A turbocharger compressor impeller with high performance blades

Abstract

The present invention discloses a turbocharger compressor impeller with high-performance blades, comprising a hub (1); a plurality of pairs of blade groups are cross-distributed at equal intervals along the circumferential direction around the upper surface of the hub (1) and around the vertical central axis of the hub (1); each pair of blade groups comprises a long blade (2) and a splitter blade (3) distributed at intervals; the long blade (2) and the splitter blade (3) are both leaf-shaped blades; the thickness distribution curves of the long blade (2) and the splitter blade (3) conform to the Bezier spline curve. The turbocharger compressor impeller with high-performance blades disclosed by the present invention has a scientific structural design, and the blade thickness distribution curve of the impeller conforms to the high-order Bezier spline curve, which can accurately control the thickness of the pressure surface and the suction surface of the compressor impeller, and better control the gas flow direction while ensuring the blade strength, so that the air can obtain a higher pressure ratio in the same specification supercharger.

Description

Technical Field

[0001] The invention relates to the technical field of turbochargers, and in particular to a turbocharger compressor impeller with high-performance blades. Background Art

[0002] Turbocharging technology uses the exhaust gas from the engine to drive the turbine in the turbocharger to rotate, which in turn drives the compressor impeller to rotate. The compressor impeller then compresses the air and fills the compressed air into the engine. In order to make engines of the same size have higher combustion efficiency, better fuel economy and higher torque characteristics, the performance of the compressor impeller must be improved.

[0003] However, due to unreasonable structural design, existing ordinary compressor impellers have design defects such as insufficient blade strength, low natural frequency, and poor impeller aerodynamic performance, which affect the overall performance of the compressor. Summary of the invention

[0004] The purpose of the present invention is to provide a turbocharger compressor impeller with high-performance blades in view of the technical defects in the prior art.

[0005] To this end, the present invention provides a turbocharger compressor impeller with high-performance blades, comprising a hub;

[0006] A plurality of pairs of blade groups are cross-distributed at equal intervals around the upper surface of the hub and around the vertical center axis of the hub in the circumferential direction;

[0007] Each pair of blade groups includes a long blade and a splitter blade that are spaced apart;

[0008] Long blades and splitter blades are both leaf-shaped blades;

[0009] The thickness distribution curves of the long blades and splitter blades conform to the Bezier spline curve.

[0010] Among them, the thickness distribution curves of the long blades and the splitter blades conform to the high-order Bezier spline curve.

[0011] Wherein, the ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to a preset fixed ratio;

[0012] Among them, the thickness of the pressure surface is equal to the distance between the pressure surface and the middle camber surface of the blade, and the thickness of the suction surface is equal to the distance between the suction surface and the middle camber surface of the blade;

[0013] The blades include long blades or splitter blades.

[0014] Among them, the ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to 1:1, or (0.8~1.2):1.

[0015] The ratio of the streamline arc length between the maximum thickness of the blade and the air inlet end of the blade to the streamline arc length of the entire blade is in the range of 0.3 to 0.4.

[0016] The blades include long blades or splitter blades.

[0017] The ratio between the maximum thickness of the blade and the overall arc length of the middle arc line corresponding to the position point with the maximum thickness is 0.05 to 0.08;

[0018] The blades include long blades or splitter blades.

[0019] It can be seen from the technical solution provided by the present invention that, compared with the prior art, the present invention provides a turbocharger compressor impeller with high-performance blades, which has a scientific structural design, and the blade thickness distribution curve of the impeller conforms to the high-order (3-5th order) Bezier spline curve, which can accurately control the thickness of the pressure surface and suction surface of the compressor impeller, and better control the gas flow direction while ensuring the blade strength, so that the air can obtain a higher pressure ratio in the same specification supercharger, significantly improve the working efficiency of the supercharger, and effectively save energy.

[0020] The present invention can accurately control the thickness of each point of the blade, improve the aerodynamic performance of the impeller and the blade's natural vibration frequency, and in addition, while meeting the strength requirement, can reduce the weight of the impeller and the inertia. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 A schematic diagram of the three-dimensional structure of a turbocharger compressor impeller with high-performance blades provided by the present invention;

[0022] Figure 2 A turbocharger compressor impeller with high-performance blades provided by the present invention, showing a schematic diagram of a mid-camber surface of a long blade in an impeller θ-M' coordinate system;

[0023] Figure 3 A schematic diagram of a turbocharger compressor impeller with high-performance blades provided by the present invention, having an impeller θ-M' curve

[0024] Figure 4 A schematic diagram of a spline distribution model of the thickness distribution of a turbocharger compressor impeller with high-performance blades provided by the present invention;

[0025] Figure 5 A turbocharger compressor impeller with high-performance blades provided by the present invention, and a schematic diagram of the distribution curves of the thickness of the pressure surface and the suction surface of the impeller;

[0026] In the figure, 1 is the hub, 2 is the long blade, and 3 is the splitter blade. DETAILED DESCRIPTION

[0027] In order to enable those skilled in the art to better understand the scheme of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and implementation modes.

[0028] See also Figures 1 to 5 As shown, the present invention provides a turbocharger compressor impeller with high-performance blades, comprising a hub 1;

[0029] Around the upper surface of the hub 1, multiple pairs of blade groups are cross-distributed at equal intervals along the circumferential direction around the vertical center axis of the hub 1;

[0030] Each pair of blade groups includes a long blade 2 and a splitter blade 3 that are spaced apart;

[0031] The long blade 2 and the splitter blade 3 are both leaf-shaped blades;

[0032] The thickness distribution curves of the long blade 2 and the splitter blade 3 conform to the Bezier spline curve.

[0033] In the present invention, in a specific implementation, the thickness distribution curves of the long blades 2 and the splitter blades 3 conform to high-order (for example, 3rd to 5th order) Bezier spline curves.

[0034] It should be noted that, for the present invention, the blade thickness distribution curve of the impeller conforms to the high-order (3rd-5th order) Bezier spline curve, which can accurately control the thickness of the pressure surface and suction surface of the compressor impeller. While ensuring the strength of the blade, it can better control the gas flow direction, so that the air can obtain a higher pressure ratio in the same specification supercharger, significantly improve the working efficiency of the supercharger, and effectively save energy.

[0035] It should be noted that, for the present invention, Figure 2 In the θ-M' coordinate system, θ is the blade rotation angle, and M' is the integral of the blade meridian arc length over the radius. s is the arc length of the blade meridian plane.

[0036] In the present invention, in a specific implementation, the ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to a preset fixed ratio;

[0037] Among them, the thickness of the pressure surface is equal to the distance between the pressure surface and the middle camber surface of the blade, and the thickness of the suction surface is equal to the distance between the suction surface and the middle camber surface of the blade;

[0038] The blades include long blades or splitter blades.

[0039] In specific implementation, the ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to 1:1, or (0.8~1.2):1.

[0040] In the present invention, in a specific implementation, the ratio of the streamline arc length between the maximum thickness of the blade (long blade 2 or splitter blade 3) and the air inlet end (i.e., the air inlet edge at the top of the blade) of the blade (long blade 2 or splitter blade 3) and the overall streamline arc length of the blade (long blade 2 or splitter blade 3) is in the range of 0.3 to 0.4, which can improve the natural frequency of the blade.

[0041] In the present invention, in a specific implementation, the ratio between the maximum thickness of the blade (long blade 2 or splitter blade 3) and the overall arc length of the middle arc line corresponding to the position point with the maximum thickness (that is, the middle arc line of the long blade 2 or the splitter blade) is 0.05 to 0.08, which can improve the impeller pressure ratio, while improving the uniformity of the outlet airflow and improving the impeller efficiency.

[0042] It should be noted that, for the present invention, the structure of the compressor impeller includes a hub, a plurality of long blades and a plurality of splitter blades, the number of long blades and splitter blades is equal, and they are evenly distributed on the hub of the impeller in an alternating manner around the axial direction of the compressor impeller.

[0043] When designing the blades of the compressor impeller, the middle camber surface of the blade is first defined (specifically, the middle camber surface obtained by the middle camber line conforming to the Bezier curve, which is specifically embodied as follows: Figure 1 The side of the long blade shown in the figure is then used as a reference to determine the thickness distribution curves for the pressure side and the suction side. In the prior art, the thickness dimension is generally determined by empirical values ​​after removing conditions such as the draft angle. In actual use, due to special circumstances, design defects such as insufficient blade strength and low natural frequency often occur.

[0044] Therefore, in order to better control the gas flow direction while ensuring the strength of the impeller blades, so that the air can obtain a higher pressure ratio in the supercharger of the same size, improve the working efficiency of the supercharger, and effectively save energy, in the present invention, it is required to strictly control the thickness distribution curve of the compressor impeller.

[0045] For the present invention, in specific implementation, Figure 2 As shown, the long blade 2 has a mid-camber surface 20. Figure 3As shown, in the impeller θ-M' curve, the upper and lower sides of the middle arc line 21 have a suction edge 41 and a pressure edge 42. It should be noted that β1 and β2 are the blade airflow angles at the corresponding positions of the blades, that is, the angle between the blade profile and the airflow direction, which are important parameters for impeller design. β1 is the blade airflow angle at the blade inlet position, and β2 is the blade airflow angle at the blade outlet position. The size of this angle will affect the airflow velocity of the gas flowing through the blade and affect the aerodynamic performance efficiency pressure ratio.

[0046] like Figure 4 As shown in FIG. 1 , the thickness distribution spline distribution model of the impeller includes the hub thickness distribution curve A and the wheel cover thickness distribution curve B. Figure 4 In the figure, the horizontal axis S% is the proportion of the arc length S of the hub (wheel cover) in the meridian plane curve, the total arc length is 1, and the vertical axis is the blade thickness.

[0047] like Figure 5 As shown, the blade thickness distribution curve is defined, and in the θ-M' plane coordinates, the suction surface (or pressure surface) data corresponding to each streamline point can be solved.

[0048] To sum up, compared with the prior art, the turbocharger compressor impeller with high-performance blades provided by the present invention has a scientific structural design and can effectively prevent air backflow by controlling the shape of the hub curve edge and the wheel cover curve edge on both sides of the mid-arc surface of the blade, thereby greatly improving the compressor efficiency, and thus improving the efficiency of the entire turbocharger, and can effectively solve the technical deficiencies of existing impellers.

[0049] The present invention can accurately control the thickness of each point of the blade, improve the aerodynamic performance of the impeller and the blade's natural vibration frequency, and in addition, while meeting the strength requirement, can reduce the weight of the impeller and the inertia.

[0050] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A turbocharger compressor impeller with high-performance blades, characterized in that: comprising a wheel hub (1); A plurality of pairs of blade groups are cross-distributed at equal intervals along the circumferential direction around the upper surface of the hub (1) and around the vertical central axis of the hub (1); Each pair of blade groups includes a long blade (2) and a splitter blade (3) that are spaced apart from each other; The long blade (2) and the splitter blade (3) are both leaf-shaped blades; The thickness distribution curves of the long blade (2) and the splitter blade (3) conform to the Bezier spline curve; The blade profile curves of the long blade (2) and the splitter blade (3) are constructed in the θ-M' coordinate system; θ is the blade rotation angle, M' is the integral of the blade meridian arc length over the radius , s is the arc length of the blade meridian plane, r is the radius of the blade meridian plane; The thickness distribution curves of the long blade (2) and the splitter blade (3) conform to the high-order Bezier spline curve; The ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to a preset fixed ratio; The thickness of the pressure surface is equal to the distance between the pressure surface and the mid-arc surface of the blade, and the thickness of the suction surface is equal to the distance between the suction surface and the mid-arc surface of the blade; The blades include long blades or splitter blades; For the streamline arc length between the maximum thickness of the blade and the air inlet end of the blade, the ratio of the streamline arc length to the overall streamline arc length of the blade ranges from 0.3 to 0.4; The ratio between the maximum thickness of the blade and the overall arc length of the middle arc line corresponding to the position point with the maximum thickness is 0.05-0.

08.

2. The turbocharger compressor impeller with high performance blades according to claim 1, characterized in that: The ratio between the thickness of the pressure surface and the thickness of the suction surface is equal to (0.8~1.2):1.

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