Improved turbocharger

Abstract

A turbine assembly is arranged in the turbocharger, a turbine impeller is arranged in the turbine assembly, and the turbine impeller comprises a turbine disc arranged in the radial direction, a turbine wheel nose arranged in the axial direction and a plurality of blades evenly distributed in the area between the turbine disc and the turbine wheel nose. The edge of each blade comprises a front edge, a shield edge and a rear edge, a first axial position is defined at the joint of the front edge and the turbine disc, and a second axial position is defined at the joint of the rear edge and the shield edge; two side surfaces of each blade are respectively a pressure surface and a suction surface; from the first axial position to the second axial position, the radial outer side of the blade has a state of being converted from a state deviating from the suction surface to a state deviating from the pressure surface compared with the radial inner side of the position on the blade. In the application, the turbine blades are optimized from radial design to non-radial design during design, and the blade form of radial deflection enables the turbine blades to have better aerodynamic efficiency.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of turbochargers, and particularly relates to an improved turbocharger. BACKGROUND

[0002] The turbocharger is an important component in the current automobile engine system, which can make more air enter the cylinder, mix with fuel more fully, burn, significantly improve the power and torque of the engine, and also help improve fuel economy and reduce emissions.

[0003] The turbocharger has a turbine assembly, which has a turbine impeller. When the turbine impeller rotates at high speed, the high-temperature and high-pressure exhaust gas discharged by the engine is expanded in the turbine to do work, converting kinetic and thermal energy into mechanical energy to drive the compressor to do work. Therefore, the blade shape on the impeller is crucial to the energy conversion efficiency. In the prior art, the efficiency is improved by continuously improving the blade profile, so as to improve the overall efficiency of the turbocharger. Based on this, the present application further researches and improves the turbocharger. SUMMARY

[0004] In view of the deficiencies in the prior art, the present application provides an improved turbocharger. By designing the blade profile of the turbine impeller, the airflow separation is reduced, the aerodynamic loss is reduced, the airflow can flow out of the blade channel more smoothly, the generation of vortex flow is avoided, the outlet airflow blockage at high speed is reduced, and the turbine efficiency is improved.

[0005] The present application is solved by the following technical scheme.

[0006] An improved turbocharger has a turbine assembly, which has a turbine impeller. The turbine impeller includes a radially arranged turbine disc, an axially arranged turbine nose, and a plurality of blades uniformly distributed in the area between the turbine disc and the turbine nose. The edge of each blade includes a leading edge, a shroud edge, and a trailing edge. The connection between the leading edge and the turbine disc defines a first axial position, and the connection between the trailing edge and the shroud edge defines a second axial position. The two side surfaces of the blade are a pressure surface and a suction surface, respectively. From the first axial position to the second axial position, the radially outer side of the blade changes from being biased to the suction surface to being biased to the pressure surface compared to the radially inner side of the blade at that position.

[0007] In the present application, the turbine blade is designed to be non-radial from radial, and the radially biased blade shape can have better aerodynamic efficiency.

[0008] In a preferred embodiment, the deflection angle of the radial outer side of the blade is denoted as angle a in the radial section of the blade, and the angle a is positive when the pressure surface is deflected, and the angle a is negative when the suction surface is deflected, and the position where the angle a is zero is the deflection turning point P1 on the profile of the blade, and the deflection turning point P1 is located on the leading edge; and the transition point P between the leading edge and the shroud edge is located at the axial distance of 12% to 18% of the axial distance of the leading edge, preferably at the distance of 15% of the axial distance of the leading edge.

[0009] In the structure, the positive inclination angle at the air inlet can guide the airflow to enter the turbine at a suitable angle, reduce airflow separation, reduce aerodynamic loss, the negative inclination angle at the air outlet can make the airflow flow out of the blade channel more smoothly, avoid the generation of vortex, reduce the blockage of outlet airflow at high speed, thereby improving the turbine efficiency, and the P1 position is also designed and verified.

[0010] In a preferred embodiment, the angle a is +12° to -12°.

[0011] In a preferred embodiment, the number of the blades 3 is 8 to 12.

[0012] Compared with the prior art, the improved turbocharger can reduce airflow separation, reduce aerodynamic loss, make the airflow flow out of the blade channel more smoothly, avoid the generation of vortex, reduce the blockage of outlet airflow at high speed, and improve the turbine efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 It is a front view of the turbine wheel in the application.

[0014] Figure 2 It is a perspective view of the turbine wheel in the application.

[0015] Figure 3 It is a schematic view of the position of the section line of the turbine wheel in the application.

[0016] Figure 4 It is a schematic view of the section of A in the application. Figure 3

[0017] It is a schematic view of the section of B in the application. Figure 5 Figure 3 It is a schematic view of the section of C in the application.

[0018] Figure 6 Figure 3

[0019] Figure 7 Figure 3 ​​​​A cross-sectional view of point D in the diagram.

[0020] Figure 8 for Figure 3 A cross-sectional view at point E in the diagram.

[0021] Figure 9 A performance comparison is made between a radially designed turbine (with all cross-sections having an inclination angle of 0) in the prior art and the turbine impeller designed in this invention.

[0022] Figure 10 This is a graph showing the results of the software simulation.

[0023] Figure 11 The software simulation results are shown for radially designed turbines and non-radially designed turbines. Detailed Implementation

[0024] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0025] In the following embodiments, the same or similar reference numerals denote the same or similar originals or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0026] In the description of this invention, it should be understood that terms such as center, longitudinal, transverse, length, width, thickness, upper, lower, front, rear, left, right, vertical, horizontal, top, bottom, inner, outer, clockwise, counterclockwise, etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the description of this invention; therefore, they should not be construed as limiting this invention. Furthermore, terms such as first, second, etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features shown. In the description of this invention, unless otherwise expressly specified and limited, terms such as installation, connection, linking, etc., should be interpreted broadly, and those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0027] See Figures 1 to 8The present invention relates to an improved turbine impeller, comprising a radially arranged turbine disk 1, an axially arranged turbine nose 2, and a plurality of blades 3 uniformly distributed in the region between the turbine disk 1 and the turbine nose 2. Each blade 3 has an edge including a leading edge 34, a shroud edge 35, and a trailing edge 33. The connection between the leading edge 34 and the turbine disk 1 defines a first axial position, and the connection between the trailing edge 33 and the shroud edge 35 defines a second axial position. The two side surfaces of the blade 3 are a pressure surface 31 and a suction surface 32, respectively. From the first axial position to the second axial position, the radially outer side of the blade 3 changes from being biased towards the suction surface 32 to being biased towards the pressure surface 31 compared to the radially inner side of the blade at that point.

[0028] In traditional turbine blades, the blades are basically radially designed, meaning that the blades do not have a radial deflection angle. In this application, the turbine blades are optimized from a radial design to a non-radial design. The radially deflected blade shape can make it have better aerodynamic efficiency.

[0029] Specifically, in this application, on the radial cross section of the blade 3, the deflection angle of the radially outer side relative to the radially inner side at that point on the blade is denoted as angle a. Angle a is positive when deflected towards the pressure surface 31 and negative when deflected towards the suction surface 32. The position where angle a is zero is the deflection turning point P1 in the blade shape. This deflection turning point P1 is located on the leading edge 34. There is a transition point P between the leading edge 34 and the edge 35 of the shield. The axial distance from the transition point P to the deflection turning point P1 is 12% to 18% of the axial distance of the leading edge 34, preferably 15%.

[0030] Looking at the attached diagram, from the attached diagram... Figure 4 To be continued Figure 8 As can be seen, on the radial section of the blade, there is an inclination angle, namely angle α, between the line connecting the outer side of the blade to the center of the blade base and the line connecting the center of the blade base to the center of rotation. Specifically, the angle α is +12° to -12°.

[0031] The positive inlet tilt angle design guides the airflow into the turbine at a suitable angle, reducing airflow separation and aerodynamic losses. The negative outlet tilt angle design allows the airflow to flow out of the blade passage more smoothly, avoiding the generation of vortices and reducing outlet airflow blockage at high speeds, thereby improving turbine efficiency.

[0032] In this application, the number of blades 3 is 8 to 12. This application also relates to a turbocharger, in which the turbine assembly has the aforementioned turbine impeller. Other structures of the turbocharger can be conventional structures in the prior art.

[0033] Appendix Figure 9This is a performance comparison between a radially designed turbine (with all cross-sections having an inclination angle of 0) in the prior art and the turbine impeller designed in this invention. Black represents the original turbine, and blue represents the new turbine. Under the condition that the flow capacity of the two is the same, the efficiency of the new turbine can be improved by 2%-5%.

[0034] Furthermore, by combining the software simulation results with the attached... Figure 10 See, attached Figure 10 The left image shows a radially designed turbine, while the right image shows a non-radially designed turbine. It can be seen that traditional radially designed turbines have significant drawbacks: a low-pressure zone exists on the suction surface, and the pressure gradient from the pressure surface to the suction surface is large, leading to complex secondary flows and energy loss. The non-radial turbine design in this application can reduce the pressure gradient within the channel by bending the blades, thereby reducing and weakening the generation of secondary flows, minimizing separation and losses, and improving turbine efficiency.

[0035] Furthermore, in conjunction with the appendix Figure 11 See, attached Figure 11 The left image shows a radially designed turbine, while the right image shows a non-radially designed turbine. It can be seen that traditional radially designed turbines have a drawback: during turbine rotation, large vortices are generated on the pressure surface, causing significant energy loss. The non-radial turbine of this invention effectively solves this problem by tilting the outlet blades towards the suction surface, reducing vortex generation and improving efficiency.

[0036] Furthermore, this application also simulated the Mach number distribution cloud map of different blade height sections using software, and concluded that: the Mach number at the non-radial turbine outlet of this invention is reduced, the residual velocity loss is reduced, and the efficiency loss is reduced.

[0037] As can be seen from the above description, in this application, the design of the positive tilt angle at the air inlet can guide the airflow into the turbine at a suitable angle, reduce airflow separation, and reduce aerodynamic losses. The design of the negative tilt angle at the air outlet can enable the airflow to flow out of the blade passage more smoothly, avoid the generation of vortices, reduce the blockage of the outlet airflow at high speed, thereby improving turbine efficiency. The P1 position has also been designed and verified.

[0038] Therefore, it can be seen that the present invention provides an improved turbine impeller. By designing the blade profile, it can reduce airflow separation, reduce aerodynamic losses, allow airflow to flow out of the blade channel more smoothly, avoid the generation of vortices, reduce outlet airflow blockage at high speeds, and thus improve turbine efficiency.

[0039] The scope of protection of this invention includes, but is not limited to, the above embodiments. The scope of protection of this invention is defined by the claims. Any substitutions, modifications, or improvements to this technology that are easily conceived by those skilled in the art fall within the scope of protection of this invention.

Claims

1. An improved turbocharger having a turbine assembly having a turbine impeller comprising a radially arranged turbine disk (1), an axially arranged turbine nose (2), and a plurality of blades (3) uniformly distributed in the region between the turbine disk (1) and the turbine nose (2), each blade (3) having an edge including a leading edge (34), a shroud edge (35), and a trailing edge (33), characterized in that: The connection between the leading edge (34) and the turbine disk (1) defines a first axial position, and the connection between the trailing edge (33) and the edge of the shield (35) defines a second axial position; The two sides of the blade (3) are a pressure surface (31) and a suction surface (32), respectively. From the first axial position to the second axial position, the radial outer side of the blade (3) has a shape that changes from a suction-oriented surface (32) to a pressure-oriented surface (31) compared to the radial inner side of the blade at that position.

2. An improved turbocharger according to claim 1, characterized in that, On the radial section of the blade (3), the deflection angle of the radial outer side relative to the radial inner side of the blade at that point is denoted as angle a. When deflected toward the pressure surface (31), angle a is positive, and when deflected toward the suction surface (32), angle a is negative. The position when angle a is zero is the deflection turning point P1 in the blade shape. This deflection turning point P1 is located on the leading edge (34). There is a transition point P between the leading edge (34) and the edge of the shield (35), and the axial distance from the transition point P to the deflection turning point P1 is 12% to 18% of the axial distance of the leading edge (34).

3. An improved turbocharger according to claim 2, characterized in that, The angle α is +12° to -12°.

4. An improved turbocharger according to claim 3, characterized in that, The number of blades (3) is 8 to 12.

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