Turbine structure
By designing a wheel back chamfer in the turbine structure and optimizing stress distribution, the stress concentration problem of traditional turbine structures under high speed and high temperature environments is solved, improving the fatigue life and structural strength of the turbine, and enhancing reliability and safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-24
- Publication Date
- 2026-04-10
AI Technical Summary
Traditional turbine structures are prone to stress concentration under high-speed rotation and high-temperature environments, especially at the junction of the turbine back and the blades, leading to fatigue cracks and structural failure. Existing technologies lack chamfer design and fail to fully utilize the strength of the material and optimize stress distribution.
Design a turbine structure in which a wheel back chamfer is formed between the wheel back section and the connecting section of the turbine body, including a first chamfer section and a second chamfer section. The chamfer radius of the first chamfer section is larger than that of the second chamfer section. The stress distribution is optimized and stress concentration is reduced by using two chamfer sections with different degrees of curvature.
It improves the fatigue life and overall structural strength of the turbine, is suitable for high-speed and high-temperature environments, enhances the reliability and safety of the turbine, and reduces the stress concentration factor by more than 50%.
Smart Images
Figure CN224107457U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to turbine technical field especially a turbine structure. BACKGROUND
[0002] With the increasingly prominent environmental problems and energy resources, turbocharger constitutes indispensable parts of engine. Turbocharger is full use exhaust pipe exhausts high temperature waste gas contains thermal energy, kinetic energy and pressure energy, blows turbine high speed rotation, thereby drives on same rotating shaft's air compressor impeller high speed rotation, makes the air density that enters engine cylinder increases, has increased engine intake, has improved engine power, has reduced fuel consumption rate, has reduced waste gas pollution, has reduced emission level, has energy -conserving, environmental protection efficacy.
[0003] And turbine is one of the core parts of the supercharger, the structural design, structural strength and durability reliability requirement of the turbine directly determines the performance, service life, emission effect of the supercharger, therefore, the structural optimization of the turbine is particularly important.
[0004] The traditional turbine structure is prone to stress concentration under high speed rotation and high temperature environment, especially at the connecting part of the back of the wheel and the blade, leading to fatigue crack and structural failure, in the prior art, the back of the turbine lacks chamfered circumference design, and the strength of the material cannot be fully utilized and the stress distribution is not optimized, so that stress concentration is easily generated, reducing the service life of the turbocharger.
[0005] In view of this, it is necessary to provide a turbine structure to solve or at least alleviate the above-mentioned defects. CONTENT OF THE UTILITY MODEL
[0006] The main purpose of the utility model is to provide a turbine structure to solve the problem of stress concentration caused by the lack of chamfered design of the back of the turbine structure in the prior art.
[0007] To achieve the above-mentioned purpose, the utility model provides a turbine structure, which comprises a turbine body and a plurality of turbine blades, wherein,
[0008] The plurality of turbine blades are arranged along the circumference of the turbine body and connected to the turbine body.
[0009] The turbine body comprises a back section and a connecting section, and a back chamfer is formed between the back section and the connecting section, the back chamfer comprises a first chamfer section and a second chamfer section, wherein,
[0010] The first end of the first chamfer section is connected with the outer ring side of the back section, the second end of the first chamfer section is connected with the first end of the second chamfer section, the second end of the second chamfer section is connected with the connecting section, and the chamfer radius of the first chamfer section is greater than the chamfer radius of the second chamfer section.
[0011] Preferably, the chamfer radius of the first chamfer section ranges from 37mm to 39mm.
[0012] Preferably, the chamfer radius of the second chamfer section ranges from 17mm to 19mm.
[0013] Preferably, the chamfer radius of the first chamfer section is 38mm, and the chamfer radius of the second chamfer section is 18mm.
[0014] Preferably, the first chamfer section and the second chamfer section are integrally arranged.
[0015] Preferably, a third chamfer section is formed on the outer ring side of the connecting section, and one end of the third chamfer section close to the back section is connected with the second end of the second chamfer section.
[0016] Preferably, the number of the turbine blades is twelve, and the twelve turbine blades are arranged at intervals along the circumference of the turbine body.
[0017] Preferably, the blade surface of each turbine blade is arranged in a curved shape.
[0018] Preferably, the turbine blades are arranged at equal intervals.
[0019] Compared with the prior art, the turbine structure has the following beneficial effects:
[0020] The turbine structure comprises a turbine body and a plurality of turbine blades, the plurality of turbine blades are arranged at intervals along the circumference of the turbine body and connected to the turbine body, the turbine body comprises a back section and a connecting section, a back chamfer is formed between the back section and the connecting section, the back chamfer comprises a first chamfer section and a second chamfer section, the first end of the first chamfer section is connected with the outer ring side of the back section, the second end of the first chamfer section is connected with the first end of the second chamfer section, and the second end of the second chamfer section is connected with the connecting section. Thus, the stress distribution is optimized by arranging the back chamfer, and the fatigue life of the turbine is improved; the back chamfer is divided into two chamfer sections with different bending degrees, the chamfer radius of the first chamfer section is greater than the chamfer radius of the second chamfer section, the bending degree of the chamfer close to the inner ring side of the back is greater, the root stress concentration can be better reduced, the overall structural strength of the turbine is optimized, the turbine is suitable for high-speed and high-temperature environments, and the reliability and safety of the turbine are improved. BRIEF DESCRIPTION OF DRAWINGS
[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or in the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings described below only show some of the embodiments of the present application, and for those skilled in the art, other drawings can also be obtained according to the structures shown in the drawings without creative labor.
[0022] Figure 1 It is a front view of the overall structure in an embodiment of the present application.
[0023] Figure 2 It is a partial enlarged view of the wheel back chamfer in an embodiment of the present application.
[0024] Figure 3 It is a stress distribution diagram of the turbine structure of the prior art before optimization.
[0025] Figure 4 It is a stress distribution diagram of the turbine structure in the present application after optimization.
[0026] The purposes, functional features and advantages of the present application will be further described with reference to the embodiments and the drawings.
[0027] Explanation of the drawings:
[0028] 10, turbine body; 110, wheel back section; 120, connecting section; 121, third chamfer section; 130, wheel back chamfer; 131, first chamfer section; 132, second chamfer section; 20, turbine blade. DETAILED DESCRIPTION
[0029] It should be understood that the specific embodiments described herein are only used to explain the present application, and are not used to limit the present application.
[0030] The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.
[0031] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative position relationship, movement condition, etc. between the components in a certain posture (as shown in the drawings), and if the certain posture changes, the directional indications also change accordingly.
[0032] In addition, the description of "first", "second" and the like in the present application is only for the purpose of description and cannot be understood as indicating or implying the relative importance of the technical features or implying the number of the technical features indicated. Therefore, the features limited by "first" and "second" can explicitly or implicitly include at least one of the features. In addition, the technical solutions of various embodiments can be combined with each other, but it must be based on the realization of ordinary skilled in the art, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, nor in the protection scope required by the present application.
[0033] Please refer to the accompanying Figures 1-4 The present application provides a turbine structure in one embodiment, comprising a turbine body 10 and a plurality of turbine blades 20. Specifically as follows:
[0034] A plurality of turbine blades 20 are arranged along the circumference of the turbine body 10 and connected to the turbine body 10; the turbine body 10 comprises a back section 110 and a connecting section 120, a back chamfer 130 is formed between the back section 110 and the connecting section 120, the back chamfer 130 comprises a first chamfer section 131 and a second chamfer section 132; wherein the first end of the first chamfer section 131 is connected to the outer ring side of the back section 110, the second end of the first chamfer section 131 is connected to the first end of the second chamfer section 132, the second end of the second chamfer section 132 is connected to the connecting section 120, and the chamfer radius of the first chamfer section 131 is greater than that of the second chamfer section 132.
[0035] Specifically, the turbine body 10 is used for mounting the turbine blade 20 to form a complete turbine structure, and is usually provided with a plurality of turbine blades 20, which are arranged along the circumference of the turbine structure and connected to the turbine body 10 (rotor shaft). Preferably, the number of turbine blades 20 can be twelve, and twelve turbine blades 20 are arranged along the circumference of the turbine body 10. In addition to the structures well known to those skilled in the art such as rotor shaft and hub, the turbine body 10 further comprises a back section 110 and a connecting section 120, and the connecting section 120 is used to connect with the turbine shaft. Therefore, when the turbine shaft is driven to rotate, stress concentration phenomenon is usually generated between the back section 110 and the connecting section 120, resulting in fatigue crack and structural failure. The present application forms a back chamfer 130 between the back section 110 and the connecting section 120, and reduces stress concentration by increasing the structure of the back chamfer 130.
[0036] Wherein, the back chamfer 130 comprises a first chamfer section 131 (such as Figure 2 R1) and a second chamfer section 132 (such as Figure 2As shown in R2), by adopting the form of two different bending degree chamfer sections to form the structural form of different structural thickness and chamfer size, in detail, the first chamfer section 131 is arranged close to the outer ring side of the back section 110, so that the first end of the first chamfer section 131 is connected with the outer ring side of the back section 110, and the second chamfer section 132 is arranged close to the connecting section 120 (the inner ring side of the back section 110, i.e. the root), so that the second end of the second chamfer section 132 is connected with the connecting section 120, and the first chamfer section 131 and the second chamfer section 132 are connected with each other, and in the processing, the first chamfer section 131 and the second chamfer section 132 can be arranged in one piece, so that the curved surface is relatively smooth and no cracks are generated; and in a preferred embodiment of the present application, the chamfer radius of the first chamfer section 131 is greater than the chamfer radius of the second chamfer section 132, and it can be understood that the greater the chamfer radius, the more gentle the bending degree of the chamfer arc, so that in the range of similar arc length, the part with smaller chamfer radius has greater bending degree of the arc, so that the distance from the axis of the back section 110 is greater, that is, the bending degree of the arc of the second chamfer section 132 is more curved than that of the first chamfer section 131, and the closer to the inner ring side (root) of the back section 110, the greater the distance from the axis of the back section 110, so as to just reduce the problem of stress concentration at the inner ring side (root) of the back section 110, thereby improving the fatigue life of the turbine, optimizing the overall structural strength of the turbine, and being suitable for high speed and high temperature environment; improving the reliability and safety of the turbine.
[0037] Preferably, the chamfer radius of the first chamfer section 131 is in the range of 37mm-39mm, and the chamfer radius of the second chamfer section 132 is in the range of 17mm-19mm, in the connection of the two chamfer sections in this range, the stress concentration at the root can be reduced, and the normal operation of the structure of the component can be met, so as to improve the fatigue life of the turbine structure, and it should be noted that this range is obtained through calculation and analysis and combined with actual working condition test.
[0038] In a preferred embodiment of the present application, the chamfer radius of the first chamfer section 131 is 38mm, and the chamfer radius of the second chamfer section 132 is 18mm, and the first chamfer section 131 and the second chamfer section 132 form the back chamfer 130, and compared with the traditional turbine structure, the back chamfer 130 increases the root mass, and through finite element analysis (FEA) and actual working condition test, it is verified that the turbine structure of the present application has excellent performance in high speed (>10,000rpm) and high temperature (>800℃) environment, and the stress concentration coefficient is reduced by more than 50%, which is verified by finite element analysis and actual working condition test, and specific reference is made to the attached Figure 3 ~attachedFigure 4 The third chamfer section 121 is connected to the second end of the second chamfer section 132.
[0039] Further, the outer ring side of the connecting section 120 is formed with a third chamfer section 121, which is connected to the second end of the second chamfer section 132 near one end of the wheel back section 110.
[0040] It should be noted that the third chamfer section 121 can make the connection between the connecting section 120 and the wheel back chamfer 130 more smooth, so as to avoid the sudden change of the structural surface bending form and the large stress mutation rate, thereby affecting the structural strength of the connection between the connecting section 120 and the wheel back chamfer 130. Therefore, the third chamfer section 121 is connected to the second end of the second chamfer section 132 near one end of the wheel back section 110; wherein the chamfer radius of the third chamfer section 121 can be set to 2.5mm, which can be tested and set according to the width of the connecting section 120 and the smoothness of the connection, and the person skilled in the art can select according to the actual situation.
[0041] Further, the blade surface of each turbine blade 20 is arranged in a curved shape.
[0042] It should be noted that in this way, the aerodynamic performance can be improved, the secondary flow loss can be reduced, and the reaction degree can be uniformized along the blade height by reasonably organizing the flow of low-energy fluid, thereby improving the flow condition of the blade root area.
[0043] Further, the plurality of turbine blades 20 are arranged at equal intervals.
[0044] It should be noted that the equal interval arrangement can improve the uniformity of airflow flow, reduce energy loss, and thereby improve the aerodynamic efficiency of the turbine.
[0045] The above is only the preferred embodiment of the present application, and does not limit the patent range of the present application, and any equivalent structure or equivalent process transformation using the content of the present application specification and drawings, or direct or indirect application in other related technical fields, are also included in the patent protection range of the present application.
Claims
1. A turbine structure, characterized by, The turbine body and a plurality of turbine blades are included; wherein The plurality of turbine blades are arranged at intervals along the circumference of the turbine body and connected to the turbine body; The turbine body includes a back section and a connecting section, and a back chamfer is formed between the back section and the connecting section, the back chamfer including a first chamfer section and a second chamfer section; wherein The first end of the first chamfer section is connected to the outer ring side of the back section, the second end of the first chamfer section is connected to the first end of the second chamfer section, the second end of the second chamfer section is connected to the connecting section, and the chamfer radius of the first chamfer section is greater than the chamfer radius of the second chamfer section.
2. The turbine structure of claim 1, wherein The chamfer radius of the first chamfer section ranges from 37mm to 39mm.
3. The turbine structure of claim 2, wherein, The chamfer radius of the second chamfer section ranges from 17mm to 19mm.
4. The turbine structure of claim 3, wherein, The chamfer radius of the first chamfer section is 38mm, and the chamfer radius of the second chamfer section is 18mm.
5. The turbine structure of claim 1, wherein The first chamfer section and the second chamfer section are integrally formed.
6. The turbine structure of claim 1, wherein The outer ring side of the connecting section is formed with a third chamfer section, one end of the third chamfer section close to the back section is connected to the second end of the second chamfer section.
7. The turbine structure of claim 1, wherein The number of the turbine blades is twelve, and the twelve turbine blades are arranged at intervals along the circumference of the turbine body.
8. The turbine structure of claim 7, wherein, The surface of each turbine blade is curved.
9. The turbine structure of claim 7, wherein, The plurality of turbine blades are equidistantly arranged.