Aviation fuel control system and method of controlling the same

Abstract

The present application relates to aviation fuel control technical field, specifically, it is a kind of aviation fuel control system and control method thereof;Including fuel circulation system and electrical measurement and control system, electrical measurement and control system is used to control the temperature, flow and pressure of circulating fuel in fuel circulation system;Fuel circulation system includes first regulating valve group, explosion-proof electric heater group, heat preservation assembly, pump group, second regulating valve group and temperature measuring assembly, product export is sequentially connected first regulating valve group, explosion-proof electric heater group, heat preservation assembly and pump group between product import, and product import and product export end are equipped with temperature measuring assembly;The pipeline connected between first regulating valve group, explosion-proof electric heater group and the pipeline connected between pump group, product import are communicated, and the pipeline of this communication is connected second regulating valve group;The present application can control the temperature, pressure and flow of fuel into the product under test, help to improve the stable fuel condition for the combustion test of product, improve the accuracy of combustion test.

Description

Technical Field

[0001] This invention relates to the field of aviation fuel control technology, and more specifically, to an aviation fuel control system and its control method. Background Technology

[0002] According to the "CCAR-25-R4 Airworthiness Standards for Transport Category Aircraft" issued by the Ministry of Transport, the fuel temperature must be at least 43°C when the fuel system is operating in hot weather conditions. The fuel tank test specifies that the fuel tank can withstand an internal pressure of at least 24.2 kPa. From the above standards, it can be seen that the conduits, joints and accessories for transporting flammable liquids in aviation fuel tanks and engines must undergo fire resistance tests. However, there are many types of products that are tested, and the requirements for the temperature, pressure and flow rate of imported fuel are different for each product.

[0003] Currently, the lubricating oil used in fire resistance tests of aviation combustion system products is generally drawn from the fuel tank using an external fuel supply pump. After being heated to the test temperature, the lubricating oil can enter the test specimen. The test specimen undergoes a fire resistance test under specified operating conditions. The lubricating oil that has passed through the test specimen can be pumped back to the fuel tank for circulation. In current lubricating oil circulation systems, pressure regulating valves are installed on the fuel supply outlet pipeline to regulate the fuel supply outlet pressure, and flow regulating valves are also set up to regulate the oil volume. Through iterations of aviation fuel circulation systems, lubricating oil circulation systems usually have functions of temperature control, pressure control, or flow control. However, aviation fuel circulation systems with large flow ranges and pressure thresholds, and which can accurately control temperature, have not yet been disclosed. Furthermore, current technologies only focus on improving the control of single conditions such as temperature, flow, and pressure, and have not disclosed solutions for maintaining the stability of aviation lubricating oil during the improvement process.

[0004] Therefore, there is an urgent need to provide an aviation fuel control system and its control method that can achieve stable circulating heating of fuel under high pressure, high temperature and high flow rate compared with the existing technology. Summary of the Invention

[0005] To address the aforementioned problems, this invention provides an aviation fuel control system and its control method.

[0006] To achieve the above objectives, the technical solution of the present invention is as follows:

[0007] An aviation fuel control system includes a fuel circulation system and an electrical measurement and control system. The electrical measurement and control system is used to control the temperature, flow rate, and pressure of the circulating fuel in the fuel circulation system. The fuel circulation system is connected to the product to perform fuel circulation.

[0008] The fuel circulation system includes a first regulating valve group, an explosion-proof electric heater group, a heat insulation component, a pump group, a second regulating valve group, and a temperature measuring component. The first regulating valve group, the explosion-proof electric heater group, the heat insulation component, and the pump group are connected in series from the product outlet to the product inlet. The temperature measuring component is provided at both the product inlet and the product outlet.

[0009] The pipe connecting the first regulating valve group and the explosion-proof electric heater group is connected to the pipe connecting the pump group and the product inlet, and the second regulating valve group is connected in series on the connected pipe.

[0010] Furthermore, a cooling component is connected in series between the explosion-proof electric heater group and the first regulating valve group, and the electrical measurement and control system controls whether the fuel at the product outlet is cooled by passing through the cooling component.

[0011] Furthermore, a first ball valve assembly is connected in series between the first regulating valve assembly and the cooling component. The first ball valve assembly is also equipped with a flow meter. The electrical measurement and control system controls the first ball valve assembly to regulate the flow of the fuel circulation system.

[0012] Furthermore, a first filter assembly is provided between the pump assembly and the product inlet.

[0013] Furthermore, the insulation component includes a fuel tank and several valves. The fuel tank is equipped with valves at both the fuel input end and the fuel output end. A pipeline with valves connected in series is connected in parallel to the pipeline connecting the fuel tank and the two valves.

[0014] The electrical measurement and control system controls the valves inside the insulation component to ensure that fuel circulates through the fuel tank when the fuel quantity is greater than a threshold and does not circulate through the fuel tank when the fuel quantity is less than the threshold.

[0015] Furthermore, the fuel tank includes an outer layer and an inner layer, and the outer layer and the inner layer are provided with insulation cotton.

[0016] The fuel tank is also connected to a nitrogen filling device.

[0017] Furthermore, the explosion-proof electric heater assembly includes several heaters and a heating furnace, the heaters and the heating furnace are connected, and the several heaters are connected in a star shape and are arranged perpendicular to the horizontal plane as a whole.

[0018] Furthermore, the first regulating valve group includes several regulating valves arranged in parallel; the second regulating valve group also includes several regulating valves arranged in parallel.

[0019] Furthermore, the pump set includes several plunger pumps and centrifugal pumps, with the plunger pumps connected in parallel and the plunger pumps and centrifugal pumps also connected in parallel. Each plunger pump is connected to a pipeline with a check valve and a pressure gauge in series, and the centrifugal pump is also connected to a pipeline with a check valve and a pressure gauge in series.

[0020] An aviation fuel control method, using any of the above-mentioned aviation fuel control systems, includes the following steps:

[0021] S1. Connect the fuel circulation system to the product under test, start the pump set, and perform fuel circulation;

[0022] S2. By adjusting the opening of the regulating valves in the first regulating valve group and the second regulating valve group, and by observing the flow rate value in the first ball valve group and the product inlet pressure value, the pressure and flow rate of the fuel circulation system are regulated so that the pressure and flow rate of the fuel at the product inlet meet the product test standards.

[0023] S3. By controlling the cooling components and explosion-proof electric heater group and observing the temperature value at the product inlet, the temperature of the fuel circulation system is regulated so that the temperature of the fuel at the product inlet reaches the product test standard.

[0024] S4. After conducting the test and reading the required data, the pressure, flow rate, and temperature of the fuel circulation system are regulated by controlling the first regulating valve group, the second regulating valve group, the explosion-proof electric heater group, and the cooling component. After the circulation is cooled to below the standard temperature, all pumps in the pump group are turned off, and the test ends.

[0025] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0026] (1) The present invention can control the temperature, pressure and flow rate of fuel entering the test product, which helps to improve the stable fuel conditions for combustion test of fuel system products, improve the accuracy of combustion test, and allow the test fuel to be used repeatedly, which has economic benefits and energy-saving and environmental protection significance.

[0027] (2) The thermal insulation component of the present invention has two flow modes: one is through the fuel tank, which is provided for products that require a large amount of fuel for testing, and the other is without passing through the fuel tank, which is provided for products that require a small amount of fuel for testing, so that products that require different amounts of fuel for testing can be tested stably.

[0028] (3) The present invention also includes a fuel recovery system, which can recover the remaining fuel in the product after the product test is completed and return the fuel to the fuel tank, thus preventing fuel waste. Attached Figure Description

[0029] Figure 1 This is a schematic diagram of the aviation fuel control system of the present invention.

[0030] Figure 2a This is a schematic diagram of the explosion-proof electric heater assembly of the present invention.

[0031] Figure 2b This is a front view of the electric heater of the present invention.

[0032] Figure 2c This is a side view showing the internal structural connections of the electric heater according to the present invention.

[0033] Figure 3 This is a schematic diagram showing the connection between the nitrogen filling device and the fuel tank of the present invention.

[0034] Figure 4a This is a schematic diagram of the fuel tank structure of the present invention.

[0035] Figure 4b This is a cross-sectional view of the internal structure of the fuel tank display of the present invention.

[0036] Figure 4c This is a cross-sectional view of the internal structure of the fuel tank display of the present invention from another perspective.

[0037] Figure 4d This is a schematic diagram of the upper structure of the fuel tank display of the present invention.

[0038] Figure 5a This is a flowchart of the pressure control process of the present invention.

[0039] Figure 5b This is a flowchart of the flow control process of the present invention.

[0040] Figure 5c This is a flowchart of the temperature control process of the present invention.

[0041] Figure 6 This is a flowchart of the fuel control method of the present invention.

[0042] Explanation of reference numerals in the attached figures:

[0043] 1. Fuel tank; 101. Flange; 102. Fixed top cover; 103. Movable top cover; 104. Folding handle; 105. Outer layer of fuel tank; 106. Fixed connecting plate; 107. Support leg; 108. Welded hand valve; 109. Temperature sensor; 1010. Wafer ball valve; 1011. Single-ended thread; 1012. Insulation cotton; 1013. First return pipe; 1014. Baffle; 1015. Second return pipe; 1016. Double internal thread elbow; 1017. Inner and outer layer supports; 1018. Inner layer of fuel tank; 1019. Seamless steel pipe; 2. First wafer ball valve; 3. First filter; 4. First metal 5. Hoses; 6. Centrifugal pump; 7. First plunger pump; 8. Second plunger pump; 9. First check valve; 10. Second check valve; 11. Third check valve; 12. Safety valve; 13. Second metal hose; 14. Third metal hose; 15. First regulating valve; 16. Second regulating valve; 17. Third filter; 18. First pressure transmitter; 19. First resistance temperature detector (RTD); 20. Differential pressure transmitter; 21. Second RTD; 22. Third regulating valve; 23. Fourth regulating valve; 24. Fifth regulating valve; 25. First electric ball valve; 26. Second electric ball valve; 27. First vortex valve. 28. Second turbine flow meter; 29. ​​Three-way regulating valve; 30. Heat exchanger; 31. Third resistance temperature detector (RTD) thermometer; 32. Fourth RTD thermometer; 33. Liquid level gauge; 34. Nitrogen filling device; 341. Fourth pressure gauge; 342. Gas filter; 343. High-pressure pressure reducing valve; 344. High-pressure manual valve; 345. Nitrogen cylinder; 35. Third electric ball valve; 36. Fourth electric ball valve; 37. First pressure gauge; 38. Second pressure gauge; 39. Third pressure gauge; 40. Fifth electric ball valve; 41. Fourth metal hose; 42. Second clamp-on ball valve; 43. Fifth metal hose; 44. 45. Centrifugal oil pump; 46. High-pressure ball valve; 47. Needle valve; 48. Explosion-proof electric heater assembly; 49. Junction box; 40. Stuffing box; 41. Junction manifold; 42. RTD terminal block; 43. RTD mounting plate; 44. Terminal block; 45. Cold end transition liner; 46. Lifting ring; 477. Heater flange; 48. Heater tube; 49. Right-side baffle plate; 40. Temperature RTD; 41. Left-side baffle plate; 42. Insulation layer; 43. Pressure gauge valve; 44. Fourth filter; 55. Fifth RTD thermometer; 56. Second pressure transmitter. Detailed Implementation

[0044] The technical solution of the present invention will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are not all embodiments of the present invention. All other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present invention. It should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0045] This invention provides an aviation fuel control system, including a fuel circulation system, a fuel recovery system, and an electrical measurement and control system. The electrical measurement and control system controls the fuel circulation system, which is connected to a product to form a circulation system. The fuel circulation system includes a first regulating valve group, a first ball valve group, a cooling component, an explosion-proof electric heater group 47, a heat insulation component, a pump group, a first filter group, a second regulating valve group, and a temperature measuring component. The product has a product inlet and a product outlet at both ends. The first regulating valve group, the first ball valve group, the cooling component, the explosion-proof electric heater group 47, the heat insulation component, the pump group, and the first filter group are connected in series between the product outlet and the product inlet. The pipe between the cooling component and the explosion-proof electric heater group 47 is connected to the pipe between the pump group and the first filter group. The second regulating valve group is connected in series on the connecting pipe. The temperature measuring component is installed at the product inlet and the product outlet.

[0046] like Figure 1 As shown, the upper end of the product is designated as the product outlet, and the lower end is designated as the product inlet. The temperature measuring components include a first resistance thermometer 19 and a second resistance thermometer 21. The product inlet is equipped with a first pressure transmitter 18 and a first resistance thermometer 19 for measuring the temperature and pressure of the fuel at the product inlet. The product outlet is equipped with a second resistance thermometer 21 for measuring the temperature of the fuel at the product outlet. Differential pressure transmitters 20 are connected in parallel at both ends of the product, and a pressure gauge valve 48 is also connected in series on this parallel pipeline.

[0047] The first regulating valve group includes several regulating valves arranged in parallel, preferably three regulating valves arranged in parallel, namely the third regulating valve 22, the fourth regulating valve 23, and the fifth regulating valve 24; the first ball valve group includes several ball valves and flow meters arranged in parallel, preferably two ball valves arranged in parallel, namely a first electric ball valve 25 and a second electric ball valve 26, with a first turbine flow meter 27 connected in series on the parallel branch of the first electric ball valve 25, and a second turbine flow meter 28 connected in series on the parallel branch of the second electric ball valve 26, to facilitate the pressure regulation of the fuel circulation system pipeline; the cooling component includes a heat exchanger 30 and a three-way regulating valve 2. 9 and the third resistance thermometer 31, one side of the three-way regulating valve 29 is connected to the first ball valve group, one fuel output end of the three-way regulating valve 29 is connected to the heat exchanger 30, and the other fuel output end of the three-way regulating valve 29 is connected to the pipeline connecting the cooling component and the explosion-proof electric heater group 47. The third resistance thermometer 31 is connected to the fuel output end of the cooling component to measure the temperature of the fuel after it has been heated by the cooling component. The heat exchanger 30 is also connected to cooling water. A fifth electric ball valve 40 is connected in series on the pipeline connecting the heat exchanger 30 and the cooling water. A fourth metal hose 41 is connected in series between the first ball valve group and the cooling component.

[0048] A fifth resistance thermometer 50 and a second pressure transmitter 51 are connected in series between the explosion-proof electric heater assembly 47 and the insulation component. The insulation component includes a fuel tank 1 and several valves. Valves are provided at both the fuel inlet and fuel outlet of the fuel tank 1. A pipeline is connected in parallel to the valves at both ends of the fuel tank 1, and valves are also provided on this pipeline. Preferably, the insulation component has three valves: a third electric ball valve 35, a fourth electric ball valve 36, and a first wafer-type ball valve 2. The third electric ball valve 35 is located at the fuel inlet of the fuel tank 1, the first wafer-type ball valve 2 is located at the fuel outlet of the fuel tank 1, and the fourth electric ball valve 36 is located on the pipeline connected in parallel with the fuel tank 1. The third electric ball valve 35 and the fourth electric ball valve 36 are interlocked. During testing, the third electric ball valve 35 and the fourth electric ball valve 36 cannot be closed simultaneously. When the amount of fuel circulating inside the fuel circulation system is greater than the threshold, the third electric ball valve 35 opens, and the fuel flows through the fuel tank 1 and then into the pump unit for circulation. If the amount of fuel circulating inside the fuel circulation system is less than the threshold, the fourth electric ball valve 36 opens, and the fuel flows directly into the pump unit for circulation without passing through the fuel tank 1. The fuel tank 1 can keep the fuel warm. When the fuel level is low, it does not pass through the fuel tank 1, which can prevent a small amount of fuel from passing through the fuel tank 1 and reducing the fuel level again. A first filter 3 is connected in series between the heat preservation component and the pump unit.

[0049] The pump set includes several plunger pumps and centrifugal pumps 5, which are connected in parallel. Each plunger pump is connected to a pipeline with a check valve and a pressure gauge in series. The centrifugal pump 5 is also connected to a pipeline with a check valve and a pressure gauge in series. Preferably, two plunger pumps and one centrifugal pump 5 are set up, namely a first plunger pump 6, a second plunger pump 7, and a centrifugal pump 5. The first plunger pump 6 is connected in parallel to the fuel flow direction with a second metal hose 12, the first plunger pump 6, a second check valve 9, and a second pressure gauge 38 in series. The second plunger pump 7 is connected in parallel to the fuel flow direction with a third metal hose 13, the second plunger pump 7, a third check valve 10, and a first pressure gauge 37 in series. The centrifugal pump 5 is connected in parallel to the fuel flow direction with a first metal hose 4, a centrifugal pump 5, a first check valve 8, and a third pressure gauge 39 in series. The check valve can prevent fuel backflow. The pipeline connecting the fuel tank 1 to the pump set and the first filter set is connected, and a safety valve 11 is connected in series on this pipeline.

[0050] The second regulating valve group includes several regulating valves arranged in parallel, preferably two, namely the first regulating valve 14 and the second regulating valve 15. The first regulating valve group is set up to facilitate the change of the flow resistance of the pipeline and to facilitate the control of the pressure of the fuel circulation system. The first filter group includes a second filter 16 and a third filter 17 arranged in series. The second filter 16 is a 20-micron filter and the third filter 17 is a 5-micron filter. A high-pressure ball valve 45 and a needle valve 46 are connected in series between the first filter group and the product inlet.

[0051] One end of the fuel recovery system is connected to the fuel tank 1, and the other end is connected to the product inlet. The system is connected in sequence from the fuel tank 1 to the product inlet to the fourth filter 49, the centrifugal oil pump 44, the fifth metal hose 43, and the second clamp ball valve 42. With the fuel recovery system, when the test is completed, there will be a large amount of oil in the product area. The centrifugal oil pump 44 can pump the oil back, reducing oil loss when changing products.

[0052] like Figure 2a As shown, the explosion-proof electric heater assembly 47 includes several heaters and a heating furnace. Each heater includes a housing and a heating core. The heating core is detachably connected inside the housing. The heating core and the heating furnace are electrically connected. The number of heating cores is greater than three, preferably three. The heating cores are connected in a star configuration as shown in Figure 2 and used perpendicular to the horizontal plane, which helps to reduce the usable space. The fuel in the flow channel flows from a to b and from bottom to top, ensuring the pipe is filled with liquid and preventing dry burning. The explosion-proof electric heater assembly 47 of this application also features convenient maintenance. When maintenance is needed, the damaged heating core can be directly removed and replaced. For safety reasons, the electric heating furnace adopts an explosion-proof wiring configuration to reduce surface load and prevent excessive carbonization of the fuel. The fuel flow rate inside the explosion-proof electric heater assembly 47 is set to 1.2 W / cm³. 2This reduces the safety hazards associated with heating too much fuel at once.

[0053] The structure of the heater is as follows Figure 2b , Figure 2c As shown, the device includes a heater tube 4710, a heater flange 479, an insulation layer 4714, cold-end transition liner 477, a manifold, and a junction box 471. One end of the heater tube 4710 is fixedly connected to the heater flange 479. The end of the heater flange 479 away from the heater tube 4710 is connected to the insulation layer 4714. Several cold-end transition liners 477 are connected to the end of the insulation layer 4714 away from the heater flange 479. The cold-end transition liners 477 are perpendicular to the insulation layer 4714. The end of the cold-end transition liners 477 away from the insulation layer 4714 is connected to the junction box 473. The end of the junction box 473 away from the cold-end transition liner 477 is connected to the junction box 471. A stuffing box 472 is fixedly connected to the outer wall of the junction box 473. The stuffing box 472 communicates with the interior of the junction box 473. The interior of the junction box 473 is a hollow structure. The device includes a resistance temperature detector (RTD) terminal block 474, a RTD mounting plate 475, and a junction box 476. The RTD terminal block 474 is fixed to the inner wall connected to the junction box 471. The RTD terminal block 474 is connected to the RTD mounting plate 475 on the side away from the junction box 471. A cold end transition liner 477 extends into the junction box 473 and is connected to two junction boxes 476 at one end. Each junction box 476 is connected to the same number of cold end transition liners 477. The outer wall of the heater flange 479 is also provided with two lifting rings 478. The heater tube 4710 has several left-slotted baffles 4713 and several right-slotted baffles 4711 along its length. The left-slotted baffles 4713 and right-slotted baffles 4711 are staggered. The baffles are used to change the liquid flow direction. The outer wall of the heater tube 4710 is also fitted with a temperature RTD 4712.

[0054] like Figure 1 , Figure 3 As shown, the fuel tank 1 is also connected to a nitrogen filling device 34. The nitrogen filling device 34 includes a fourth pressure gauge 341, an air filter 342, a high-pressure pressure reducing valve 343, a high-pressure air manual valve 344, and a nitrogen cylinder 345. The pressure gauge, air filter 342, high-pressure pressure reducing valve 343, and high-pressure air manual valve 344 are connected sequentially between the fuel tank 1 and the nitrogen cylinder 345. A breather is also provided on the upper part of the fuel tank 1. The fuel tank 1 is also equipped with a fourth thermal resistance thermometer 32 and a liquid level gauge 33. During the heating test, the fuel tank 1 is filled with nitrogen to achieve the function of isolating air with inert gas, so as to maximize the safety protection during high temperature and high pressure fuel tests.

[0055] like Figure 4a , Figure 4b , Figure 4c , Figure 4d As shown, the fuel tank 1 is cubic in shape and made of stainless steel. The bottom of the fuel tank 1 is designed with an offset sloping structure, which is beneficial for collecting contaminant particles in the fuel. The fuel tank 1 includes an inner layer 1018, an outer layer 105, a fixed top cover 102, and a movable top cover 103. An inner and outer layer support 1017 is provided between the inner layer 1018 and the outer layer 105, and thermal insulation cotton 1012 is provided between the inner layer 1018 and the outer layer 105. The thermal insulation cotton 1012 is made of aluminum silicate cotton. The outer layer 105 and the inner layer 1018 are made of stainless steel plates welded together. The outer layer 105 of the fuel tank is constructed by connecting parts together to provide insulation. Support legs 107 are located at the four corners of the lower part of the outer layer 105. The outer layer 105 is fixedly connected to the support legs 107 via a fixed connecting plate 106. The upper part of the fuel tank 1 has a fixed top cover 102 and a movable top cover 103. A folding handle 104 is provided on the upper wall of the movable top cover 103 for easy opening. The inner layer 1018 of the fuel tank has a baffle 1014 that divides the interior of the inner layer 1018 into two parts. The inner layer 1018 also has a first return pipe 1013 and a second return pipe 1015. The first return pipe 1013 is located on one side of the baffle 1014, and the second return pipe 1015 is located on the other side of the baffle 1014. The upper end of the first return pipe 1013 is sequentially connected to a single-ended thread 1011 and a double-threaded elbow 1016. One end of the double-threaded elbow 1016 is connected to the single-ended thread 1011, and the other end is connected to a seamless steel pipe 1019. The seamless steel pipe 1019 passes through the side wall of the fuel tank 1, and the end extending out of the fuel tank 1 is connected to a flange 101. The upper end of the second return pipe is also sequentially connected to a single-ended thread 1011 and a double-threaded elbow 1016. One end of the double-threaded elbow 1015 is connected to... A single-ended wire 1011 is connected to a seamless steel pipe 1019 at one end. The other end of the seamless steel pipe 1019 is also connected to a double-inner-thread elbow 1016. The double-inner-thread elbow 1016 is bent upward and its upper end is connected to the seamless steel pipe 1019. The seamless steel pipe 1019 passes through the fixed upper cover 102 and its end extending out of the fixed upper cover 102 is connected to a flange 101. A temperature sensor 109 is provided on the outer wall of the outer layer 105 of the fuel tank to measure the fuel temperature inside the fuel tank 1. A welded hand valve 108 is also provided at the lower part of the fuel tank 1, and a clamp ball valve 1010 is also provided on the side wall of the fuel tank 1.

[0056] The electrical measurement and control system mainly consists of a comprehensive control console, electrical control cabinet, field pipeline measurement and control system, and software control system. It can realize data acquisition, storage, query, and temperature, flow, and pressure control and alarm monitoring functions. The system control is remote, and the remote control is realized on a remote computer. The electrical measurement and control system mainly controls the flow, pressure, and temperature on site. Through the control console, it is electrically connected to thermometers, pressure gauges, and flow meters respectively, and controls the opening of the corresponding valves on site to control the pressure, temperature, and flow in the pipeline. It can realize the automatic adjustment of temperature, pressure, and flow after the electrical measurement and control system is turned on.

[0057] like Figure 5a As shown, the pressure control method is as follows: First, the PLC controller sets the pressure, the PLC controller transmits the signal to the analog output module, the analog output module controls the regulating valve, and then the pressure sensor feeds back the pressure value. The feedback pressure value is fed back by the analog acquisition module, and the set pressure is adjusted based on the feedback from the analog acquisition module.

[0058] like Figure 5b As shown, the flow control method is as follows: the set flow value is input into the industrial control computer, then the PLC controller controls the frequency converter, which in turn controls the motor in the pump group. The flow sensor then feeds back the flow value on the pipeline. The data acquisition card collects the flow value information and feeds it back. The set flow value is adjusted based on the feedback flow value.

[0059] like Figure 5c As shown, the temperature control method is as follows: the set temperature value is input into the industrial control computer, the valve opening is controlled by the PLC controller to achieve the set temperature in the pipeline, the temperature value in the pipeline is measured by the temperature sensor, the temperature value in the pipeline is fed back by the analog signal acquisition module, and the set temperature is adjusted according to the feedback temperature value.

[0060] This application also provides a control method for an aviation fuel control system, such as... Figure 6 As shown, it includes the following steps:

[0061] S1. Connect the fuel circulation system to the product under test, start the pump set, and perform fuel circulation;

[0062] S101. Connect the fuel circulation system to the product under test;

[0063] S102. Open the first regulating valve 14, the second regulating valve 15, the third regulating valve 22, the fourth regulating valve 23 and the fifth regulating valve 24, and open them to 100%. At the same time, adjust the three-way regulating valve 29 to be connected to the heat exchanger 30. Then open the first electric ball valve 25, the second electric ball valve 26, the third electric ball valve 35, the fourth electric ball valve 36 and the fifth electric ball valve 40, and keep the electric ball valves open to 100%.

[0064] S103. When the pressure is 2 MPa or above, use the first plunger pump 6 and the second plunger pump 7. When the pressure is below 2 MPa, use the centrifugal pump 5.

[0065] S104. Observe whether the value of the first pressure transmitter 18 is within a reasonable range. The reasonable range is 10Kpa-300Kpa. If the value of the first pressure transmitter 18 is not within a reasonable range, stop the pump and stop the test.

[0066] S2. By adjusting the opening of the regulating valves in the first regulating valve group and the second regulating valve group, and by observing the flow rate value in the first ball valve group and the product inlet pressure value, the pressure and flow rate of the fuel circulation system are regulated so that the pressure and flow rate of the fuel at the product inlet meet the product test standards.

[0067] S201. Gradually reduce the opening of the first regulating valve 14, while keeping the second regulating valve 15 open, or directly close the first regulating valve 14 or the second regulating valve 15.

[0068] S202, repeat step S201 until the values ​​of the first turbine flow meter 27 and the second turbine flow meter 28 reach the process requirements, then gradually close the third regulating valve 22, keep the fourth regulating valve 23 and the second regulating valve 15 open, or directly close one of the third regulating valve 22, the fourth regulating valve 23 and the fifth regulating valve 24, and use one regulating valve for regulation.

[0069] S203, repeat step S202 until at least one of the first turbine flow meter 27 and the second turbine flow meter 28 and the value of the first pressure transmitter 18 simultaneously meet the process requirements.

[0070] S3. Close the third electric ball valve 35 or the fourth electric ball valve 36. The third electric ball valve 35 and the fourth electric ball valve 36 cannot be closed at the same time. Turn on the explosion-proof electric heater group 47. By observing the third thermal resistance thermometer 31 and adjusting the flow distribution of the three-way regulating valve 29, the temperature of the fuel after circulation is reduced to below the standard temperature. Then, the cooled fuel is heated by passing through the explosion-proof electric heater group 47. By observing the value of the first thermal resistance thermometer, it is determined whether the temperature of the fuel at the product inlet has reached the test standard temperature.

[0071] S4. After the pressure, flow rate and temperature of the fuel at the product inlet reach the test standard, conduct the test, read the required data, and regulate the pressure, flow rate and temperature of the fuel circulation system by controlling the first regulating valve group, the second regulating valve group, the explosion-proof electric heater group and the cooling component. After the circulation is cooled to below the standard temperature, turn off all the pumps in the pump group and the test ends.

[0072] S401. After conducting the test and reading the required data, stop the explosion-proof electric heater group 47, open the third electric ball valve 35, open the first regulating valve 14, the second regulating valve 15, the third regulating valve 22, the fourth regulating valve 23 and the fifth regulating valve 24, adjust the three-way regulating valve 29 to the pipeline connected in parallel with the heat exchanger 30, and open the flow rate to the maximum to increase the cooling flow rate.

[0073] S402. Observe the values ​​of the first turbine flow meter 27 and the second turbine flow meter 28. If the values ​​are small, adjust the opening of the first regulating valve 14 and the second regulating valve 15 appropriately to increase the cooling flow.

[0074] S403. Observe the values ​​of the first resistance thermometer 19 and the fourth resistance thermometer 32. After circulating and cooling down to below 30°C, turn off the centrifugal pump 5, the first plunger pump 6 and the second plunger pump 7. The test ends.

[0075] A first regulating valve group is installed at the inlet of the circulation path after combustion, serving as the main back pressure valve to regulate the pipeline pressure. A second regulating valve group is installed to change the flow resistance of the main and branch paths in the system, thereby controlling the flow rate of the main path and the pressure at the outlet of the circulation path. A first ball valve group is installed, which also has a position feedback signal, to monitor the fuel flow rate.

[0076] The explosion-proof electric heater assembly 47 can heat the fuel to the required value with an error of no more than 3°C. After each combustion test, the fuel will heat up due to the combustion test and the friction between the liquid and the inner wall of the pipe. The required temperature needs to be checked before the next combustion. This is achieved by connecting cooling water through the heat exchanger 30. After the fuel is cooled by the cooling component, it is heated again inside the explosion-proof electric heater assembly 47. This facilitates the heating of fuel that has not reached the required temperature after cooling. The fuel tank 1 has a heat preservation effect, which can keep the heated fuel warm. Temperature measuring components are provided at both the product inlet and the product outlet to facilitate accurate measurement of the temperature of the fuel entering the product and to determine whether the fuel at the product outlet needs to be cooled.

[0077] Metal hoses are installed before and after each type of pump to absorb shock. A check valve and a shock-resistant pressure gauge are installed at the fuel outlet of the pump to prevent backflow and damage to the pump. A safety valve 11 is installed in the downstream branch of the pump to protect the entire system and prevent overpressure. A third electric ball valve 35 and a fourth electric ball valve 36 are installed to achieve two circulation modes. At high flow rates, fuel can be temporarily stored in fuel tank 1, which can also be used for heat preservation to prevent the fuel temperature from dropping. At low flow rates, fuel can bypass fuel tank 1 to prevent the fuel volume from decreasing again due to insufficient fuel passing through fuel tank 1, thus preventing fuel from failing to circulate. The second filter 16 and the third filter 17 are equipped with differential pressure alarms to remind the filter element to be replaced in time when it is clogged, ensuring the stable operation of the entire system.

[0078] Since different aviation fuel system products have different requirements for the temperature, pressure and flow rate of fuel entering the product, this invention is applicable to combustion tests under fuel flow rate range (60~18000) L / h and pressure range (0.14~12) MPa. It can simultaneously control the temperature, pressure and flow rate of fuel entering the test product, which helps to improve the stable fuel conditions for combustion tests of fuel system products, improve the accuracy of combustion tests, and allow for multiple cycles of test fuel, which has economic benefits and energy-saving and environmental protection significance.

[0079] The above specific embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to examples, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. An aviation fuel control system, characterized in that, It includes a fuel circulation system and an electrical measurement and control system. The electrical measurement and control system is used to control the temperature, flow rate and pressure of the circulating fuel in the fuel circulation system. The fuel circulation system is connected to the product to circulate fuel. The fuel circulation system includes a first regulating valve group, an explosion-proof electric heater group, a heat insulation component, a pump group, a second regulating valve group, and a temperature measuring component. The first regulating valve group, the explosion-proof electric heater group, the heat insulation component, and the pump group are connected in series from the product outlet to the product inlet. The temperature measuring component is provided at both the product inlet and the product outlet. The pipe connecting the first regulating valve group and the explosion-proof electric heater group is connected to the pipe connecting the pump group and the product inlet, and the second regulating valve group is connected in series on the connected pipe. The insulation component includes a fuel tank and several valves. The fuel tank has valves at both the fuel input and fuel output ends. A pipeline with valves connected in series is connected in parallel to the pipeline connecting the fuel tank and the two valves. The electrical measurement and control system controls the valves inside the insulation component to ensure that fuel circulates through the fuel tank when the fuel quantity is greater than a threshold and does not circulate through the fuel tank when the fuel quantity is less than the threshold.

2. The aviation fuel control system according to claim 1, characterized in that, A cooling component is connected in series between the explosion-proof electric heater group and the first regulating valve group. The electrical measurement and control system controls whether the fuel at the product outlet is cooled by passing through the cooling component.

3. The aviation fuel control system according to claim 2, characterized in that, A first ball valve assembly is connected in series between the first regulating valve assembly and the cooling component. The first ball valve assembly is also equipped with a flow meter. The electrical measurement and control system controls the first ball valve assembly to regulate the flow of the fuel circulation system.

4. The aviation fuel control system according to claim 1, characterized in that, A first filter set is also provided between the pump set and the product inlet.

5. An aviation fuel control system according to claim 1, characterized in that, The fuel tank includes an outer layer and an inner layer, and the outer and inner layers are provided with insulation cotton. The fuel tank is also connected to a nitrogen filling device.

6. An aviation fuel control system according to claim 1, characterized in that, The explosion-proof electric heater group includes several heaters and a heating furnace. The heaters and the heating furnace are connected. The several heaters are connected in a star shape and are arranged perpendicular to the horizontal plane as a whole.

7. An aviation fuel control system according to claim 1, characterized in that, The first regulating valve group includes several regulating valves arranged in parallel; the second regulating valve group also includes several regulating valves arranged in parallel.

8. An aviation fuel control system according to claim 1, characterized in that, The pump set includes several plunger pumps and centrifugal pumps. The plunger pumps are connected in parallel, and the plunger pumps and centrifugal pumps are also connected in parallel. Each plunger pump is connected to a pipeline with a check valve and a pressure gauge in series, and the centrifugal pump is connected to a pipeline with a check valve and a pressure gauge in series.

9. A control method using an aviation fuel control system according to any one of claims 1-8, characterized in that, Includes the following steps: S1. Connect the fuel circulation system to the product under test, start the pump set, and perform fuel circulation; S2. By adjusting the opening of the regulating valves in the first regulating valve group and the second regulating valve group, and by observing the flow rate value in the first ball valve group and the product inlet pressure value, the pressure and flow rate of the fuel circulation system are regulated so that the pressure and flow rate of the fuel at the product inlet meet the product test standards. S3. By controlling the cooling components and explosion-proof electric heater group and observing the temperature value at the product inlet, the temperature of the fuel circulation system is regulated so that the temperature of the fuel at the product inlet reaches the product test standard. S4. After conducting the test and reading the required data, the pressure, flow rate, and temperature of the fuel circulation system are regulated by controlling the first regulating valve group, the second regulating valve group, the explosion-proof electric heater group, and the cooling component. After the circulation is cooled to below the standard temperature, all pumps in the pump group are turned off, and the test ends.

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