Integrated wide-rotating-speed aviation fuel electric gear pump

Abstract

A permanent magnet synchronous motor, an internal gear pump and a hollow shaft oil recharging pump are integrally designed, and through shell packaging, shaftless outward extension, immersion of a motor assembly in fuel oil, replacement of a fan for cooling and heat dissipation, arrangement of a main oil suction port and an auxiliary oil suction port, and the pressurization effect of the hollow shaft oil recharging pump, the integrated wide-rotation-speed aviation fuel oil electric gear pump is formed. The problem of insufficient oil absorption under the high-rotating-speed working condition is solved. The device specifically comprises a gear pump head assembly 1, a permanent magnet synchronous motor assembly 2, a shell assembly 3, a hollow shaft oil supplementing pump 4, a first ball bearing 5 and a second ball bearing 6, and the gear pump head assembly 1 is mounted in a gear pump head mounting seat 3-2 and is positioned by a second positioning pin 1-11; the hollow shaft oil recharging pump 4 is formed by integrally fusing a motor main shaft and an oil recharging pump, and the central axis of the gear shaft 1-3 coincides with the central axis of the hollow shaft oil recharging pump 4; in the gear pump head assembly 1, a gear shaft 1-3 is supported between an oil suction side plate 1-1 and an oil discharge side plate 1-8 through a first sliding bearing 1-2 and a second sliding bearing 1-7, and the first sliding bearing 1-2 and the second sliding bearing 1-7 are installed on the oil suction side plate 1-1 and the oil discharge side plate 1-8 respectively. And the oil absorption side plate 1-1, the oil discharge side plate 1-8 and the static pressure support ring 1-6 are positioned by the first positioning pin 1-5 and are fixed by the screw 1-10.

Description

Technical Field

[0001] The present invention relates to the integrated technology of the power unit in the aviation engine fuel supply system, and particularly to an integrated wide-speed aviation fuel electric gear pump. Background Art

[0002] As the core actuating component of the aircraft fuel system, the electric aviation fuel pump undertakes the key task of continuously and stably transporting fuel under different flight conditions. With the development of the more-electric aircraft technology and the increasing requirements of new aviation engines for the wide-range regulation ability of the fuel system, the traditional electric fuel pump faces severe challenges in terms of structural design, operating condition adaptability, and system reliability. The traditional electric aviation fuel pump mainly adopts a split electromechanical coupling structure, in which the drive motor and the gear pump are connected by a mechanical coupling, and a split housing design is adopted, resulting in problems such as large volume, high noise, and potential external leakage. Aiming at the inherent problems of the traditional electric aviation fuel pump, Patent CN119641490A and CN115898861A respectively disclose an integrated electric aviation fuel and lubricating oil pump device and a fault-tolerant design method for an integrated aviation fuel pump, which integrate the fuel pump / lubricating oil pump / external meshing gear pump with the motor, etc., simplify the overall structure, save the occupied space and cost, and at the same time reduce the fault points of the system and ensure the reliability of the electric fuel pump. Patent CN109958563B discloses a new type of gear-type electric fuel pump, which improves the pump efficiency through the driving gear and two driven gears linked by the rotor shaft.

[0003] Summarize the above technical deficiencies: 1. Defects of the traditional split structure: The motor and the pump body are mechanically connected in a split manner, resulting in too large axial dimensions, increased risk of external leakage due to dynamic sealing points, and difficulty in realizing modular maintenance; 2. Insufficient speed adaptation ability: Restricted by insufficient oil suction, the effective speed range of the traditional fixed-speed motor plus mechanical speed regulation scheme only covers 500 - 6000 rpm, which cannot meet the wide-range speed regulation requirements of 200 - 12000 rpm required by the new generation of aviation engines. Under extreme conditions, the fuel supply fluctuation can reach ±15%, making it difficult to meet the precise fuel supply requirements under wide speed ratio conditions; 3. Low thermal management efficiency: Insulation aging is likely to occur in a high-temperature fuel environment (>150°C); 4. Power density bottleneck: The power density requirement for aviation application scenarios reaches more than 2.5 kW / kg, and the traditional design is difficult to meet the lightweight requirements. Summary of the Invention

[0004] The object of the present invention is to provide an integrated wide-speed aviation fuel electric gear pump.

[0005] The present invention is an integrated wide-speed aviation fuel electric gear pump, which includes a gear pump head assembly 1, a permanent magnet synchronous motor assembly 2, a housing assembly 3, a hollow shaft oil replenishing pump 4, a first ball bearing 5 and a second ball bearing 6. Among them, the gear pump head assembly 1 includes an oil suction side plate 1-1, a first sliding bearing 1-2, a gear shaft 1-3, an internal gear ring 1-4, a first positioning pin 1-5, a static pressure support ring 1-6, a second sliding bearing 1-7, an oil discharge side plate 1-8, a high-pressure rectangular sealing ring 1-9, a screw 1-10 and a second positioning pin 1-11; the permanent magnet synchronous assembly 2 includes a junction box cover 2-1, a wiring board 2-2, a junction box body 2-3, an O-ring 2-4, a terminal 2-5, a connecting piece 2-6, a nut 2-7, a cable 2-8, a winding 2-9, a first cover plate 2-10, a permanent magnet rotor 2-11, a second cover plate 2-10 and a flat key 2-13; the housing assembly 3 includes a front end cover 3-1, a gear pump head mounting seat 3-2, a main oil suction port 3-2-a, a first support end cover 3-3, a support 3-4, a housing 3-5, a second support end cover 3-6 and a rear end cover 3-7. The gear pump head assembly 1 and the permanent magnet synchronous motor assembly 2 are encapsulated in the housing assembly 3. The permanent magnet rotor 2-11 and the hollow shaft oil replenishing pump 4 are connected into one body by a flat key 2-13 and are supported and positioned by the first ball bearing 5 and the second ball bearing 6. The first ball bearing 5 and the second ball bearing 6 are respectively installed inside the first support end cover 3-3 and the second support end cover 3-6. The first support end cover 3-3 and the second support end cover 3-6 are respectively fixed to both ends inside the housing 3-5 by screws. The hollow shaft oil replenishing pump 4 is provided with an internal spline 4-c, which is connected to the internal spline 1-3-a on the gear shaft 1-3 of the gear pump head assembly 1. The gear pump head assembly 1 is installed inside the gear pump head mounting seat 3-2 and is positioned by the second positioning pin 1-11; the hollow shaft oil replenishing pump 4 is integrally formed by a motor main shaft and an oil replenishing pump, and the central axes of the gear shaft 1-3 and the hollow shaft oil replenishing pump 4 coincide; in the gear pump head assembly 1, the gear shaft 1-3 is supported between the oil suction side plate 1-1 and the oil discharge side plate 1-8 by the first sliding bearing 1-2 and the second sliding bearing 1-7. The first sliding bearing 1-2 and the second sliding bearing 1-7 are respectively installed on the oil suction side plate 1-1 and the oil discharge side plate 1-8. The oil suction side plate 1-1, the oil discharge side plate 1-8 and the static pressure support ring 1-6 are positioned by the first positioning pin 1-5 and are fixed by screws 1-10.

[0006] The beneficial effects of the present invention are as follows: The integrated wide-speed aviation fuel electric gear pump has the following advantages: 1. High efficiency. The main oil suction circuit and the auxiliary oil suction circuit are set to supply oil to the gear pump head in a dual - way manner. Under the conditions of high - speed and ultra - high - speed operation, the pressurized liquid supply capacity of the hollow - shaft oil replenishing pump in the auxiliary oil suction circuit is enhanced, further strengthening the oil suction capacity; frequency conversion speed regulation, the gear pump adapts to the high - efficiency working area of the motor, with high energy conversion efficiency, supplying on demand and small capacity loss; sufficient oil suction, good lubrication of the friction pair, no dynamic seal, and small viscous friction and mechanical friction power losses.

[0007] 2. High heat - dissipation efficiency. The high - heat - generation area of the motor is usually in the winding part. In the present invention, the motor winding and the permanent - magnet rotor are completely immersed in the liquid, and under the enhanced flow of the hollow - shaft oil replenishing pump, the heat - dissipation efficiency of the present invention is high.

[0008] 3. Low noise. There is no cooling fan; sufficient oil suction at high speed, and small cavitation noise.

[0009] 4. Small size and light weight. The permanent - magnet synchronous motor, internal - meshing gear pump, hollow - shaft oil replenishing pump, etc. are integrated in an integrated design, greatly shortening the axial dimension and reducing the weight.

[0010] 5. Wide applicable range of medium viscosity. In addition to low - viscosity fuel, high - viscosity hydraulic oil is also applicable.

[0011] 6. Convenient installation, disassembly and maintenance. The gear pump is designed as a pump - head assembly and adopts spline - inserted connection, which is convenient for installation and disassembly. The friction pair belongs to the vulnerable parts, and the maintenance or replacement is convenient.

[0012] 7. No external leakage. The shaft has no external extension, completely avoiding external leakage. Brief Description of the Drawings

[0013] Figure 1 is the structural schematic diagram of the present invention, Figure 2 is the three - dimensional assembly drawing of the gear pump - head assembly, Figure 3 is the three - dimensional exploded view of the gear pump - head assembly, Figure 4 is the wiring box assembly and wiring schematic diagram, Figure 5 Exploded view of the motor assembly, Figure 6Explosion diagram of the housing assembly; the reference numerals and corresponding names are: gear pump head assembly 1, oil suction side plate 1-1, crescent plate 1-1-a, first oil inlet 1-1-b, first sliding bearing 1-2, gear shaft 1-3, external spline 1-3-a, central hole 1-3-b, oil replenishing hole 1-3-c, internal gear ring 1-4, first positioning pin 1-5, hydrostatic support ring 1-6, hydrostatic support groove 1-6-a, first oil passage groove 1-6-b, second sliding bearing 1-7, oil discharge side plate 1-8, second oil inlet 1-8-a, oil discharge port 1-8-b, high-pressure rectangular sealing ring 1-9, screw 1-10, second positioning pin 1-11, permanent magnet synchronous motor assembly 2, junction box cover 2-1, wiring board 2-2, junction box body 2-3, O-ring 2-4, terminal post 2-5, connecting piece 2-6, nut 2-7, cable 2-8, winding 2-9, first cover plate 2-10, permanent magnet rotor 2-11, second cover plate 2-10 and flat key 2-13, housing assembly 3, front end cover 3-1, outlet 3-1-a, gear pump head mounting seat 3-2, main oil suction port 3-2-a, oil groove 3-2-b, first support end cover 3-3, second oil passage groove 3-3-a, first set screw hole 3-3-b, support 3-4, housing 3-5, auxiliary oil suction port 3-5-a, lifting lug seat 3-5-b, winding support rib 3-5-c, third oil passage groove 3-5-d, second support end cover 3-6, fourth oil passage groove 3-6-a, second set screw hole 3-6-b, rear end cover 3-7, hollow shaft oil replenishing pump 4, flat keyway 4-a, centrifugal hole 4-b, internal spline 4-c, hollow shaft 4-d, first ball bearing 5, second ball bearing 6. Detailed implementation manners

[0014] The principles and features of the present invention will be described below in conjunction with the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0015] As Figures 1 to 6As shown in the figure, the present invention is an integrated wide-speed aviation fuel electric gear pump, which integrates a permanent magnet synchronous motor, an internal gear pump, and a hollow shaft oil replenishing pump through an integrated design. Through the housing encapsulation, there is no shaft extension outside, the motor assembly is immersed in the fuel, replacing the fan cooling and heat dissipation. A main oil suction port and an auxiliary oil suction port are set, and with the boosting effect of the hollow shaft oil replenishing pump, the problem of insufficient oil suction under high-speed conditions is improved. Specifically, it includes a gear pump head assembly 1, a permanent magnet synchronous motor assembly 2, a housing assembly 3, a hollow shaft oil replenishing pump 4, a first ball bearing 5, and a second ball bearing 6. Among them, the gear pump head assembly 1 includes an oil suction side plate 1-1, a first sliding bearing 1-2, a gear shaft 1-3, an internal gear ring 1-4, a first positioning pin 1-5, a static pressure support ring 1-6, a second sliding bearing 1-7, an oil discharge side plate 1-8, a high-pressure rectangular sealing ring 1-9, a screw 1-10, and a second positioning pin 1-11; the permanent magnet synchronous component 2 includes a junction box cover 2-1, a wiring board 2-2, a junction box body 2-3, an O-ring 2-4, a terminal post 2-5, a connecting piece 2-6, a nut 2-7, a cable 2-8, a winding 2-9, a first cover plate 2-10, a permanent magnet rotor 2-11, a second cover plate 2-10, and a flat key 2-13; the housing assembly 3 includes a front end cover 3-1, a gear pump head mounting seat 3-2, a first support end cover 3-3, a support 3-4, a housing 3-5, a second support end cover 3-6, and a rear end cover 3-7. The gear pump head assembly 1 and the permanent magnet synchronous motor assembly 2 are encapsulated in the housing assembly 3. The permanent magnet rotor 2-11 and the hollow shaft oil replenishing pump 4 are connected into one body by a flat key 2-13 and are supported and positioned by the first ball bearing 5 and the second ball bearing 6. The first ball bearing 5 and the second ball bearing 6 are respectively installed inside the first support end cover 3-3 and the second support end cover 3-6. The first support end cover 3-3 and the second support end cover 3-6 are respectively fixed to both ends inside the housing 3-5 by screws. The hollow shaft oil replenishing pump 4 is provided with an internal spline 4-c, which is connected to the internal spline 1-3-a on the gear shaft 1-3 of the gear pump head assembly 1. The gear pump head assembly 1 is installed inside the gear pump head mounting seat 3-2 and is positioned by the second positioning pin 1-11; the hollow shaft oil replenishing pump 4 is integrally formed by the motor main shaft and the oil replenishing pump, and the central axes of the gear shaft 1-3 and the hollow shaft oil replenishing pump 4 coincide; in the gear pump head assembly 1, the gear shaft 1-3 is supported between the oil suction side plate 1-1 and the oil discharge side plate 1-8 by the first sliding bearing 1-2 and the second sliding bearing 1-7. The first sliding bearing 1-2 and the second sliding bearing 1-7 are respectively installed on the oil suction side plate 1-1 and the oil discharge side plate 1-8. The oil suction side plate 1-1, the oil discharge side plate 1-8, and the static pressure support ring 1-6 are positioned by the first positioning pin 1-5 and fixed by the screw 1-10.

[0016] As Figures 1 to 3As shown, a crescent plate 1-1-a and a first oil inlet 1-1-b are provided on the oil suction side plate 1-1. The crescent plate 1-1-a is fixed between the internal gear ring 1-4 and the gear shaft 1-3, serving to separate the high and low pressure chambers and for sealing. An external spline 1-3-a, a central hole 1-3-b, and a replenishing oil hole 1-3-c are provided on the gear shaft 1-3. The axis of the replenishing oil hole 1-3-c is perpendicular to that of the central hole 1-3-b and radially penetrates the gear shaft 1-3 to introduce the cool oil on the low pressure side to the sliding bearing part, serving for lubrication and heat dissipation. A static pressure support groove 1-6-a and a first oil passage groove 1-6-b are provided on the static pressure support ring 1-6. A second oil inlet 1-8-a and an oil discharge port 1-8-b are provided on the oil discharge side plate 1-8. The first oil passage groove 1-6-b communicates with the first oil inlet 1-1-b and the second oil inlet 1-8-a to ensure oil suction on both sides of the gear pump.

[0017] As Figure 1 、 Figure 6 shown, a main oil suction port 3-2-a communicating with an oil groove 3-2-b is provided on the gear pump head mounting seat 3-2. A second oil passage groove 3-3-a and a first set screw hole 3-3-b are provided on the first support end cover 3-3. An auxiliary oil suction port 3-5-a, a lifting lug seat 3-5-b, a winding support rib 3-5-c, and a third oil passage groove 3-5-d are provided on the housing 3-5. The number of the winding support ribs 3-5-c and the third oil passage grooves 3-5-d is the same and they are evenly distributed inside the housing 3-5. The number of the support ribs 3-5-c and the third oil passage grooves 3-5-d can be adapted according to the actual working conditions or fields of use, such as restrictions on structural strength, light weight, etc. The lifting lug seat 3-5-b and the junction box body 2-3 are saddle-shaped and are respectively welded to the housing 3-5 with the support 3-4. A fourth oil passage groove 3-6-a and a second set screw hole 3-6-b are provided on the second support end cover 3-6. The first set screw hole 3-3-b and the second set screw hole 3-6-b are mainly used for disassembly.

[0018] As Figure 1 、 Figure 5 shown, a flat key groove 4-a, a centrifugal hole 4-b, an internal spline 4-c, and a hollow shaft 4-d are provided on the hollow shaft oil replenishing pump 4. The hollow shaft 4-d communicates with the centrifugal hole 4-b. The included angle formed by the axis of the centrifugal hole 4-c and the axis of the hollow shaft oil replenishing pump 4 is in the range of 45° to 60°.

[0019] As Figures 1 to 3 、 Figure 5 、 Figure 6As shown in the figure, the main oil suction port 3-2-a is connected to the first oil inlet 1-1-b, the first oil passage groove 1-6-b, and the second oil inlet 1-8-a to form the main oil suction circuit, which is the main oil suction path under normal rotational speed; the auxiliary oil suction port 3-5-a is communicated with the second oil passage groove 3-3-a, the third oil passage groove 3-5-d, the fourth oil passage groove 3-6-a, the hollow shaft 4-d, the centrifugal holes 4-b, and the first oil inlet 1-1-b to form the auxiliary oil suction circuit and the heat dissipation circuit. Under high-speed and ultra-high-speed operating conditions, it serves as the second oil suction path to enhance the oil suction capacity of the gear pump and strengthen heat dissipation at the same time; the oil discharge port 1-8-b is communicated with the outlet 3-1-a on the front end cover 3-1 to form the oil discharge circuit.

[0020] As Figure 1 , Figure 4 As shown in the figure, the O-ring 2-4 is installed on the junction box body 2-3. Six terminal posts 2-5 are smeared with thread sealant and installed on the wiring board 2-2, and are fixed to the junction box body 2-3 by screws. The liquid is sealed inside the housing assembly 3 through static sealing and thread sealant to prevent the liquid from leaking out of the junction box, thereby affecting the oil suction airtightness of the gear pump.

[0021] The working process of the present invention is as follows: Before the integrated wide-speed aviation fuel electric gear pump of the present invention is started, oil injection is carried out through the auxiliary oil suction port 3-5-a. When liquid is discharged from the main oil suction port 3-2-a, all the air inside the pump is discharged. Subsequently, the power supply of the motor controller is connected and started. Driven by the electromagnetic force, the hollow shaft oil supply pump 4 rotates, and at the same time drives the gear shaft 1-3 and the internal gear ring 1-4 to engage and work. The oil enters the pump interior through the main oil suction port 3-2-a and the auxiliary oil suction port 3-5-a at the same time. The auxiliary oil circuit mainly passes through the second oil passage groove 3-3-a, the third oil passage groove 3-5-d, the fourth oil passage groove 3-6-a, the hollow shaft 4-d, and after being pressurized by the centrifugal holes 4-b, it reaches the first oil inlet 1-1-b, and then is sucked into the gear pump interior and discharges high-pressure oil through the engagement of the gear pump. When the integrated wide-speed aviation fuel electric gear pump operates at a normal rotational speed (rotational speed ≤ 3000 r / min), the main oil suction circuit plays a leading role, and the auxiliary oil suction circuit is mainly used for heat dissipation; when operating at a high rotational speed (rotational speed ≥ 3000 r / min) and an ultra-high rotational speed (rotational speed ≥ 8000 r / min), the auxiliary oil suction circuit is strengthened and pressurized by the hollow shaft oil supply pump 4 to supply oil to the gear pump. The higher the rotational speed, the stronger the pressurization ability of the hollow shaft oil supply pump, and the higher the oil suction efficiency of the integrated wide-speed aviation fuel electric gear pump, while strengthening the heat dissipation effect; during this process, the auxiliary oil suction circuit mainly takes out the heat generated by the motor and bearings, etc., and the main oil suction circuit can also take out the heat generated by the gear pump head to complete the cooling of the whole machine.

Claims

1. Integrated wide-speed aviation fuel electric gear pump, comprising a gear pump head assembly (1), a permanent magnet synchronous motor assembly (2), a housing assembly (3), a hollow shaft oil replenishing pump (4), a first ball bearing (5) and a second ball bearing (6), wherein the gear pump head assembly (1) includes an oil suction side plate (1-1), a first sliding bearing (1-2), a gear shaft (1-3), an internal gear ring (1-4), a first positioning pin (1-5), a static pressure support ring (1-6), a second sliding bearing (1-7), an oil discharge side plate (1-8), a high-pressure rectangular sealing ring (1-9), a screw (1-10) and a second positioning pin (1-11); the permanent magnet synchronous assembly (2) includes a junction box cover (2-1), a wiring board (2-2), a junction box body (2-3), an O-ring (2-4), a terminal (2-5), a connecting piece (2-6), a nut (2-7), a cable (2-8), a winding (2-9), a first cover plate (2-10), a permanent magnet rotor (2-11), a second cover plate (2-10) and a flat key (2-13); the housing assembly (3) includes a front end cover (3-1), a gear pump head mounting seat (3-2), a main oil suction port (3-2-a), a first support end cover (3-3), a support (3-4), a housing (3-5), a second support end cover (3-6) and a rear end cover (3-7), characterized in that The gear pump head assembly (1) and the permanent magnet synchronous motor assembly (2) are encapsulated within the housing assembly (3). The permanent magnet rotor (2-11) and the hollow shaft oil make-up pump (4) are connected into an integral body through a flat key (2-13), and are supported and positioned by a first ball bearing (5) and a second ball bearing (6). The first ball bearing (5) and the second ball bearing (6) are respectively installed inside the first support end cover (3-3) and the second support end cover (3-6). The first support end cover (3-3) and the second support end cover (3-6) are respectively fixed to both ends inside the housing (3-5) by screws. The hollow shaft oil make-up pump (4) is provided with an internal spline (4-c), which is connected to the internal spline (1-3-a) on the gear shaft (1-3) of the gear pump head assembly (1). The gear pump head assembly (1) is installed inside the gear pump head mounting seat (3-2) and is positioned by a second positioning pin (1-11); the hollow shaft oil make-up pump (4) is integrally formed by the motor main shaft and the oil make-up pump, and the central axes of the gear shaft (1-3) and the hollow shaft oil make-up pump (4) coincide; in the gear pump head assembly (1), the gear shaft (1-3) is supported between the oil suction side plate (1-1) and the oil discharge side plate (1-8) by a first sliding bearing (1-2) and a second sliding bearing (1-7). The first sliding bearing (1-2) and the second sliding bearing (1-7) are respectively installed on the oil suction side plate (1-1) and the oil discharge side plate (1-8). The oil suction side plate (1-1), the oil discharge side plate (1-8) and the hydrostatic support ring (1-6) are positioned by a first positioning pin (1-5) and fixed by screws (1-10).

2. The integrated wide-speed aviation fuel electric gear pump according to claim 1, characterized in that: The oil suction side plate (1-1) is provided with a crescent plate (1-1-a) and a first oil inlet (1-1-b); the gear shaft (1-3) is provided with an external spline (1-3-a), a central hole (1-3-b) and an oil make-up hole (1-3-c). The axis of the oil make-up hole (1-3-c) is perpendicular to the axis of the central hole (1-3-b) and radially penetrates the gear shaft (1-3); the hydrostatic support ring (1-6) is provided with a hydrostatic support groove (1-6-a) and a first oil passage groove (1-6-b); the oil discharge side plate (1-8) is provided with a second oil inlet (1-8-a) and an oil discharge port (1-8-b).

3. The integrated wide-speed aviation fuel electric gear pump according to claim 1, characterized in that: The described gear pump head mounting seat (3-2) is provided with a main oil suction port (3-2-a) which communicates with an oil tank (3-2-b). The first support end cover (3-3) is provided with a second oil passage groove (3-3-a) and a first setscrew hole (3-3-b); the housing (3-5) is provided with an auxiliary oil suction port (3-5-a), a lifting lug seat (3-5-b), a winding support rib (3-5-c) and a third oil passage groove (3-5-d), wherein the number of the winding support ribs (3-5-c) and the third oil passage grooves (3-5-d) is the same and they are evenly distributed inside the housing (3-5); the lifting lug seat (3-5-b) and the junction box body (2-3) are in a saddle shape and are respectively welded to the housing (3-5) with the support (3-4); the second support end cover (3-6) is provided with a fourth oil passage groove (3-6-a) and a second setscrew hole (3-6-b).

4. The integrated wide-speed aviation fuel electric gear pump according to claim 1, wherein: The described hollow shaft makeup oil pump (4) is provided with a flat key groove (4-a), a centrifugal hole (4-b), an internal spline (4-c) and a hollow shaft (4-d), wherein the hollow shaft (4-d) communicates with the centrifugal hole (4-b); the included angle formed by the axis of the centrifugal hole (4-c) and the axis of the hollow shaft makeup oil pump (4) is in the range of 45° to 60°.

5. The integrated wide-speed aviation fuel electric gear pump according to claim 1, wherein: The main oil suction port (3-2-a) communicates with the first oil inlet (1-1-b), the first oil passage groove (1-6-b) and the second oil inlet (1-8-a) to form a main oil suction circuit; the auxiliary oil suction port (3-5-a) communicates with the second oil passage groove (3-3-a), the third oil passage groove (3-5-d), the fourth oil passage groove (3-6-a), the hollow shaft (4-d), the centrifugal hole (4-b) and the first oil inlet (1-1-b) to form an auxiliary oil suction circuit and a heat dissipation oil circuit; the oil discharge port (1-8-b) communicates with the outlet (3-1-a) on the front end cover (3-1) to form an oil discharge circuit.

6. The integrated wide-speed aviation fuel electric gear pump according to claim 1, characterized in that: The described O-ring (2-4) is installed on the junction box body (2-3). Six terminal posts (2-5) are smeared with thread sealant, installed on the wiring board (2-2) and fixed to the junction box body (2-3) by screws.

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