Split type pipeline stop valve for airplane and fuel system

Abstract

The invention provides a split type pipeline stop valve for an airplane and a fuel system. The split type pipeline stop valve for the airplane comprises an electricity utilization mechanism, a connecting rod assembly and a valve body assembly, the electricity utilization mechanism is connected with the connecting rod assembly through an output shaft, the connecting rod assembly is movably connected with the valve body assembly, and the electricity utilization mechanism is installed on a wing fuel tank and located outside the fuel tank; the connecting rod assembly and the valve body assembly are located in the oil tank. Due to the fact that the electricity utilization mechanism is located outside the oil tank, the electricity utilization mechanism does not need to enter the oil tank to be disassembled and assembled during maintenance, the installation and maintenance cost is reduced, meanwhile, it is not needed to consider that oil enters the electricity utilization mechanism, the risk that the fuel tank is burnt and exploded due to discharging of the electricity utilization mechanism is reduced, and the split type stop valve can achieve the pipeline fluid stop function. The device is simple in structure and stable and reliable in working performance.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation fuel design, and in particular relates to a split pipeline cut-off valve and a fuel system for an aircraft. Background Art

[0002] The widely used pipeline shut-off valve currently installed inside the oil tank can realize the pipeline fluid shut-off function, but because it is designed as an integrated type, it is necessary to enter the oil tank for disassembly and assembly during maintenance. This structure increases the installation and maintenance costs. At the same time, the power mechanism of the shut-off valve is installed as a whole in the oil tank. Not only does the design need to consider preventing oil from entering the power mechanism, but it also needs to prevent the power mechanism from discharging, which poses a safety hazard.

[0003] Therefore, a split pipeline shut-off valve is needed which has a simple mechanical structure, is easy to install and maintain on site, has an electrical mechanism located outside the oil tank, and can realize the pipeline fluid shut-off function. Summary of the invention

[0004] In order to solve the technical problems of high installation and maintenance costs and potential safety hazards of integrated pipeline shut-off valves in related technologies, the present invention provides a split-type pipeline shut-off valve for aircraft, which has a simple structure, stable and reliable working performance, and an electric mechanism located outside the fuel tank, which is convenient for on-site installation and maintenance, reduces installation and maintenance costs, effectively reduces the risk of fuel tank explosion caused by discharge of the electric mechanism, and can realize a split-type shut-off valve with pipeline fluid shut-off function. The technical solution is as follows:

[0005] In a first aspect, a split pipeline shut-off valve for an aircraft is provided, comprising: an electric mechanism, a connecting rod assembly, and a valve body assembly, wherein the electric mechanism is connected to the connecting rod assembly via an output shaft, the connecting rod assembly is movably connected to the valve body assembly, the electric mechanism is mounted on a wing oil tank and is located outside the oil tank; the connecting rod assembly and the valve body assembly are located inside the oil tank.

[0006] Since the power-consuming mechanism is located outside the fuel tank, there is no need to enter the fuel tank for disassembly and assembly during maintenance, which reduces the installation and maintenance costs. At the same time, there is no need to consider the oil entering the power-consuming mechanism, which reduces the risk of the fuel tank exploding due to discharge of the power-consuming mechanism. This is a split shut-off valve that can realize the pipeline fluid cut-off function.

[0007] When the shut-off valve is working, the electric mechanism is energized, and the output shaft connected to the electric mechanism drives the connecting rod assembly to rotate, and the connecting rod assembly drives the valve in the valve body assembly to rotate, closing or opening the fuel passage, thereby realizing the connection and cutoff of the pipeline.

[0008] Among them, the connecting rod assembly includes a first transmission shaft, a second transmission shaft, a fork shaft, a universal joint cross block, a mounting flange, and a bushing. The first transmission shaft is connected to the electric mechanism through an output shaft, the fork shaft is connected to the first transmission shaft through a universal joint cross block, the first transmission shaft is connected to the mounting flange through a bushing, the mounting flange is fixed to the wing beam through fasteners, and the second transmission shaft is connected to the cross-axis universal coupling on the valve body assembly.

[0009] Among them, the valve body assembly includes a spherical valve, a movable sleeve, a cross-axis universal coupling, a valve seat at the inlet end of the ball valve, and a valve seat at the outlet end of the ball valve. The spherical valve is fixed on the movable sleeve, and the valve seat at the inlet end of the ball valve and the valve seat at the outlet end of the ball valve are connected to the movable sleeve through threads. The cross-axis universal coupling is connected to the spherical valve through the movable sleeve, and the cross-axis universal coupling is connected to the second transmission shaft on the connecting rod assembly.

[0010] The aircraft split pipeline shut-off valve further comprises a safety valve located in the fuel tank, and the safety valve is connected to the valve body assembly via threads.

[0011] When the pressure of the fluid in the pipeline increases due to temperature changes, the safety valve opens and releases the pressure at both ends of the cut-off valve into the oil tank.

[0012] When the shut-off valve is working, the electrical mechanism is energized, and the output shaft connected to the electrical mechanism drives the first transmission shaft in the connecting rod assembly to rotate. The first transmission shaft drives the fork shaft and the second transmission shaft to rotate through the universal joint cross block. The second transmission shaft in the connecting rod assembly drives the valve in the valve body assembly to rotate through the cross-axis universal coupling on the valve body assembly, closing or opening the fuel passage, thereby realizing the connection and cutoff of the pipeline.

[0013] Wherein, the power-consuming mechanism is installed on the wing oil tank through fasteners and is located outside the oil tank.

[0014] Wherein, the safety valve is threadedly connected to the valve body assembly.

[0015] In a second aspect, a fuel system is provided, comprising a split pipeline shut-off valve for an aircraft as described in any one of the first aspects.

[0016] The beneficial effects of the present invention are at least:

[0017] The split-type pipeline shut-off valve for aircraft includes: an electric mechanism, a connecting rod assembly, and a valve body assembly. The electric mechanism is connected to the connecting rod assembly through an output shaft, and the connecting rod assembly is movably connected to the valve body assembly. The electric mechanism is installed on the wing fuel tank and is located outside the fuel tank; the connecting rod assembly and the valve body assembly are located inside the fuel tank. Since the electric mechanism is located outside the fuel tank, there is no need to enter the fuel tank for disassembly and assembly during maintenance, which reduces the installation and maintenance costs. At the same time, there is no need to consider the oil entering the electric mechanism, which reduces the risk of the fuel tank exploding due to discharge of the electric mechanism. The split shut-off valve can realize the pipeline fluid shut-off function. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the cut-off valve structure;

[0019] Figure 2 is a schematic diagram of the connecting rod assembly structure;

[0020] Figure 3 It is a schematic diagram of the structure of the valve body assembly;

[0021] Among them: power mechanism 1, connecting rod assembly 2, valve body assembly 3, safety valve 4, bolt 5, transmission shaft 21, transmission shaft 22, fork shaft 23, universal joint cross block 24, mounting flange assembly 25, sleeve 26, ball valve 31, movable sleeve 32, cross-axis universal coupling 33, ball valve inlet end valve seat 34, ball valve outlet end valve seat 35. DETAILED DESCRIPTION

[0022] The present invention is further described in detail below through specific implementation modes and drawings.

[0023] The present invention provides a split type pipeline cut-off valve for aircraft, see Figure 1 , including: an electric mechanism 1, a connecting rod assembly 2, and a valve body assembly 3;

[0024] The connecting rod assembly 2 is connected to the valve body assembly 3 through a movable sleeve. The transmission shaft in the connecting rod assembly 2 rotates, driving the valve in the valve body assembly 3 to rotate, thereby closing or opening the fuel passage.

[0025] The power-consuming mechanism 1 is connected to the connecting rod assembly 2 via an output shaft. When the power-consuming mechanism 1 is energized, the output shaft of the power-consuming mechanism 1 drives the transmission shaft in the connecting rod assembly 2 to rotate.

[0026] The electric mechanism 1 is mounted on the wing oil tank by means of bolts 5 and is located outside the oil tank, so it can be disassembled and maintained separately without entering the oil tank.

[0027] The safety valve 4 is connected to the valve body assembly 3 through threads. When the pressure of the fluid in the pipeline increases due to temperature changes, the safety valve opens to release the pressure at both ends of the cut-off valve into the oil tank.

[0028] When the shut-off valve of the present invention is actually working, the electric mechanism 1 is energized, and the output shaft of the electric mechanism 1 drives the transmission shaft in the connecting rod assembly 2 to rotate, driving the valve in the valve body assembly 3 to rotate, closing or opening the fuel passage, thereby realizing the connection and cut-off functions of the pipeline. The fluid in the pipeline causes the pressure to increase due to temperature changes, and the safety valve 4 opens to release the pressure at both ends of the shut-off valve into the fuel tank.

[0029] In one embodiment, if Figure 2 As shown, the connecting rod assembly 2 includes a first transmission shaft 21, a second transmission shaft 22, a fork shaft 23, a universal joint cross block 24, a mounting flange 25, and a shaft sleeve 26;

[0030] The first transmission shaft 21 is connected to the electrical mechanism 1 through the output shaft. When the electrical mechanism 1 is energized, the output shaft of the electrical mechanism 1 drives the first transmission shaft 21, the fork shaft 23, and the second transmission shaft 22 to rotate together, driving the valve in the valve body assembly 3 to rotate, closing or opening the fuel passage, thereby realizing the connection and cutoff functions of the pipeline.

[0031] In one embodiment, see Figure 3 The valve body assembly 3 includes a spherical valve 31, a movable sleeve 32, a cross-axis universal coupling 33, a valve seat 34 at the inlet end of the ball valve, and a valve seat 35 at the outlet end of the ball valve;

[0032] The cross-axis universal coupling 33 is connected to the second transmission shaft 22 on the connecting rod assembly 2. The second transmission shaft 22 in the connecting rod assembly 2 is driven to rotate through the output shaft of the electric mechanism 1. The second transmission shaft 22 in the connecting rod assembly 2 rotates the valve in the valve body assembly 3 through the cross-axis universal coupling 33 to close or open the fuel passage, thereby realizing the connection and cutoff functions of the pipeline.

[0033] Another embodiment of the present invention further provides a fuel system, including the split pipeline cut-off valve for aircraft provided in the embodiment of the present invention.

[0034] The present invention provides a split-type pipeline shut-off valve for aircraft, which can realize the function of pipeline shut-off. The shut-off valve has a simple and effective mechanical structure and stable and reliable working performance. Compared with the integrated shut-off valve, the split-type shut-off valve has an electric mechanism located outside the fuel tank, which is convenient for on-site maintenance. It only needs to remove the electric mechanism, and there is no need to empty the fuel in the fuel tank and enter the fuel tank for maintenance, thus reducing maintenance costs. At the same time, the electric mechanism of the split-type shut-off valve is located outside the fuel tank, which effectively reduces the risk of the fuel tank exploding due to discharge of the electric mechanism.

[0035] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A split type pipeline cut-off valve for aircraft, characterized in that: include: An electric mechanism, a connecting rod assembly, and a valve body assembly, wherein the electric mechanism is connected to the connecting rod assembly via an output shaft, the connecting rod assembly is movably connected to the valve body assembly, the electric mechanism is installed on the wing oil tank and is located outside the oil tank; the connecting rod assembly and the valve body assembly are located inside the oil tank.

2. The split-type pipeline cut-off valve for aircraft according to claim 1, characterized in that: When the shut-off valve is working, the electric mechanism is energized, and the output shaft connected to the electric mechanism drives the connecting rod assembly to rotate. The connecting rod assembly drives the valve in the valve body assembly to rotate, closing or opening the fuel passage, thereby achieving the connection and cutoff of the pipeline.

3. The aircraft split pipeline cut-off valve according to claim 2, characterized in that: The connecting rod assembly includes a first transmission shaft, a second transmission shaft, a fork shaft, a universal joint cross block, a mounting flange, and a bushing. The first transmission shaft is connected to the electric mechanism through an output shaft, the fork shaft is connected to the first transmission shaft through a universal joint cross block, the first transmission shaft is connected to the mounting flange through a bushing, the mounting flange is fixed to the wing beam through fasteners, and the second transmission shaft is connected to the cross-axis universal coupling on the valve body assembly.

4. The aircraft split-type pipeline cut-off valve according to claim 3, characterized in that: The valve body assembly includes a spherical valve, a movable sleeve, a cross-axis universal coupling, a valve seat at the inlet end of the ball valve, and a valve seat at the outlet end of the ball valve. The spherical valve is fixed on the movable sleeve, and the valve seat at the inlet end of the ball valve and the valve seat at the outlet end of the ball valve are connected to the movable sleeve through threads. The cross-axis universal coupling is connected to the spherical valve through the movable sleeve, and the cross-axis universal coupling is connected to the second transmission shaft on the connecting rod assembly.

5. The aircraft split pipeline cut-off valve according to claim 4, characterized in that: The split-type pipeline cut-off valve for aircraft further comprises a safety valve located in the oil tank, and the safety valve is connected to the valve body assembly through threads.

6. The aircraft split pipeline cut-off valve according to claim 4, characterized in that: When the shut-off valve is working, the electric mechanism is energized, and the output shaft connected to the electric mechanism drives the first transmission shaft in the connecting rod assembly to rotate. The first transmission shaft drives the fork shaft and the second transmission shaft to rotate through the universal joint cross block. The second transmission shaft in the connecting rod assembly drives the valve in the valve body assembly to rotate through the cross-axis universal coupling on the valve body assembly, closing or opening the fuel passage, thereby realizing the connection and cutoff of the pipeline.

7. The aircraft split-type pipeline cut-off valve according to claim 1, characterized in that: The power-consuming mechanism is mounted on the wing oil tank through fasteners and is located outside the oil tank.

8. The aircraft split-type pipeline cut-off valve according to claim 5, characterized in that: The safety valve is threadedly connected to the valve body assembly.

9. A fuel system, characterized in that: It comprises the split pipeline cut-off valve for aircraft as described in any one of claims 1 to 8.

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