Aviation pressure oil pumping joint

Abstract

The present invention relates to an aviation pressure oil pumping joint, one end of the hose joint assembly of the oil pumping joint is connected to the oil delivery hose, the other end of the hose joint assembly is clamped with a filter screen, the filter screen is set in a direction that matches the fuel flow direction, and one end of the hose joint assembly clamped with the filter screen is connected to a pressure stabilizer through a connector, the connector is composed of a first connector and a second connector, the second connector is sleeved with the first connector, the first connector is sleeved with one end of the hose joint assembly clamped with the filter screen, and the internal pressure stabilizing spring support force of the pressure stabilizer is 0.08Mpa±0.01Mpa. The aviation pressure oil pumping joint of the present invention is firmly connected, there is no leakage during the oil pumping process, the negative pressure of the oil pumping does not exceed 0.08Mpa, and the oil pumping filter screen can filter oil products normally, which fully meets the oil pumping requirements of airlines and prevents the filter screen from being deformed and damaged by suction.

Description

Technical Field

[0001] The invention relates to the technical field of aviation equipment, in particular to an aviation pressure oil pumping joint. Background Art

[0002] The aircraft refueling connector is installed at the end of the aircraft fuel delivery hose, and is a device that implements aircraft pressure refueling, can control pressure and filter impurities. The aircraft refueling connector includes a hose connector seat, a filter card slot, a regulator and a refueling port connector. The aircraft connector is the last link to ensure that the refueling pressure does not damage the aircraft after the oil enters the aircraft; the filtration is intact and impurities cannot enter the aircraft; the seal with the aircraft is intact, and there is no oil leakage or falling off during the refueling connection.

[0003] Airlines need to drain the fuel (pump oil) when they inspect or repair the fuel tank of an aircraft. At present, they all use aircraft refueling connectors to refuel and pump oil. The commonly used one is the HJS63A aviation pressure refueling connector produced by Changzhou Lantian Tengfei Aviation Equipment Co., Ltd., which is the aviation pressure refueling connector disclosed in the invention patent with Chinese patent publication number CN101259948. However, the existing aircraft refueling connector is not suitable for draining the fuel from the aircraft. For example, when the aircraft undergoes a C check, the pressure required for refueling and pumping is different; and the fuel flow directions of pumping and refueling are opposite. If the existing aircraft refueling connector is used for pumping oil, the filter built into the aircraft refueling connector will be deformed or even damaged, and the pumping flow rate will be slow, which poses a great safety hazard.

[0004] At the same time, since all oil pumping is done through refueling joints, tank refueling trucks all have oil pumping functions, which leads to the mixing of oil pumping vehicles and no fixed oil pumping truck.

[0005] Due to the lack of a dedicated oil extraction joint, oil extraction operations on aircraft pose a great safety hazard to production safety work. The normal oil extraction flow cannot be achieved, resulting in reverse filtration of the filter; the oil cannot be extracted at the pressure required by the aircraft, and there is a potential risk of damaging the aircraft. If the oil extraction system is not perfect, there may even be a situation where oil is refueled after extraction, which will directly add the filtered impurities into the aircraft, which may cause serious unsafe accidents. Summary of the invention

[0006] Purpose of the invention:

[0007] The invention provides an aviation pressure oil extraction joint, which aims to solve the problem that the oil extraction pressure does not meet the requirements and the filter screen is reversed when the existing aircraft refueling joint is used for oil extraction.

[0008] Technical solution:

[0009] An aviation pressure oil pumping joint, the oil pumping joint comprises a hose joint assembly, a stabilizer and a joint body assembly, one end of the stabilizer is fixedly connected to one end of the joint body assembly, the other end of the joint body assembly is connected to the aircraft oil receiving port, one end of the hose joint assembly is connected to the oil delivery hose, the other end of the hose joint assembly is clamped to the filter screen, the top end of the filter screen faces the hose joint assembly connected to one end of the oil delivery hose, and the end of the hose joint assembly clamped to the filter screen is connected to the stabilizer through a connector, the connector consists of a first connector and a second connector, the first connector is sleeved in the second connector, the first connector and the second connector are threadedly connected, and both are clamped to the stabilizer, the hose joint assembly is sleeved in the first connector to clamp one end of the filter screen, and a flange is provided at the contact between the first connector and the filter screen; the clamping point between the stabilizer and the first connector and the second connector is set as a stepped structure, and the stabilizer is fixedly connected to the second connector; a pressure stabilizing spring with a supporting pressure of 0.08Mpa±0.01Mpa is provided inside the stabilizer.

[0010] A rolling track and a first sealing ring groove are provided at the connection between the hose joint assembly and the first connector, a filling steel ball is clamped between the rolling track and the first connector, and a first sealing ring is provided in the first sealing ring groove.

[0011] The connection between the first connector and the hose joint assembly is arranged as a rotating sealing connection structure, which includes a filling steel ball hole and a locking sleeve. A filling steel ball is arranged in the filling steel ball hole. The locking sleeve is connected to the first connector through a first fixing bolt and contacts with the filling steel ball. A thread is arranged at the contact between the first connector and the second connector.

[0012] The filter screen is 60 mesh.

[0013] A visual window is also provided on the voltage stabilizer.

[0014] Advantages and effects:

[0015] The aviation pressure oil pumping joint of the present invention is firmly connected, there is no leakage during the oil pumping process, the oil pumping pressure is stable, and the oil pumping filter can normally filter oil products, which fully meets the oil pumping requirements of airlines, eliminates the safety hazards of the filter screen being deformed and damaged by suction, and oil pumping not being performed according to the aircraft oil pumping pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the assembly structure of the hose joint assembly and the connector;

[0017] Figure 2 It is a schematic diagram of the hose joint assembly structure;

[0018] Figure 3 is a cross-sectional view of a first connecting member;

[0019] Figure 4is a schematic diagram of the structure of the first connecting member;

[0020] Figure 5 is a schematic diagram of the structure of the second connecting member;

[0021] Figure 6 is a schematic diagram of the voltage stabilizer structure;

[0022] Figure 7 This is a schematic diagram of the overall structure of the aviation pressure oil pumping joint;

[0023] Markings in the figure: 1. Hose joint assembly, 11. Raceway, 12. First sealing ring slot, 2. Filter, 3. First connecting body, 31. Flange, 32. Flange groove, 33. Filling steel ball, 34. Locking sleeve, 35. First fixing bolt, 36. First bolt fixing groove, 37. Filling steel ball hole, 38. Second bolt fixing groove, 4. Second connecting body, 41. Second fixing bolt, 5. Voltage stabilizer, 51. First step surface, 52. Second step surface, 53. Voltage stabilizer spring, 54. Visual window, 6. Connector body assembly, 7. Protective sleeve, 8. Protective cover, 9. Electrostatic wire assembly, 10. First sealing ring, 11. Second sealing ring, 12. Third sealing ring. DETAILED DESCRIPTION

[0024] The present invention is described below in conjunction with the accompanying drawings.

[0025] The present invention provides an aviation pressure oil pumping joint by improving the partial structure of the existing aviation pressure refueling joint, that is, improving the structure of the hose joint assembly 1, the first connector 3, the second connector 4 and the stabilizer 5, so that the setting direction of the filter 2 matches the fuel flow direction, the negative pressure of the oil pumping does not exceed 0.08 MPa, and the structural design in which the first connector 3 is sleeved in the second connector 4 and the hose joint assembly 1 is sleeved in the first connector 3 is not only convenient for disassembly, but also avoids the problems of easy storage of fuel and easy aging of the sealing ring in the existing aviation pressure refueling joint, and at the same time increases the stability of the connection between each other.

[0026] like Figure 1 and Figure 6-7As shown, an aviation pressure oil pumping joint, the oil pumping joint includes a hose joint assembly 1, a stabilizer 5 and a joint body assembly 6, one end of the stabilizer 5 is fixedly connected to one end of the joint body assembly 6, the other end of the joint body assembly 6 is connected to the aircraft refueling port, one end of the hose joint assembly 1 is connected to the oil delivery hose, and the other end of the hose joint assembly 1 is clamped with a filter 2, the filter 2 is a conical structure, the top end (i.e., the tip) of the filter 2 faces the end of the hose joint assembly 1 connected to the oil delivery hose, the top end of the filter 2 faces the end of the hose joint assembly 1 connected to the oil delivery hose, the setting direction of the filter 2 matches the fuel flow direction, that is, the concave surface of the filter 2 is opposite to the fuel flow direction, thereby avoiding the phenomenon that the filter 2 is shriveled or even damaged when the aviation pressure refueling joint is used to pump aircraft fuel, and the oil pumping flow rate is high, which can meet the requirements of different oil pumping vehicles for the oil pumping flow rate during the oil pumping operation, and is conducive to emptying the fuel in the aircraft without damaging the aircraft. One end of the hose joint assembly 1 that is clamped with the filter 2 is connected to the stabilizer 5 through a connector, and the connector is composed of a first connector 3 and a second connector 4. The first connector 3 is sleeved inside the second connector 4, and the first connector 3 and the second connector 4 are threadedly connected and are both clamped with the stabilizer 5. One end of the hose joint assembly 1 that is clamped with the filter 2 is sleeved inside the first connector 3, and a flange 31 is provided at the contact between the first connector 3 and the filter 2; the clamping point between the stabilizer 5 and the first connector 3 and the second connector 4 is set to a stepped structure, and the stabilizer 5 is fixedly connected with the second connector 4 by bolts.

[0027] Whether it is an aviation pressure oil extraction joint or an aviation pressure refueling joint, oil leakage must be avoided, and oil leakage is often caused by aging of the sealing rings at the connection of each component. During the use of the existing aviation pressure refueling joint (refer to the invention patent with Chinese patent publication number CN101259948), when the oil leakage of the joint body assembly is not considered, the connection points that are more prone to oil leakage are the connection between the hose joint seat and the filter card slot, and the connection between the filter card slot and the stabilizer. The reason is analyzed as follows: during the refueling process, the fuel directly impacts the filter card slot through the hose joint seat, resulting in fuel easily retained at the connection between the hose joint seat and the filter card slot, and the sealing ring set ages quickly; the fuel directly impacts the stabilizer through the filter card slot, resulting in fuel easily retained at the connection between the filter card slot and the stabilizer, and the sealing ring set ages quickly. To solve this technical problem, the present invention improves the connection between the voltage stabilizer 5 and the first connector 3 and the second connector 4 according to the flow direction of the pumped fuel, that is, the connection between the voltage stabilizer 5 and the first connector 3 and the second connector 4 is set to a stepped structure, such as Figure 6 As shown, the second step surface 52 and the lower end surface of the second connector 4 (the lower end surface is as shown in Figure 5 The first step surface 51 and the lower end surface of the first connecting body 3 (the lower end surface is as shown in FIG. Figure 3 ,4 The end surface below the first connector as shown in the figure is in contact with the clamping connection. At this time, the fuel flows directly into the first connector 3 along the stabilizer 5, and there is no impact on the connection between the stabilizer 5 and the first connector 3, and there is no fuel retention, thereby reducing the damage to the second sealing ring 11 set at the first connector 3 and the second connector 4, reducing the damage to the third sealing ring 12 set at the second connector 4 and the stabilizer 5, extending the service life of the second sealing ring 11 and the third sealing ring 12, and reducing the number of replacement times of the sealing rings; secondly, at the first connector A flange 31 is provided at the contact point between the first connector 3 and the filter 2, and a flange groove 32 is formed between the flange 31 and the outer wall of the first connector 3. The filter 2 is installed on the hose joint assembly 1, and the end of the filter 2 and the hose joint assembly 1 is just inserted into the flange groove 32. According to the flow direction of the pumped oil, the fuel will flow directly into the filter 2 along the flange 31 for filtration, and there will be no fuel retention, thereby avoiding damage to the first sealing ring 10 between the first connector 3 and the hose joint assembly 1, extending the service life of the first sealing ring 10, and reducing the number of replacement times of the sealing ring. At the same time, the present invention sleeves the first connector 3 inside the second connector 4, and the hose joint assembly 1 inside the first connector 3, which is not only convenient for disassembly, but also increases the stability of the connection between each other.

[0028] A pressure stabilizing spring 53 with a supporting pressure of 0.08Mpa±0.01Mpa is arranged inside the pressure stabilizer 5. That is, the pressure stabilizer 5 ensures that the fuel pressure at the outlet of the aviation pressure oil pumping joint is within 0.08Mpa±0.01Mpa during the oil pumping operation. If the pressure exceeds this pressure, the pressure stabilizing valve of the pressure stabilizer will compress the pressure stabilizing spring 53, thereby closing the entire pressure stabilizing valve and cutting off the oil delivery channel, thereby ensuring the stability of the oil pumping pressure. When the pressure stabilizing spring 53 is set thinner and the supporting pressure is less than 0.08Mpa, the supporting pressure is small and the stability is poor; when the pressure stabilizing spring 53 is set thicker and the supporting pressure is greater than 0.08Mpa, it leads to a high pressure during oil pumping, which poses a safety hazard to the aircraft fuel tank; only when the supporting pressure of the pressure stabilizing spring 53 is 0.08Mpa±0.01Mpa, the stability of the oil pumping pressure is guaranteed, the pressure is small during oil pumping, the fuel flow rate is stable, and there is no damage to the aircraft.

[0029] like Figure 1-4 As shown, a raceway 11 and a first sealing ring groove 12 are provided at the connection between the hose joint assembly 1 and the first connector 3, a filling steel ball 33 is clamped between the raceway 11 and the first connector 3, and a first sealing ring 10 is provided in the first sealing ring groove 12. One end of the hose joint assembly 1 connected to the oil delivery hose is in the form of an existing structure.

[0030] The connection between the first connector 3 and the hose joint assembly 1 is set as a rotating seal connection structure, which includes a filling steel ball hole 37 and a locking sleeve 34. The filling steel ball hole 37 is provided with a filling steel ball 33. The locking sleeve 34 is connected to the first connector 3 through a first fixing bolt 35 and contacts with the filling steel ball 33. The rotating seal connection structure can realize that the hose joint and the aviation pressure pumping joint can rotate relative to each other within 360°; the contact between the first connector 3 and the second connector 4 is provided with a thread. That is, the first connector 3 and the second connector 4 are threadedly connected to make the connection more stable. A groove for placing the second sealing ring 11 is provided above the thread, and a second bolt fixing groove 38 for inserting the second fixing bolt 41 is provided above the groove. When the first connector 3 and the second connector 4 are threadedly connected and fixed, the second fixing bolt 41 is tightened to stably connect the first connector 3 and the second connector 4.

[0031] A first bolt fixing groove 36 is arranged below the filling ball hole 37, and the first bolt fixing groove 36 can be clamped into the first fixing bolt 35. Two wire retaining ring groove bodies are arranged below the first bolt fixing groove 36, and wire retaining rings are arranged in the wire retaining ring groove bodies, and a limiting groove is formed between the two wire retaining rings.

[0032] When the first fixing bolt 35 is in the first bolt fixing groove 36 and is tightened, the first connecting body 3 and the hose joint assembly 1 are in a locked state. Figure 1 As shown, the locking sleeve 34 contacts the filling steel ball 33 so that the filling steel ball 33 is stuck in the raceway 11, thereby realizing the locked rotational sealing connection between the first connector 3 and the hose joint assembly 1; when the first fixing bolt 35 is loosened, the locking sleeve 34 is pulled downward so that the first fixing bolt 35 is stuck in the limiting groove between the two wire retaining rings. At this time, the filling steel ball 33 is separated from the raceway 11 and stuck in the groove at the upper end of the locking sleeve 34, thereby realizing the unlocking and separation of the first connector 3 and the hose joint assembly 1.

[0033] The filter 2 is 60 mesh. The aircraft refueling specification requires that the filter should not be less than 60 mesh. In the present invention, the filter 2 is set to 60 mesh, which not only meets the requirements of the aircraft refueling specification, but also is smaller than the 100 mesh or 200 mesh of the filter in the aviation pressure refueling joint. Since the oil pumping pressure is relatively low, in order to ensure that the fuel in the aircraft fuel tank is completely drained, a certain flow rate needs to be guaranteed, so the filter 2 is set to 60 mesh, which not only meets the requirements of the specification, but also can maximize the fuel flow rate and intercept fuel impurities.

[0034] like Figure 6 , 7As shown, a visual window 54 is also provided on the pressure regulator 5. Specifically, a threaded hole is provided on the side wall of the pressure regulator 5, a piece of high-pressure resistant glass is placed in the threaded hole, and sealing rings are provided in front and behind the high-pressure resistant glass, and finally fixed with hollow bolts. The visual window 54 is convenient for observing whether there is fuel flowing out of the pressure regulator 5 and the direction of fuel flow, so as to timely discover the mixing of aviation pressure refueling joints and aviation pressure oil extraction joints.

[0035] The joint body assembly 6, protective sleeve 7, protective cover 8 and electrostatic wire assembly 9 of the aviation pressure oil pumping joint are consistent with the existing HJS63A aviation pressure refueling joint produced by Changzhou Lantian Tengfei Aviation Equipment Co., Ltd. The joint body assembly 6 is used to achieve the docking of the aircraft underwing connection seat, control the opening and closing of the refueling (oil pumping) valve, and has a safety interlocking insurance mechanism; the protective sleeve 7 and protective cover 8 play a protective role to prevent the aviation pressure oil pumping joint from being damaged due to accidental falling; the material of the electrostatic wire assembly 9 is stainless steel and brass, and the static electricity generated during the oil pumping process is promptly conducted through the wire to ensure the safety of oil pumping.

[0036] The material of the aircraft oil extraction joint is made completely according to the material of the aircraft refueling joint, LY12 aluminum alloy. Then the material is hard-oxidized (plating is added to increase the hardness of the aluminum alloy). The joint body assembly 6 is connected to the stabilizer 5 by bolts. After the lower end surface of the second connector 4 contacts the first step surface 51 of the stabilizer 5, the second connector 4 is fixedly connected to the stabilizer 5 by bolts, and the first connector 3 is screwed and sleeved in the second connector 4 until the first connector 3 contacts the second step surface 52 of the stabilizer 5, and the second fixing bolt 41 is tightened to fix the first connector 3 and the second connector 4. Then, the end of the hose joint assembly 1 inserted into the filter 2 is inserted into the flange groove 32 formed between the flange 31 and the outer wall of the first connector 3, and the locking sleeve 34 is pushed upward to insert the filling steel ball 33 into the raceway 11 of the hose joint assembly 1, and the first fixing bolt 35 is inserted into the first bolt fixing groove 36 and tightened to fix the hose joint assembly 1 to the first connector 3. The other end of the hose joint assembly 1 is connected to the oil delivery hose, and finally the joint body assembly 6 is docked with the aircraft refueling port to carry out oil pumping operations. At this time, the fuel in the aircraft fuel tank flows into the joint body assembly 6, and after being stabilized by the voltage stabilizer 5, it converges to the area where the first connector 3 and the second connector 4 are connected, and then filtered by the filter 2. The fuel flow rate is stable and flows into the fuel pumping truck through the oil delivery hose.

[0037] The aircraft was pumped oil using the aviation pressure refueling joint and the aviation pressure oil pumping joint of the present invention, 30 times each. The comparison results are shown in the following table:

[0038] Number of times the filter has been damaged Number of times impurities are retained on the filter The pumping flow rate is slow, less than 300 liters per minute Aviation pressure refueling connector 5 12 17 Aviation pressure oil pumping joint 0 0 0

[0039] As can be seen from the above table, the use of this aviation pressure oil pumping joint for oil pumping operations can avoid damage to the filter, the retention of impurities outside the filter, and can ensure the oil pumping flow rate. In summary, the use of this aviation pressure oil pumping joint for oil pumping operations, the voltage stabilizer limits the fuel pressure at the outlet of the aviation pressure oil pumping joint to 0.08Mpa±0.01Mpa, ensuring the stability of the oil pumping pressure; the adjustment of the direction and mesh size of the filter avoids the influence of the shrinkage and deformation of the filter during the oil pumping operation, as well as the safety hazards caused by the retention of impurities outside the filter during the refueling operation, and can meet the requirements of different oil pumping vehicles for the oil pumping flow rate to avoid damage to the aircraft; the second connector and the first connector hose joint assembly are connected in sequence, which is not only convenient for disassembly, but also increases the stability of the connection between each other, while avoiding the retention of fuel in the oil pumping joint, and also reduces damage to the sealing ring, extending the service life of the sealing ring.

[0040] The following conclusions were drawn from the actual trial of the aviation pressure oil pumping joint of the present invention for about two months: the aviation pressure oil pumping joint is firmly connected, there is no leakage during the oil pumping process, the negative pressure of the oil pumping does not exceed 0.08MPA, and the oil pumping filter can filter the oil normally, which fully meets the oil pumping requirements of the airline company, eliminates the safety hazards of the filter being damaged by suction, and pumping oil that does not meet the aircraft oil pumping pressure.

Claims

1. An aviation pressure oil pumping joint, the oil pumping joint comprising a hose joint assembly (1), a pressure regulator (5) and a joint body assembly (6), one end of the pressure regulator (5) being fixedly connected to one end of the joint body assembly (6), and the other end of the joint body assembly (6) being connected to an aircraft oil receiving port, characterized in that: One end of the hose joint assembly (1) is connected to the oil delivery hose, and the other end of the hose joint assembly (1) is clamped with the filter screen (2). The top end of the filter screen (2) faces the end of the hose joint assembly (1) connected to the oil delivery hose, and the end of the hose joint assembly (1) clamped with the filter screen (2) is connected to the voltage stabilizer (5) through a connector. The connector is composed of a first connector (3) and a second connector (4). The second connector (4) is internally sleeved with the first connector (3), and the first connector (3) and the second connector (4) are threadedly connected. The first connector (3) is connected to the first connector (3) and is clamped with the voltage stabilizer (5); the first connector (3) is sleeved with the hose joint assembly (1) to clamp one end of the filter screen (2); and a flange (31) is provided at the contact point between the first connector (3) and the filter screen (2); the clamping point between the voltage stabilizer (5) and the first connector (3) and the second connector (4) is provided with a stepped structure, and the voltage stabilizer (5) and the second connector (4) are fixedly connected; and a voltage stabilizer spring (53) with a supporting pressure of 0.08Mpa±0.01Mpa is provided inside the voltage stabilizer (5); A rotary seal connection structure is provided at a connection point between the first connecting body (3) and the hose joint assembly (1), the rotary seal connection structure comprising a filling steel ball hole (37) and a locking sleeve (34), a filling steel ball (33) being provided in the filling steel ball hole (37), the locking sleeve (34) being connected to the first connecting body (3) via a first fixing bolt (35) and in contact with the filling steel ball (33); a thread is provided at a contact point between the first connecting body (3) and the second connecting body (4); A roller track (11) and a first sealing ring groove (12) are provided at the connection between the hose joint assembly (1) and the first connector (3); a filling steel ball (33) is clamped between the roller track (11) and the first connector (3); and a first sealing ring (10) is provided in the first sealing ring groove (12).

2. The aviation pressure oil pumping joint according to claim 1, characterized in that: The filter (2) is 60 mesh.

3. The aviation pressure oil pumping joint according to claim 1, characterized in that: A visual window (54) is also provided on the voltage stabilizer (5).

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