Impeller, gas compressor and supercharger

Abstract

The utility model particularly relates to an impeller, a gas compressor and a supercharger, and the impeller comprises a hub and blades arranged on the hub. Projection lines of the air inlet front edge and the air outlet tail edge of the blade towards the blade meridian plane of the impeller are an air inlet edge and an air outlet edge respectively, and projection lines of the hub curved surface and the blade profile curved surface of the blade towards the blade meridian plane are a hub molded line and a blade top molded line respectively. At least two middle skeleton lines are arranged between the blade top molded line and the hub molded line, the air inlet edge and the air outlet edge can be equally divided by the at least two middle skeleton lines, and the blade profile bending angle distribution of the blade on any middle skeleton line conforms to a Bezier curve. According to the blade, the positions and the shapes of the at least two middle skeleton lines between the blade top molded line and the hub molded line are limited to conform to the Bezier curve, so that the blade profile bending angle of the blade can be accurately controlled, the pneumatic stability of the blade under the low-flow working condition can be improved, and the service life of the blade is prolonged. And the air inlet requirement of a large-flow engine supercharger can be met.

Description

Technical Field

[0001] The utility model relates to the technical field of turbochargers, and particularly relates to an impeller, a compressor and a supercharger. Background Art

[0002] In a traditional engine, power is generated by fuel combustion in a cylinder. Since the amount of fuel input is limited by the amount of air inhaled into the cylinder, the power generated by the engine is also limited. To increase the output power, only more air can be compressed into the cylinder to increase the fuel amount, thereby improving the combustion work capacity.

[0003] A turbocharger is a mechanical device that can increase the output power of an engine without changing the working efficiency, and at the same time, effectively reduce the fuel consumption rate of the engine. In recent years, engine supercharging technology has developed rapidly, and supercharging technology plays an important role in reducing emissions, increasing power, and restoring high-altitude performance.

[0004] For a turbocharger, a compressor impeller is the core component of the turbocharger. The design of a high-pressure ratio and high-efficiency compressor has always been the pursuit goal of the compressor impeller.

[0005] In existing multi-cylinder power generation diesel engines, generally multiple turbochargers operate in coordination. As the pressure ratio of the supercharger continues to increase, the working flow rate of the compressor will break through the corresponding minimum limit value, causing flow separation on the suction surface of the impeller and generating a large number of stall clusters in the flow channel. At this time, large-amplitude pressure fluctuations and air flow swallowing phenomena occur at the inlet and outlet, and at the same time, accompanied by severe vibration of the impeller and the whistling sound emitted by the high-speed air flow, the supercharger surges.

[0006] However, the existing turbocharger impellers are more inclined to high-speed and small-displacement working conditions, and the intake air flow rate is small, which cannot meet the intake air flow requirements of marine engines. At the same time, due to unreasonable structural design of ordinary compressor impellers, the blade profile of the impeller is not variable, and after increasing the intake air volume, phenomena such as insufficient blade strength, low self-vibration frequency, and poor dynamic balance performance will occur, reducing the performance of the compressor. Summary of the Utility Model

[0007] The purpose of the utility model is to at least solve the problem that the existing turbocharger impeller cannot meet the intake air flow requirements of a large-flow engine. This purpose is achieved by the following technical solutions:

[0008] A first aspect of the present utility model provides an impeller. The impeller includes a hub and blades provided on the hub. It is characterized in that the projection lines of the air inlet leading edge and the air outlet trailing edge of the blades onto the meridional plane of the impeller blades are respectively the air inlet edge and the air outlet edge, and the projection lines of the hub surface and the blade profile surface of the blades onto the meridional plane of the blades are respectively the hub profile line and the tip profile line;

[0009] At least two middle bone lines are provided between the tip profile line and the hub profile line. The at least two middle bone lines can equally divide the air inlet edge and the air outlet edge, and the blade profile bend angle distribution of the blade on any one of the middle bone lines conforms to a Bezier curve.

[0010] For the blade of the present utility model, by providing at least two middle bone lines between the tip profile line and the hub profile line of the blade, and defining that the two ends of the at least two middle bone lines respectively equally divide the air inlet edge and the air outlet edge, and the blade profile bend angle distribution of the blade on any one of the middle bone lines conforms to the shape of a Bezier curve, it helps to achieve precise control of the blade profile bend angle. Not only can it improve the control of the air flow movement on the premise of ensuring the strength of the impeller, improve the aerodynamic stability of the blade under low-flow conditions, but also enable it to meet the air inlet requirements of a large-flow engine supercharger.

[0011] In addition, for the blade according to the present utility model, it may also have the following additional technical features:

[0012] In some embodiments of the present utility model, both the air inlet edge and the air outlet edge are straight lines and are perpendicularly arranged, and both the tip profile line and the hub profile line are Bezier spline curves.

[0013] In some embodiments of the present utility model, the blade thickness distribution of the blade on any one of the middle bone lines conforms to a Bezier curve.

[0014] In some embodiments of the present utility model, a first middle bone line, a second middle bone line, and a third middle bone line are sequentially arranged between the tip profile line and the hub profile line;

[0015] The blade has a first direction perpendicular to the meridional plane of the blade. Along the first direction, a first middle bone section is formed by making a section of the blade passing through the first middle bone line on the blade, a second middle bone section is formed by making a section of the blade passing through the second middle bone line on the blade, and a third middle bone section is formed by making a section of the blade passing through the third middle bone line on the blade;

[0016] The blade has a second direction that extends from the intake leading edge towards the exhaust trailing edge and along the hub profile line. Along the second direction, the dimensions of the first midrib section, the second midrib section, and the third midrib section in the first direction first increase and then decrease, and the rate of change of the dimension of the first midrib section is less than the rate of change of the dimension of the second midrib section, and the rate of change of the dimension of the second midrib section is less than the rate of change of the dimension of the third midrib section. The second direction is perpendicular to the first direction.

[0017] In some embodiments of the present invention, along a third direction, the dimensions of the first midrib section, the second midrib section, and the third midrib section in the first direction increase in sequence, and the third direction is perpendicular to the first midrib section, the second midrib section, and the third midrib section simultaneously.

[0018] In some embodiments of the present invention, along the second direction, the curve of the thickness change of the blade on the first midrib line is M-shaped, and the thickness change of the blade on the second midrib line and the third midrib line both first increase and then decrease.

[0019] In some embodiments of the present invention, the blade has a thickness value b on the second midrib line, and the blade has a thickness value c on the third midrib line, where b = 0.4 - 0.6c.

[0020] In some embodiments of the present invention, the major diameter of the impeller is 140 - 155 mm, and the minor diameter of the impeller is 90 - 110 mm;

[0021] The number of the blades is at least 8, and all the blades are arranged at equal intervals in sequence along the circumferential direction of the hub. The second aspect of the present invention also provides a compressor, including the impeller as described in the present invention.

[0022] Compared with the prior art, the compressor provided by the present invention has the technical advantages possessed by the above-mentioned impeller, which will not be elaborated here.

[0023] The third aspect of the present invention also provides a supercharger, including the compressor as described in the present invention.

[0024] Compared with the prior art, the supercharger provided by the present invention has the technical advantages possessed by the above-mentioned compressor, which will not be elaborated here. Description of the Drawings

[0025] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the following detailed description of the preferred embodiments. The drawings are only for the purpose of showing the preferred embodiments and are not considered to be a limitation of the present utility model. Also, throughout the drawings, the same reference numerals are used to denote the same components. In the drawings:

[0026] Figure 1 Schematically shows a schematic structural diagram of an impeller according to an embodiment of the present utility model;

[0027] Figure 2 is Figure 1 A schematic structural diagram of the impeller shown in the second perspective;

[0028] Figure 3 is Figure 1 A schematic structural diagram of the blade of the impeller shown in the blade meridian plane;

[0029] Figure 4 is Figure 3 The blade profile curvature diagram of the first middle bone line shown in;

[0030] Figure 5 is Figure 3 The blade profile curvature diagram of the second middle bone line shown in;

[0031] Figure 6 is Figure 3 The blade profile curvature diagram of the third middle bone line shown in;

[0032] Figure 7 is Figure 3 The line shape of several middle bone lines shown in;

[0033] Figure 8 is Figure 3 The thickness control curve diagram of the first middle bone line shown in;

[0034] Figure 9 is Figure 3 The thickness control curve diagram of the second middle bone line shown in;

[0035] Figure 10 is Figure 3 The thickness control curve diagram of the third middle bone line shown in.

[0036] The reference numerals in the drawings are represented as follows:

[0037] 100, impeller; 101, air inlet; 102, air outlet;

[0038] 10, blade; 20, hub;

[0039] 1, blade meridian plane;

[0040] 2. Outline profile line;

[0041] 3. Tip profile line;

[0042] 4. Inlet edge;

[0043] 5. Outlet edge;

[0044] 6. First middle bone line;

[0045] 7. Second middle bone line;

[0046] 8. Third middle bone line. Detailed implementation manners

[0047] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided so that the present disclosure can be more thoroughly understood and the scope of the present disclosure can be fully conveyed to those skilled in the art.

[0048] It should be understood that the terms used herein are for the purpose of describing specific exemplary embodiments only and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" as used herein may also include the plural forms. The terms "include", "comprise", "contain" and "have" are inclusive and thus specify the presence of the stated features, steps, operations, elements and / or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring them to be performed in the particular order described or illustrated, unless the order of performance is explicitly stated. It should also be understood that additional or alternative steps may be used.

[0049] Although the terms first, second, third, etc. may be used herein to describe multiple elements, components, regions, layers, and / or sections, these elements, components, regions, layers, and / or sections should not be limited by these terms. These terms may only be used to distinguish one element, component, region, layer, or section from another. Unless the context clearly indicates otherwise, terms such as "first", "second", and other numerical terms do not imply an order or sequence when used herein. Thus, the first element, component, region, layer, or section discussed below may be referred to as the second element, component, region, layer, or section without departing from the teachings of the exemplary embodiments.

[0050] For ease of description, spatial relative relation terms may be used in the text to describe the relationship of one element or feature shown in the figure with respect to another element or feature. These relative relation terms are, for example, "inner", "outer", "inside", "outside", "below", "beneath", "above", "over", etc. Such spatial relative relation terms are intended to include different orientations of the device during use or operation in addition to the orientations depicted in the figure. For example, if the device in the figure is flipped, an element described as "below" or "beneath" other elements or features will then be oriented as "above" or "over" other elements or features. Thus, the exemplary term "below" can include both upper and lower orientations.

[0051] A traditional engine generates power by burning fuel in a cylinder. Since the amount of fuel input is limited by the amount of air inhaled into the cylinder, the power generated by the engine is also limited. A turbocharger is a mechanical device that can increase the output power of an engine while maintaining the same working efficiency. Specifically, it uses the energy of an exhaust gas turbine to drive and pre-compress the air before it enters the cylinder, so as to achieve the purpose of increasing the air density and the intake air volume. For a turbocharger, the compressor impeller is the core component, and the design of a high-pressure ratio and high-efficiency compressor has always been the pursuit goal of the compressor impeller.

[0052] In existing multi-cylinder power generation diesel engines, generally multiple turbochargers operate in coordination. As the pressure ratio of the turbocharger continues to increase, the working flow rate of the compressor will break through the corresponding minimum limit value, causing flow separation on the suction surface of the impeller and generating a large number of stall clusters in the flow channel. At this time, large-amplitude pressure fluctuations and air flow swallowing phenomena occur at the inlet and outlet, and at the same time, there are violent vibrations of the impeller and whistling sounds emitted by the high-speed air flow, and the compressor surges.

[0053] Among them, compressor surge refers to a low-frequency and high-amplitude air flow vibration phenomenon that occurs along the axis direction of the compressor. This low-frequency and high-amplitude air flow oscillation is a large source of excitation force, which will cause strong mechanical vibrations of the compressor components and cause serious damage to the components in a very short time.

[0054] However, the existing turbocharger impellers are more inclined to high-speed and small-displacement working conditions, and the intake air flow is relatively small, which cannot meet the intake air flow requirements of marine engines. At the same time, due to unreasonable structural design of ordinary compressor impellers, the blade profile of the impeller is not variable, and at the same time, after increasing the intake air volume, there will be phenomena such as insufficient blade strength, low self-vibration frequency, and poor dynamic balance performance, reducing the performance of the compressor.

[0055] To solve the above problems, as Figures 1-3As shown in the figure, the present utility model proposes an impeller 100 to solve the problem that the existing impellers of turbochargers cannot meet the intake air flow requirements of large-flow engines.

[0056] In terms of the overall design, the impeller 100 includes a hub 20 and blades 10 provided on the hub 20. The projection lines of the leading edge and the trailing edge of the blades 10 onto the blade meridional plane 1 of the impeller 100 are respectively the intake edge 4 and the outlet edge 5. The projection lines of the hub surface and the blade profile surface of the blades 10 onto the blade meridional plane 1 are respectively the hub profile line 2 and the tip profile line 3. At least two middle rib lines are provided between the tip profile line 3 and the hub profile line 2, and the at least two middle rib lines can equally divide the intake edge 4 and the outlet edge 5. The blade profile bend angle distribution of the blade 10 on any middle rib line conforms to the Bezier curve.

[0057] Specifically, by providing at least two middle rib lines between the tip profile line 3 and the hub profile line 2 of the blade 10, and defining that the two ends of the at least two middle rib lines respectively equally divide the intake edge 4 and the outlet edge 5, and the blade profile bend angle distribution of the blade 10 on any middle rib line conforms to the shape of the Bezier curve, it helps to achieve precise control of the blade profile bend angle of the blade 10. Not only can it improve the control of the air flow movement on the premise of ensuring the strength of the impeller 100, improve the aerodynamic stability of the blade 10 under low-flow conditions, but also enable it to meet the intake requirements of the supercharger of large-flow engines.

[0058] It should be understood that the impeller 100 includes blades 10. Among them, the blades 10 have an intake leading edge, an outlet trailing edge, a hub surface and a tip surface. The intake leading edge is the side surface of the blade 10 facing the intake port 101, and the outlet trailing edge is the side surface of the blade 10 facing the outlet port 102. The middle arc surface (blade profile surface) of the blade 10, the edge close to the hub 20 is the hub surface, and the edge of the middle arc surface of the blade 10 far from the hub 20 is the tip surface. As Figure 3 shown, the projection of the intake leading edge onto the blade meridional plane 1 is the intake edge 4, and the projection of the outlet trailing edge onto the blade meridional plane 1 is the outlet edge 5. Both the intake edge 4 and the outlet edge 5 are straight lines and are perpendicularly arranged; the projection of the hub surface onto the blade meridional plane 1 is the hub profile line 2, and the projection of the intake leading edge onto the blade meridional plane 1 is the tip profile line 3. The front end of the hub profile line 2 and the front end of the tip profile line 3 are respectively connected to the two ends of the intake edge 4. The tail end of the hub profile line 2 and the tail end of the tip profile line 3 are respectively connected to the two ends of the outlet edge 5.

[0059] It should be noted that the blade meridian plane 1 is a longitudinal section passing through the axis line of the impeller 100. The front end of the tip profile line 3 refers to the end of the tip projection onto the blade meridian plane 1 that is closer to the air inlet 101 of the impeller 100, and the tail end of the tip profile line 3 refers to the end of the tip projection onto the blade meridian plane 1 that is closer to the air outlet 102 of the impeller 100; the front end of the hub profile line 2 refers to the end of the hub 20 projection onto the blade meridian plane 1 that is closer to the air inlet 101 of the impeller 100, and the tail end of the hub profile line 2 refers to the end of the hub 20 projection onto the blade meridian plane 1 that is closer to the air outlet 102 of the impeller 100.

[0060] It needs to be further understood that the length of the hub profile line 2 is greater than the length of the tip profile line 3. Moreover, both the hub profile line 2 and the tip profile line 3 conform to the Bezier spline curve. Preferably, the hub profile line 2 and the tip profile line 3 are respectively in the shape of a high-order (3 - 7 order) Bezier spline curve, where the high-order Bezier spline curve can specifically be a fifth-order Bezier spline curve.

[0061] Specifically, the hub profile line 2 of the blade 10 conforms to the high-order Bezier spline curve, which can precisely control the hub profile line 2 of the impeller 100 of the compressor and control the gas flow direction in the meridian passage of the impeller 100. At the same time, the tip profile line 3 of the blade 10 also conforms to the high-order Bezier spline curve. In this way, it can precisely control the tip profile line 3 of the compressor impeller 100, effectively prevent gas backflow, and at the same time effectively control the gap size between the compressor impeller 100 and the compressor housing to prevent air leakage, greatly improving the efficiency of the compressor, thereby improving the overall efficiency of the turbocharger.

[0062] Still as Figure 3 shown, the inlet edge 4 and the outlet edge 5 are both straight lines and are perpendicularly arranged. By defining the shape and position of the inlet edge 4 and the outlet edge 5 in the blade meridian plane 1, cooperating with the hub profile line 2 and the tip profile line 3 can effectively determine the shape of the blade 10, which is convenient for determining the following middle bone line and the bending shape of the middle arc surface corresponding to the middle bone line, and is also convenient for subsequent adjustment and structural optimization.

[0063] It needs to be further understood that at least two middle bone lines are provided between the tip profile line 3 and the hub profile line 2, and the at least two middle bone lines can equally divide the inlet edge 4 and the outlet edge 5, that is to say, the setting of the middle bone lines can divide the blade meridian plane 1 into at least three parts. Preferably, a first middle bone line 6, a second middle bone line 7, and a third middle bone line 8 are successively arranged between the tip profile line 3 and the hub profile line 2. Among them, the first middle bone line 6, the second middle bone line 7, and the third middle bone line 8 equally divide the inlet edge 4 and the outlet edge 5 into four equal parts.

[0064] Meanwhile, the blade camber angle distribution of the blade 10 on any mid-line conforms to the Bezier curve. Specifically, the first mid-line 6, the second mid-line 7, and the third mid-line 8 are all controlled by 7 control points to achieve the blade camber angle. As Figures 4-6 shown, with the intake leading edge facing the exhaust trailing edge and the direction along the hub profile extension as the second direction, along the second direction, 7 control points are selected on the first mid-line 6, the second mid-line 7, and the third mid-line 8, and the Bezier curve is constructed according to the blade camber curvature of the 7 control points, so as to realize the adjustment of the blade 10, and then the aerodynamic performance can be specifically adjusted with the surge margin and the compressor efficiency as the goals.

[0065] It should be noted that the selection of the 7 control points can be determined by simulation equipment. Among them, the control points are selected as 7, mainly considering the calculation difficulty and accuracy, so as to effectively and quickly obtain the Bezier spline curve, so as to accurately control the tangent direction of the curve control points, the curve is smooth, continuous and differentiable, and thus more conforms to the high-order Bezier spline curve. Taking the control points as independent variables, after adjusting the blade camber angle control points, it is beneficial to accurately control the gas flow direction. At this time, the blade camber angle distribution of the blade is fitted by the above three Bezier curves.

[0066] Furthermore, the blade 10 has a first direction perpendicular to the blade meridian plane 1. Along the first direction, a section passing through the first mid-line 6 is made on the blade 10 to form a first mid-line section, a section passing through the second mid-line 7 is made on the blade 10 to form a second mid-line section, and a section passing through the third mid-line 8 is made on the blade 10 to form a third mid-line section.

[0067] Meanwhile, along the second direction, the dimensions of the first mid-line section, the second mid-line section, and the third mid-line section in the first direction first increase and then decrease, and the dimension change rate of the first mid-line section is less than that of the second mid-line section, and the dimension change rate of the second mid-line section is less than that of the third mid-line section. The second direction is perpendicular to the first direction.

[0068] Specifically, by limiting the mid-line section shapes of the blade 10 on the first mid-line 6, the second mid-line 7, and the third mid-line 8, the blade camber angles of the blades 10 of the impeller 100 on the three mid-arc surfaces can be effectively determined, and then the sweep angle structure can be determined, which helps to reduce the outlet Mach number of the impeller 100. At the same time, the aerodynamic load of the blade 10 can be reduced, and it has good aerodynamic performance, and can better maintain stable operation under low flow conditions, allowing the compressor to provide a stable flow within a wider range of engine operating conditions.

[0069] It should be understood that the first middle rib cross-section is the cross-section formed when the middle arc surface passes through the first middle rib line 6, and the first direction is the extending direction of the middle arc surface. Correspondingly, the second middle rib cross-section is the cross-section formed when the middle arc surface passes through the second middle rib line 7, and the third middle rib cross-section is the cross-section formed when the middle arc surface passes through the third middle rib line 8. At the same time, in combination with Figures 4-6 as shown, among them, the blade profile curvature of the first middle rib line 6 shows a trend of first decreasing and then increasing in the middle part, and the blade profile curvatures of the second middle rib line 7 and the third middle rib line 8 both show a decreasing trend. Among them, the decreasing trend of the blade profile curvature of the second middle rib line 7 is first fast and then slow, while the decreasing trend of the blade profile curvature of the third middle rib line 8 is first slow and then fast.

[0070] In combination with as Figure 7 shown, the first middle rib cross-section has a first dimension in the first direction, where the first direction is the direction perpendicular to the first middle rib line 6. Correspondingly, the second middle rib cross-section has a second dimension, and the third middle rib cross-section has a third dimension. Along the second direction, the first dimension, the second dimension, and the third dimension all show a trend of first increasing and then decreasing. At the same time, the dimension change rate of the first middle rib cross-section is less than that of the second middle rib cross-section, and the dimension change rate of the second middle rib cross-section is less than that of the third middle rib cross-section. By limiting the changes of the first dimension, the second dimension, and the third dimension, the linear shapes of the blade at the first middle rib line 6, the second middle rib line 7, and the third middle rib line 8 can be directly determined, and further the change of the blade profile bend angle can be determined.

[0071] Since the larger the blade profile bend angle, the greater the degree of blade profile bending. Therefore, by limiting the linear shapes of the first middle rib line 6, the second middle rib line 7, and the third middle rib line 8, the sweep angle can be increased on the blade 10 of the impeller 100, which further helps to reduce the outlet Mach number of the impeller 100, reduce the aerodynamic load of the blade 10, and enable the impeller 100 with the blade 10 to have better aerodynamic performance.

[0072] It should be further understood that along the third direction, the dimensions of the first middle rib cross-section, the second middle rib cross-section, and the third middle rib cross-section in the first direction increase in sequence, and the third direction is perpendicular to the first middle rib cross-section, the second middle rib cross-section, and the third middle rib cross-section at the same time.

[0073] It should be understood that as Figure 7 shown, the arrow direction from left to right in the figure is the above-mentioned third direction. Along the third direction, the values of the first dimension, the second dimension, and the third dimension increase in sequence, so that the degree of blade profile bending can be further determined, and further the outlet Mach number of the impeller 100 can be effectively reduced, and the aerodynamic load of the blade 10 can be reduced.

[0074] Furthermore, along the second direction, the curve of the thickness change of the blade 10 on the first median line 6 is of M type, and the thickness changes of the blade 10 on the second median line 7 and the third median line 8 both increase first and then decrease.

[0075] Specifically, the blade 10 of the supercharger impeller 100 has a defined blade 10 thickness at each position along the blade 10. By defining the blade 10 thickness distribution of the first median line 6, the second median line 7, and the third median line 8 in the second direction, the adjustment of the blade 10 thickness can be achieved, and thus the strength of the blade 10 can be effectively enhanced, and the dynamic balance of the impeller 100 at high speeds can be improved.

[0076] It should be understood that, as Figures 8-10 shown, several control points are selected for the first median line 6, the second median line 7, and the third median line 8 along the second direction, and the thickness values at these points are adjusted accordingly, and then simulation is carried out in the simulation software to determine the dynamic balance effect of the impeller 100 at high speeds. Among them, the change of the thickness value of the first median line 6 presents an M type, that is, it increases first, then decreases, then increases again and then decreases. The change of the thickness values of the second median line 7 and the third median line 8 both show a trend of increasing first and then decreasing, and during the decreasing process, the change of the thickness is first accelerated and then slowed down.

[0077] It should be noted that the fluctuation of the thickness value of the second median line 7 during the slowing-down process is small, and the fluctuation of the thickness value of the third median line 8 during the slowing-down process is large, and part of the change shows an obvious trend of increasing first and then decreasing.

[0078] Furthermore, the blade 10 has a thickness value b on the second median line 7, and the blade 10 has a thickness value c on the third median line 8, where b = 0.4 - 0.6c.

[0079] Specifically, by defining the thickness value of the blade 10 on the second median line 7 to be 0.4 - 0.6 times its thickness value on the third median line 8, the thickness between the blade 10 and the hub 20 can be effectively increased, which helps to enhance the strength of the blade 10, improve the dynamic balance of the impeller 100 at high speeds, and improve the use effect of the impeller 100.

[0080] It should be understood that, as Figure 9 and Figure 10As shown, the thickness of the second middle rib line 7 has an initial value b1, a maximum value b2, and a final value b3, and the thickness of the third middle rib line 8 has an initial value c1, a maximum value c2, and a final value c3. Among them, b1 can be 0.0012, c1 can be 0.0025, and b1 = 0.48c1; b2 can be 0.0029, c2 can be 0.0064, and b2 ≈ 0.46c2; b3 can be 0.0010, c3 can be 0.0020, and b3 = 0.50c3. With such settings, the camber angle and thickness distribution of the blade 10 can conform to the Bezier curve, so as to achieve precise control of the blade 10 model, which helps to achieve better aerodynamic performance, so that the impeller 100 with the blade 10 can meet the intake requirements of a large-flow engine supercharger.

[0081] Furthermore, the large diameter of the impeller 100 is 140 - 155 mm, and the small diameter of the impeller 100 is 90 - 110 mm; the number of blades 10 is at least 8, and they are arranged at equal intervals along the circumferential direction of the hub 20 in sequence.

[0082] Specifically, by limiting the large diameter and small diameter of the impeller 100, the distribution can be coordinated with the number of blades 10, so as to ensure the structural strength of the impeller 100 and the use effect of the impeller 100, making it applicable to a turbocharger with a relatively high intake flow rate.

[0083] It should be understood that in this embodiment, the impeller 100 is made of high-strength aluminum alloy. The impeller 100 has a hub 20 and a plurality of blades 10 evenly distributed at equal intervals along the axial direction of the hub 20. As Figure 1 and Figure 2 shown, the top of the hub 20 is a small diameter, and the bottom of the hub 20 is a large diameter. Among them, the large diameter of the impeller 100 is 155 mm, and the small diameter of the impeller 100 is 100 mm. At the same time, the number of blades 10 is 10, and all the blades 10 are arranged at equal intervals centered on the hub 20. With such settings, it is not only applicable to a turbocharger with a relatively high intake flow rate. At the same time, the impeller 100 has a relatively high allowable temperature.

[0084] It should be noted that the allowable temperature is the highest temperature at which the impeller 100 can be used normally, that is, the impeller 100 of the present application can be used in an environment with a temperature of 200 °C and maintain a good use effect, which helps to improve the applicability and use effect of the impeller 100 and ensure its service life.

[0085] In addition, this embodiment also relates to a compressor, which specifically includes the impeller 100 as described above.

[0086] Since the compressor provided by the present utility model includes the impeller 100 among the above, therefore, the beneficial effects possessed by the impeller 100 are all included in the compressor provided by the present utility model.

[0087] In addition, this embodiment also relates to a supercharger, which specifically includes the compressor as described above.

[0088] Since the supercharger provided by the present utility model includes the compressor among the above, therefore, the beneficial effects possessed by the compressor are all included in the supercharger provided by the present utility model.

[0089] As described above, only the preferred specific embodiment of the present utility model is provided, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed by the present utility model should be covered by the protection scope of the present utility model. Therefore, the protection scope of the present utility model should be subject to the protection scope of the claims.

Claims

1. An impeller, comprising a hub and blades arranged on the hub, characterized in that: The projection lines of the air inlet leading edge and the air outlet trailing edge of the blade onto the blade meridian plane of the impeller are the air inlet edge and the air outlet edge respectively, and the projection lines of the hub curved surface and the blade profile curved surface of the blade onto the blade meridian plane are the hub profile line and the blade tip profile line respectively; At least two center ribs are provided between the tip profile and the hub profile. The at least two center ribs can divide the air inlet edge and the air outlet edge into equal parts. The distribution of the blade profile angle on any center rib conforms to a Bezier curve.

2. The impeller according to claim 1, characterized in that: The air inlet edge and the air outlet edge are both straight lines and are vertically arranged, and the blade tip profile and the hub profile both conform to the Bezier spline curve.

3. The impeller according to claim 2, characterized in that: The thickness distribution of the blade at any of the center bone lines conforms to a Bezier curve.

4. The impeller according to claim 3, characterized in that: A first middle skeleton line, a second middle skeleton line and a third middle skeleton line are sequentially arranged between the blade tip profile line and the hub profile line; The blade has a first direction perpendicular to the blade meridian plane, along the first direction, a section through the first mid-bone line is made on the blade to form a first mid-bone cross section, a section through the second mid-bone line is made on the blade to form a second mid-bone cross section, and a section through the third mid-bone line is made on the blade to form a third mid-bone cross section; The blade has a second direction extending from the air inlet leading edge toward the air outlet trailing edge and along the hub profile line. Along the second direction, the sizes of the first center bone section, the second center bone section and the third center bone section in the first direction first increase and then decrease, respectively, and the size change rate of the first center bone section is smaller than the size change rate of the second center bone section, the size change rate of the second center bone section is smaller than the size change rate of the third center bone section, and the second direction is perpendicular to the first direction.

5. The impeller according to claim 4, characterized in that: Along the third direction, the sizes of the first middle bone section, the second middle bone section and the third middle bone section in the first direction increase sequentially, and the third direction is perpendicular to the first middle bone section, the second middle bone section and the third middle bone section at the same time.

6. The impeller according to claim 4, characterized in that Along the second direction, a curve of thickness variation of the blade on the first center line is M-shaped, and thickness variations of the blade on the second center line and the third center line both increase first and then decrease.

7. The impeller according to claim 6, characterized in that The blade has a thickness value b on the second center line, and the blade has a thickness value c on the third center line, wherein b=0.4-0.6c.

8. The impeller according to claim 1, characterized in that The major diameter of the impeller is 140-155 mm, and the minor diameter of the impeller is 90-110 mm; The number of the blades is at least 8, and all the blades are arranged in sequence and at equal intervals along the circumference of the hub.

9. A compressor, characterized in that: Comprising an impeller as claimed in any one of claims 1 to 8.

10. A supercharger, characterized in that: Comprising the compressor as claimed in claim 9.

Images