reliability requirement of the contact surface between the insert top surface 21 of the insert 20 and the blade top surface 16 of the blade 12 mentioned above.

[0113] In the illustrated embodiment, the partition wall end face 3121 of the partition wall 312 is in contact with the nozzle outer peripheral surface 14 of the nozzle 10. Figure 3 and Figure 5 It can also be seen that the width of the outer peripheral surface 14 of the nozzle 10 is greater than the width of the inner peripheral surface 15 of the nozzle. In other words, the nozzle 10 has a thickened outer peripheral portion.

[0114] The specific steps for assembling the nozzle assembly 100 are as follows: First, the insert 20 is fixed to the intermediate body 200 by the pin 30; Subsequently, the nozzle 10 with the fixed blade 12 is positioned at the top surface 21 of the insert 20; Next, the housing 310 of the turbine 300 is placed on the intermediate body step 210 of the intermediate body 200, such that the end face 3111 of the vortex section of the housing 310 abuts against the outer peripheral surface 24 of the insert 20 and the side surface 211 of the step portion of the intermediate body step 210, thereby supporting the nozzle 10 from both sides in the axial direction of the turbocharger with the insert 20, and stably clamping the nozzle 10 with fixed blades between the two.

[0115] Thus, the assembly of the nozzle assembly 100 in the turbocharger is completed. When the turbocharger is working, the exhaust gas from the engine flows through the first flow channel 313 and the second flow channel 314 in the vortex section 311 of the turbine housing 300 to the exhaust gas flow path where the nozzle 10 is located. In this flow path, the exhaust gas is guided by the blades 12 of the nozzle 10 and rushes towards the turbine impeller 320 at a suitable angle, driving the turbine impeller 320 to rotate.

[0116] In the nozzle assembly 100, the housing 310 and insert 20 of the turbine 300 can be designed independently according to the intermediate body 200 of the applicable turbocharger, without the need for adjustment when the nozzle 10 or turbine impeller 320 is replaced. This allows turbine impellers 320 with different flow rate specifications to share the same set of turbine 300 housing 310 and insert 20 for the nozzle assembly 100, and adaptation can be achieved simply by replacing the nozzle 10 with the blade 12 of the corresponding profile 13.

[0117] In the nozzle assembly 100, a three-section modular separable structure is achieved by providing the nozzle 10 with fixed blades 12, the insert 20, and the turbine housing 310 as three independent components. As mentioned above, the nozzle 10, as an independent and replaceable component, can be machined or selected with corresponding, matching blades 12 and profiles 13 parameters according to different turbine impeller specifications. When the turbine impeller 320 specifications change, only the pre-tightened elastic element needs to be released and the nozzle 10 with the appropriate blade profile 13 needs to be replaced, while the turbine housing 310 and insert 20 remain universal for different turbine impeller 320 specifications.

[0118] The housing 310 and insert 20 of the turbine 300 can be adapted to the corresponding intermediate body 200, thus making the housing 310 and insert 20 a platform-reusable common part. This avoids the problem of machining a matching nozzle structure for each turbine impeller 320, shortens the development cycle, and reduces processing costs because the nozzle 10 can be machined separately. The nozzle assembly 100 eliminates the need to machine an entire nozzle structure separately for different specifications of turbine impellers 320, avoiding the problems of poor versatility and low adaptability of existing fixed-blade nozzles. In addition, the independently machined nozzle 10 can achieve higher machining accuracy of the blade 12 profile 13. Combined with the elastic preload component and high-precision machined mating surfaces, it achieves contact surface sealing, meeting the sealing requirements without the need for additional sealing rings. This avoids the problem of sealing ring failure in the high-temperature operating environment of exhaust gas in existing separate nozzles.

[0119] The nozzle assembly 100 achieves a balance of high performance, low cost, and high flexibility, reducing the processing and adaptation costs of the nozzle structure for turbochargers.

[0120] Other implementation methods

[0121] Although this application has been described with reference to examples of nozzle assemblies for turbines used in turbochargers in the accompanying drawings, it should be understood that embodiments within the scope of this application are applicable to fixed flow guide nozzles or fluid machinery flow guides of other turbine machinery having similar structures and / or functions.

[0122] Although the arrangement of the blades 12 of the nozzle 10 has been described above with reference to the accompanying drawings, wherein the blades 12 on both sides of the nozzle body 11 are arranged in a mirror-symmetric manner with respect to the nozzle body 11, in other embodiments not shown, the blades 12 on both sides of the nozzle body 11 may also be arranged non-mirror-symmetrically with respect to the nozzle body 11 as needed, that is, the blades 12 on both sides of the nozzle body 11 are arranged independently of each other. This non-mirror-symmetric arrangement of the blades 12 on both sides of the nozzle body 11 is particularly suitable for the housing 310 of a turbine 300 with a twin-vortex design, to accommodate the airflow requirements of the two vortices respectively. Accordingly, the insert top surface 21 of the insert 20 on both sides of the nozzle body 11 that contacts the blades 12 of the nozzle 10 and provides support to the nozzle 10, and the inner peripheral surface 315 of the housing 310 of the turbine 300 may be constructed non-mirror-symmetrically.

[0123] Although the arrangement of the blades 12 of the nozzle 10 has been described above with reference to the accompanying drawings, wherein the blades 12 on both sides of the nozzle body 11 are uniformly arranged in the circumferential direction, that is, the blades 12 are uniformly spaced apart, in other embodiments not shown, the blades 12 on both sides of the nozzle body 11 may also be non-uniformly arranged in the circumferential direction as needed.

[0124] Although the arrangement of the blades 12 of the nozzle 10 has been described above with reference to the accompanying drawings, wherein the slope angle formed by the extending direction of the leading edge L to the trailing edge T of each blade 12 and the radial direction at the location of the trailing edge T of the blade 12 is the same, in other embodiments not shown, the aforementioned slope angles of the blades 12 can be formed differently from each other as needed during the machining of the nozzle 10. For example, a plurality of blades 12 on both sides of the nozzle body 11 may have at least two different sizes of slope angles.

[0125] Although the arrangement of the blades 12 of the nozzle 10 has been described above with reference to the accompanying drawings, wherein the design of the profile 13 of each blade 12 from the leading edge L to the trailing edge T is the same, in other embodiments not shown, different profiles 13 may be used in the plurality of blades 12 as needed.

[0126] The foregoing description has already given many features and advantages, including various alternative implementations, as well as details of the structure and function of the apparatus and methods. This document is intended to be exemplary and is not exhaustive or limiting.

[0127] It will be apparent to those skilled in the art that various modifications can be made within the full scope indicated by the broad superordinate meaning of the terms expressed in the appended claims, particularly in terms of structure, materials, elements, components, shapes, dimensions, and arrangements of components, including combinations of these aspects within the scope of the principles described herein. Such various modifications are intended to be included herein, provided they do not depart from the spirit and scope of the appended claims.

Claims

1. A nozzle assembly (100) for a turbocharger, the turbocharger comprising a turbine (300) and an intermediate body (200), characterized in that, The nozzle assembly (100) includes: The casing (310) of the turbine (300); The nozzle (10) has a plurality of blades (12) extending from both sides of an annular nozzle body (11), each blade (12) having a profile (13) for guiding gas flow; An insert (20) is disposed at the intermediate body (200) and is independent of the housing (310) and the nozzle (10). The nozzle (10) is sandwiched between the housing (310) and the insert (20) in the axial direction of the turbocharger, such that the blades (12) located on both sides of the nozzle body (11) abut against the insert top surface (21) of the insert (20) and the inner peripheral surface (315) of the housing (310) with their respective blade top surfaces (16).

2. The nozzle assembly (100) as claimed in claim 1, characterized in that, The nozzle assembly (100) further includes an elastic element that is pre-tensioned and arranged between the intermediate body (200) of the turbocharger and the insert (20) to press the insert top surface (21) of the insert (20) against the blade top surface (16) of the blade (12) of the nozzle (10) in the axial direction, such that the insert top surface (21) of the insert (20) is sealed against the blade top surface (16) of the blade (12) of the nozzle (10).

3. The nozzle assembly (100) as claimed in claim 2, characterized in that, No seal is provided between the insert (20) and the nozzle (10), nor is a seal provided between the nozzle (10) and the housing (310) of the turbine (300).

4. The nozzle assembly (100) as claimed in claim 2, characterized in that, The insert (20) is designed to be annular, and an insert step (23) is formed on the insert inner circumferential surface (26) of the insert (20). The elastic element is pre-tensioned and arranged between the intermediate body (200) and the insert step (23).

5. The nozzle assembly (100) as claimed in any one of claims 2 to 4, characterized in that, The elastic element is the cover spring (340) of the turbocharger.

6. The nozzle assembly (100) as claimed in claim 1, characterized in that, The nozzle assembly (100) further includes a pin (30) for connecting the insert (20) and the intermediate body (200), and the intermediate body (200) has an insert receiving portion (220) in which the insert (20) is accommodated. The bottom of the insert receiving portion (220) has an opening (221), and the bottom surface (22) of the insert (20) opposite to the top surface (21) of the insert has a hole (25). The pin (30) is disposed in the opening (221) and the hole (25) of the insert receiving portion (220).

7. The nozzle assembly (100) as claimed in claim 1, characterized in that, The housing (310) has a vortex section (311) which rests on the intermediate body step (210) of the intermediate body (200). The end face (3111) of the vortex section (311) is designed to fit the side face (211) of the intermediate body step (210), and the side face (3112) of the vortex section (311) is designed to fit the bottom face (212) of the intermediate body step (210).

8. The nozzle assembly (100) as claimed in claim 7, characterized in that, The insert (20) is received in the insert receiving portion (220) of the intermediate body (200), and the insert outer peripheral surface (24) of the insert (20) is fitted with the end face (3111) of the vortex section (311) of the housing (310) of the turbine (300) to form a contact surface.

9. The nozzle assembly (100) as claimed in claim 7, characterized in that, The vortex section (311) has a partition wall (312) that divides the vortex section (311) into a first flow channel (313) and a second flow channel (314) that are independent of each other.

10. The nozzle assembly (100) as claimed in claim 9, characterized in that, The partition wall end face (3121) of the partition wall (312) is in contact with the nozzle outer peripheral surface (14) of the nozzle (10).

11. The nozzle assembly (100) as claimed in claim 1, characterized in that, The nozzle body (11) of the nozzle (10) has a thickened outer peripheral portion, such that the width of the outer peripheral surface (14) of the nozzle (10) is greater than the width of the inner peripheral surface (15) of the nozzle (10).

12. The nozzle assembly (100) as claimed in claim 1, characterized in that, The blade (12) of the nozzle (10) is designed with a slope or a non-planar slope.

13. The nozzle assembly (100) as claimed in claim 1, characterized in that, The multiple blades (12) located on both sides of the nozzle body (11) are arranged spaced apart from each other in the circumferential direction, wherein for each blade (12), the extension direction from the leading edge end (L) to the trailing edge end (T) of the blade (12) forms a slope angle with the radial direction at the location of the trailing edge end (T).

14. The nozzle assembly (100) as claimed in claim 13, characterized in that, The slope angle of each blade (12) is the same.

15. The nozzle assembly (100) as claimed in claim 13, characterized in that, The plurality of blades (12) have at least two different slope angles.

16. The nozzle assembly (100) as claimed in claim 1, characterized in that, The multiple blades (12) located on both sides of the nozzle body (11) are arranged in a mirror symmetry with respect to the nozzle body (11), or the multiple blades (12) located on both sides of the nozzle body (11) are arranged in a non-mirror symmetry with respect to the nozzle body (11).

17. A turbocharger, characterized in that, The turbocharger includes: A turbine (300) having a housing (310); Intermediate (200); and The nozzle assembly (100) according to any one of claims 1 to 16.

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