A forward centrifugal fan impeller with guide vanes and a dehumidifier using the same

Abstract

The application relates to the technical field of dehumidifiers, in particular to a forward centrifugal fan impeller with guide vanes and a dehumidifier applying the same, wherein the fan impeller comprises a hub, a guide ring, a plurality of main vanes and a plurality of guide vanes; the plurality of guide vanes are arranged at intervals along the circumference of the hub annular area, each guide vane is twisted and distributed from inside to outside in the guide annular area and the distribution annular area from the vane front end of the guide vane to the vane tail end of the guide vane; a plurality of main vanes are arranged at intervals between the two adjacent guide vanes, the plurality of main vanes are arranged at intervals along the circumference of the guide annular area, each main vane is twisted and distributed from inside to outside in the distribution annular area from the vane front end of the main vane to the vane tail end of the main vane; the vane tail end of each main vane and each guide vane is fixedly connected to the inner ring of the guide ring. The application can solve the technical problems of the traditional forward centrifugal fan impeller, such as air flow impact loss, prominent wideband noise and narrow high-efficiency working interval.

Description

Technical Field

[0001] This invention relates to the field of dehumidifier technology, and more particularly to a forward centrifugal fan impeller with guide vanes and a dehumidifier using the same. Background Technology

[0002] In dehumidifiers, air conditioning fans, and air purifiers, the forward centrifugal fan impeller, as a core airflow driving component, directly determines the overall energy efficiency and user experience through its aerodynamic performance and acoustic quality. Currently, traditional forward centrifugal fan impellers generally face the following key technical challenges during actual operation:

[0003] (1) Significant airflow impact loss and flow separation: In the inlet area of ​​the main blade of a traditional impeller, the airflow needs to turn sharply from the axial direction to the radial direction, which easily forms a large inlet angle of attack deviation, resulting in a violent impact between the airflow and the leading edge of the blade. At the same time, a serious flow separation phenomenon occurs on the suction surface of the main blade. This problem directly causes a large amount of kinetic energy loss, making it difficult to improve the total pressure efficiency of the fan and failing to meet the current equipment's stringent requirements for high energy efficiency.

[0004] (2) Prominent broadband noise pollution: The unsteady separation flow field of traditional blades will generate a large number of unstable vortices. The generation, development and collapse of these vortices are the main sources of broadband noise in wind turbines. Especially in the critical frequency bands of equipment operation, the noise sound pressure level is high, which seriously affects the user's comfort and is difficult to adapt to application scenarios with high acoustic environment requirements.

[0005] (3) Narrow high-efficiency operating range: Traditional blades are extremely sensitive to inflow conditions. Under non-design conditions (such as air volume fluctuations), they are prone to rotational stall, which leads to a sharp decline in fan performance. Their high-efficiency operating range is limited, and their anti-interference ability is weak. They cannot adapt to the fluctuations in air volume demand caused by environmental changes (such as room area and humidity differences) in actual applications, which limits the applicable range and operational stability of the fan. Summary of the Invention

[0006] One objective of this invention is to propose a forward centrifugal fan impeller with guide vanes to solve the technical problems of traditional forward centrifugal fan impellers, such as airflow impact loss, prominent broadband noise, and narrow high-efficiency operating range.

[0007] Another object of the present invention is to provide a dehumidifier comprising a forward centrifugal fan impeller having guide vanes as described above.

[0008] To achieve this objective, the present invention adopts the following technical solution:

[0009] A forward-curved centrifugal fan impeller with guide vanes includes a hub, a guide ring, multiple main blades, and multiple guide vanes;

[0010] The main blades and guide vanes are staggered along the circumference of the hub;

[0011] Along the axial direction of the hub, the hub is divided into three concentric annular regions outward from the rotation center O': the hub annular region, the guide annular region, and the splitting annular region.

[0012] Multiple guide vanes are arranged circumferentially along the hub annular region, and each guide vane is twisted from the front end to the rear end of the guide vane and distributed from the inside to the outside in the guide annular region and the diversion annular region.

[0013] Multiple main blades are spaced apart between two adjacent guide vanes. The multiple main blades are spaced apart circumferentially along the guide ring area. Each main blade is twisted and distributed from the inside to the outside in the diversion ring area from the blade tip to the blade tail.

[0014] The blade shape of the main blade is consistent with the blade shape portion of the guide blade located in the diversion annular region;

[0015] The tail end of each main blade and the tail end of each guide blade are fixedly connected to the inner ring of the guide ring.

[0016] Preferably, the guide vane has a pressure surface and a suction surface;

[0017] Along the axial direction of the guide vane, the peripheral contour of the guide vane is formed by the leading edge of the vane, the pressure edge of the vane, the trailing edge of the vane, and the suction edge of the vane.

[0018] The connection points between the leading edge, pressure edge, trailing edge, and suction edge of the blade are defined as design point G, design point B, design point A, and design point H, respectively.

[0019] The leading edge of the blade is controlled by curve GH, and the trailing edge of the blade is controlled by curve AB, and both curve GH and curve AB are standard circular arcs;

[0020] Both the blade pressure edge and the blade suction edge are wavy lines extending from the blade leading edge to the blade trailing edge;

[0021] A point on the blade pressure edge is defined as the design point F, and the blade pressure edge is controlled and set by curves BF and FG.

[0022] A point on the suction edge of the blade is defined as design point E, and the suction edge of the blade is controlled and set by curves AE and EH;

[0023] The curves AE, EH, BF, and FG are all formed by B-spline curves;

[0024] Connect the design point E and the design point F to form curve EF;

[0025] The curves AB, BF, EF and AE enclose a region ABEF, which is distributed in the diversion ring region.

[0026] The curves FG, GH, EF, and EH enclose a region EFGH, which is distributed within the flow-guiding annular region.

[0027] Preferably, a point on the curve AE is defined as design point C, and a point on the curve BF is defined as design point D. The design point C and the design point D are connected to form curve CD.

[0028] The curves AB, BD, CD and AC enclose a region ABCD, and the blade shape of region ABCD located on the guide vane is cut to form the blade shape of the main blade.

[0029] Preferably, the leading edge of the adjacent guide vanes is defined to be controlled by curve G1H1, the two endpoints of curve G1H1 are defined as design point G1 and design point H1, and curve G1H1 is defined to be controlled by design point G1 and design point H1.

[0030] Define the angle ∠G1OG formed by the design point G1, the rotation center O', and the design point G as θ1;

[0031] Define the angle ∠G1OH formed by the design point G1, the rotation center O', and the design point H as θ2;

[0032] Define the angle ∠G1OB formed by the design point G1, the rotation center O', and the design point B as θ3;

[0033] Define the angle ∠G1OA formed by the design point G1, the rotation center O', and the design point A as θ4;

[0034] Define the angle ∠G1OF formed by the design point G1, the rotation center O', and the design point F as θ5;

[0035] Define the angle ∠G1OE formed by the design point G1, the rotation center O', and the design point E as θ6;

[0036] Define the angle ∠G1OD formed by the design point G1, the rotation center O', and the design point D as θ7;

[0037] Define the angle ∠G1OC formed by the design point G1, the rotation center O', and the design point C as θ8;

[0038] Among them, θ2=m1×θ1, 1.02<m1<1.05; θ3=m2×θ1, 1.6<m 2＜ 1.8; θ4=m3×θ1, 1.72<m3<1.91; θ5=m4×θ1, 1.75<m4<1.94; θ6=m5×θ1, 1.79<m5<2.03; θ7=m6×θ1, 1.8<m6<2.1; θ8=m7×θ1, 1.82<m7<1.85; m1, m2, m3, m4, m5, m6 and m7 are all design parameters.

[0039] Preferably, the inner radius of the guide ring is defined as R1;

[0040] The straight-line distance from the design point C and the design point D to the rotation center O' is defined as R2;

[0041] The straight-line distance from the design point E and the design point F to the rotation center O' is defined as R3;

[0042] The straight-line distance from the design point G to the rotation center O' is defined as R4;

[0043] The straight-line distance from the design point H to the rotation center O' is defined as R5;

[0044] The maximum radii of the hub annular region, the guide annular region, and the splitter annular region are defined as R, respectively. 轮毂 R 导流 R 分流 ;

[0045] Where R1=R 分流 ; R2=n1×R1, 0.79<n1<0.87; R3=R 导流 =n2×R1, 0.78<n2<0.83; R4=n3×R1, 0.52<n3<0.55; R5=n4×R1, 0.51<n4<0.54; R 轮毂 =n5×R1, 0.42<n5<0.47; n1, n2, n3, n4 and n5 are all design parameters.

[0046] Preferably, the straight line connecting the design point A and the design point E is defined as the straight line AE, and a parallel line IJ is drawn parallel to the straight line AE. The two endpoints of the parallel line IJ are defined as the design point I and the design point J, respectively. The curve AE is controlled and set by the design point I and the design point J.

[0047] Define the included angle ∠IAE formed by the design point I, the design point A, and the design point E as α1;

[0048] Define the included angle ∠JEA formed by the design point J, the design point E, and the design point A as α2;

[0049] Define the linear distance between the straight line AE and the parallel line IJ as h1;

[0050] Where, 53° < α1 < 55°, 72° < α2 < 75°, 6.1mm < h1 < 7.4mm;

[0051] Define the straight line connection between the design point E and the design point H as the straight line EH, draw a parallel line MN parallel to the straight line EH, define the two end points on the parallel line MN as the design point M and the design point N respectively, and the curve EH is set by controlling the design point M and the design point N;

[0052] Define the included angle ∠MEH formed by the design point M, the design point E, and the design point H as α5;

[0053] Define the included angle ∠NHE formed by the design point N, the design point H, and the design point E as α6;

[0054] Define the linear distance between the straight line EH and the parallel line MN as h3;

[0055] Where, 38° < α5 < 42°, 30° < α6 < 33°, 7.6mm < h3 < 8.4mm.

[0056] Preferably, define the straight line connection between the design point B and the design point F as the straight line BF, draw a parallel line KL parallel to the straight line BF, define the two end points on the parallel line KL as the design point K and the design point L respectively, and the curve BF is set by controlling the design point K and the design point L;

[0057] Define the included angle ∠KBF formed by the design point K, the design point B, and the design point F as α3;

[0058] Define the included angle ∠LFB formed by the design point L, the design point F, and the design point B as α4;

[0059] Define the linear distance between the straight line BF and the parallel line KL as h2;

[0060] Where, 67° < α3 < 71°, 79° < α4 < 82°, 6.8mm < h2 < 7.4mm;

[0061] Define the straight line connecting the design point F and the design point G as the straight line FG. Draw a parallel line OP parallel to the straight line FG. Define the two endpoints of the parallel line OP as the design point O and the design point P, respectively. The curve FG is controlled and set by the design point O and the design point P.

[0062] Define the angle ∠OFH formed by the design points O, F, and H as α7;

[0063] Define the included angle ∠PGF formed by the design points P, G, and F as α8;

[0064] Define the straight-line distance between the line FG and the parallel line OP as h4;

[0065] Among them, 27°<α7<31°, 30°<α8<34°, and 7.5mm<h4<9.2mm.

[0066] Preferably, the guide vane has a top surface and a bottom surface, and the bottom surface is fitted to the hub;

[0067] In the radial direction of the guide vane, the peripheral contour of the guide vane is formed by the top edge of the vane, the inner edge of the vane, the bottom edge of the vane, and the outer edge of the vane.

[0068] Three points on the curve EH are defined as design point Q, design point R, and design point U, with design point R located between design point Q and design point U.

[0069] In the radial direction of the guide vane, the top edge of the vane is controlled and set by a straight line AE, a straight line EQ, a curve QR, a curve RU and a straight line UH, wherein the curves QR and RU are both formed by B-spline curves;

[0070] Define the straight line connecting the design point Q and the design point R as the straight line QR. Draw a parallel line ST parallel to the straight line QR. Define the two endpoints of the parallel line ST as the design point S and the design point T, respectively. The curve QR is controlled and set by the design point S and the design point T.

[0071] Define the included angle ∠SQR formed by the design points S, Q, and R as α9;

[0072] Define the angle ∠TRQ formed by the design points T, R, and Q as α. 10 ;

[0073] Define the straight-line distance between the line QR and the parallel line ST as h5;

[0074] Define the straight line connecting the design point R and the design point U as the straight line RU. Draw a parallel line VW parallel to the straight line RU. Define the two endpoints of the parallel line VW as the design point V and the design point W, respectively. The curve RU is controlled and set by the design point R and the design point W.

[0075] Define the angle ∠VRU formed by the design points V, R, and U as α. 11 ;

[0076] Define the angle ∠WUR formed by the design points W, U, and R as α. 12 ;

[0077] Define the straight-line distance between the straight line RU and the parallel line VW as h6;

[0078] The axial distance between design point Q and design point U is defined as h7;

[0079] The axial distance between design point Q and design point R is defined as h8;

[0080] The radial distance between design point Q and design point H is defined as h9;

[0081] Define the radial distance between design point Q and design point R as h. 10 ;

[0082] Define the radial distance between design point Q and design point U as h. 11 ;

[0083] Among them, 16°<α9<19°, 24°<α 10 <27°, 2.3mm<h5<5.5mm; α 11 =α 10 , 19°<α 12 <22°, 1.2mm<h6<1.5mm; h8=i1×h7, 0.69<i1<0.75; h 10 =i2×h9,0.53<i2<0.62;h 11 =i3×h9, 0.85<i3<0.91; i1, i2 and i3 are all design parameters.

[0084] Preferably, along the axial direction of the guide vane, the midpoint of curve AB, the midpoint line between curve AE and curve BF, the midpoint of curve EF, the midpoint line between curve EH and curve FG, and the midpoint of curve GH are taken and connected in sequence to form the vane centerline.

[0085] Take any point on the centerline of the blade as design point P1. Draw a normal line through design point P1 and intersect the blade pressure edge and the blade suction edge at design points P3 and P2 respectively. Define the straight line length between design point P2 and design point P3 as the blade normal thickness corresponding to design point P1.

[0086] Along the axial direction of the hub, the blade normal thickness δ(ρ,θ) at the design point P1 can be expressed as a function of polar coordinates (ρ, θ) established with the rotation center O' as the origin, as shown below:

[0087] δ(ρ,θ)=a·[x(ρ,θ)]³+b·[x(ρ,θ)]²+c·[x(ρ,θ)]+d;

[0088] Wherein, the polar radius ρ is the straight-line distance from the design point P1 to the rotation center O', the polar angle θ is the circumferential angle of the line connecting the design point P1 and the rotation center O', and x(ρ,θ) is the coordinate of the design point P1 in polar coordinates (ρ, θ);

[0089] a is the dominant curvature factor, and a∈[-0.0025, -0.0015];

[0090] b is the convexity control factor, and b∈[-0.16, -0.13];

[0091] c is the global gradient factor, and c∈[-3.5,-2.8];

[0092] d is the reference thickness factor associated with the reference thickness, and d∈[19.0, 23.0].

[0093] A dehumidifier includes a forward centrifugal fan impeller with guide vanes as described above.

[0094] One of the above technical solutions has the following beneficial effects:

[0095] (1) Reduce airflow impact and separation to improve the total pressure efficiency of the fan: Addressing the technical problem of "significant airflow impact loss and flow separation in traditional impellers" in the background technology, this is solved through two major design approaches: First, pre-rotation control of the guide vanes corrects the airflow direction, eliminates inflow angle of attack deviation, and avoids severe impact between the airflow and the leading edge of the main blades; second, matching the airfoil shapes of the main blades and guide vanes achieves a smooth airflow transition, suppresses flow separation on the suction surface of the main blades, and reduces kinetic energy loss. The combination of these two approaches significantly improves the total pressure efficiency of the fan, meeting the stringent requirements for high energy efficiency.

[0096] (2) Suppressing broadband noise and optimizing acoustic quality: Addressing the technical problem of "prominent broadband noise pollution from traditional blades" in the background technology, the pre-swirl effect of the guide vanes can break the large-scale separation vortex formed by the airflow within the impeller, reducing the generation of unsteady separation flow (the main source of traditional broadband noise); at the same time, the smooth airflow transition avoids the superposition of turbulent noise, and the periodic layout of the main blades and guide vanes further reduces the pulsation of the rotating airflow. Ultimately, the noise sound pressure level in the key frequency band of the wind turbine can be significantly reduced, improving user comfort and making it suitable for scenarios with high acoustic requirements.

[0097] (3) Expanding the high-efficiency operating range and enhancing anti-interference capability: In response to the technical problem of "narrow high-efficiency operating range of traditional blades" in the background technology, the pre-rotation effect of the guide vanes reduces the impeller's sensitivity to inflow conditions. Even under non-design conditions (such as air volume fluctuations of ±2%), the guide vanes can still ensure effective connection between the airflow and the main blades by adjusting the airflow pre-rotation angle, thus avoiding rotational stall. At the same time, the structural stability of the guide ring ensures the stable operation of the impeller under different air volume requirements, significantly expanding the high-efficiency operating range. This allows it to adapt to air volume fluctuations caused by differences in room area and humidity, thus expanding the applicable range of the fan.

[0098] (4) Compact and reliable structure, suitable for multiple application scenarios: The integrated layout of guide vanes, main blades, guide rings and hub, combined with the periodic layout of guide vanes and main blades, ensures aerodynamic performance while taking into account structural compactness, avoiding extra parts occupying too much space, and can be adapted to equipment with limited installation space such as dehumidifiers, air conditioner fans, and air purifiers; In addition, the fixing effect of the guide ring enhances the structural strength of the blades, reduces the risk of vibration during high-speed rotation, and extends the service life of the equipment. Attached Figure Description

[0099] Figure 1 This is a schematic diagram of a forward centrifugal fan impeller with guide vanes.

[0100] Figure 2 This is a top view schematic diagram of a forward-curved centrifugal fan impeller with guide vanes;

[0101] Figure 3 This is a bottom view schematic diagram of a forward-curved centrifugal fan impeller with guide vanes;

[0102] Figure 4 This is a cross-sectional schematic diagram of a forward centrifugal fan impeller with guide vanes;

[0103] Figure 5 This is an axial structural diagram of the guide vanes in a forward centrifugal fan impeller with guide vanes;

[0104] Figure 6This is an axial design drawing of the guide vanes in a forward centrifugal fan impeller with guide vanes;

[0105] Figure 7 This is a profile design drawing of the guide vanes in a forward centrifugal fan impeller with guide vanes;

[0106] Figure 8 This is a profile design drawing of the guide vanes in a forward centrifugal fan impeller with guide vanes;

[0107] Figure 9 This is a radial structural diagram of the guide vanes in a forward-curved centrifugal fan impeller with guide vanes;

[0108] Figure 10 This is a radial design drawing of the guide vanes in a forward-curved centrifugal fan impeller with guide vanes;

[0109] Figure 11 This is a radial design drawing of the guide vanes in a forward-curved centrifugal fan impeller with guide vanes;

[0110] Figure 12 This is a design drawing of the radial angles of the guide vanes and main blades in a forward centrifugal fan impeller with guide vanes;

[0111] Figure 13 This is a design drawing of the radial radius of the guide vanes and main blades in a forward centrifugal fan impeller with guide vanes;

[0112] Figure 14 This is a comparison chart of the spectra of the embodiments and comparative examples;

[0113] Figure 15 This is a flow field diagram of an embodiment;

[0114] In the attached diagram: 1. Guide vane; 11. Pressure surface; 12. Suction surface; 13. Leading edge of the blade; 14. Pressure edge of the blade; 15. Trailing edge of the blade; 16. Suction edge of the blade; 17. Top edge of the blade; 18. Inner edge of the blade; 19. Bottom edge of the blade; 110. Outer edge of the blade; 111. Centerline of the blade; 2. Main blade; 3. Guide ring; 4. Hub; 41. Hub annular area; 42. Guide annular area; 43. Diverter annular area. Detailed Implementation

[0115] The technical solution of the present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0116] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "left," "right," "vertical," "level," "top," "bottom," "inner," "outer," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0117] Furthermore, the terms "first" and "second" 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 indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0118] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0119] A forward centrifugal fan impeller with guide vanes includes a hub 4, a guide ring 3, multiple main blades 2 and multiple guide vanes 1;

[0120] Multiple main blades 2 and guide vanes 1 are staggered along the circumference of the hub 4;

[0121] Along the axial direction of the hub 4, the hub 4 is divided into three concentric annular regions outward from the rotation center O', including the hub annular region 41, the guide annular region 42, and the diversion annular region 43;

[0122] Multiple guide vanes 1 are arranged circumferentially along the hub annular region 41, and each guide vane 1 is twisted from the inside to the outside from the front end of the guide vane 1 to the rear end of the guide vane 1 in the guide annular region 42 and the diversion annular region 43.

[0123] Multiple main blades 2 are spaced apart between two adjacent guide vanes 1. The multiple main blades 2 are spaced apart along the circumference of the guide ring area 42. Each main blade 2 is twisted from the inside to the outside in the diversion ring area 43 from the front end of the blade to the tail end of the blade.

[0124] The blade shape of the main blade 2 is the same as the blade shape portion of the guide blade 1 located in the diversion annular region 43.

[0125] The tail end of each main blade 2 and the tail end of each guide blade 1 are fixedly connected to the inner ring of the guide ring 3.

[0126] Addressing the issues of airflow impact loss, prominent broadband noise, and narrow high-efficiency operating range inherent in traditional forward centrifugal fan impellers, this technical solution is based on the core design logic of "blade pre-swirl control, blade aerodynamic optimization, and periodic layout." Through an integrated structure of "hub partitioning + main flow blade coordination + blade profile matching + guide ring fixation," it achieves the reconstruction and optimization of the impeller flow field. The specific working process is as follows:

[0127] like Figure 1-3 As shown, the flow rate deviation is first eliminated by pre-swirl correction using guide vanes 1. The hub 4 is divided into a hub annular region 41, a guide annular region 42, and a flow splitting annular region 43 along the axial direction. Guide vanes 1 are circumferentially spaced along the hub annular region 41 and cover the guide annular region 42 and the flow splitting annular region 43 from the front end to the rear end of the vanes. When the airflow enters the impeller axially, it first contacts the guide vanes 1. The guide vanes 1 use their specific tilt angle and curvature to pre-swirl control the axial airflow, generating a directional vortex system, which forcibly changes the relative velocity direction of the airflow. This avoids the problem of "airflow turning sharply from axial to radial" in traditional impellers, allowing the airflow to enter the flow splitting annular region 43 at a near-ideal angle of attack, laying the foundation for subsequent entry into the main blade 2 flow channel.

[0128] Secondly, by matching the airfoil profiles of the main blade 2 and the guide blade 1, a smooth airflow transition is achieved: multiple main blades 2 are spaced apart between adjacent guide blades 1, preferably 5-7 main blades, and the airfoil profiles of the main blades 2 are consistent with the airfoil profiles of the guide blades 1 located in the flow splitting annular region 43. After the airflow has been pre-swirled by the guide blades 1, it precisely connects with the main blades 2 in the flow splitting annular region 43: due to the airfoil matching, the airflow can smoothly transition from the flow channel of the guide blades 1 to the flow channel of the main blades 2, avoiding the phenomenon of "violent impact between the airflow and the leading edge of the main blades 2" in traditional impellers; at the same time, the main blades 2 are only distributed in the flow splitting annular region 43, and the guide blades 1 cover both the flow splitting annular region 42 and the flow splitting annular region 43, forming a synergistic path of "pre-swirling first, then guiding the air", further suppressing the flow separation on the suction surface of the main blades 2.

[0129] Finally, the flow field stability is enhanced by using the guide ring 3 for fixed constraints: the tail ends of the main blade 2 and the guide blade 1 are both fixed to the inner ring of the guide ring 3, and the guide ring 3 provides structural support for the main blade 2 and the guide blade 1, ensuring the positional accuracy of the main blade 2 and the guide blade 1 when rotating at high speed, and avoiding flow field turbulence caused by blade vibration.

[0130] To further explain, the guide vane 1 has a pressure surface 11 and a suction surface 12; in the axial direction of the guide vane 1, the peripheral contour of the guide vane 1 is formed by the blade leading edge 13, the blade pressure edge 14, the blade trailing edge 15 and the blade suction edge 16.

[0131] The connection points between the blade leading edge 13, the blade pressure edge 14, the blade trailing edge 15, and the blade suction edge 16 are defined as design point G, design point B, design point A, and design point H, respectively.

[0132] The leading edge 13 of the blade is controlled by curve GH, and the trailing edge 15 of the blade is controlled by curve AB, and both curve GH and curve AB are standard circular arcs;

[0133] Both the blade pressure edge 14 and the blade suction edge 16 are wavy lines extending from the blade leading edge 13 to the blade trailing edge 15; a point on the blade pressure edge 14 is defined as design point F, and the blade pressure edge 14 is controlled by curves BF and FG; a point on the blade suction edge 16 is defined as design point E, and the blade suction edge 16 is controlled by curves AE and EH; curves AE, EH, BF, and FG are all formed by B-spline curves;

[0134] Connect the design point E and the design point F to form curve EF;

[0135] The curves AB, BF, EF and AE enclose a region ABEF, which is distributed in the diversion ring region 43.

[0136] The curves FG, GH, EF and EH enclose a region EFGH, which is distributed in the flow-guiding annular region 42.

[0137] like Figure 3-6 As shown, the hub 4 is known to be divided into a guide ring region 42 and a flow splitting ring region 43 along the axial direction. Therefore, the guide blade 1 divides the functional areas of the two regions by the contour curve: the area EFGH enclosed by curves FG, GH, EF and EH is distributed in the guide ring region 42, and the area ABEF enclosed by curves AB, BF, EF and AE is distributed in the flow splitting ring region 43.

[0138] When the airflow enters the impeller axially, it first enters the EFGH region of the guide ring region 42. The blade leading edge 13, blade pressure edge 14 and blade suction edge 16 in this region adopt the optimized blade profile of "standard circular arc + B spline curve". The specific curvature of the curve can be used to implement pre-swirl control of the axial airflow, generate a directional vortex system, initially correct the airflow direction, and avoid the technical problem of "axial airflow directly turning radially" in traditional impellers.

[0139] After pre-swirl in the EFGH region, the airflow enters the ABEF region of the splitting annular region 43. In this region, the blade trailing edge 15, blade pressure edge 14, and blade suction edge 16 adopt an optimized airfoil profile of "standard circular arc + B-spline curve," precisely aligned with the distribution area of ​​the main blade 2. On one hand, the B-spline characteristics of curves BF and AE can dynamically adjust the flow channel cross-section according to changes in airflow velocity, eliminating local separation of airflow at the transition point. On the other hand, the ABEF region of the guide vane 1 is spaced apart from the main blade 2, and the airfoil profile of the main blade 2 matches the airfoil profile of the ABEF region of the guide vane 1, allowing the pre-swirled airflow to enter the flow channel of the main blade 2 at a near-ideal angle of attack, completely avoiding severe impact between the airflow and the leading edge of the main blade 2.

[0140] To further explain, a point on the curve AE is defined as design point C, and a point on the curve BF is defined as design point D. The design point C and the design point D are connected to form curve CD.

[0141] The curves AB, BD, CD and AC enclose a region ABCD, and the blade shape of region ABCD located on the guide vane 1 is cut to form the blade shape of the main blade 2.

[0142] like Figure 6 As shown, to achieve flow field coordination between the main blade 2 and the guide vane 1, the airfoil region ABCD on the guide vane 1 is extracted as the airfoil of the main blade 2. Essentially, this reuses the aerodynamically optimized core profile of the guide vane 1. Furthermore, curves AE and BF are both B-spline curves, offering the advantage of flexible adaptation to airflow characteristics. Region ABCD precisely contains this optimized curve segment. When the airflow enters the main blade 2 flow channel after pre-swirl by the guide vane 1, because the airfoil of the main blade 2 originates from the core adaptation region of the guide vane 1, the flow direction and velocity gradient of the airflow between the main blade 2 and the guide vane 1 can be seamlessly connected. This completely avoids the technical problem of "airflow turning impact caused by the independent design of the main blade 2 airfoil" in traditional impellers, forcibly correcting the relative velocity direction of the airflow and eliminating inlet angle of attack deviation.

[0143] To further explain, the leading edge 13 of adjacent guide vanes 1 is defined to be controlled by curve G1H1, and the two endpoints of curve G1H1 are defined to be design point G1 and design point H1, respectively. Curve G1H1 is defined to be controlled by design point G1 and design point H1.

[0144] Define the angle ∠G1OG formed by the design point G1, the rotation center O', and the design point G as θ1;

[0145] Define the angle ∠G1OH formed by the design point G1, the rotation center O', and the design point H as θ2;

[0146] Define the angle ∠G1OB formed by the design point G1, the rotation center O', and the design point B as θ3;

[0147] Define the angle ∠G1OA formed by the design point G1, the rotation center O', and the design point A as θ4;

[0148] Define the angle ∠G1OF formed by the design point G1, the rotation center O', and the design point F as θ5;

[0149] Define the angle ∠G1OE formed by the design point G1, the rotation center O', and the design point E as θ6;

[0150] Define the angle ∠G1OD formed by the design point G1, the rotation center O', and the design point D as θ7;

[0151] Define the angle ∠G1OC formed by the design point G1, the rotation center O', and the design point C as θ8;

[0152] Among them, θ2=m1×θ1, 1.02<m1<1.05; θ3=m2×θ1, 1.6<m 2＜ 1.8; θ4=m3×θ1, 1.72<m3<1.91; θ5=m4×θ1, 1.75<m4<1.94; θ6=m5×θ1, 1.79<m5<2.03; θ7=m6×θ1, 1.8<m6<2.1; θ8=m7×θ1, 1.82<m7<1.85; m1, m2, m3, m4, m5, m6 and m7 are all design parameters.

[0153] like Figure 12As shown, taking the rotation center O' of hub 4 as the base point, the angle ∠G1OG formed by the design point G1 of curve G1H1 in the leading edge 13 of adjacent guide vanes 1 and the design point G of the leading edge 13 of the current guide vane 1 is defined as θ1. This angle directly determines the circumferential spacing density of guide vanes 1, providing a reference for all subsequent angle parameters, ensuring that multiple guide vanes 1 are uniformly distributed circumferentially along the hub annular region 41, avoiding flow field turbulence caused by uneven spacing, and providing a stable circumferential basis for airflow pre-swirl.

[0154] Based on θ1, the proportional relationships of the remaining 7 included angles are established, and each proportional coefficient m1-m7 is within the defined aerodynamic optimization range. Its core function is to ensure, through angle linkage, that the key design points (design points H, B, A, F, E, D, and C) of the main blade 2 and guide blade 1 are highly matched with the airflow trajectory in the circumferential direction.

[0155] ∠G1OH, i.e., θ2, is finely adjusted by m1 (1.02 < m1 < 1.05) to the position of the design point H of the leading edge suction surface of the guide vane 1, so that the curve GH can accurately receive the axial inflow and initially guide the airflow to pre-swirl.

[0156] ∠G1OB, i.e. θ3, and ∠G1OA, i.e. θ4 are located by m2 (1.6 < m2 < 1.8) and m3 (1.72 < m3 < 1.91), respectively, to ensure that the curve AB of the trailing edge 15 of the blade can smoothly guide the pre-swirled airflow into the flow channel of the main blade 2.

[0157] ∠G1OF, i.e. θ5, and ∠G1OE, i.e. θ6 are located at the design point F of the blade pressure edge 14 and the design point E of the blade suction edge 16 by m4 (1.75 < m4 < 1.94) and m5 (1.79 < m5 < 2.03), so that curves BF and AE can adapt to the acceleration requirements of the airflow in the middle of the guide vane 1 and suppress local separation.

[0158] ∠G1OD (θ7) and ∠G1OC (θ8) are positioned at design points D and C via m6 (1.8 < m6 < 2.1) and m7 (1.82 < m7 < 1.85), respectively, to ensure that the circumferential position of the intercepted area ABCD (i.e., the blade shape of the main blade 2) completely coincides with the installation area of ​​the main blade 2 (i.e., the diversion ring area 43), thus achieving seamless docking between the blade shape of the main blade 2 and the guide blade 1.

[0159] To further clarify, the inner radius of the guide ring 3 is defined as R1;

[0160] The straight-line distance from the design point C and the design point D to the rotation center O' is defined as R2;

[0161] The straight-line distance from the design point E and the design point F to the rotation center O' is defined as R3;

[0162] The straight-line distance from the design point G to the rotation center O' is defined as R4;

[0163] The straight-line distance from the design point H to the rotation center O' is defined as R5;

[0164] The maximum radii of the hub annular region 41, the guide annular region 42, and the splitter annular region 43 are defined as R, respectively. 轮毂 R 导流 R 分流 ;

[0165] Where R1=R 分流 ; R2=n1×R1, 0.79<n1<0.87; R3=R 导流 =n2×R1, 0.78<n2<0.83; R4=n3×R1, 0.52<n3<0.55; R5=n4×R1, 0.51<n4<0.54; R 轮毂 =n5×R1, 0.42<n5<0.47; n1, n2, n3, n4 and n5 are all design parameters.

[0166] like Figure 13 As shown, firstly, the inner radius of the guide ring 3 is defined as R1, and it is explicitly stated that R1 = R 分流 This binding relationship directly connects the guide ring 3 to the core working area (i.e., the flow splitting annular region 43) of the main blade 2. The inner radius R1 of the guide ring 3 serves as the reference for all radius parameters, ensuring that the radial positions of the hub partition, the key design points of the main blade, and the key design points of the guide blade all revolve around the working area of ​​the main blade 2. This avoids flow field disruption caused by radial dimension misalignment and lays the dimensional foundation for a smooth transition of airflow from the guide annular region 42 to the flow splitting annular region 43.

[0167] Secondly, based on R1, define the maximum radius of the hub annular region 41 and the maximum radius of the guide annular region 42: R 导流 =n2×R1 (0.78<n2<0.83), R 轮毂 =n5×R1 (0.42<n5<0.47), and R 导流 <R 分流 This forms a radial gradient partition of "hub ring area 41 → guide ring area 42 → split ring area 43", which can guide the airflow to gradually accelerate and turn along the radial gradient: the axial inflow first enters the guide ring area 42 to complete the pre-rotation, and then enters the split ring area 43 to dock with the main blade 2, avoiding the impact loss caused by the "single-section radial rapid rotation" of the traditional impeller.

[0168] Finally, the radial positions of the key design points (design points C, D, E, F, G, and H) of the main blade 2 and guide blade 1 are bound to R1 using proportionality coefficients n1-n4, and all coefficients are within the defined aerodynamic optimization range to ensure that each design point is highly compatible with the airflow characteristics.

[0169] Specifically, R2 (distance from design points C and D to O) = n1 × R1 (0.79 < n1 < 0.87): Design points C and D are the key points for truncating the two-blade profile of the main blade (region ABCD). R2 is slightly smaller than R1 (i.e., R... 分流 This ensures that the blade profile of the main blade 2 is completely distributed within the diversion annular region 43, thus matching the function of the main blade 2 in "receiving the pre-swirling airflow and guiding it to the outlet".

[0170] R3 (distance from design points E and F to O) = R 导流 =n2×R1: Design points E and F are the key points of the pressure edge and suction edge 16 of the guide vane 1. Their radial positions coincide with the maximum radius of the guide ring area 42, ensuring that the airfoil of the guide vane 1 in the guide ring area 42 (region EFGH) can fully guide the airflow pre-swirl, and at the same time form a radial connection with the airfoil of the main blade 2 in the split ring area 43 (region ABCD).

[0171] R4 (distance from design point G to O) = n3 × R1 (0.52 < n3 < 0.55), R5 (distance from design point H to O) = n4 × R1 (.51 < n4 < .54): Design point G and design point H are the two endpoints of the leading edge 13 of the blade. The smaller radial distance allows the leading edge curve GH to receive the axial inflow near the hub 4. The longer radial extension section enables the airflow to smoothly turn from axial to radial, avoiding abrupt impact.

[0172] To further explain, the straight line connecting design point A and design point E is defined as line AE. A parallel line IJ is drawn parallel to line AE. The two endpoints of the parallel line IJ are defined as design point I and design point J, respectively. The curve AE is controlled and set by design point I and design point J.

[0173] Define the included angle ∠IAE formed by the design points I, A, and E as α1;

[0174] Define the included angle ∠JEA formed by the design points J, E and A as α2;

[0175] Define the straight-line distance between the line AE and the parallel line IJ as h1;

[0176] Among them, 53°<α1<55°, 72°<α2<75°, and 6.1mm

[0177] Define the straight line connecting the design point E and the design point H as the straight line EH. Draw a parallel line MN parallel to the straight line EH. Define the two endpoints of the parallel line MN as the design point M and the design point N, respectively. The curve EH is controlled and set by the design point M and the design point N.

[0178] Define the included angle ∠MEH formed by the design points M, E, and H as α5;

[0179] Define the included angle ∠NHE formed by the design points N, H and E as α6;

[0180] Define the straight-line distance between the line EH and the parallel line MN as h3;

[0181] Among them, 38°<α5<42°, 30°<α6<33°, and 7.6mm<h3<8.4mm.

[0182] like Figure 7 As shown, curve AE is the trailing edge section of the suction edge 16 of the guide vane 1, and its profile directly affects the adhesion and transition smoothness of the airflow on the suction surface. Precise control of curve AE is achieved through "parallel line IJ + included angle α1 + included angle α2 + distance h1": Parallel line IJ is drawn with straight line AE as the reference, and the distance h1 between parallel line IJ and curve AE is defined (6.1mm < h1 < 7.4mm), providing basic contour constraints for B-spline curve (curve AE), ensuring that the curve curvature changes smoothly and avoiding local separation of airflow on the suction surface; at the same time, ∠IAE=α1 (53° < α1 < 55°) and ∠JEA=α2 (72° < α2 < 75°) are defined, and the positions of design point I and design point J are limited by the two included angles. α1 ensures that curve AE can smoothly connect with the blade profile of main blade 2 in the part close to the intercepted area ABEF of main blade 2, eliminating the turning impact of airflow from guide vane 1 to main blade 2; α2 optimizes the bending trend of curve AE in the middle section, adapts to the velocity gradient after airflow pre-swirl, maintains pressure balance on the suction surface, and suppresses the generation of separation vortices.

[0183] ​The curve EH serves as the leading edge segment of the blade suction edge 16 in the guide vane 1, and its profile determines the pre-whirl effect of the axial inflow and the initial air guiding direction. Precise control is achieved through "parallel line MN + included angle α5 + included angle α6 + distance h3": Taking the straight line EH as the reference to draw the parallel line MN, setting the spacing h3 (7.6 mm < h3 < 8.4 mm) to ensure that the bending degree of the curve EH can guide the axial air flow to gradually turn radially, avoiding the impact loss caused by the "sharp turn" of the traditional impeller; at the same time, defining ∠MEH = α5 (38° < α5 < 42°) and ∠NHE = α6 (30° < α6 < 33°), the positions of the design point M and the design point N are controlled by the included angle limit. α5 optimizes the curvature of the curve EH in the middle section (near the design point E) so that the pre-whirled air flow can smoothly transition to the curve AE; α6 adjusts the air guiding angle of the curve EH in the leading edge section (near the design point H) to ensure that the axial inflow can cut into the blade leading edge 13 at an ideal attack angle, reducing the air flow impact and weakening the strength of the leading edge separation vortex at the same time.

[0184] For further illustration, define the straight line connection between the design point B and the design point F as the straight line BF, draw a parallel line KL parallel to the straight line BF, define the two end points on the parallel line KL as the design point K and the design point L respectively, and the curve BF is controlled and set by the design point K and the design point L;

[0185] Define the included angle ∠KBF formed by the design point K, the design point B and the design point F as α3;

[0186] Define the included angle ∠LFB formed by the design point L, the design point F and the design point B as α4;

[0187] Define the straight line distance between the straight line BF and the parallel line KL as h2;

[0188] Among them, 67° < α3 < 71°, 79° < α4 < 82°, 6.8 mm < h2 < 7.4 mm;

[0189] Define the straight line connection between the design point F and the design point G as the straight line FG, draw a parallel line OP parallel to the straight line FG, define the two end points on the parallel line OP as the design point O and the design point P respectively, and the curve FG is controlled and set by the design point O and the design point P;

[0190] [[ID=2I]]Define the included angle ∠OFH formed by the design point O, the design point F and the design point H as α7;

[0191] Define the included angle ∠PGF formed by the design point P, the design point G and the design point F as α8;

[0192] Define the straight line distance between the straight line FG and the parallel line OP as h4;

[0193] Among them, 27°<α7<31°, 30°<α8<34°, and 7.5mm<h4<9.2mm.

[0194] like Figure 8 As shown, curve BF, as the trailing edge segment of the pressure edge 14 in guide vane 1, directly determines the acceleration efficiency of the airflow on the pressure surface and the smoothness of the transition to the main blade 2. Precise control is achieved through "parallel line KL + included angle α3 + α4 + distance h2": A parallel line KL is drawn based on the straight line BF, and the distance between them is set to h2 (6.8mm < h2 < 7.4mm), providing a basic profile constraint for the B-spline curve (curve BF). The gentle distance ensures uniform curvature change of curve BF, avoiding local separation of the airflow on the pressure surface due to abrupt changes in the profile, while providing a stable pressure gradient to drive efficient airflow acceleration; simultaneously, ∠KBF = α3 (67° < α3 < 71°), ∠LFB = α4 (79° < α4 < 82°) defines the positions of design points K and L by two included angles: α3 optimizes the profile of curve BF in the intercepted area ABCD (design point D) near the main blade 2, ensuring that the airflow on the pressure surface can smoothly connect with the pressure surface of the main blade 2, eliminating the turning impact of the airflow from the guide vane 1 to the main blade 2, and avoiding kinetic energy loss; α4 adjusts the curvature trend of curve BF in the middle section (near design point F), adapts to the velocity increment after the airflow pre-swirls, maintains the stability of the pressure field on the pressure surface, and suppresses the generation of unsteady vortices.

[0195] Curve FG, serving as the leading edge section of the pressure flange 14 in guide vane 1, determines the initial pre-swirl direction and introduction efficiency of the axial inflow on the pressure surface. Precise control is achieved through "parallel line OP + included angle α7 + included angle α8 + distance h4": A parallel line OP is drawn based on the straight line FG, and the distance between them is set to h4 (7.5mm < h4 < 9.2mm). This ensures that the curvature of curve FG guides the axial airflow to gradually turn radially. The longer distance design allows the leading edge section of the curve to have a smoother turning trajectory, avoiding the severe impact caused by the traditional impeller's "rapid axial-to-radial rotation" and reducing airflow stagnation losses. Simultaneously, ∠OFG = α7 (27° < α7 < 31°) is defined. ∠PGF=α8 (30°<α8<34°), the positions of the control endpoints O and P are limited by the included angle: α7 optimizes the curvature of curve FG in the middle section (close to the design point F), so that the airflow on the pressure surface can smoothly connect with curve BF to form a continuous acceleration channel; α8 adjusts the air guide angle of curve FG in the leading edge section (close to the design point G), ensuring that the axial inflow can cut into the front edge of the pressure surface at a near-ideal angle of attack, reducing impact loss, and forming a directional vortex system in conjunction with the leading edge 13 of the suction surface blades to enhance the pre-swirl effect of the airflow.

[0196] To further explain, the guide vane 1 has a top surface and a bottom surface, and the bottom surface is fitted with the hub 4;

[0197] In the radial direction of the guide vane 1, the peripheral contour of the guide vane 1 is formed by the top edge 17, the inner edge 18, the bottom edge 19 and the outer edge 110 of the vane.

[0198] Three points on the curve EH are defined as design point Q, design point R, and design point U, with design point R located between design point Q and design point U.

[0199] In the radial direction of the guide vane 1, the top edge 17 of the vane is controlled and set by a straight line AE, a straight line EQ, a curve QR, a curve RU and a straight line UH, wherein the curves QR and RU are both formed by B-spline curves;

[0200] Define the straight line connecting the design point Q and the design point R as the straight line QR. Draw a parallel line ST parallel to the straight line QR. Define the two endpoints of the parallel line ST as the design point S and the design point T, respectively. The curve QR is controlled and set by the design point S and the design point T.

[0201] Define the included angle ∠SQR formed by the design points S, Q, and R as α9;

[0202] Define the angle ∠TRQ formed by the design points T, R, and Q as α. 10 ;

[0203] Define the straight-line distance between the line QR and the parallel line ST as h5;

[0204] Define the straight line connecting the design point R and the design point U as the straight line RU. Draw a parallel line VW parallel to the straight line RU. Define the two endpoints of the parallel line VW as the design point V and the design point W, respectively. The curve RU is controlled and set by the design point R and the design point W.

[0205] Define the angle ∠VRU formed by the design points V, R, and U as α. 11 ;

[0206] Define the angle ∠WUR formed by the design points W, U, and R as α. 12 ;

[0207] Define the straight-line distance between the straight line RU and the parallel line VW as h6;

[0208] The axial distance between design point Q and design point U is defined as h7;

[0209] The axial distance between design point Q and design point R is defined as h8;

[0210] The radial distance between design point Q and design point H is defined as h9;

[0211] Define the radial distance between design point Q and design point R as h. 10 ;

[0212] Define the radial distance between design point Q and design point U as h. 11 ;

[0213] Among them, 16°<α9<19°, 24°<α 10 <27°, 2.3mm<h5<5.5mm; α 11 =α 10 , 19°<α 12 <22°, 1.2mm<h6<1.5mm; h8=i1×h7, 0.69<i1<0.75; h 10 =i2×h9,0.53<i2<0.62;h 11 =i3×h9, 0.85<i3<0.91; i1, i2 and i3 are all design parameters.

[0214] like Figure 4 , 6 As shown in Figures 9-11, the radial peripheral contour of the guide vane 1 is formed by the top edge 17, the inner edge 18, the bottom edge 19, and the outer edge 110. Specifically, the top edge 17 is formed by the radial projection of the suction edge 16 onto the guide vane 1; the bottom edge 19 is formed by the radial projection of the mounting profile of the blade bottom surface onto the guide vane 1; the inner edge 18 is formed by the radial projection of the leading edge of the guide vane 1 onto the guide vane 1; and the outer edge 110 is formed by the radial projection of the trailing edge of the guide vane 1 onto the guide vane 1. Each edge precisely corresponds to the core functional area of ​​the guide vane 1.

[0215] The blade tip edge 17 is formed by the radial projection of the blade suction edge 16, and is controlled by straight lines AE, EQ, QR, RU, and UH. Among them, curves QR and RU serve as the core optimized profiles (both B-spline curves) in the tip region of the guide vane 1, achieving precise flow control through the parameters of "parallel lines + included angle + distance," focusing on solving the problem of tip leakage loss.

[0216] First, control the QR curve: draw a parallel line ST based on the straight QR, with a spacing of h5 (2.3mm < h5 < 5.5mm), to ensure a gentle curvature of the QR curve and avoid airflow separation at the blade tip due to abrupt changes in the profile; simultaneously, ∠SQR = α9 (16° < α9 < 19°), ∠TRQ = α 10 (24°<α)10 <27°) Limit the positions of the control design points S and T, and optimize the profile of the curve QR close to point Q to ensure a smooth connection with the straight line EQ; α 10 Then adjust the curvature of the middle section of the QR curve to weaken the intensity of the leaking airflow at the blade tip by guiding the profile, thereby reducing leakage losses.

[0217] Secondly, curve RU control: Using the straight line RU as a reference, draw a parallel line VW with a spacing of h6 (1.2mm < h6 < 1.5mm) to ensure a smooth transition between curve RU and curve QR at point R; ∠VRU = α 11 (α) 11 =α 10 ), ∠WUR=α 12 (19°<α) 12 <22°) defines the locations of design points V and W, α 11 Ensure the curvature of the two curve segments is consistent to avoid turbulence in the airflow at point R; α 12 The profile of the RU curve near point U is optimized to connect with the straight line UH, further suppressing the interference between the leaking airflow at the blade tip and the mainstream.

[0218] Finally, the axial and radial distances are coordinated: axial distances h7 and h8 are correlated through a coefficient i1 to ensure that the blade tip cutting depth (h7) matches the axial position of point R (h8), avoiding insufficient structural strength due to excessive cutting depth or leakage suppression failure due to insufficient cutting depth; simultaneously, radial distances h9, h1, and h... 11 By correlating coefficients i2 and i3, it is ensured that the radial coverage of curves QR and RU is consistent with the trajectory of the leaking airflow at the blade tip, with a radial distance h. 10 Make the curve QR cover the core area of ​​the blade tip leakage, with a radial distance h. 11 The RU section of the curve extends to the leading edge, and the two work together to form a "gradient" blade tip profile, gradually weakening the energy of the leaking airflow and reducing its interference with the mainstream field.

[0219] The blade bottom edge 19 is formed by the projection of the blade bottom surface mounting profile. Because the blade bottom surface is in contact with the hub 4, the lower edge can be completely adapted to the surface of the hub 4, avoiding airflow leakage caused by radial clearance.

[0220] The inner edge 18 and outer edge 110 of the blade are formed by the projection of the blade tip and the blade tail, respectively, and match the radial range of the hub partition (hub annular region 41 - guide annular region 42 - flow splitting annular region 43) to ensure that the airflow moves in an orderly manner along the radial gradient and avoids the problem of "radial flow field disorder" in traditional impellers.

[0221] To further explain, along the axial direction of the guide vane 1, the midpoint of curve AB, the midpoint line between curve AE and curve BF, the midpoint of curve EF, the midpoint line between curve EH and curve FG, and the midpoint of curve GH are taken and connected in sequence to form the vane centerline 111.

[0222] Take any point on the blade centerline 111 as design point P1, draw a normal line through design point P1 and intersect the blade pressure edge 14 and the blade suction edge 16 at design points P3 and P2 respectively, and define the straight line length between design point P2 and design point P3 as the blade normal thickness corresponding to design point P1.

[0223] Along the axial direction of the hub 4, the blade normal thickness δ(ρ,θ) at the design point P1 can be expressed as a function of polar coordinates (ρ, θ) established with the rotation center O' as the origin, as shown below:

[0224] δ(ρ,θ)=a·[x(ρ,θ)]³+b·[x(ρ,θ)]²+c·[x(ρ,θ)]+d;

[0225] Wherein, the polar radius ρ is the straight-line distance from the design point P1 to the rotation center O', the polar angle θ is the circumferential angle of the line connecting the design point P1 and the rotation center O', and x(ρ,θ) is the coordinate of the design point P1 in polar coordinates (ρ, θ);

[0226] a is the dominant curvature factor, and a∈[-0.0025, -0.0015];

[0227] b is the convexity control factor, and b∈[-0.16, -0.13];

[0228] c is the global gradient factor, and c∈[-3.5,-2.8];

[0229] d is the reference thickness factor associated with the reference thickness, and d∈[19.0, 23.0].

[0230] like Figure 5-6 As shown, along the axial direction of the guide vane 1, the centerline 111 of the vane is formed by selecting the midpoint of the key curve and connecting the midpoint line in sequence. This centerline 111 is the core reference for thickness design and is characterized by polar coordinate functions to achieve precise control of non-uniform thickness: the normal thickness at the design point P1 is expressed as a function of polar coordinates (ρ,θ) (δ(ρ,θ)=a・[x(ρ,θ)]³+b・[x(ρ,θ)]²+c・[x(ρ,θ)]+d), where the functions of each coefficient are as follows:

[0231] Curvature dominance factor a (∈ [-0.0025, -0.0015]): Dominates the curvature variation of the thickness distribution. When a is in this range, a reasonable thickening zone can be formed at the leading edge 13 of the blade (to resist airflow impact), while avoiding excessive thinning of the trailing edge that could cause flutter. If a > -0.0025, the leading edge thickening zone disappears and cannot buffer airflow impact; if a < -0.0015, the trailing edge strength is insufficient, and structural flutter is likely to occur during high-speed rotation.

[0232] Convexity control factor b (∈[-0.16, -0.13]): controls the chordal position of the blade's maximum thickness point, which is crucial for maintaining the balance of the pressure gradient on the blade surface. The value of b ensures that the maximum thickness point is located in the chordal 4%-6% region, which can provide a stable pressure gradient for airflow to achieve efficient energy conversion and avoid local airflow separation caused by the offset of the maximum thickness point.

[0233] Global gradient factor c (∈[-3.5,-2.8]): determines the thickness gradient of the blade leading edge 13. Its value directly affects the effect of inflow angle of attack correction. If c exceeds this range, the leading edge thickness change will be too steep or too slow, which will cause the airflow to be unable to cut into the blade channel in the ideal direction, resulting in impact loss.

[0234] Reference thickness factor d (∈[19.0, 23.0]): associated with the reference thickness of the blade, which is the key to balancing aerodynamic performance and structural strength. If the value of d is too large, the blade will be too thick, increasing airflow friction drag; if the value of d is too small, the structural strength will be insufficient and unable to withstand aerodynamic loads. The value in this range can simultaneously meet the requirements of "low airflow drag" and "high structural reliability".

[0235] A dehumidifier includes a forward centrifugal fan impeller with guide vanes as described above.

[0236] To further demonstrate the performance of the combined application of main blades and guide vanes on a wind turbine impeller in this invention, a comparative example was used, consisting only of main blades without guide vanes. Performance test results were obtained under the same test conditions. The wind turbine performance test data are shown in the table below, and the spectrum comparison diagram is shown in the figure below. Figure 14 As shown, the flow field diagram of the combined action of the main blade and the guide vanes is as follows: Figure 15 As shown.

[0237]

[0238] Wind turbine performance test data shows that, at the same rotational speed, adding guide vanes increases airflow by more than 20%, while noise decreases. This achieves a dual optimization of "increased volume and reduced noise." The principle behind this is that the guide vanes effectively streamline the intake airflow, reducing eddies and resistance, thereby improving aerodynamic efficiency and static pressure utilization, allowing the wind turbine to output a larger airflow in a quieter state.

[0239] As can be clearly seen from the spectrum comparison chart, in the key human ear sensitive frequency range of 200Hz to 1000Hz, the noise sound pressure level after adding the guide vanes is significantly lower, and the overall spectrum curve is flatter. This means that it effectively smooths out the high energy peaks caused by disordered turbulence, making the noise sound quality become softer and more uniform from rough and abrupt, thus achieving a quality improvement from "noisy" to "quiet" in terms of auditory experience.

[0240] The flow field diagram showing the combined effect of the guide vanes and main blades reveals that the streamlines with the guide vanes are smooth and regular, effectively guiding the airflow to enter the impeller at a better angle and more evenly, greatly suppressing the generation and shedding of vortices. This not only reduces flow losses and improves airflow and efficiency, but also weakens the noise caused by turbulence and vortex impacts at the source, achieving dual optimization of aerodynamic and acoustic performance.

[0241] The technical principles of the present invention have been described above with reference to specific embodiments. These descriptions are merely for explaining the principles of the invention and should not be construed as limiting the scope of protection of the invention in any way. Based on this explanation, those skilled in the art can readily conceive of other specific embodiments of the invention without inventive effort, and these equivalent variations or substitutions are all included within the scope defined by the claims of this application.

Claims

1. A forward-curved centrifugal fan impeller with guide vanes, characterized in that, It includes a hub (4), a guide ring (3), multiple main blades (2) and multiple guide vanes (1); Multiple main blades (2) and guide vanes (1) are staggered along the circumference of the hub (4); Along the axial direction of the hub (4), the hub (4) is divided into three concentric annular regions outward from the rotation center O', including the hub annular region (41), the guide annular region (42), and the diversion annular region (43). Multiple guide vanes (1) are arranged circumferentially along the hub annular region (41), and each guide vane (1) is twisted from the front end of the guide vane (1) to the rear end of the guide vane (1) in sequence from the inside to the outside in the guide annular region (42) and the diversion annular region (43). Multiple main blades (2) are spaced apart between two adjacent guide vanes (1). The multiple main blades (2) are spaced apart circumferentially along the guide ring area (42). Each main blade (2) is twisted from the front end to the rear end of the blade and distributed in the diversion ring area (43) from the inside to the outside. The blade shape of the main blade (2) is consistent with the blade shape of the guide blade (1) located in the diversion annular region (43); The tail end of each main blade (2) and the tail end of each guide blade (1) are fixedly connected to the inner ring of the guide ring (3); The guide vane (1) has a pressure surface (11) and a suction surface (12). Along the axial direction of the guide vane (1), the peripheral contour of the guide vane (1) is formed by the leading edge (13), the pressure edge (14), the trailing edge (15), and the suction edge (16). The connection points between the leading edge (13), pressure edge (14), trailing edge (15), and suction edge (16) of the blade are defined as design point G, design point B, design point A, and design point H, respectively. The leading edge (13) of the blade is controlled by curve GH, and the trailing edge (15) of the blade is controlled by curve AB. Both curve GH and curve AB are standard circular arcs. The blade pressure edge (14) and the blade suction edge (16) are both wavy lines extending from the blade leading edge (13) to the blade trailing edge (15); A point on the blade pressure edge (14) is defined as the design point F, and the blade pressure edge (14) is controlled and set by curves BF and FG; A point on the blade suction edge (16) is defined as design point E, and the blade suction edge (16) is controlled and set by curves AE and EH; The curves AE, EH, BF, and FG are all formed by B-spline curves; Connect the design point E and the design point F to form curve EF; The curves AB, BF, EF and AE enclose a region ABEF, which is distributed in the diversion ring region (43). The curves FG, GH, EF and EH enclose a region EFGH, which is distributed in the flow-guiding annular region (42). Define a point on the curve AE as design point C, define a point on the curve BF as design point D, and connect design point C and design point D to form curve CD; The curves AB, BD, CD and AC enclose a region ABCD, and the blade shape of region ABCD located on the guide vane (1) is cut to form the blade shape of the main blade (2).

2. The forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, The leading edge (13) of the adjacent guide vanes (1) is defined to be controlled by the curve G1H1. The two endpoints of the curve G1H1 are defined as design point G1 and design point H1, and the curve G1H1 is defined to be controlled by the design point G1 and design point H1. Define the angle ∠G1OG formed by the design point G1, the rotation center O', and the design point G as θ1; Define the angle ∠G1OH formed by the design point G1, the rotation center O', and the design point H as θ2; Define the angle ∠G1OB formed by the design point G1, the rotation center O', and the design point B as θ3; Define the angle ∠G1OA formed by the design point G1, the rotation center O', and the design point A as θ4; Define the angle ∠G1OF formed by the design point G1, the rotation center O', and the design point F as θ5; Define the angle ∠G1OE formed by the design point G1, the rotation center O', and the design point E as θ6; Define the angle ∠G1OD formed by the design point G1, the rotation center O', and the design point D as θ7; Define the angle ∠G1OC formed by the design point G1, the rotation center O', and the design point C as θ8; Where θ2 = m1 × θ1, 1.02 < m1 < 1.05; θ3=m2×θ1, 1.6<m2<1.8; θ4=m3×θ1, 1.72<m3<1.91; θ5=m4×θ1, 1.75<m4<1.94; θ6=m5×θ1, 1.79<m5<2.03; θ7=m6×θ1, 1.8<m6<2.1; θ8=m7×θ1, 1.82<m7<1.85; m1, m2, m3, m4, m5, m6 and m7 are all design parameters.

3. The forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, The inner radius of the guide ring (3) is defined as R1; The straight-line distance from the design point C and the design point D to the rotation center O' is defined as R2; The straight-line distance from the design point E and the design point F to the rotation center O' is defined as R3; The straight-line distance from the design point G to the rotation center O' is defined as R4; The straight-line distance from the design point H to the rotation center O' is defined as R5; The maximum radii of the hub annular region (41), the guide annular region (42), and the splitting annular region (43) are defined as R, respectively. 轮毂 R 导流 R 分流 ; Where R1=R 分流 ; R2=n1×R1, 0.79<n1<0.87; R3=R 导流 =n2×R1, 0.78 < n2 < 0.83; R4=n3×R1, 0.52<n3<0.55; R5=n4×R1, 0.51<n4<0.54; R 轮毂 =n5×R1,0.42<n5<0.47; n1, n2, n3, n4, and n5 are all design parameters.

4. The forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, Define the straight line connecting the design point A and the design point E as the straight line AE. Draw a parallel line IJ parallel to the straight line AE. Define the two endpoints of the parallel line IJ as the design point I and the design point J, respectively. The curve AE is controlled and set by the design point I and the design point J. Define the included angle ∠IAE formed by the design points I, A, and E as α1; Define the included angle ∠JEA formed by the design points J, E and A as α2; Define the straight-line distance between the line AE and the parallel line IJ as h1; Among them, 53°<α1<55°, 72°<α2<75°, and 6.1mm<h1<7.4mm; Define the straight line connecting the design point E and the design point H as the straight line EH. Draw a parallel line MN parallel to the straight line EH. Define the two endpoints of the parallel line MN as the design point M and the design point N, respectively. The curve EH is controlled and set by the design point M and the design point N. Define the included angle ∠MEH formed by the design points M, E, and H as α5; Define the included angle ∠NHE formed by the design points N, H and E as α6; Define the straight-line distance between the line EH and the parallel line MN as h3; Among them, 38°<α5<42°, 30°<α6<33°, and 7.6mm<h3<8.4mm.

5. A forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, Define the straight line connecting the design point B and the design point F as the straight line BF. Draw a parallel line KL parallel to the straight line BF. Define the two endpoints of the parallel line KL as the design point K and the design point L, respectively. The curve BF is controlled and set by the design point K and the design point L. Define the included angle ∠KBF formed by the design points K, B, and F as α3; Define the included angle ∠LFB formed by the design points L, F, and B as α4; Define the straight-line distance between the line BF and the parallel line KL as h2; Among them, 67°<α3<71°, 79°<α4<82°, and 6.8mm<h2<7.4mm; Define the straight line connecting the design point F and the design point G as the straight line FG. Draw a parallel line OP parallel to the straight line FG. Define the two endpoints of the parallel line OP as the design point O and the design point P, respectively. The curve FG is controlled and set by the design point O and the design point P. Define the angle ∠OFH formed by the design points O, F, and H as α7; Define the included angle ∠PGF formed by the design points P, G, and F as α8; Define the straight-line distance between the line FG and the parallel line OP as h4; Among them, 27°<α7<31°, 30°<α8<34°, and 7.5mm<h4<9.2mm.

6. A forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, The guide vane (1) has a top surface and a bottom surface, and the bottom surface is fitted with the hub (4). In the radial direction of the guide vane (1), the peripheral contour of the guide vane (1) is formed by the top edge (17), the inner edge (18), the bottom edge (19) and the outer edge (110) of the vane; Three points on the curve EH are defined as design point Q, design point R, and design point U, with design point R located between design point Q and design point U. In the radial direction of the guide vane (1), the top edge (17) of the vane is controlled by straight line AE, straight line EQ, curve QR, curve RU and straight line UH, and curves QR and RU are both formed by B-spline curves; Define the straight line connecting the design point Q and the design point R as the straight line QR. Draw a parallel line ST parallel to the straight line QR. Define the two endpoints of the parallel line ST as the design point S and the design point T, respectively. The curve QR is controlled and set by the design point S and the design point T. Define the included angle ∠SQR formed by the design points S, Q, and R as α9; Define the angle ∠TRQ formed by the design points T, R, and Q as α. 10 ; Define the straight-line distance between the line QR and the parallel line ST as h5; Define the straight line connecting the design point R and the design point U as the straight line RU. Draw a parallel line VW parallel to the straight line RU. Define the two endpoints of the parallel line VW as the design point V and the design point W, respectively. The curve RU is controlled and set by the design point R and the design point W. Define the angle ∠VRU formed by the design points V, R, and U as α. 11 ; Define the angle ∠WUR formed by the design points W, U, and R as α. 12 ; Define the straight-line distance between the straight line RU and the parallel line VW as h6; The axial distance between design point Q and design point U is defined as h7; The axial distance between design point Q and design point R is defined as h8; The radial distance between design point Q and design point H is defined as h9; Define the radial distance between design point Q and design point R as h. 10 ; Define the radial distance between design point Q and design point U as h. 11 ; Among them, 16°<α9<19°, 24°<α 10 <27°, 2.3mm<h5<5.5mm; a 11 =a 10 ,19°<α 12 <22°,1.2mm<h6<1.5mm; h8=i1×h7, 0.69<i1<0.75; h 10 =i2×h9,0.53<i2<0.62; h 11 =i3×h9,0.85<i3<0.91; i1, i2, and i3 are all design parameters.

7. A forward-curved centrifugal fan impeller with guide vanes according to claim 1, characterized in that, Along the axial direction of the guide vane (1), the midpoint of curve AB, the midpoint line between curve AE and curve BF, the midpoint of curve EF, the midpoint line between curve EH and curve FG, and the midpoint of curve GH are taken and connected in sequence to form the blade centerline (111). Take any point on the blade centerline (111) as design point P1, draw a normal line through design point P1 and intersect the blade pressure edge (14) and blade suction edge (16) at design point P3 and design point P2 respectively, and define the straight line length between design point P2 and design point P3 as the blade normal thickness at design point P1. Along the axial direction of the hub (4), the blade normal thickness δ(ρ,θ) corresponding to the design point P1 is expressed as a function of polar coordinates (ρ, θ) established with the rotation center O' as the origin, as shown below: δ(ρ,θ)=a·[x(ρ,θ)]³+b·[x(ρ,θ)]²+c·[x(ρ,θ)]+d; Wherein, the polar radius ρ is the straight-line distance from the design point P1 to the rotation center O', the polar angle θ is the circumferential angle of the line connecting the design point P1 and the rotation center O', and x(ρ,θ) is the coordinate of the design point P1 in polar coordinates (ρ, θ); a is the dominant curvature factor, and a∈[-0.0025, -0.0015]; b is the convexity control factor, and b∈[-0.16, -0.13]; c is the global gradient factor, and c∈[-3.5,-2.8]; d is the reference thickness factor associated with the reference thickness, and d∈[19.0, 23.0].

8. A dehumidifier, characterized in that, Including a forward-curved centrifugal fan impeller with guide vanes as described in any one of claims 1-7.

Images