A vortex air duct structure direct current fan

Abstract

The utility model discloses a vortex type air duct structure direct current fan, including fan casing, air inlet pipe, axial air inlet, exhaust end pipe, motor, turbine disc, axial flow oar, shaft and mixed flow needle. Fan casing inside is provided with semicircle radial air duct cavity, and turbine disc and axial flow oar rotate arrangement among them, and motor rotates turbine disc through coaxial connection drive. Air inlet pipe and axial air inlet constitute axial suction passage, and exhaust end pipe and air duct cavity intercommunication form directional discharge path. Turbine disc sets up guide vane along radial, and produces steady vortex type radial airflow with air duct shape surface. Through the synergistic effect of gradual change air duct structure and composite impeller system, make whole machine realize high efficiency suction, pressurization, mixed flow and stable exhaust, have compact structure, mixed flow efficiency is high, the advantage that output flow field is stable, be applicable to high performance air circulation and combustion premixing equipment.

Description

Technical Field

[0001] This utility model relates to the field of gas transportation and aerodynamic equipment technology, specifically a DC fan with a vortex duct structure. Background Technology

[0002] As a crucial component in combustion systems, gas delivery systems, and air circulation equipment, the internal flow channel structure and impeller organization of fans directly affect the airflow intake efficiency, flow field stability, and exhaust capacity. In existing technologies, DC fans generally employ an axial intake and radial exhaust arrangement, typically featuring a single axial impeller or centrifugal turbine disk, utilizing axial or radial airflow to complete the air delivery process. While this structure can meet general airflow output requirements, its relatively simple flow field organization limits the airflow energy conversion efficiency, making it less than ideal for confined spaces or high-efficiency output scenarios.

[0003] In typical DC axial flow fans, axial blades primarily rely on axial intake and exhaust to transport gas. However, their ability to control local flow field disturbances is limited, making it difficult to effectively improve output energy density. On the other hand, while existing turbine fans can form partial vortex structures through radial flow channels, the airflow duct between the turbine disk and the casing is mostly a fixed curvature structure. This leads to energy loss and unstable flow direction during radial flow. For applications with limited space or requiring high mixing and high stability flow fields, traditional structures often struggle to simultaneously achieve both high axial flow output and high radial compression characteristics.

[0004] Furthermore, in existing mixed-flow fan technologies, some solutions attempt to improve the mixing effect by incorporating disturbance components around the impeller. However, these disturbance structures are mostly of a single form and their fit with the axial mainstream is not tight enough, resulting in insufficient flow field superposition and limited mixing efficiency. Simultaneously, the flow channel shapes of existing fans often employ fixed radii or straight-line transition structures, making it easy for the airflow entering the turbine region to generate wall-attached and separated flows, affecting overall airflow stability and limiting the sustainability of the pressurization effect.

[0005] In summary, existing fans generally suffer from the following shortcomings: First, it is difficult to form a composite flow field with both high flow rate and high mixing degree by combining axial flow and radial vortex flow; second, the guiding effect of traditional duct surfaces on airflow is limited, failing to effectively improve pressurization and exhaust efficiency; third, the configuration of circumferential disturbance structures is insufficient, resulting in inadequate mixing and poor output flow field stability; and fourth, it is difficult to simultaneously achieve high-efficiency airflow guidance, sufficient mixing, and low-noise output within a compact fan structure. Therefore, there is an urgent need for a fan structure that can combine axial intake, radial pressurization, multi-point disturbance mixing, and stable exhaust capabilities within a compact design, in order to improve the shortcomings of existing equipment in terms of mixing efficiency, energy conversion efficiency, and output flow field stability. Utility Model Content

[0006] This invention aims to solve the technical problems of existing DC fans, such as insufficient mixing efficiency, low flow field stability, and limited exhaust effect, and provides a DC fan with a vortex-type duct structure that is compact, enhances mixing, and stabilizes exhaust. This fan achieves a synergistic effect of axial intake, radial pressurization, and multi-point disturbance mixing by constructing a gradually changing semi-circular radial duct inside the fan casing, combined with a composite airflow organization structure consisting of a turbine disk, axial propeller, and mixing needles. This significantly improves the fan's exhaust efficiency and flow field uniformity.

[0007] The overall design of this invention is as follows: a semi-circular radial air duct cavity is set inside the fan casing, and a composite flow field is formed by the turbine disk and axial propeller driven by a motor; at the same time, mixing needles are arranged on the outer periphery of the shaft to generate disturbance in the axial mainstream, thereby achieving enhanced mixing and stable discharge of airflow. Through the synergistic effect of multiple structures, the fan can achieve a continuous, stable, and high-energy-density exhaust effect within a limited volume.

[0008] In a preferred embodiment, the technical solution of this utility model includes the following:

[0009] This utility model employs a vortex-type duct structure DC fan, comprising a fan housing with a semi-circular radial duct cavity on its inner side for forming a vortex-type duct. A turbine disk and an axial propeller are rotatably mounted within the duct cavity. The front end of the fan housing has an air inlet and an axial air inlet communicating with the duct cavity, while the side has an exhaust pipe communicating with the duct cavity. A motor is mounted at the rear end, with its output shaft coaxially connected to the turbine disk. A shaft is fixed at the center of the turbine disk, with one end of the shaft fixedly connected to the surface of the axial propeller. Several mixing needles are arranged around the outer periphery of the shaft. The specific technical effect is that the fan can simultaneously form an axial mainstream and a radial vortex flow, thereby obtaining a composite airflow system with enhanced mixing.

[0010] In a preferred example, the turbine disk is provided with multiple evenly distributed guide vanes along the radial direction, and each guide vane is matched with the semi-circular diameter air duct surface of the inner wall of the fan casing. The specific technical effect is to enable the radial airflow to obtain more stable guidance and compression within the air duct, thereby improving the pressurization capacity and flow continuity of the vortex airflow.

[0011] In a preferred example, the axial propeller employs a convex curved blade structure and is integrally connected to the turbine disk. The specific technical effect is to achieve higher intake efficiency of the axial intake airflow during rotation and to ensure that the axial airflow and radial vortex flow form synchronous mixing within the air duct cavity.

[0012] In a preferred example, the mixing needles are arranged in an array along the circumferential direction of the shaft, and each mixing needle is inclined along the axial direction towards the exhaust pipe. The specific technical effect is that the mixing needles create multi-point disturbances in the axial high-speed airflow, which allows the radial and axial airflows to be fully superimposed, thereby improving the overall mixing efficiency and output stability of the fan.

[0013] In a preferred example, a conical transition structure is used to connect the air inlet and the axial air inlet. The specific technical effect is to ensure that the airflow achieves a stable diameter reduction and flow direction transition before entering the air duct cavity, thereby improving the intake efficiency of the axial propeller.

[0014] In a preferred example, the exhaust pipe and the fan housing are integrally formed and extend along the curved surface of the housing. The specific technical effect is to reduce airflow separation at the exhaust end, making the exhaust direction more stable and improving the overall operational smoothness of the fan.

[0015] In a preferred example, the motor employs an external mounting structure, secured to the rear end face of the fan housing via multiple fastening connection points. The specific technical benefits include improved motor installation reliability and maintainability, reduced internal duct space occupancy, and enhanced duct flow.

[0016] In a preferred example, the turbine disk and axial propeller assembly are integrally mounted at the center of a semi-circular radial air duct inside the wind turbine casing. The specific technical effect is to ensure the symmetry and stability of the composite flow field, enabling the wind turbine to maintain efficient airflow balance during operation.

[0017] The beneficial effects achieved by this utility model are as follows:

[0018] 1. In this invention, a gradually varying semi-circular diameter vortex-type air duct structure is constructed inside the fan casing, and a turbine disk and axial flow propeller are rotatably installed within it. This causes the airflow to sequentially form a composite flow field of axial mainstream and radial vortex flow after entering the air duct cavity. The guide vanes of the turbine disk arranged radially cooperate with the semi-circular diameter air duct surface, enabling the airflow to obtain stable pressurization and guidance during rotation. This allows the fan to achieve higher flow density and exhaust efficiency within a limited volume, significantly improving the uniformity and continuity of gas delivery.

[0019] 2. In this invention, the axial flow propeller adopts an outwardly convex curved blade structure, combined with a central shaft and circumferentially arranged mixing needles. This creates a multi-point disturbance zone within the axial high-speed airflow, allowing the axial flow and vortex flow to fully superimpose, thus improving the overall mixing efficiency of the gas in the duct. The array-like distribution of the mixing needles further enhances the airflow disturbance effect, making the output flow field at the exhaust end more stable, reducing vortex losses during fan operation, and improving noise control. Attached Figure Description

[0020] Figure 1This is a schematic diagram of the overall structure of one embodiment of the present utility model;

[0021] Figure 2 This is an exploded structural diagram of one embodiment of the present invention;

[0022] Figure 3 This is a schematic diagram of the turbine disk and axial flow propeller structure according to one embodiment of the present invention;

[0023] Figure 4 This is a schematic diagram of the axial flow propeller and shaft structure according to an embodiment of the present invention.

[0024] Figure label:

[0025] 100. Fan casing; 110. Motor; 101. Air inlet; 102. Axial air inlet; 103. Exhaust pipe;

[0026] 200, turbine disk; 300, axial propeller; 310, shaft; 311, mixing needle. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features of the present utility model can be combined with each other.

[0028] It should be understood that these descriptions are merely exemplary and not intended to limit the scope of this invention.

[0029] The following describes, with reference to the accompanying drawings, some embodiments of the present invention, providing a vortex-type duct structure DC fan.

[0030] Combination Figures 1-4 As shown, this utility model provides a vortex-type duct structure DC fan, including a fan housing 100, an air inlet 101, an axial air inlet 102, an exhaust pipe 103, a motor 110, a turbine disk 200, an axial propeller 300, a shaft 310, and a mixing needle 311. The interior of the fan housing 100 is configured with a semi-circular radial duct cavity for guiding airflow to form a vortex flow field. The turbine disk 200 and the axial propeller 300 are both rotatably mounted in the semi-circular radial duct cavity of the fan housing 100 and rotate synchronously under the drive of the motor 110.

[0031] In this embodiment, the air inlet 101 is located at the front end of the fan housing 100, forming the external air intake interface of the fan. The rear side of the air inlet 101 is connected to the axial air inlet 102 inside the fan housing 100. The axial air inlet 102 directly corresponds to the location of the turbine disk 200 and the axial propeller 300, allowing the gas entering the fan to enter the semi-circular radial air duct cavity in the axial direction. The exhaust pipe 103 is fixedly connected to the side of the fan housing 100. The exhaust pipe 103 communicates with the semi-circular radial air duct cavity and is used to discharge the gas processed by the turbine disk 200 and the axial propeller 300 from the fan.

[0032] In this embodiment, the motor 110 is fixedly installed at the rear end of the fan housing 100. The output shaft of the motor 110 passes through the inside of the fan housing 100 and is coaxially connected to the turbine disk 200, enabling the turbine disk 200 to rotate at high speed under the drive of the motor 110. A shaft 310 is fixedly provided at the center of the turbine disk 200, and one end of the shaft 310 is fixedly connected to the surface of the axial flow propeller 300, so that the axial flow propeller 300 can rotate synchronously with the turbine disk 200 under the drive of the shaft 310. Several mixing needles 311 are arranged in a circumferential array around the outer periphery of the shaft 310. The mixing needles 311 are used to form a disturbance region in the air duct cavity, causing the axial high-speed airflow and vortex airflow to mix and superimpose inside the fan.

[0033] In this embodiment, to enhance the airflow guiding capability of the turbine disk 200, multiple evenly distributed guide vanes are arranged radially on the turbine disk 200. Each guide vane is matched with the semi-circular diameter air duct surface of the inner wall of the fan housing 100, so that a stable and continuous vortex radial airflow can be generated within the semi-circular radial air duct when the turbine disk 200 rotates. Through the air duct geometric matching between the turbine disk 200 and the fan housing 100, the airflow can be accelerated, compressed, and guided along the inner wall of the housing, ultimately achieving a high exhaust efficiency.

[0034] In this embodiment, the axial flow propeller 300 adopts a convex curved blade structure. The convex curved surface can form an axial mainstream with suction capacity when rotating, allowing the airflow to enter the air duct cavity at high speed in the axial direction. The axial flow propeller 300 and the turbine disk 200 adopt an integrated connection structure, which ensures that the two maintain precise synchronization when rotating, and at the same time ensures that the radial vortex airflow generated by the turbine disk 200 and the axial airflow generated by the axial flow propeller 300 form a stable composite flow field inside the fan casing 100.

[0035] In this embodiment, the mixing needles 311 are arranged in an array along the outer periphery of the shaft 310, with each mixing needle 311 inclined towards the exhaust pipe 103 in the axial direction. This inclined arrangement allows the mixing needles 311 to create disturbance points in the axial airflow channel when the axial propeller 300 rotates, resulting in more thorough mixing and superposition between the radial vortex and the axial mainstream, thereby improving the uniformity and stability of the airflow inside the fan.

[0036] In this embodiment, the air inlet 101 and the axial air inlet 102 are connected by a conical transition structure. This structure allows the external air to gradually contract from the larger cross section at the inlet to the smaller channel of the axial air inlet 102, so that the gas entering the air duct cavity can be stably accelerated during the transition process and fit into the suction direction of the axial flow propeller 300, thereby improving the overall air intake efficiency of the fan.

[0037] In this embodiment, the exhaust pipe 103 and the fan housing 100 adopt an integral molding structure. The exhaust pipe 103 extends along the curved surface of the fan housing 100, allowing the exhaust direction to transition naturally along the curved surface structure, reducing airflow separation at the outlet and making the exhaust more stable. At the same time, the integral molding structure improves the housing strength, enabling the device to maintain high structural stability under the impact of airflow during high-speed rotation.

[0038] In this embodiment, the motor 110 adopts an external mounting structure. Its mounting end face is fixed to the rear end face of the fan housing 100 through multiple fastening connection points, so that the motor 110 can be reliably installed outside the housing, which is convenient for maintenance. At the same time, it reduces the structural complexity inside the fan housing 100 and makes the internal air duct area more unobstructed.

[0039] In this embodiment, the turbine disk 200 and the axial flow propeller 300 assembly are integrally installed in the central area of ​​the semi-circular radial air duct of the fan housing 100. The rotation center axis of the turbine disk 200 and the axial flow propeller 300 is consistent with the geometric center of the fan housing 100, so that the airflow forms a stable composite flow pattern in the central area and is discharged towards the exhaust pipe 103 under the guidance of the air duct cavity structure.

[0040] Working principle and usage process of this utility model:

[0041] When the motor 110 starts, its output shaft drives the turbine disk 200 to rotate at high speed within the semi-circular radial air duct cavity of the fan housing 100. During rotation, the guide vanes of the turbine disk 200, arranged radially, guide the airflow along the semi-circular radial air duct surface of the inner wall of the fan housing 100, creating a stable vortex flow path along the inner surface of the housing. Because the air duct cavity adopts a gradually contracting semi-circular diameter structure, the radial flow generated by the rotation of the turbine disk 200 is further compressed, guided, and forms a pressurized vortex flow field along the interior of the housing.

[0042] Simultaneously, the shaft 310 located at the center of the turbine disk 200 drives the axial propeller 300 to rotate synchronously. The convex curved blade structure of the axial propeller 300 draws in and accelerates the airflow entering the axial inlet 102 along the axial direction, guiding the formation of a stable axial main airflow. Several mixing needles 311 arranged on the outer periphery of the shaft 310, as the axial propeller 300 rotates, further create a disturbance enhancement effect between the axial flow and the radial vortex flow, causing the main airflow and the peripheral vortex flow to form a continuous mixing and superposition within the duct cavity, improving the overall energy exchange efficiency of the gas within the duct.

[0043] The aforementioned axial high-speed airflow and semi-circular radial vortex airflow are superimposed, compressed, and guided inside the fan casing 100 before converging towards the exhaust pipe 103, forming a stable directional high-velocity discharge effect at the exhaust pipe 103.

[0044] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0045] Although embodiments of the present invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A DC fan with a vortex-type duct structure, characterized in that, include: A fan housing (100) has a semi-circular radial air duct cavity on its inner side for forming a vortex-type air duct, and a turbine disk (200) and an axial flow propeller (300) are rotatably mounted on the inner side; the front end of the fan housing (100) is provided with an air inlet (101), and an axial air inlet (102) communicating with the air duct cavity is formed at the air inlet (101); an exhaust end pipe (103) is fixedly connected to the side of the fan housing (100), and the exhaust end pipe ( 103) is connected to the semi-circular radial air duct cavity; a motor (110) is fixedly installed at the rear end of the fan housing (100); the output shaft of the motor (110) is coaxially connected to the turbine disk (200); a shaft (310) is fixed at the center of the turbine disk (200), one end of the shaft (310) is fixedly connected to the surface of the axial flow propeller (300), and a plurality of mixing needles (311) are arranged on the outer periphery of the shaft (310).

2. The DC fan with a vortex duct structure according to claim 1, characterized in that, The turbine disk (200) is provided with a plurality of uniformly distributed guide blades along the radial direction, which are matched with the semi-circular diameter air duct surface of the inner wall of the fan housing (100).

3. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The axial flow propeller (300) has an outwardly convex curved blade structure, and the axial flow propeller (300) and the turbine disk (200) adopt an integrated connection structure.

4. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The shaft (310) has multiple mixing needles (311) arranged in an array along the circumference, and each mixing needle (311) is inclined towards the exhaust pipe (103) along the axial direction.

5. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The air inlet (101) and the axial air inlet (102) are connected by a conical transition surface to form a gradually changing flow channel with adjustable premixed airflow direction.

6. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The exhaust pipe (103) and the fan housing (100) are integrally formed and extend along the curved surface of the housing.

7. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The motor (110) adopts an external mounting structure, and its mounting end face is fixed to the rear end face of the fan housing (100) through multiple fastening connection points.

8. A DC fan with a vortex-type duct structure according to claim 1, characterized in that, The turbine disk (200) and the axial propeller (300) assembly are integrally installed at the center of the semi-circular radial air duct inside the wind turbine casing (100).

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