A flow-guided self-venting aviation fuel centrifugal pump

Abstract

The utility model belongs to aviation oil delivery centrifugal pump technical field discloses a kind of flow guide type self-bleeding aviation oil delivery centrifugal pump, including shell, impeller and motor, the bottom of shell is equipped with annular oil inlet, shell vertical middle part is impeller cavity, impeller is arranged in impeller cavity, outlet pipe is arranged on the shell of same height in impeller cavity, motor is arranged in the shell above impeller cavity;Wherein, flow guide cone is equipped in shell inside corresponding import oil, flow guide cone is conical body, cone tip is aligned with the shaft of impeller.The exhaust structure of this centrifugal pump is simple, easy to operate, product is light in weight, small in size, anticavitation performance is high, electromechanical integration is high, improve the reliability and efficiency of oil delivery pump simultaneously.

Description

Technical Field

[0001] This utility model belongs to the technical field of aviation fuel centrifugal pumps, and relates to a centrifugal pump structure, specifically a guide-flow self-venting aviation fuel centrifugal pump. Background Technology

[0002] Aviation fuel centrifugal pumps are pumps that use the centrifugal force generated by the rotation of an impeller to transport fuel. When the pump inlet is close to the fuel tank floor, the fuel entering the pump body has poor operating conditions and is prone to cavitation. In addition, due to the sloshing of the fuel level in the tank, gas enters the pump body. When the gas cannot be expelled quickly, the impeller cannot make proper contact with the fuel, which greatly reduces the boost pressure and flow rate of the fuel pump, causing the pump to malfunction.

[0003] Traditional centrifugal oil pumps typically have a base plate below the inlet and a filter assembly around it. While this structure can filter impurities in the fuel and protect the impeller, it cannot guide the fuel entering the pump or improve the fuel intake conditions. An international patent, PL3311027T3, discloses an exhaust valve and a self-exhausting pump with the same valve. In this patent, the self-exhausting pump has an internal exhaust valve that automatically and quickly expels air from the pump casing, especially the volute. Although the exhaust effect of this self-exhausting pump is very ideal, the exhaust valve structure is complex and increases the weight of the self-exhausting pump product. Summary of the Invention

[0004] To address the aforementioned issues, this utility model provides a flow-guided self-exhausting centrifugal pump for aviation fuel transfer. This pump features a simple design, novel concept, low manufacturing cost, and convenient operation and management. During operation, it effectively guides the fuel entering the pump body and simultaneously removes any air remaining in the pump body.

[0005] The technical solution of this utility model is as follows: A guide-flow self-exhausting aviation fuel centrifugal pump includes a casing, an impeller, and a motor. The bottom of the casing has an circumferential oil inlet, and the middle of the casing is a vertical impeller cavity with the impeller located in the impeller cavity. The outlet pipe is located on the casing at the same height as the impeller cavity, and the motor is located in the casing above the impeller cavity. A guide cone is provided inside the casing corresponding to the oil inlet. The guide cone is a cone with its tip aligned with the shaft of the impeller.

[0006] Furthermore, the flow channel at the rear end of the oil inlet forms a structure with a gradually expanding cross-sectional area under the shaping of the guide cone, connecting to the impeller cavity.

[0007] Furthermore, the conical surface of the guide cone is a concave arc surface.

[0008] Furthermore, an exhaust port is provided on the rear end cover at the top of the housing, and the impeller cavity is connected to the outside of the housing through the gap of the lower bearing of the motor and the exhaust port.

[0009] Furthermore, a pressure sensor is provided on the side of the housing corresponding to the height of the motor, and the bottom of the pressure sensor is connected to the outlet pipe.

[0010] Furthermore, the outlet pipe is equipped with a one-way valve.

[0011] Technical effects of this utility model: The exhaust structure of this utility model is simple and easy to operate. The product is lightweight, small in size, has high cavitation resistance, and high electromechanical integration, while improving the reliability and efficiency of the oil pump. Attached Figure Description

[0012] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0013] Figure 1 This is a schematic diagram of a flow-guided self-exhausting aviation fuel centrifugal pump according to an embodiment of the present utility model; Figure 2 yes Figure 1 AA view.

[0014] Among them, 1—guide cone, 2—shell, 3—rear end cover, 4—one-way valve, 5—oil inlet, 6—impeller, 7—motor, 8—exhaust port, 9—pressure sensor, 10—outlet pipe. Detailed Implementation

[0015] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0016] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating directions or positional relationships, are given in the accompanying drawings and are used only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include more than one of those features. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0017] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integrated connections; they can refer to mechanical connections or point connections; they can refer to direct connections or indirect connections 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.

[0018] Example 1: A guide-flow self-exhausting aviation fuel centrifugal pump includes a housing 2, an impeller 6, and a motor 7. The bottom of the housing 2 is provided with an circumferential oil inlet, and the vertical middle part of the housing 2 is an impeller cavity, in which the impeller 6 is located. The outlet pipe 10 is located on the housing 2 at the same height as the impeller cavity, and the motor 7 is located in the housing 2 above the impeller cavity. A guide cone 1 is provided inside the housing 2 corresponding to the oil inlet. The guide cone 1 is a cone, and the tip of the cone is aligned with the shaft of the impeller 6.

[0019] The flow channel at the rear end of the oil inlet forms a structure with a gradually expanding cross-sectional area under the shaping of the guide cone 1, which connects to the impeller cavity.

[0020] The conical surface of the guide cone 1 is a concave arc surface.

[0021] An exhaust port 8 is provided on the rear end cover 3 at the top of the housing 2. The impeller cavity is connected to the outside of the housing 2 through the gap of the lower bearing of the motor 7 and the exhaust port 8.

[0022] A pressure sensor 9 is provided on the side of the housing 2 at the height of the motor 7, and the bottom of the pressure sensor 9 is connected to the outlet pipe 10.

[0023] The outlet pipe 10 is equipped with a one-way valve 4.

[0024] Example 2: refer to Figure 1 and Figure 2 A guide-flow self-venting centrifugal pump for aviation fuel transfer may include: a guide cone 1, a housing 2, a rear end cover 3, a one-way valve 4, an oil inlet 5, an impeller 6, a motor 7, an exhaust port 8, a pressure sensor 9, and an outlet pipe 10. The rear end cover 3 has five exhaust ports 8, each with a diameter of 1 mm.

[0025] This invention utilizes a guide cone 1 at the inlet to effectively guide the fuel entering the pump body, improving fuel intake conditions and enhancing the pump's cavitation resistance. The rear cover 3 has an exhaust port 8, allowing for the complete removal of air from the pump body at any time. Compared to previous designs, it lacks a complex self-exhaust valve, resulting in a simpler structure.

[0026] The oil centrifugal pump has an internal venting channel, which can completely remove the air stored in the pump body at any time. Compared with the past, it does not have a complicated self-venting valve, and the structure is simpler. The inlet of the oil transfer centrifugal pump is equipped with a guide cone or guide baffle, which can effectively guide the fuel entering the pump body, improve the fuel intake conditions, and enhance the cavitation resistance of the oil transfer pump. The fuel pump outlet is equipped with a one-way valve to ensure that fuel does not flow back to other fuel tanks through the centrifugal pump. The electromechanical integrated design includes a pressure sensor installed in the oil pump outlet pipeline, which can detect changes in the oil pump outlet pressure in real time.

[0027] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A guide-flow self-venting centrifugal pump for aviation fuel transfer, characterized in that, The device includes a housing (2), an impeller (6), and a motor (7). The bottom of the housing (2) is provided with an circumferential oil inlet. The middle vertical part of the housing (2) is the impeller cavity, and the impeller (6) is located in the impeller cavity. The outlet pipe (10) is located on the housing (2) at the same height as the impeller cavity. The motor (7) is located in the housing (2) above the impeller cavity. A guide cone (1) is provided in the housing (2) corresponding to the oil inlet. The guide cone (1) is a cone, and the tip of the cone is aligned with the shaft of the impeller (6).

2. The guide-flow self-exhausting aviation fuel centrifugal pump according to claim 1, characterized in that, The flow channel at the rear end of the oil inlet forms a structure with a gradually expanding cross-sectional area under the shaping of the guide cone (1), which connects to the impeller cavity.

3. A guide-flow self-exhausting aviation fuel centrifugal pump according to claim 1, characterized in that, The conical surface of the guide cone (1) is a concave arc surface.

4. A guide-flow self-exhausting aviation fuel centrifugal pump according to claim 1, characterized in that, An exhaust port (8) is provided on the rear end cover (3) at the top of the housing (2). The impeller cavity is connected to the outside of the housing (2) through the gap of the lower bearing of the motor (7) and the exhaust port (8).

5. A guide-flow self-exhausting aviation fuel centrifugal pump according to claim 1, characterized in that, A pressure sensor (9) is provided on the side of the housing (2) at the height position corresponding to the motor (7), and the bottom of the pressure sensor (9) is connected to the outlet pipe (10).

6. A guide-flow self-venting aviation fuel centrifugal pump according to claim 1, characterized in that, The outlet pipe (10) is equipped with a one-way valve (4).

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