Flow distribution disc and high-speed heavy-load long-endurance aviation hydraulic pump

Abstract

The application discloses a flow distribution disc and a high-speed heavy-load long-time aviation hydraulic pump, and the flow distribution disc is used on the aviation hydraulic pump, wherein the aviation hydraulic pump comprises a swash plate (3), a main shaft (2), a rotor (7) and the flow distribution disc (8), the rotor (7) is provided with a plunger hole (70), the flow distribution disc (8) is provided with a high-pressure area window (80) and a low-pressure area window (81), the flow distribution disc (8) is provided with a first throttling hole (82) for communicating a shell cavity of the aviation hydraulic pump, and the first throttling hole (82) is located in a region from the high-pressure area window (80) to the low-pressure area window (81) in the rotating direction of the main shaft (2). The application has the advantages that the reliability and the service life of the hydraulic pump can be improved.

Description

Technical Field

[0001] This invention belongs to the field of aviation hydraulic pumps, and particularly relates to a distribution plate and a high-speed, heavy-duty, long-endurance aviation hydraulic pump. Background Technology

[0002] like Figure 6 and Figure 8 As shown, the existing aviation hydraulic pump (hereinafter referred to as the hydraulic pump) is a variable displacement pump. Its structure includes a drive shaft 1, one end of which is connected to the main unit, and the other end of which is connected to the main shaft 2 of the hydraulic pump. When the main unit drives the drive shaft 1 to rotate, the drive shaft 1 drives the main shaft 2 to rotate. The main shaft 2 drives the rotor 7, plunger 6, slipper 4, chuck 5 and other rotating components to rotate. Since the swashplate 3 has an angle and does not rotate with the main shaft 2, the plunger 6 makes a linear reciprocating motion in the plunger hole 70 of the rotor 7, driving the oil to be discharged from the plunger hole 70 and the plunger cavity waist-shaped hole 71. Through the low-pressure area window 81 or the high-pressure area window 80 of the distribution plate 8, the hydraulic pump realizes the oil suction and discharge process, and then supplies oil to the hydraulic system. The swashplate plunger pump of publication number CN208416785U also belongs to the variable displacement pump with the above structure.

[0003] With the development of aircraft hydraulic technology, high-speed and heavy-duty operation is an inevitable trend in the development of aviation hydraulic pumps. High-speed and heavy-duty hydraulic pumps are beneficial for reducing the size of power components, reducing the size and weight of aircraft, and improving the aircraft's load-bearing and maneuverability. However, the higher the speed of the hydraulic pump, the greater the mechanical losses caused by fluid friction damping; the higher the working pressure of the hydraulic pump, the greater the volumetric and throttling losses. Most of the power lost by the hydraulic pump is converted into heat, resulting in a large temperature rise in the hydraulic pump. Therefore, high-speed and heavy-duty operation of hydraulic pumps inevitably leads to an increase in the thermal equilibrium temperature of the hydraulic pump. This is especially true for aircraft such as transport aircraft and bombers that need to operate for long periods of time. Due to their large size and long-term operation under high-pressure and zero-flow conditions, the heat generated by the hydraulic pump is mainly transferred to the outside through the return oil. Because the return oil pipeline of the aircraft hydraulic system is long and usually equipped with oil filters and safety valves, the return oil pressure of the hydraulic pump is high, resulting in a small return oil volume. If the return oil flow is too low, heat cannot be transferred to the outside in time, leading to excessively high oil temperature inside the pump chamber. Due to the low viscosity or carbonization of the oil, an oil film cannot form between the friction pairs, resulting in abnormal wear or even seizing. Simultaneously, excessively high oil temperature also causes rapid aging of the seals inside the hydraulic pump, easily leading to oil leakage. Therefore, excessively high hydraulic pump oil temperature will significantly reduce the reliability and lifespan of the hydraulic pump, affecting aircraft flight safety. Summary of the Invention

[0004] The purpose of this invention is to provide a distribution plate and a high-speed, heavy-duty, long-endurance aviation hydraulic pump. This invention has the advantage of improving the reliability and lifespan of the hydraulic pump.

[0005] The technical solution of the present invention: a distribution plate for use on an aviation hydraulic pump, the aviation hydraulic pump including a swashplate, a main shaft, a rotor and a distribution plate, the rotor being provided with a plunger hole, the distribution plate being provided with a high-pressure zone window and a low-pressure zone window, the distribution plate being provided with a first throttling orifice for connecting to the housing cavity of the aviation hydraulic pump, the first throttling orifice being located in the region from the high-pressure zone window to the low-pressure zone window in the rotation direction of the main shaft;

[0006] The plane that passes through the axis of rotation of the swashplate and is parallel to the swashplate is defined as the swashplate reference plane. A coordinate system is established on the swashplate reference plane. The X-axis of the coordinate system passes through the axis of principal axis 2. The direction from the outer end of principal axis 2 to the inner end of principal axis 2 is the positive direction of the X-axis. The Y-axis of the coordinate system passes through the axis of rotation of the swashplate. The Z-axis of the coordinate system is determined according to the right-hand rule.

[0007] Let α denote the angle of rotation of the swashplate around the Y-axis, β denote the angle of rotation of the swashplate around the Z-axis, φ1 denote the angle between the high-pressure zone window and the Z-axis, θ0 denote the angle of projection of the plunger cavity's waist-shaped orifice onto the distribution plate, and θ1 denote the angle between the first throttling orifice and the Z-axis.

[0008] Equation 1 satisfies the following formula conditions: Formula 2: Formula 3:

[0009] In the aforementioned distribution panel, in formula three,

[0010] In the aforementioned distribution plate, a second throttling orifice is provided on one side of the first throttling orifice.

[0011] In the aforementioned distribution plate, a one-way valve is provided on the distribution plate, and both the first throttling orifice and the second throttling orifice are connected to the housing cavity of the aviation hydraulic pump through the one-way valve.

[0012] In the aforementioned distribution plate, the one-way valve includes a valve sleeve embedded from the outer wall of the distribution plate. The inner end of the valve sleeve contracts inward to form a stepped surface. The inner end of the valve sleeve is connected to the first throttling orifice and the second throttling orifice. The outer end of the valve sleeve is provided with a guide mechanism. A valve core is provided inside the valve sleeve. One end of the valve core abuts against the stepped surface, and the other end of the valve core passes through the guide mechanism. The other end of the valve core is slidably connected to the guide mechanism.

[0013] In the aforementioned distribution plate, the guiding mechanism is a perforated plate fixed to the valve sleeve. The perforated plate is provided with a guide tube through which the valve core passes, and the perforated plate is provided with multiple through holes distributed around the guide tube.

[0014] A high-speed, heavy-duty, long-endurance aviation hydraulic pump includes the aforementioned distribution plate.

[0015] Compared with existing technologies, this invention, based on the existing distribution plate, sets up a throttling orifice in the area between the high-pressure zone window and the low-pressure zone window to connect the housing cavity of the aviation hydraulic pump. This increases the return oil volume of the hydraulic pump without affecting its output characteristics, thereby avoiding problems such as abnormal wear of the friction pair, seal failure, and engine seizure caused by excessive temperature rise of the hydraulic pump under high-speed, heavy-load, and long-duration operation. This improves the reliability and lifespan of the hydraulic pump. Furthermore, the throttling orifice can guide air bubbles between the distribution plate and the rotor into the housing cavity, reducing the retention of air bubbles between the distribution plate and the rotor and preventing cavitation caused by annihilation. This further reduces abnormal wear of the friction pair formed by the distribution plate and the rotor, improving the reliability and lifespan of the hydraulic pump. Therefore, this invention has the advantage of improving the reliability and lifespan of the hydraulic pump. Attached Figure Description

[0016] Figure 1 This is a front view of the present invention.

[0017] Figure 2 yes Figure 1 A diagram at point AA.

[0018] Figure 3 This is a schematic diagram showing the projection relationship of the swashplate onto the distribution plate in the coordinate system.

[0019] Figure 4 This is a front view of the perforated disk.

[0020] Figure 5 yes Figure 4 The right view.

[0021] Figure 6 This is a structural schematic diagram of an existing aviation hydraulic pump.

[0022] Figure 7 This is a schematic diagram of the swashplate in a coordinate system.

[0023] Figure 8 This is a schematic diagram of the connection between the rotor, plunger, and distributor plate in an existing aviation hydraulic pump.

[0024] The labels in the attached diagram are as follows: 1-drive shaft; 2-main shaft; 3-swashplate; 4-slipper; 5-chuck; 6-plunger; 7-rotor; 70-plunger bore; 71-plunger cavity waist-shaped bore; 8-distribution plate; 80-high pressure zone window; 81-low pressure zone window; 82-first throttling orifice; 83-second throttling orifice; 9-one-way valve; 90-valve sleeve; 91-valve core; 92-perforated plate; 93-guide tube; 94-through hole; 100-deflection shaft. Detailed Implementation

[0025] The present invention will be further described below with reference to the accompanying drawings and embodiments, but this should not be construed as limiting the present invention.

[0026] Example 1. The structure of an existing aviation hydraulic pump, such as... Figure 6 and Figure 8 As shown, the system includes a drive shaft 1, one end of which is connected to the host machine (such as a motor), and the other end of which is connected to the main shaft 2 of the hydraulic pump. When the host machine drives the drive shaft 1 to rotate, the drive shaft 1 drives the main shaft 2 to rotate. The main shaft 2 drives the rotor 7, plunger 6, slipper 4, chuck 5 and other rotating components to rotate. Since the swashplate 3 has an angle and does not rotate with the main shaft 2, the plunger 6 makes a linear reciprocating motion in the plunger hole 70 of the rotor 7, driving the oil to be discharged from the plunger hole 70 and the plunger cavity waist-shaped hole 71. Through the low-pressure area window 81 or the high-pressure area window 80 of the distribution plate 8, the hydraulic pump realizes the oil suction and discharge process, and then supplies oil to the hydraulic system.

[0027] like Figure 7 As shown, for clarity, Figure 7 Only one plunger 6 is drawn. The plane that passes through the rotation axis 101 of the swashplate 3 and is parallel to the swashplate 3 is defined as the reference plane of the swashplate 3. A coordinate system is established on the reference plane of the swashplate 3. The X-axis of the coordinate system passes through the axis of the master spindle 2. The direction from the outer end of the master spindle 2 to the inner end of the master spindle 2 is the positive direction of the X-axis. The Y-axis of the coordinate system passes through the rotation axis of the swashplate 3. The Z-axis of the coordinate system is determined according to the right-hand rule.

[0028] Let α be the angle by which the swashplate 3 rotates around the Y-axis, i.e., the swashplate 3's swing angle; and let β be the angle by which the swashplate 3 rotates around the Z-axis, i.e., the additional angle of the swashplate 3. The additional angle β causes the upper and lower dead points of the shoe 4-plunger 6 assembly on the swashplate 3 to change to the deflection axis 100 (the upper dead point refers to the position where the plunger 6 extends outward to its limit in the plunger hole 70, at which point the plunger hole 70 stops sucking oil and begins to discharge oil; the lower dead point refers to the position where the plunger 6 extends inward to its limit in the plunger hole 70, at which point the plunger 6 cavity stops discharging oil and begins to suck oil). To increase the pump's power density, reduce outlet pressure pulsation, and improve control characteristics, there is an additional angle β around the Z-axis on the swashplate plane. This additional angle causes the upper and lower dead points of the shoe-plunger assembly on the swashplate to change to the deflection axis 100, thus changing the flow field characteristics of the aviation hydraulic pump. According to the coordinate transformation relationship, the deflection angle γ of the upper and lower dead points can be obtained as follows:

[0029]

[0030] A distribution plate, improved from the existing distribution plate 8 of the aviation hydraulic pump, has the following characteristics: Figure 1 and Figure 2As shown, the distribution plate 8 is provided with a first throttling hole 82 and a second throttling hole 83. In the rotation direction of the main shaft 2, the first throttling hole 82 and the second throttling hole 83 are both used to connect the housing cavity of the hydraulic pump. The first throttling hole 82 and the second throttling hole 83 are both located in the area from the high pressure zone window 80 to the low pressure zone window 81.

[0031] like Figure 3 As shown, assuming the hydraulic pump rotates clockwise, the angle between the high-pressure zone window 80 and the Z-axis is denoted as φ1. The angle of the projection of the plunger cavity waist-shaped orifice 71 (referring to the plunger cavity waist-shaped orifice 71 whose projection is located between the high-pressure zone window 80 and the low-pressure zone window 81) onto the distribution plate 8 is denoted as θ0. The angle of the plunger cavity waist-shaped orifice 71 projected onto the distribution plate 8 refers to the angle formed by projecting the plunger cavity waist-shaped orifice 71 onto the distribution plate 8 after connecting the two ends of the plunger cavity waist-shaped orifice 71 to the coordinate origin respectively. The angle between the first throttling orifice 82 and the Z-axis is denoted as θ1. To improve the volumetric efficiency of the hydraulic pump, it is necessary to ensure that:

[0032]

[0033]

[0034] The best one is:

[0035] At this time, when the plunger 6 moves from the high-pressure zone window 80 to the low-pressure zone window 81, on the one hand, the waist-shaped orifice 71 of the plunger cavity disengages from the high-pressure zone window 80, preventing the volumetric efficiency loss caused by the backflow of high-pressure oil into the plunger orifice 70; on the other hand, the waist-shaped orifice 71 of the plunger cavity quickly communicates with the first throttling orifice 82. Since the plunger orifice 70 is filled with high-pressure oil at this time, the oil in the plunger orifice 70 enters the housing cavity of the hydraulic pump through the first throttling orifice 82. The air bubbles generated by the high-speed flow of oil in the plunger orifice 70 also enter the housing cavity through the first throttling orifice 82, preventing the air bubbles from staying between the rotor 7 and the distribution plate 8, and avoiding the cavitation problem caused by the annihilation of air bubbles on the surfaces of the rotor 7 and the distribution plate 8. The position of the second throttling orifice 83 can be set according to the actual working conditions. After multiple tests and comparisons, it can be seen that the setting of the second throttling orifice 83 can make the oil pressure relief process in the plunger orifice 70 smoother, thereby reducing pressure shock and noise, and improving the stability and reliability of the hydraulic pump operation.

[0036] The distribution plate 8 is equipped with a one-way valve 9. Both the first throttling orifice 82 and the second throttling orifice 83 are connected to the housing cavity of the hydraulic pump through the one-way valve 9. The one-way valve 9 includes a valve sleeve 90 embedded in the outer wall of the distribution plate 8. The inner end of the valve sleeve 90 tapers inward to form a stepped surface. The inner end of the valve sleeve 90 connects to the first throttling orifice 82 and the second throttling orifice 83. The outer end of the valve sleeve 90 connects to the housing cavity of the hydraulic pump and is equipped with a guide mechanism. A valve core 91 is provided inside the valve sleeve 90. One end of the valve core 91 abuts against the stepped surface, and the other end of the valve core 91 passes through the guide mechanism, and the other end of the valve core 91 is slidably connected to the guide mechanism. The guide mechanism is a perforated plate 92 fixed to the valve sleeve 90. The perforated plate 92 has a guide tube 93 through which the valve core 91 passes, and multiple through holes 94 distributed around the guide tube 93. The oil pressure released from the plunger orifice 70 passes through the first throttling orifice 82, the second throttling orifice 83, and the valve sleeve 90, pushing open the valve core 91 and causing the check valve 9 to open. The oil then enters the hydraulic pump housing cavity through the through-hole 94 until the oil pressure in the plunger orifice 70 decreases to the same level as the housing cavity pressure. When the oil pressure in the plunger orifice 70 decreases below the housing cavity pressure, the valve core 91 moves under the action of the oil pressure in the housing cavity and abuts against the stepped surface, closing the check valve 9 and preventing oil from entering the plunger orifice 70.

[0037] An aviation hydraulic pump comprising the aforementioned distribution plate.

[0038] Example 2. Unlike Example 1, there is no second throttling orifice 83.

Claims

1. A distribution plate for use on an aviation hydraulic pump, the aviation hydraulic pump comprising a swashplate (3), a main shaft (2), a rotor (7), and a distribution plate (8), wherein the rotor (7) is provided with a plunger hole (70), a plunger (6) is provided in the plunger hole (70), the plunger (6) is connected to the swashplate (3) via a slipper (4), and the distribution plate (8) is provided with a high-pressure area window (80) and a low-pressure area window (81), characterized in that: The distribution plate (8) is provided with a first throttling hole (82) for connecting the housing cavity of the aviation hydraulic pump. In the rotation direction of the main shaft (2), the first throttling hole (82) is located in the area from the high pressure zone window (80) to the low pressure zone window (81). The plane that passes through the rotation axis of the swashplate (3) and is parallel to the swashplate (3) is defined as the reference plane of the swashplate (3). A coordinate system is established on the reference plane of the swashplate (3). The X-axis of the coordinate system passes through the axis of the principal axis (2). The direction from the outer end of the principal axis (2) to the inner end of the principal axis (2) is the positive direction of the X-axis. The Y-axis of the coordinate system passes through the rotation axis of the swashplate (3). The Z-axis of the coordinate system is determined according to the right-hand rule. Let α denote the angle of rotation of the swashplate (3) around the Y-axis, β denote the angle of rotation of the swashplate (3) around the Z-axis, and β denote the angle between the high-pressure zone window (80) and the Z-axis. The angle between the projection of the waist-shaped hole (71) of the plunger cavity onto the distribution plate (8) is denoted as θ0, and the angle between the first throttling hole (82) and the Z-axis is denoted as θ1. The assembly consisting of the slipper (4) and the plunger (6) moves on the swashplate and has upper and lower dead points. The upper and lower dead points are projected onto the distribution plate (8) under the action of the additional angle β. The line connecting the projections of the upper and lower dead points forms the deflection axis (100). The deflection angle of the deflection axis (100) relative to the Z-axis is denoted as γ. The following formula conditions must be met. Formula 1: , Formula 2: , Formula 3: ; The distribution plate (8) is equipped with a check valve (9), and the first throttle hole (82) is connected to the housing cavity of the hydraulic pump through the check valve (9).

2. The distribution plate according to claim 1, characterized in that: In the third formula, .

3. The distribution plate according to claim 1, characterized in that: A second throttling orifice (83) is provided on one side of the first throttling orifice (82).

4. The distribution plate according to claim 3, characterized in that: The second throttle orifice (83) is connected to the housing cavity of the aviation hydraulic pump through a one-way valve (9).

5. The distribution plate according to claim 4, characterized in that: The one-way valve (9) includes a valve sleeve (90) embedded from the outer wall of the distribution plate (8). The inner end of the valve sleeve (90) is contracted inward to form a stepped surface. The inner end of the valve sleeve (90) is connected to the first throttling hole (82) and the second throttling hole (83). The outer end of the valve sleeve (90) is provided with a guide mechanism. The valve sleeve (90) is provided with a valve core (91). One end of the valve core (91) abuts against the stepped surface, and the other end of the valve core (91) passes through the guide mechanism. The other end of the valve core (91) is slidably connected to the guide mechanism.

6. The distribution plate according to claim 5, characterized in that: The guiding mechanism is a perforated disc (92) fixed to the valve sleeve (90). The perforated disc (92) is provided with a guide tube (93) through which the valve core (91) passes. The perforated disc (92) is provided with multiple through holes (94) distributed around the guide tube (93).

7. A high-speed, heavy-duty, long-endurance aviation hydraulic pump, characterized in that: Includes the distribution plate as described in any one of claims 1-6.

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