An aeronautical cooling fan

Abstract

The utility model belongs to airship, aviation cooling fan technical field relates to an aviation cooling fan. Including volute, impeller, the outlet of volute is tangential outlet, the air inlet of volute and the import of impeller adopt the form of cover joint, and the impeller includes long blade, short blade, wheel cover, wheel disc, vice blade, long blade, short blade set up between wheel cover and wheel disc, and long blade, short blade are alternately arranged, and the outer surface of wheel disc is equipped with vice blade. The utility model makes the pressure rise of cooling fan and the efficiency get the remarkable improvement, can satisfy the heat dissipation demand of certain manned airship. Solve the problem of the possibility reduction of fan power increase in the prior art, and can guarantee the safety risk brought by high speed.

Description

Technical Field

[0001] This utility model belongs to the technical field of airships and aviation cooling fans, and relates to an aviation cooling fan. Background Technology

[0002] Optimized structure for airship and aircraft cooling fans. Currently, domestically produced cooling fans of this type have shortcomings, specifically including: Figure 4 The internal leakage (serial number 13), external leakage (serial number 14), sudden increase in impeller outlet cross section causing sudden release loss (serial number 15), and large diffusion factor between two adjacent blades causing negative layer separation and vortex zone (serial number 16) all indicate performance degradation, which limits the performance of the product when used in the aerospace field. Further improving pressure rise and efficiency is imperative.

[0003] Meanwhile, measures to increase pressure rise and efficiency by increasing the rotation speed not only increase the power consumption of the cooling fan, but also reduce the reliability of the fan and increase the risk. Utility Model Content

[0004] Utility Model Purpose This paper proposes a structure to improve the performance of a cooling fan and meet the heat dissipation requirements of the aerospace industry. It addresses the issue of reduced performance due to increased fan power in existing technologies, while also mitigating the safety risks associated with high-speed operation.

[0005] Technical solution An aviation cooling fan includes a volute 1 and an impeller 2; the outlet of the volute 1 is a tangential outlet 12; the air inlet 3 of the volute 1 and the inlet of the impeller 2 are connected in a sleeve manner; the impeller 2 includes long blades 5, short blades 6, a wheel cover 7, a wheel disk 8, and auxiliary blades 9; the long blades 5 and short blades 6 are disposed between the wheel cover 7 and the wheel disk 8, and the long blades 5 and short blades 6 are arranged alternately; the outer surface of the wheel disk 8 is provided with auxiliary blades 9.

[0006] Furthermore, the short blade 6 is disposed on the impeller 2 and located at the outlet 2 / 3.

[0007] Furthermore, the auxiliary blade 9 is disposed on the wheel disk 8 and located on the side close to the motor.

[0008] Furthermore, the auxiliary blades 9 are circumferentially distributed and evenly arranged on the outer surface of the wheel disk 8.

[0009] Furthermore, the auxiliary blade 9 and the wheel disk 8 are integrally formed structures.

[0010] Furthermore, it also includes a bladeless diffuser 10, which is disposed around the impeller 2 and is used for deceleration and pressurization.

[0011] The beneficial effects of this application are as follows: The aforementioned utility model significantly improves the pressure rise and efficiency of the cooling fan, meeting the heat dissipation requirements of a manned airship. It solves the problem of increased fan power and reduced potential hazards in existing technologies, while also ensuring safety during high-speed operation. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the present invention (front, rear, and cross-sectional views). Figure 2 Here is a diagram of the impeller structure; Figure 3a This is a schematic diagram of an existing elbow. Figure 3b This is a schematic diagram of the tangential outlet of this novel invention; Figure 4 This is a schematic diagram of the existing technology structure. Detailed Implementation

[0013] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions in the embodiments of this utility model will be described in more detail below with reference to the embodiments of this utility model. In the examples, the same or similar reference numerals denote the same or similar components or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this utility model. The embodiments described below with reference to the embodiments are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model. The embodiments of this utility model will be described in detail below with reference to their specific implementation.

[0014] The specific structure of this type of aviation cooling fan is as follows: Figure 1 As shown, it specifically includes components such as a volute 1, an impeller 2, and an air inlet 3, with number 4 in the figure indicating the air inlet being connected to the impeller inlet via a sleeve connection. The impeller consists of long blades 5, short blades 6, a wheel cover 7, a wheel disc 8, auxiliary blades 9 located near the motor, and a bladeless diffuser 10, as detailed below. Figure 2 As shown.

[0015] In one embodiment of this utility model, the most important innovation compared to the prior art is that the two outlets of the volute are changed from the 90° bend 11 to the tangential outlet 12 (see Figure 3).

[0016] In one embodiment of this utility model, in order to reduce the diffusion factor of the impeller, a short blade 6 is added between two adjacent long blades at a distance of 2 / 3 from the outlet. This reduces the pressure loss caused by an excessively large diffusion factor in the blade flow channel (see...). Figure 2 ).

[0017] In one embodiment of this utility model, a bladeless diffuser 10 is provided at the blade outlet to further reduce the pressure loss when the airflow leaves the impeller.

[0018] In one embodiment of this utility model, an auxiliary blade 9 is added to the side of the wheel near the motor to prevent airflow from leaking outward along the axial direction.

[0019] In one embodiment of this utility model, the air inlet of the imported cooling fan and the impeller inlet are designed to be connected in a sleeve-type configuration instead of a butt joint, which reduces the internal leakage loss of the cooling fan.

[0020] The solution for this cooling fan is to redesign the volute outlet structure from a right-angle bend to a large-arc tangential outlet. Figure 3b (Section 12) reduces vortex losses of airflow inside the volute; short blades are added between adjacent long blades ( Figure 2 (Section 6) reduces losses caused by excessive diffusion factor in the flow channel; a rotating bladeless diffuser is added at the blade outlet ( Figure 2 (Section 10) improves static pressure rise and efficiency; secondary blades are added to the back of the impeller disc ( Figure 2 (Section 9) to prevent airflow leakage; the air inlet and impeller inlet are designed from a butt joint to a socket joint. Figure 1 (Section 4) reduces internal airflow leakage losses. These measures significantly improve fan performance and efficiency, meeting the cooling requirements of a certain airship.

[0021] The performance before and after the improvement is shown in Table 1 and Table 2, respectively.

[0022] Table 1 Performance before improvement

[0023] Table 2 Performance Table After Improvement .

[0024] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0025] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0026] The above description is merely a specific embodiment of this utility model and is not intended to limit this utility model. Within the spirit and principles of this utility model, any person skilled in the art may use the above-disclosed technical content to make changes or modifications to equivalent embodiments for application in other fields. However, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of this utility model without departing from the technical solution of this utility model, as well as any modifications, equivalent substitutions, improvements, etc., should be included within the protection scope of this utility model.

Claims

1. An aviation cooling fan, characterized in that, It includes a volute and an impeller; the outlet of the volute is a tangential outlet; the air inlet of the volute and the inlet of the impeller are connected in a sleeve form; the impeller includes long blades, short blades, a wheel cover, a wheel disk, and auxiliary blades; the long blades and short blades are arranged between the wheel cover and the wheel disk, and the long blades and short blades are arranged alternately; the outer surface of the wheel disk is provided with auxiliary blades.

2. The fan as described in claim 1, characterized in that, The short blades are disposed on the impeller and located at the outlet.

3. The fan as described in claim 1, characterized in that, The auxiliary blades are mounted on the wheel disk and located near the motor.

4. The fan as described in claim 1, characterized in that, The auxiliary blades are circumferentially distributed and evenly arranged on the outer surface of the wheel disk.

5. The fan as described in claim 1, characterized in that, The auxiliary blades and the wheel disk are integrally formed.

6. The fan as described in claim 1, characterized in that, It also includes a bladeless diffuser, which is located around the impeller and is used for deceleration and pressurization.

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