High maneuverability aircraft fuel tank, fuel supply system and fuel supply method

Abstract

The present invention discloses a high-maneuverability aircraft fuel tank, a fuel supply system, and a fuel supply method, which belong to the technical field of aircraft fuel supply. The high-maneuverability aircraft fuel tank includes an outer shell, the interior of which is provided with a partition plate, which divides the interior of the outer shell into an independent central electrical chamber and oil chambers on both sides. An oil sac is provided in the oil chamber, and the two ends of the oil sac are respectively fixed to the front end plate and the rear end plate at the two ends of the oil chamber. A multi-porous oil extraction pipe is provided in the oil sac, and the two ends of the multi-porous oil extraction pipe are respectively fixed to the front end plate and the rear end plate. The multi-porous oil extraction pipe is an anti-flattening hose, and the multi-porous oil extraction pipe is immersed in the fuel. The high-maneuverability aircraft fuel tank, fuel supply system, and fuel supply method described in the present invention can solve the problems of unstable fuel supply flow and low space utilization in the existing fuel supply; it has the advantages of simple structure and light weight.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuel supply, and in particular to a fuel tank, a fuel supply system and a fuel supply method for a high-maneuverability aircraft. Background Art

[0002] Hypersonic vehicles, with their high speed, maneuverability, and precision, are impervious to interception by existing missile defense systems. They can carry out long-range, precision strikes against high-value targets on land and at sea, representing an advanced asymmetric strike method. However, this high maneuverability presents significant challenges to the design of fuel supply systems.

[0003] The main function of the fuel supply system is to provide a steady supply of fuel to the engine. Based on the operating environment of a highly maneuverable aircraft, the fuel supply system has the following requirements:

[0004] 1. Ensure the required flow rate and minimum pressure during engine startup and aircraft maneuvering, and ensure stable flow rate;

[0005] 2. Maintain the internal pressure bearing requirements of thin-walled fuel tanks to ensure sufficient structural strength and rigidity;

[0006] 3. The main body of the tank should meet the lightweight requirements;

[0007] 4. Provide supply system filling, draining and pressurizing devices.

[0008] The common aircraft fuel supply system uses a rubber bladder type liquid supply device, which has the following shortcomings:

[0009] 1. The system's fuel filling method involves adding fuel to the rubber bladder through the outlet pipe, allowing the air in the bladder to escape through the vent pipe above. This method of fuel filling is not easy to completely expel the air in the bladder, resulting in large fluctuations in the fuel supply flow.

[0010] 2. The outlet pipe is a hard pipe. When the liquid level is lower than a certain distance from the outlet pipe, due to the contraction of the rubber bag, the liquid below needs to pass through the slit formed by the rubber bag to enter the outlet pipe. The resistance to flow in the slit is large, which will cause a significant decrease in flow rate.

[0011] 3. The outlet pipe is too short. When the aircraft maneuvers and the fuel is concentrated on the left end of the rubber bag, if the amount of fuel is too small to submerge the outlet pipe, a narrow gap will form between the main fuel body and the outlet pipe, increasing the resistance and causing a significant decrease in flow rate.

[0012] 4. The storage tank is a pressure container. Usually the storage tank is designed as a rotating body. In some specific cases, the space utilization rate is not high, and the common rectangular cross-section pressure container is difficult to meet the requirements of lightweight.

[0013] Therefore, it is urgent to develop a fuel supply system that can provide aircraft with continuous and stable fuel. Summary of the Invention

[0014] The purpose of the present invention is to provide a high-maneuverability aircraft fuel tank, a fuel supply system and a fuel supply method to solve the problems of unstable fuel supply flow and low space utilization in the existing fuel supply.

[0015] To achieve the above-mentioned objectives, the present invention provides a high-maneuverability aircraft fuel tank, comprising an outer shell, wherein a partition is provided inside the outer shell, the partition divides the interior of the outer shell into an independent electrical cavity in the middle and oil cavities on both sides, an oil sac is provided in the oil cavity, and the two ends of the oil sac are respectively fixed to the front end plate and the rear end plate at the two ends of the oil cavity, a multi-porous oil extraction pipe is provided inside the oil sac, and the two ends of the multi-porous oil extraction pipe are respectively fixed to the front end plate and the rear end plate, the multi-porous oil extraction pipe is an anti-flattening hose, and the multi-porous oil extraction pipe is immersed in fuel.

[0016] Preferably, a fixed joint is provided in the middle of the front end plate, an outlet joint is provided in the middle of the rear end plate, and both ends of the oil bag and the porous oil extraction pipe are fixed on the fixed joint and the outlet joint respectively.

[0017] Preferably, a temperature sensor for monitoring the oil temperature in the oil sac is provided on the rear end plate, and the temperature sensor is located inside the oil sac.

[0018] Preferably, the length of the porous oil extraction pipe is greater than the length of the oil chamber, and the density of the porous oil extraction pipe is 1.01-1.5 times the density of the fuel; the porous oil extraction pipe is a PVC steel wire hose.

[0019] Preferably, the partition includes a bow plate and a chord plate, the bow plate is aligned and connected with the chord plate, the bow plate is located in the oil cavity, the cross section of the oil cavity is a rectangular structure, and the cross section of the shell is a rectangular structure.

[0020] A fuel supply system includes the above-mentioned high-maneuverability aircraft fuel tank, a boosting unit, a filling unit and a discharge unit. The boosting unit is used to pass gas between the outer shell and the oil bladder for boosting the pressure. The filling unit is connected to one end of the multi-porous oil extraction pipe and is used to inject fuel into the oil bladder. The discharge unit is connected to one end of the multi-porous oil extraction pipe and is used to provide fuel to the combustion chamber or the wall cooling system pipeline.

[0021] Preferably, the boosting unit includes a high-pressure gas cylinder, which is connected to the outer shell through a connecting pipe. A gate valve, a first-level pressure reducing valve, a second-level pressure reducing valve and an electric explosion valve are sequentially arranged on the connecting pipe from the high-pressure gas cylinder to the outer shell; the boosting unit is used to provide an extrusion pressure of 0.05MPa-0.2MPa for the oil bag.

[0022] Preferably, the filling unit includes a vent pipe, which is arranged on the outer shell, the air inlet end of the vent pipe is located between the outer shell and the oil bag, an exhaust valve is provided on the vent pipe, the oil inlet end of the multi-porous oil pipe is connected to the oil barrel or vacuum pump through a filling pipe, and a fuel filling valve is provided on the filling pipe.

[0023] Preferably, the discharge adding unit includes a discharge adding main pipe and a discharge adding branch pipe, the discharge adding branch pipe is connected to the porous oil extraction pipe through the discharge adding main pipe, the discharge adding main pipe is provided with a filter, a discharge adding valve and a first pressure sensor, and the discharge adding branch pipe is provided with a fuel pump, a second pressure sensor and a diaphragm valve.

[0024] The fuel supply method based on the above fuel supply system includes the following steps:

[0025] S1. Fill the bladder with oil, open the exhaust valve and fuel filling valve, and close the exhaust valve. Connect the fuel filling valve to a vacuum pump to evacuate all air from the bladder and piping. Then disconnect the fuel filling valve from the vacuum pump and connect it to a fuel drum. Fill the bladder with fuel through the fuel filling valve, filling pipe, and multi-hole oil pipe. The air between the bladder and the casing is discharged from the casing through the vent pipe and exhaust valve.

[0026] S2. When draining oil, the gate valve and electric explosion valve on the high-pressure gas cylinder are opened, and the exhaust valve and fuel filling valve are closed; the high-pressure gas enters the shell after passing through the first-stage pressure reducing valve and the second-stage pressure reducing valve, providing squeezing force for the oil bag;

[0027] S3. Open the fuel pump and the filling and discharging valve. The fuel in the oil bag enters the filling and discharging main pipe through the porous oil intake pipe under the extrusion pressure. After being filtered by the filter, it is sent to the combustion chamber or the wall cooling system pipeline by the fuel pump through the diaphragm valve.

[0028] The advantages and positive effects of the high-maneuverability aircraft fuel tank, fuel supply system, and fuel supply method described in this invention include: By providing a multi-hole fuel pipe and controlling its length, density, and properties, a stable fuel flow rate can be provided to the aircraft. The structural arrangement of the booster unit and refueling unit also enhances the stability of the fuel supply. The lightweight design of the fuel tank simplifies the structure, improves the tank's integration, and facilitates improved space utilization.

[0029] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a schematic diagram of the three-dimensional structure of the fuel tank according to an embodiment of the present invention;

[0031] Figure 2 This is a schematic diagram of the cross-sectional structure of a fuel tank according to an embodiment of the present invention;

[0032] Figure 3 This is a schematic diagram of the longitudinal cross-section structure of a fuel tank according to an embodiment of the present invention;

[0033] Figure 4 This is a schematic diagram of the internal side structure of a fuel tank according to an embodiment of the present invention;

[0034] Figure 5 Schematic diagram of the partition structure of an embodiment of the present invention;

[0035] Figure 6 This is a schematic diagram of the oil chamber force analysis structure according to an embodiment of the present invention;

[0036] Figure 7 This is a schematic diagram of the stress analysis structure of the partition according to an embodiment of the present invention;

[0037] Figure 8 Schematic diagram of the fuel supply system according to an embodiment of the present invention.

[0038] Reference numerals

[0039] 1. High-pressure gas cylinder; 2. Gate valve; 3. First-stage pressure reducing valve; 4. Second-stage pressure reducing valve; 5. Electric explosion valve; 6. Fuel tank; 7. Oil bag; 8. Multi-hole oil extraction pipe; 9. Vent pipe; 10. Cover; 11. Exhaust valve; 12. Fuel filling valve; 13. Filter; 14. Filling and discharging valve; 15. First pressure sensor; 16. Fuel pump; 17. Second pressure sensor; 18. Diaphragm valve; 19. Temperature sensor; 61. Housing; 62. Partition; 63. Electrical chamber; 64. Oil chamber; 65. Front end plate; 66. Rear end plate; 67. Flange; 68. Fixed joint; 69. Outlet joint; 610. Bow plate; 611. String plate. DETAILED DESCRIPTION

[0040] In the description of the present invention, it should be noted that the terms "upper", "lower", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or the orientations or positional relationships in which the inventive product is usually placed when in use. These are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limitations on the present invention. In the description of the present invention, it should also be noted that, unless otherwise expressly specified and limited, the terms "setting", "installation" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be a communication between the internal parts of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0041] In this application, unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which this application belongs. In the event of any inconsistency, the meaning described in this specification or the meaning derived from the contents recorded in this specification shall prevail. In addition, the terms used herein are only for the purpose of describing the embodiments of this application and are not intended to limit this application. In order to accurately describe the technical content in this application and to accurately understand the present invention, the following explanations or definitions are given for the terms used in this specification before describing the specific embodiments:

[0042] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0043] like Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 As shown. A high-maneuverability aircraft fuel tank includes an outer shell 61, and a partition 62 is provided inside the outer shell 61. Two partitions 62 are symmetrically arranged inside the outer shell 61. The partition 62 is fixedly connected to the outer shell 61 by welding. The partition 62 divides the interior of the outer shell 61 into an independent electrical chamber 63 in the middle and oil chambers 64 on both sides. The electrical chamber is used to arrange cables, engine isolation sections and engine combustion chambers, oil pipelines, and high-pressure gas cylinders 1 and their gas pipelines. Integrating the combustion chamber with the fuel tank 6 improves the compactness of the fuel tank 6 structure. An oil bladder 7 is provided in the oil chamber 64, and the two ends of the oil bladder 7 are respectively fixed to the front end plate 65 and the rear end plate 66 at the two ends of the oil chamber 64. A multi-porous oil extraction pipe 8 is provided inside the oil bladder 7, and the two ends of the multi-porous oil extraction pipe 8 are respectively fixed to the front end plate 65 and the rear end plate 66. The multi-porous oil extraction pipe 8 is used to inject fuel into the oil bladder 7 or discharge fuel from the oil bladder 7.

[0044] A fixed joint 68 is provided in the middle of the front end plate 65, and an outlet joint 69 is provided in the middle of the rear end plate 66. Both ends of the oil bag 7 and the porous oil pipe 8 are fixed on the fixed joint 68 and the outlet joint 69 respectively.

[0045] Flanges 67 are provided on both the upper and lower surfaces of the housing 61. These flanges 67 are used to seal access openings provided on the housing 61. Rubber gaskets seal the flanges 67 and the access openings. The access openings facilitate installation and maintenance of the internal pipelines and combustion chamber of the housing 61. Flanges 67, fixing joints 68, outlet joints 69, front plate 65, and rear plate 66 are all secured to the housing 61 by screws or welding. A tight seal must be maintained between the front plate 65 and rear plate 66 and the housing 61 to prevent leakage of gas from within the housing 61.

[0046] The multi-porous fuel line 8 is a crush-resistant hose. In this embodiment, it is a PVC steel hose, which prevents it from being crushed and ensures smooth fuel supply. The length of the multi-porous fuel line 8 is greater than the length of the oil chamber 64, allowing it to be distributed axially along the oil chamber 64, which helps reduce the residual fuel in the oil chamber 64. During aircraft maneuvers, the multi-porous fuel line 8 is always perpendicular to the combined force of inertia and gravity, ensuring that it remains submerged in the fuel, effectively preventing the problem of a sharp drop in flow due to narrow flow. Furthermore, when the aircraft accelerates or decelerates, the hose converges toward the end due to inertia. Without a crush-resistant device, the hose could bend, significantly increasing fluid resistance. Using a PVC steel hose or other hose with a built-in crush-resistant device can effectively prevent this. The density of the porous fuel pipe 8 is 1.01-1.5 times that of the fuel. The density of the porous fuel pipe 8 is slightly greater than that of the fuel. This ensures that, during normal operation, the weight acting on the porous fuel pipe 8 is greater than its buoyancy, causing it to sag downward. Furthermore, because the density of the porous fuel pipe 8 is close to that of the fuel, the porous fuel pipe 8 has better fuel tracking performance during maneuvering flight, closely following the direction of fuel concentration and thereby ensuring that the porous fuel pipe 8 remains submerged in the fuel.

[0047] A temperature sensor 19 for monitoring the oil temperature in the oil bladder 7 is provided on the rear end plate 66 . The temperature sensor 19 is located inside the oil bladder 7 . The temperature sensor 19 is mounted on the outlet connector 69 .

[0048] like Figure 5 As shown, the partition 62 comprises a bow plate 610 and a chord plate 611. Bow plate 610 is a curved plate, while chord plate 611 is a flat plate. The edges of bow plate 610 and chord plate 611 are aligned and securely connected by welding. Bow plate 610 is located within the oil chamber 64. Both the housing 61 and the oil chamber 64 have rectangular cross-sections. For pressure vessels with rectangular cross-sections, the use of a "bow" cross-section plate can effectively save space compared to the common rib-flat plate structure; compared to a simple flat plate structure, the use of a "bow" cross-section plate can effectively reduce weight.

[0049] like Figure 6 、 Figure 7 As shown in the figure, air pressure P acts directly on the bow plate 610. This force is converted by the unique structure of the bow plate 610 into a vertical tension on the chord plate 611 and a horizontal tension on the housing 61. F1 is the horizontal tension exerted by the housing 61 on the partition 62, and F2 is the vertical tension exerted by the housing 61 on the partition 62. The structure of the partition 62 helps reduce the horizontal force exerted on the partition 62, thereby improving its stability and service life.

[0050] like Figure 8A fuel supply system includes a fuel tank 6, a pressurizing unit, a filling unit, and a draining unit. The pressurizing unit is used to introduce gas between the housing 61 and the oil bladder 7, squeezing the oil bladder 7. The filling unit is connected to one end of a multi-porous oil extraction pipe 8 and is used to inject fuel into the oil bladder 7. The draining unit is also connected to one end of the multi-porous oil extraction pipe 8 and is used to supply fuel to the combustion chamber or the wall cooling system pipeline.

[0051] The booster unit includes a high-pressure gas cylinder 1, which is connected to the housing 61 via a connecting pipe. The connecting pipe is provided with a gate valve 2, a first-stage pressure-reducing valve 3, a second-stage pressure-reducing valve 4, and an electric explosion valve 5 in the direction from the high-pressure gas cylinder 1 to the housing 61. The booster unit is used to provide an extrusion pressure of 0.05MPa-0.2MPa to the oil bag 7, preferably 0.1MPa.

[0052] The refueling unit includes a vent pipe 9 mounted on the outer shell 61. The inlet end of the vent pipe 9 is located between the outer shell 61 and the fuel bladder 7. This pipe is used to expel gas from the outer shell 61, facilitating fuel filling into the fuel bladder 7. A vent valve 11 is installed on the vent pipe 9. The inlet end of the multi-hole fuel pipe 8 is connected to an oil drum or vacuum pump via a refueling pipe. A fuel refueling valve 12 is installed on the refueling pipe. A protective cover 10 surrounds the refueling valve 12 and the exhaust valve 11.

[0053] The fuel supply and discharge unit consists of a main fuel supply and discharge pipe and several branch fuel supply and discharge pipes, which are arranged in parallel. The branch fuel supply and discharge pipes are connected to the multi-hole fuel supply pipe 8 through the main fuel supply and discharge pipe. The main fuel supply and discharge pipe is equipped with a filter 13, a fuel supply and discharge valve 14, and a first pressure sensor 15. The branch fuel supply and discharge pipes are also equipped with a fuel pump 16, a second pressure sensor 17, and a diaphragm valve 18. When the fuel pump 16 is not started, the diaphragm valve 18 is closed. When the fuel pump 16 is started, the pressure rises, and the diaphragm valve 18 opens.

[0054] The fuel supply method based on the above fuel supply system includes the following steps:

[0055] S1. Fill the oil bladder 7 with oil. Open the exhaust valve 11 and fuel filling valve 12, and close the fill-and-discharge valve 14. Connect the fuel filling valve 12 to a vacuum pump to evacuate all air from the oil bladder 7 and the pipeline. Then disconnect the fuel filling valve 12 from the vacuum pump and connect it to a fuel drum. Fuel is then added to the oil bladder 7 via the fuel filling valve 12, the filling pipe, and the multi-hole oil pipe 8. The air between the oil bladder 7 and the housing 61 is discharged from the housing 61 through the vent pipe 9 and the exhaust valve 11. After refueling is complete, close the exhaust valve 11 and fuel filling valve 12.

[0056] S2. During oil discharge, the gate valve 2 and electric explosion valve 5 on the high-pressure gas cylinder 1 are opened, and the exhaust valve 11 and fuel filling valve 12 are closed. The high-pressure gas enters the housing 61 after passing through the first-stage pressure reducing valve 3 and the second-stage pressure reducing valve 4, providing a squeezing pressure of 0.1 MPa to the oil bladder 7, facilitating the discharge of the fuel in the oil bladder 7 through the porous oil extraction pipe 8.

[0057] S3. Turn on the fuel pump 16 and the add / discharge valve 14. The fuel in the oil bag 7 enters the add / discharge main pipe through the porous oil intake pipe 8 under the extrusion pressure. After being filtered by the filter 13, it is sent by the fuel pump 16 through the diaphragm valve 18 to the combustion chamber or the wall cooling system pipeline.

[0058] Therefore, the use of the high-maneuverability aircraft fuel tank, fuel supply system and fuel supply method described in the present invention can solve the problems of unstable fuel supply flow and low space utilization in the existing industry; and has the advantages of simple structure and light weight.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit the same. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solutions of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A high maneuverability aircraft fuel tank, characterized by: The housing comprises a partition plate disposed inside the housing, the partition plate dividing the interior of the housing into an independent electrical chamber in the middle and oil chambers on both sides, an oil sac disposed in the oil chamber, the ends of the oil sac being fixed to the front end plate and the rear end plate at both ends of the oil chamber, a multi-porous oil extraction pipe disposed inside the oil sac, the ends of the multi-porous oil extraction pipe being fixed to the front end plate and the rear end plate, the multi-porous oil extraction pipe being a crush-proof hose, and the multi-porous oil extraction pipe being immersed in the fuel; The electrical cavity is used to arrange cables, engine isolation sections and engine combustion chambers, oil pipelines, high-pressure gas cylinders and their gas pipelines, integrating the combustion chamber with the fuel tank to improve the compactness of the fuel tank structure.

2. A high maneuverability aircraft fuel tank according to claim 1, characterized in that: A fixed joint is provided in the middle of the front end plate, an outlet joint is provided in the middle of the rear end plate, and both ends of the oil bag and the porous oil extraction pipe are fixed on the fixed joint and the outlet joint respectively.

3. The high maneuverability aircraft fuel tank according to claim 1, characterized in that: A temperature sensor for monitoring the oil temperature in the oil bag is provided on the rear end plate, and the temperature sensor is located inside the oil bag.

4. The high maneuverability aircraft fuel tank according to claim 1, characterized in that: The length of the porous oil extraction pipe is greater than the length of the oil cavity, and the density of the porous oil extraction pipe is 1.01-1.5 times the density of the fuel; the porous oil extraction pipe is a PVC steel wire hose.

5. The high maneuverability aircraft fuel tank according to claim 1, characterized in that: The partition includes a bow plate and a chord plate, the bow plate is aligned with the chord plate and connected, the bow plate is located in the oil cavity, the cross section of the oil cavity is a rectangular structure, and the cross section of the shell is a rectangular structure.

6. A fuel supply system, characterized in that: It comprises the high-maneuverability aircraft fuel tank, the boosting unit, the filling unit and the draining unit as described in any one of claims 1 to 5, the boosting unit being used to pass gas between the outer shell and the oil bladder for pressurization, the filling unit being connected to one end of the multi-porous oil extraction pipe, the filling unit being used to inject fuel into the oil bladder, the draining unit being connected to one end of the multi-porous oil extraction pipe, and the draining unit being used to provide fuel to the combustion chamber or the wall cooling system pipeline.

7. A fuel supply system according to claim 6, characterized in that: The boosting unit includes a high-pressure gas cylinder, which is connected to the outer shell through a connecting pipe. A gate valve, a first-level pressure reducing valve, a second-level pressure reducing valve and an electric explosion valve are arranged on the connecting pipe in sequence from the high-pressure gas cylinder to the outer shell; the boosting unit is used to provide an extrusion pressure of 0.05MPa-0.2MPa for the oil bag.

8. A fuel supply system according to claim 6, characterized in that: The filling unit includes a vent pipe, which is arranged on the shell. The air inlet end of the vent pipe is located between the shell and the oil bag. An exhaust valve is provided on the vent pipe. The oil inlet end of the multi-porous oil pipe is connected to the oil barrel or vacuum pump through a filling pipe, and a fuel filling valve is provided on the filling pipe.

9. A fuel supply system according to claim 6, characterized in that: The addition and discharge unit includes a main addition and discharge pipe and a branch addition and discharge pipe. The branch addition and discharge pipe is connected to the porous oil extraction pipe through the main addition and discharge pipe. The main addition and discharge pipe is provided with a filter, a addition and discharge valve and a first pressure sensor. The branch addition and discharge pipe is provided with a fuel pump, a second pressure sensor and a diaphragm valve.

10. A fuel supply method based on the fuel supply system according to any one of claims 6 to 9, characterized in that: The following steps are involved: S1. Fill the bladder with oil, open the exhaust valve and fuel filling valve, and close the exhaust valve. Connect the fuel filling valve to a vacuum pump to evacuate all air from the bladder and piping. Then disconnect the fuel filling valve from the vacuum pump and connect it to a fuel drum. Fill the bladder with fuel through the fuel filling valve, filling pipe, and multi-hole oil pipe. The air between the bladder and the casing is discharged from the casing through the vent pipe and exhaust valve. S2. When draining oil, the gate valve and electric explosion valve on the high-pressure gas cylinder are opened, and the exhaust valve and fuel filling valve are closed; the high-pressure gas enters the shell after passing through the first-stage pressure reducing valve and the second-stage pressure reducing valve, providing squeezing force for the oil bag; S3. Open the fuel pump and the filling and discharging valve. The fuel in the oil bag enters the filling and discharging main pipe through the porous oil intake pipe under the extrusion pressure. After being filtered by the filter, it is sent to the combustion chamber or the wall cooling system pipeline by the fuel pump through the diaphragm valve.

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