Turbine structure

Abstract

The invention provides a turbine structure which comprises a turbine body and a plurality of turbine blades, the turbine blades are arranged on the turbine body at intervals in the circumferential direction of the turbine body, the turbine body comprises a wheel back section and a connecting section, a wheel back chamfer is formed between the wheel back section and the connecting section, the wheel back chamfer comprises a first chamfer section and a second chamfer section, and the first chamfer section and the second chamfer section are arranged in a staggered mode. The first end of the first chamfer section is connected with the outer ring side of the wheel 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. The stress distribution is optimized by arranging the wheel back chamfer, and the fatigue life of the turbine is prolonged; the wheel back is divided into two chamfer sections with different bending degrees, and the chamfer radius of the first chamfer section is larger than that of the second chamfer section, so that the chamfer bending degree of the wheel back close to the inner ring side is larger, the root stress concentration can be better reduced, the overall structural strength of the turbine is optimized, and the turbine is suitable for high-rotating-speed and high-temperature environments; and the reliability and the safety of the turbine are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of turbines, in particular to a turbine structure. Background Art

[0002] With increasingly prominent environmental issues and energy resource constraints, turbochargers have become an indispensable component of engines. Turbochargers fully utilize the heat, kinetic, and pressure energy contained in high-temperature exhaust gases from the exhaust pipe to drive the turbine wheel at high speed, thereby driving the compressor impeller on the same shaft at high speed. This increases the density of air entering the engine cylinders, increasing the engine's air intake, improving engine power, reducing fuel consumption, exhaust pollution, and lowering emissions, resulting in energy-saving and environmentally friendly benefits.

[0003] The turbine is one of the core components of the supercharger. The structural design, structural strength and durability and reliability requirements of the turbine directly determine the performance, service life and emission effect of the supercharger. Therefore, the structural optimization of the turbine is particularly important.

[0004] Traditional turbine structures are prone to stress concentration under high-speed rotation and high-temperature environments, especially at the connection between the wheel back and the blades, leading to fatigue cracks and structural failure. In existing technologies, the wheel back of the turbine lacks a chamfered circumferential design, fails to fully utilize the strength of the material and optimize stress distribution, which easily causes stress concentration and reduces the service life of the turbocharger.

[0005] In view of this, it is necessary to propose a turbine structure to solve or at least alleviate the above-mentioned defects. Summary of the Invention

[0006] The main purpose of the present invention is to provide a turbine structure to solve the problem in the prior art that the wheel back of the turbine structure lacks a rounded corner design and is prone to cause stress concentration.

[0007] To achieve the above-mentioned object, the present invention provides a turbine structure, comprising a turbine body and a plurality of turbine blades; wherein,

[0008] The plurality of turbine blades are spaced apart along the circumference of the turbine body and connected to the turbine body;

[0009] The turbine body includes a wheel back section and a connecting section, a wheel back chamfer is formed between the wheel back section and the connecting section, and the wheel back chamfer includes a first chamfer section and a second chamfer section; wherein,

[0010] The first end of the first chamfered segment is connected to the outer ring side of the wheel back segment, the second end of the first chamfered segment is connected to the first end of the second chamfered segment, the second end of the second chamfered segment is connected to the connecting segment, and the chamfer radius of the first chamfered segment is greater than the chamfer radius of the second chamfered segment.

[0011] Preferably, the chamfer radius of the first chamfered section ranges from 37 mm to 39 mm.

[0012] Preferably, the chamfer radius of the second chamfered section is in the range of 17 mm to 19 mm.

[0013] Preferably, the chamfer radius of the first chamfered section is 38 mm, and the chamfer radius of the second chamfered section is 18 mm.

[0014] Preferably, the first chamfered section and the second chamfered section are integrally formed.

[0015] Preferably, a third chamfered section is formed on the outer ring side of the connecting section, and one end of the third chamfered section close to the wheel back section is connected to the second end of the second chamfered 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 plurality of turbine blades are arranged at equal distances from each other.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] The present invention provides a turbine structure comprising a turbine body and a plurality of turbine blades, wherein the plurality of turbine blades are arranged at intervals along the circumference of the turbine body and connected to the turbine body, wherein the turbine body comprises a wheel back section and a connecting section, wherein a wheel back chamfer is formed between the wheel back section and the connecting section, wherein the wheel back chamfer comprises 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 wheel back section, the second end of the first chamfer section is connected to the first end of the second chamfer section, and the second end of the second chamfer section is connected to the connecting section. Thus, by providing the wheel back chamfer, stress distribution is optimized and fatigue life of the turbine is improved; the wheel back chamfer is divided into two chamfer sections with different curvatures, and the chamfer radius of the first chamfer section is larger than the chamfer radius of the second chamfer section, so that the chamfer curvature of the wheel back near the inner ring side is greater, which can better reduce stress concentration at the root, thereby optimizing the overall structural strength of the turbine, being suitable for high speed and high temperature environments, and improving the reliability and safety of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0022] Figure 1 It is a schematic elevation view of the overall structure in one embodiment of the present invention;

[0023] Figure 2 This is a partial enlarged schematic diagram of the wheel back chamfer in one embodiment of the present invention;

[0024] Figure 3 Schematic diagram of stress distribution of turbine structure with conventional technology before optimization;

[0025] Figure 4 Schematic diagram of the stress distribution of the turbine structure in this application after optimization.

[0026] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings and in conjunction with the embodiments.

[0027] Description of Figure Numbers:

[0028] 10. Turbine body; 110. Wheel back section; 120. Connecting section; 121. Third chamfered section; 130. Wheel back chamfer; 131. First chamfered section; 132. Second chamfered section; 20. Turbine blade. DETAILED DESCRIPTION

[0029] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In addition, the descriptions of "first", "second", etc. in the present invention are for descriptive purposes only and should not be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of such features. In addition, the technical solutions between the various embodiments can be combined with each other, but this must be based on the fact that they can be implemented by ordinary technicians in this field. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0033] Please see the attached Figure 1-4 In one embodiment of the present invention, a turbine structure includes a turbine body 10 and a plurality of turbine blades 20. The details are as follows:

[0034] A plurality of turbine blades 20 are arranged at intervals along the circumference of the turbine body 10 and connected to the turbine body 10; the turbine body 10 includes a wheel back section 110 and a connecting section 120, and a wheel back chamfer 130 is formed between the wheel back section 110 and the connecting section 120, and the wheel back chamfer 130 includes 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 wheel 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 the chamfer radius of the second chamfer section 132.

[0035] Specifically, the turbine body 10 is used for installing the turbine blades 20 to form a complete turbine structure. Usually, a plurality of turbine blades 20 are provided, which are arranged at intervals along the circumference of the turbine structure and connected to the turbine body 10 (the rotor shaft). Preferably, the number of the turbine blades 20 can be set to twelve, and the twelve turbine blades 20 are arranged at intervals along the circumference of the turbine body 10; in addition to structures such as the rotor shaft and the hub that are well known to those skilled in the art, the turbine body 10 also includes a wheel back section 110 and a connecting section 120. The connecting section 120 is used to be connected to the turbine shaft. Therefore, when the turbine shaft is driven to rotate, stress concentration is usually easily generated between the wheel back section 110 and the connecting section 120, resulting in fatigue cracks and structural failure. However, the present application reduces stress concentration by forming a wheel back chamfer 130 between the wheel back section 110 and the connecting section 120, and increasing the wheel back chamfer 130 structure.

[0036] Wherein, the wheel back chamfer 130 includes a first chamfer section 131 (such as Figure 2 R1) and the second chamfered section 132 (as shown Figure 2As shown in R2), two chamfered sections with different bending degrees are adopted to form structures with different structural thicknesses and chamfer sizes. In detail, the first chamfered section 131 is used to be arranged close to the outer ring side of the wheel back section 110, so the first end of the first chamfered section 131 is connected to the outer ring side of the wheel back section 110, and the second chamfered section 132 is used to be connected close to the connecting section 120 (the inner ring side of the wheel back section 110, that is, the root), so the second end of the second chamfered section 132 is connected to the connecting section 120, and the first chamfered section 131 and the second chamfered section 132 are connected to each other. During processing, the first chamfered section 131 and the second chamfered section 132 can be integrally formed, so that the structural curved surface is smoother and no cracks will appear; and this application is used as a In a preferred embodiment, the chamfer radius of the first chamfer section 131 is greater than the chamfer radius of the second chamfer section 132. It can be understood that the larger the chamfer radius, the flatter the curvature of the chamfer arc. Therefore, within a similar arc length range, the smaller the chamfer radius, the more curved the arc, and thus the greater the axial distance from the wheel back section 110. That is, the arc curvature of the second chamfer section 132 is more curved than that of the first chamfer section 131, and the closer it is to the inner ring side (root) of the wheel back section 110, the greater the distance from the axial centerline of the wheel back section 110. In this way, the stress concentration problem at the inner ring side (root) of the wheel back section 110 is just reduced, 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 environments; improving the reliability and safety of the turbine.

[0037] Preferably, the chamfer radius range of the first chamfer section 131 is 37mm to 39mm, and the chamfer radius range of the second chamfer section 132 is 17mm to 19mm. In the connection of the two chamfer sections within this range, the stress concentration at the root can be better reduced, and the normal operation of the component structure can be met to improve the fatigue life of the turbine structure. However, it should be noted that this range is obtained through calculation and analysis combined with actual working condition testing.

[0038] Among them, in this application as a preferred embodiment, the chamfer radius of the first chamfer section 131 is 38 mm, and the chamfer radius of the second chamfer section 132 is 18 mm. In such a connection form of the first chamfer section 131 and the second chamfer section 132, a wheel back chamfer 130 is formed. Compared with the traditional turbine structure, the root mass is increased by the wheel back chamfer 130 segment formed in this way. Through finite element analysis (FEA) and actual working condition tests, the excellent performance of the turbine structure of the present invention in high speed (>10,000 rpm) and high temperature (>800°C) environment is verified, and the stress concentration factor is reduced by more than 50%. It has been verified by finite element analysis and actual working condition tests. Please refer to the attached for details. Figure 3 ~Attached Figure 4 As shown in .

[0039] Furthermore, a third chamfered section 121 is formed on the outer ring side of the connecting section 120 , and one end of the third chamfered section 121 close to the wheel back section 110 is connected to the second end of the second chamfered section 132 .

[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 smoother, so as to avoid a sudden change in the bending form of the structural surface and cause a large stress mutation rate, thereby affecting the structural strength of the connection between the connecting section 120 and the wheel back chamfer 130, such as the end of the third chamfer section 121 close to the wheel back section 110 is connected to the second end of the second chamfer section 132; wherein, the chamfer radius of the third chamfer section 121 can be set to 2.5 mm, which can be tested and set according to the width of the connecting section 120 and the smoothness of the connection, and those skilled in the art can make a choice according to actual conditions.

[0041] Furthermore, the blade surface of each turbine blade 20 is arranged in a curved shape.

[0042] It should be noted that this can improve aerodynamic performance, reduce secondary flow losses, and by rationally organizing the flow of low-energy fluid, make the reaction degree uniform along the blade height, thereby improving the flow conditions in the blade root area.

[0043] Furthermore, the plurality of turbine blades 20 are arranged at equal distances from each other.

[0044] It should be noted that the equidistant setting can improve the uniformity of airflow, reduce energy loss, and thus improve the aerodynamic efficiency of the turbine.

[0045] The above are only preferred embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention description and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A turbine structure, characterized in that: It includes a turbine body and a plurality of turbine blades; wherein, The plurality of turbine blades are spaced apart along the circumference of the turbine body and connected to the turbine body; The turbine body includes a wheel back section and a connecting section, a wheel back chamfer is formed between the wheel back section and the connecting section, and the wheel back chamfer includes a first chamfer section and a second chamfer section; wherein, The first end of the first chamfered segment is connected to the outer ring side of the wheel back segment, the second end of the first chamfered segment is connected to the first end of the second chamfered segment, the second end of the second chamfered segment is connected to the connecting segment, and the chamfer radius of the first chamfered segment is greater than the chamfer radius of the second chamfered segment.

2. The turbine structure according to claim 1, characterized in that: The chamfer radius of the first chamfered section ranges from 37 mm to 39 mm.

3. The turbine structure according to claim 2, characterized in that: The chamfer radius of the second chamfered section ranges from 17 mm to 19 mm.

4. The turbine structure according to claim 3, characterized in that: The chamfer radius of the first chamfered section is 38 mm, and the chamfer radius of the second chamfered section is 18 mm.

5. The turbine structure according to claim 1, characterized in that: The first chamfered section and the second chamfered section are integrally formed.

6. The turbine structure according to claim 1, characterized in that: A third chamfered section is formed on the outer ring side of the connecting section, and one end of the third chamfered section close to the wheel back section is connected to the second end of the second chamfered section.

7. The turbine structure according to claim 1, characterized in that: 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 according to claim 7, characterized in that: The blade surface of each turbine blade is arranged in a curved shape.

9. The turbine structure according to claim 7, characterized in that: The plurality of turbine blades are arranged at equal distances from each other.

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