Fuel pump impeller for inhibiting wake vortex

Abstract

The invention discloses a fuel pump impeller capable of restraining wake vortexes, and belongs to the technical field of aircraft fuel pumps, the fuel pump impeller capable of restraining the wake vortexes comprises an impeller body, the impeller body comprises a plurality of blades, the suction surface of each blade is movably provided with a fin, and the blades are arranged in the impeller body. The multiple fins are evenly arranged at intervals in the annular direction of the axis of the impeller body. The suction surface of each blade in the impeller body is movably provided with one fin, when the impeller body rotates, the multiple fins can eliminate wake vortexes generated by the blades and a volute, dynamic and static interference between a rotating component and a fixed component is reduced, the operation efficiency of the aircraft fuel pump is improved, and the service life of the aircraft fuel pump is prolonged. The problem that according to an existing impeller wake vortex restraining technology, due to the fact that holes are formed and V-shaped inwards-concave included angle structures are formed in the head portions of the blades, the strength of the blades is reduced is solved, the service life of the fuel pump impeller is prolonged, and the impeller is suitable for aircraft fuel pumps.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft fuel pumps, and in particular relates to a fuel pump impeller capable of suppressing wake vortex. Background Art

[0002] Aircraft fuel pumps are the core working components of aircraft fuel systems. After entering the impeller, fuel flows along the blades under centrifugal force. As it leaves the blade edges, the dynamic and static interference of the volute or guide vanes creates a strong flow separation, forming a noticeable wake vortex. This is particularly pronounced in pre-charged impellers, where the number of wake vortices is equal to the number of blades. As the impeller sweeps past the volute baffles, these wake vortices exacerbate the vibration and noise of the aircraft fuel pump. Therefore, it is necessary to suppress these wake vortices.

[0003] In the existing impeller wake vortex suppression technology, the wake vortex is usually suppressed by opening convection holes on the blades or opening a V-shaped concave angle structure on the blade head. For example, the existing Chinese invention patent - CN202110428441.1 - A mixed flow pump stall condition impeller wake vortex dissipation device, the mixed flow pump stall condition impeller wake vortex dissipation device achieves wake vortex suppression by setting convection holes on the blade surface; such as the existing Chinese invention patent - CN202111300325.8 - A bionic axial flow fan blade and its modification method, the bionic axial flow fan blade is modified by bionic structure of the trailing edge structure of the axial flow fan blade, and the load distribution of the bionic axial flow fan blade obtained by combining the V-shaped concave angle structure of the tail fin of fish in nature is improved, the blade tip leakage flow and wake are weakened, and the power and noise are reduced, which is particularly suitable for the field of low-pressure fans.

[0004] However, the above-mentioned method of providing convection holes on the blades and providing a V-shaped concave angle structure on the blade head will reduce the strength of the blades. The fuel pump may crack or break the blades during long-term operation, and is not suitable for the field of aircraft fuel pumps. Summary of the Invention

[0005] Based on the problems existing in the above background technology, the present invention proposes a fuel pump impeller with wake vortex suppression, which solves the problem that the existing impeller wake vortex suppression technology will reduce the blade strength and is not suitable for aircraft fuel pumps.

[0006] An embodiment of the present invention is implemented as follows: The present invention provides a fuel pump impeller for suppressing wake vortex, which includes an impeller body, the impeller body includes multiple blades, and a winglet is movably provided on the suction surface of each blade, and the multiple winglets are evenly spaced circumferentially around the axis of the impeller body.

[0007] Furthermore, one end of each of the winglets is hinged to the corresponding blade.

[0008] Furthermore, the hinge position of each of the winglets is arranged close to the outlet position of the corresponding blade.

[0009] Furthermore, the diameter of the circle formed by the plurality of wing hinge positions is D 1 is 0.75 D 2~0.95 D 2, among which, D 2 is the diameter of the impeller body.

[0010] Furthermore, the airfoils are any one of NACA0012 symmetrical airfoils, NACA0015 symmetrical airfoils and NACA0018 symmetrical airfoils.

[0011] Furthermore, a hinge hole is provided at the outlet position of the suction surface of the blade, and a hinge shaft that cooperates with the hinge hole is provided at the leading edge of each wing.

[0012] Compared with the existing impeller wake vortex suppression technology, the beneficial effects of the present invention are: 1. The present invention provides a fuel pump impeller for suppressing wake vortices. Each blade in the impeller body is provided with a movably disposed vane on the suction surface. When the impeller body rotates, the multiple vanes eliminate the wake vortices generated by the blades and the volute, reducing the dynamic and static interference between rotating and fixed components, thereby improving the operating efficiency of the aircraft fuel pump.

[0013] 2. The present invention provides a fuel pump impeller for suppressing wake vortex, which eliminates wake vortex by providing vanes. This solves the problem of reduced blade strength caused by the openings and the V-shaped concave angle structure on the blade head in existing impeller wake vortex suppression technologies, thereby extending the service life of the fuel pump impeller and being suitable for aircraft fuel pumps. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following is a brief introduction to the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without inventive work. The above and other objects, features and advantages of the present invention will become more apparent through the accompanying drawings. The same reference numerals indicate the same parts throughout the drawings. The drawings are not intentionally scaled to their actual sizes, and the focus is on illustrating the main purpose of the present invention.

[0015] Figure 1 Schematic diagram of the three-dimensional structure of a fuel pump impeller for suppressing wake vortex.

[0016] Figure 2 A schematic side view of the structure of a fuel pump impeller for suppressing wake vortex.

[0017] Figure 3 This is a schematic diagram of the structure in which the hinge hole is set on the blade.

[0018] Figure 4 This is a schematic diagram of the structure in which the hinge shaft is set on the wing.

[0019] Figure 5 This is a structural diagram of a NACA0012 symmetrical airfoil.

[0020] Figure 6 This is a structural diagram of a NACA0015 symmetrical airfoil.

[0021] Figure 7 This is a structural diagram of a NACA0018 symmetrical airfoil.

[0022] Among them, 1. impeller body; 2. blades; 3. winglets; 4. hinge hole; 5. hinge shaft. DETAILED DESCRIPTION

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0025] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0026] Please refer to Figure 1~Figure 2 As shown, the present invention provides a fuel pump impeller for suppressing wake vortex, which includes an impeller body 1, wherein the impeller body 1 includes a plurality of blades 2, and a vane 3 is movably provided on the suction surface of each blade 2, and the plurality of vanes 3 are uniformly arranged in the circumferential direction around the axis of the impeller body 1.

[0027] One end of each wing 3 is hinged to the corresponding blade 2. Figure 3 and Figure 4As shown, the outlet of the suction side of each blade 2 is provided with a hinge hole 4, and the leading edge of each winglet 3 is provided with a hinge shaft 5 that cooperates with the hinge hole 4. The hinge position of each winglet 3 is located near the outlet of the corresponding blade 2. The cooperation between the hinge shaft 5 and the hinge hole 4 realizes the hinge connection between the winglet 3 and the suction side of the blade 2.

[0028] Specifically, if Figure 2 As shown, the diameter of the circle formed by the hinged positions of the plurality of wings 3 is D 1 is 0.75 D 2~0.95 D 2, among which, D 2 is the diameter of the impeller body 1.

[0029] like Figures 5 to 7 As shown, the winglets 3 are any one of NACA0012 symmetrical airfoil, NACA0015 symmetrical airfoil and NACA0018 symmetrical airfoil. Specifically, the hinge axis 5 is set at the chord length X of the winglet 3 = 0.1.

[0030] In summary, the present invention provides a fuel pump impeller for suppressing wake vortices. Each blade 2 in the impeller body 1 is provided with a winglet 3 movably disposed on its suction surface. As the impeller body 1 rotates, the multiple winglets 3 eliminate the wake vortices generated by the blades 2 and the volute, reducing the dynamic and static interference between rotating and stationary components and improving the operating efficiency of the aircraft fuel pump. This elimination of wake vortices by providing winglets 3 addresses the problem of reduced blade strength caused by the V-shaped, inwardly concave angled structure of the openings and blade heads in existing impeller vortex suppression technologies. This extends the service life of the fuel pump impeller, making it suitable for aircraft fuel pumps.

[0031] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A fuel pump impeller for suppressing wake vortex, characterized in that: The impeller body comprises a plurality of blades, the suction surface of each blade is movably provided with a winglet, and the plurality of winglets are evenly spaced in the circumferential direction around the axis of the impeller body.

2. The fuel pump impeller for suppressing wake vortex according to claim 1, characterized in that: One end of each wing is hinged to the corresponding blade.

3. The fuel pump impeller for suppressing wake vortex according to claim 2, characterized in that: The hinge position of each winglet is arranged close to the outlet position of the corresponding blade.

4. The fuel pump impeller for suppressing wake vortex according to claim 3, characterized in that: The diameter of the circle formed by the plurality of said wing hinge positions D 1 is 0.75 D 2~0.95 D 2, among which, D 2 is the diameter of the impeller body.

5. The fuel pump impeller for suppressing wake vortex according to claim 1, characterized in that: Each of the airfoils is any one of a NACA0012 symmetrical airfoil, a NACA0015 symmetrical airfoil, and a NACA0018 symmetrical airfoil.

6. The fuel pump impeller for suppressing wake vortex according to claim 5, characterized in that: The outlet position of the suction surface of each blade is provided with a hinge hole, and the leading edge of each wing is provided with a hinge shaft matched with the hinge hole.

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