A fuel system based on a multi-temperature zone aircraft fuel tank
By storing fuel in partitions within the aircraft fuel tank and constructing a multi-temperature zone fuel circuit, the problem of reduced heat dissipation capacity caused by rising fuel temperature is solved, achieving efficient utilization of fuel heat sinks and improving the overall aircraft heat dissipation performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
- Filing Date
- 2023-09-07
- Publication Date
- 2026-07-21
AI Technical Summary
When the temperature of the fuel in the aircraft's fuel tank rises, the heat dissipation capacity of the fuel at the fuel tank outlet decreases, affecting the normal operating temperature and performance of the equipment. The thermal load on the equipment continues to increase, and excessively high fuel temperature seriously affects the heat dissipation of the entire aircraft.
The aircraft fuel tank adopts a multi-temperature zone design, dividing the fuel storage space into low-temperature, medium-temperature, and high-temperature zones, and constructing first and second fuel circuits respectively. Temperature management is achieved through flow control valves and heat exchangers to ensure selective flow and mixing of fuel between different temperature zones, thereby achieving efficient heat dissipation.
It effectively improves the heat dissipation capacity of fuel, ensures the efficient utilization of fuel heat sink, enhances the overall heat dissipation performance of the engine, and adapts to different heat load conditions through flexible fuel supply methods.
Smart Images
Figure CN117262223B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft design technology, and specifically relates to a fuel system based on a multi-temperature zone aircraft fuel tank. Background Technology
[0002] The aircraft fuel supply tank is responsible for supplying fuel to the engine. When the engine fuel consumption flow rate is lower than the fuel flow rate of the aircraft cooling circuit, the hot oil that the engine cannot burn needs to be returned to the fuel supply tank, so that the fuel temperature in the fuel supply tank gradually increases.
[0003] When the fuel temperature inside the fuel tank rises, the heat dissipation capacity of the fuel at the fuel tank outlet decreases, affecting the normal operating temperature and performance of the equipment.
[0004] The equipment's thermal load is constantly increasing, and the excessively high fuel temperature seriously affects the overall heat dissipation of the machine. Summary of the Invention
[0005] To address the aforementioned issues, this application provides a fuel system based on a multi-temperature zone aircraft fuel tank, which ensures good fuel cooling performance by using the fuel tank in separate zones.
[0006] The fuel system based on a multi-temperature zone aircraft fuel tank provided in this application mainly includes multiple fuel storage spaces to store fuel at different temperatures. The low-temperature zone fuel separately forms a first fuel circuit, the high-temperature zone fuel supplies fuel to the engine, and the low-temperature zone fuel and the high-temperature zone fuel are mixed to form a second fuel circuit. The second fuel circuit selectively supplies fuel to the engine or flows back to different fuel storage spaces according to the fuel temperature.
[0007] Preferably, the fuel storage space comprises a low-temperature fuel storage space, a medium-temperature fuel storage space, and a high-temperature fuel storage space. The low-temperature fuel storage space exchanges heat with the cooling pipes through a first fuel circuit, absorbing heat from the first fuel circuit. The low-temperature, medium-temperature, and high-temperature fuel storage spaces are connected to a second fuel circuit via flow control valves. The second fuel circuit includes multiple heat exchangers or radiators to heat the fuel. After the fuel is heated, a portion of the fuel is selectively discharged from the second fuel circuit through a three-way valve and fed into the engine. The remaining fuel continues to be selectively distributed along the second fuel circuit to the low-temperature, medium-temperature, and high-temperature fuel storage spaces. At least one of the multiple heat exchangers or radiators includes a fuel-liquid heat exchanger, used to heat the fuel in the second fuel circuit by absorbing heat from the first fuel circuit through the cooling pipes. The high-temperature fuel storage space also includes a fuel supply line directly connected to the engine.
[0008] Preferably, the low-temperature fuel storage space, the medium-temperature fuel storage space, and the high-temperature fuel storage space are formed by dividing the same fuel tank into multiple storage spaces.
[0009] Preferably, the low-temperature fuel storage space, the medium-temperature fuel storage space, and the high-temperature fuel storage space are separated by structural frame plates and heat insulation materials.
[0010] Preferably, the plurality of heat exchangers or radiators in the second fuel circuit further include a fuel-hydraulic oil radiator, a fuel-lubricating oil radiator, and an air-fuel radiator, wherein the fuel-liquid heat exchanger, the fuel-hydraulic oil radiator, and the fuel-lubricating oil radiator are located before the three-way valve of the second fuel circuit, and the air-fuel radiator is located after the three-way valve of the second fuel circuit.
[0011] Preferably, the cooling pipeline includes a first liquid cooling pipeline that absorbs fuel heat from the first fuel circuit through a liquid-fuel radiator and transfers the heat to a second liquid cooling pipeline through an evaporator. The second liquid cooling pipeline then transfers the heat to a third liquid cooling pipeline through a condenser, and the third liquid cooling pipeline transfers the heat to the second fuel circuit through a fuel-liquid heat exchanger.
[0012] Preferably, the first fuel circuit and the second fuel circuit include multiple flow control valves and temperature sensors. Temperature sensors are installed in the low-temperature fuel storage space, the medium-temperature fuel storage space and the high-temperature fuel storage space. The fuel system based on the multi-temperature zone aircraft fuel tank also includes a controller connected to each flow control valve and temperature sensor. The controller is configured to control the opening degree of each flow control valve to control the fuel input and output flow of the low-temperature fuel storage space, the medium-temperature fuel storage space and the high-temperature fuel storage space.
[0013] Preferably, the controller is further configured to lower the fuel temperature in the low-temperature fuel storage space to a first set temperature, lower the fuel temperature in the medium-temperature fuel storage space to between the first set temperature and the second set temperature, and lower the fuel temperature in the high-temperature fuel storage space to a second set temperature.
[0014] Preferably, the second fuel circuit supplies fuel to the low-temperature fuel storage space, the medium-temperature fuel storage space, and the high-temperature fuel storage space respectively via a four-way valve. When the fuel temperature in the second fuel circuit monitored by the temperature sensor before the four-way valve is lower than the first set temperature, fuel is preferentially supplied to the low-temperature fuel storage space. When the fuel temperature in the second fuel circuit monitored by the temperature sensor is higher than the second set temperature, fuel is preferentially supplied to the high-temperature fuel storage space. When the fuel temperature in the second fuel circuit monitored by the temperature sensor falls between the first set temperature and the second set temperature, fuel is preferentially supplied to the medium-temperature fuel storage space.
[0015] Preferably, the controller is further configured to:
[0016] First, fuel is supplied to the engine through the fuel supply line from the high-temperature fuel storage space, and then fuel is supplied to the engine through the second fuel circuit.
[0017] Preferably, the controller is further configured to:
[0018] First, fuel from the medium-temperature fuel storage space is used to supply fuel to the second fuel circuit, and then fuel from the low-temperature fuel storage space and the high-temperature fuel storage space is used to supply fuel to the second fuel circuit.
[0019] This application can maximize the heat dissipation capacity of the fuel heat sink. Attached Figure Description
[0020] Figure 1 This is a schematic diagram of the fuel system piping interconnection based on a multi-temperature zone aircraft fuel tank, as described in this application.
[0021] Figure 2 This is a controlled schematic diagram of the fuel system based on a multi-temperature zone aircraft fuel tank, as described in this application.
[0022] Among them, 1-four-way valve, 2-one-way valve, 3-thermal insulation material, 4-structural frame plate, 5-electric fuel pump, 6-high temperature fuel storage space, 7-structural frame plate, 8-electric fuel pump, 9-one-way valve, 10-one-way valve, 11-flow control valve, 12-flow control valve, 13-air-fuel radiator, 14-flow control valve, 15-three-way valve, 16-engine, 17-flow control valve, 18-three-way valve, 19-fuel-lubricating oil radiator, 20-fuel-hydraulic oil radiator, 21-fuel-liquid heat exchanger, 22-liquid-air heat exchanger, 23-condenser. 24-Throttle valve, 25-Evaporator, 26-Cold plate, 27-Liquid fuel radiator, 28-Pump assembly, 29-One-way valve, 30-One-way valve, 31-Structural frame plate, 32-Insulation material, 33-Structural frame plate, 34-Low-temperature fuel storage space, 35-Electric fuel pump, 36-Flow control valve, 37-Three-way valve, 38-One-way valve, 39-Compressor, 40-Flow control valve, 41-Three-way valve, 42-Medium-temperature fuel storage space, 43-Fuel supply tank, 44-Flow control valve, 45-Three-way valve, 46-60 are temperature sensors, 61-Controller. Detailed Implementation
[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0024] This application provides a fuel system based on a multi-temperature zone aircraft fuel tank, including multiple fuel storage spaces to store fuel at different temperatures. The low-temperature zone fuel separately forms a first fuel circuit, the high-temperature zone fuel supplies fuel to the engine, and the low-temperature zone fuel and the high-temperature zone fuel are mixed to form a second fuel circuit. The second fuel circuit selectively supplies fuel to the engine or flows back to different fuel storage spaces according to the fuel temperature.
[0025] like Figure 1As shown, taking a three-storage space as an example, the multiple fuel storage spaces include a low-temperature fuel storage space 34, a medium-temperature fuel storage space 42, and a high-temperature fuel storage space 6. The low-temperature fuel storage space 34 exchanges heat with the cooling pipe through the first fuel circuit, absorbing the heat from the first fuel circuit. The low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6 are connected to the second fuel circuit through a flow control valve. The second fuel circuit includes multiple heat exchangers or radiators to heat the fuel. After the fuel is heated, a portion of the fuel is selectively exported from the second fuel circuit through a three-way valve 18 and input to the engine 16. The remaining fuel continues to be selectively distributed along the second fuel circuit to the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6. Among the multiple heat exchangers or radiators, at least one fuel-liquid heat exchanger 21 is included, which is used to heat the fuel in the second fuel circuit by means of the heat absorbed from the first fuel circuit by the cooling pipe. The high-temperature fuel storage space 6 also includes a fuel supply line directly connected to the engine 16.
[0026] This application sends the fuel returned to the fuel tank from each airborne fuel circuit to different storage spaces according to temperature zone, so as to avoid the mixture of low temperature, medium temperature and high temperature fuels, which would cause changes in fuel temperature and thus affect the use of fuel heat sink.
[0027] refer to Figure 1 The fuel system based on the multi-temperature zone aircraft fuel tank mainly includes two fuel circuits. The low-temperature fuel storage space 34 is a separate fuel circuit that performs heat exchange with the cooling pipes and performs the cooling function. The heat generated by the cooling pipes is further exchanged through the second fuel circuit. The second fuel circuit is a fuel circuit formed by the combination of the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6. In this second fuel circuit, heat exchange is carried out through multiple heat exchangers or radiators, such as lubricating oil radiators and hydraulic oil radiators. After the fuel temperature rises, it is introduced into the engine 16 for use as appropriate. Correspondingly, the temperature of the exchanged lubricating oil and hydraulic oil is reduced, and they continue to perform their cooling function.
[0028] In addition to the second fuel circuit supplying fuel to the engine 16, the high-temperature fuel storage space 6 can also directly supply fuel to the engine 16.
[0029] Based on the functions of the above-mentioned pipelines, three-way valves or four-way valves are installed between each pipeline, and the flow rate of each fuel is controlled by a flow control valve. The fuel at the outlet of the fuel tank can be supplied separately or mixed with fuel from low temperature, medium temperature or high temperature zones according to the current heat load state, so as to ensure the efficient utilization of fuel heat sink.
[0030] In some alternative embodiments, the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6 are formed by dividing the same fuel tank into multiple storage spaces.
[0031] This application includes, but is not limited to, three-temperature zone fuel tanks. The three-temperature zone fuel tank is used as an example only. It can also be combined with specific application scenarios. The same fuel tank can be set with two or more temperature zones, or any two or more combinations of aircraft fuel tanks can be selected for use. In this embodiment, taking a three-temperature zone aircraft fuel tank as an example, the fuel tank is divided into three independent storage spaces (including but not limited to dividing one fuel tank into three independent storage spaces, or it can be composed of three independent fuel tanks or a combination of storage spaces of three different temperature zones in two independent fuel tanks), which are used to store low temperature, medium temperature and high temperature fuel respectively.
[0032] In some alternative embodiments, the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6 are separated by structural frame plates and heat insulation materials.
[0033] In this embodiment, the same fuel tank is designed with fuel storage spaces for two or more temperature zones. The storage spaces for two different temperature zones can be separated by structural frame plates and insulation materials, such as insulation felt, including but not limited to aerogel. Figure 1 As shown, the low-temperature fuel storage space 34 and the medium-temperature fuel storage space 42 are separated by structural frame plates 33 and 31, and heat insulation material 32 is provided between structural frame plates 33 and 31. Similarly, the medium-temperature fuel storage space 42 and the high-temperature fuel storage space 6 are separated by structural frame plates 4 and 7, and heat insulation material 3 is provided between structural frame plates 4 and 7.
[0034] In some alternative embodiments, the plurality of heat exchangers or radiators of the second fuel circuit further include a fuel-hydraulic oil radiator 20, a fuel-lubricating oil radiator 19, and an air-fuel radiator 13, wherein the fuel-liquid heat exchanger 21, the fuel-hydraulic oil radiator 20, and the fuel-lubricating oil radiator 19 are located before the three-way valve 18 of the second fuel circuit, and the air-fuel radiator 13 is located after the three-way valve 18 of the second fuel circuit.
[0035] refer to Figure 1In the second fuel circuit, fuel from the high-temperature fuel storage space 6 is pumped by the electric fuel pump 5 and a one-way valve 10 to the three-way valve 45. The flow rate of the high-temperature fuel entering the second fuel circuit is controlled by the opening of the flow control valve 44. Fuel from the medium-temperature fuel storage space 42 is pumped by the electric fuel pump 8 and a one-way valve 9. The flow rate of the medium-temperature fuel entering the second fuel circuit is controlled by the opening of the flow control valve 11. The high-temperature fuel flow and the medium-temperature fuel flow are combined and enter the three-way valve 41. At the same time, fuel from the low-temperature fuel storage space 34 is pumped by the electric fuel pump 35 and a one-way valve 38. The flow rate of the low-temperature fuel entering the second fuel circuit is controlled by the opening of the flow control valve 40. The low-temperature fuel flow also enters the three-way valve 41. The mixed fuel of up to three fuels circulates in the main pipeline of the second fuel circuit. After being heated by heat exchange in sequence through the fuel-liquid heat exchanger 21, the fuel-hydraulic oil radiator 20, and the fuel-lubricating oil radiator 19, it flows into the three-way valve 18. Figure 1 In the diagram, B represents lubricating oil and C represents hydraulic oil. The flow direction is then determined by the flow control valves 17 and 14 following the three-way valve 18. When the flow control valve 17 is opened, it is used to draw out the fuel from the second fuel circuit and deliver it to the engine 16. When the flow control valve 14 is opened, it is used to allow the fuel to continue circulating in the second fuel circuit until the fuel returns to each fuel zone.
[0036] After passing through the flow control valve 14, the fuel is first cooled by the air-fuel radiator 13. The cooled fuel then enters the four-way valve 1. The one-way valve 2, one-way valve 30, and one-way valve 29 after the four-way valve 1 determine whether the fuel enters the high-temperature fuel storage space 6, the medium-temperature fuel storage space 42, or the low-temperature fuel storage space 34.
[0037] In some alternative embodiments, the cooling pipeline includes a first liquid-cooled pipeline that absorbs fuel heat from the first fuel circuit through a liquid-fuel radiator 27 and transfers the heat to a second liquid-cooled pipeline through an evaporator 25. The second liquid-cooled pipeline then transfers the heat to a third liquid-cooled pipeline through a condenser 23, and the third liquid-cooled pipeline transfers the heat to the second fuel circuit through a fuel-liquid heat exchanger 21.
[0038] refer to Figure 1First, the first fuel circuit is described. The first fuel circuit is primarily a fuel self-circulation circuit within the low-temperature fuel storage space 34. A three-way valve 37 is added between the electric fuel pump 35 and the one-way valve 38 in the second fuel circuit, and a flow control valve 36 determines the fuel flow rate into the first fuel circuit. The first fuel circuit mainly includes a liquid-fuel radiator 27, which, as the name suggests, comprises liquid lines and fuel lines. Fuel passes through the fuel lines and exchanges heat with the coolant in the liquid lines of the cooling circuit. (Reference) Figure 1 In the cooling circuit, the first liquid cooling line sequentially connects to the pump assembly 28, the liquid-fuel radiator 27, the evaporator 25, and the cold plate 26, transferring the absorbed heat to the refrigerant on the cold side of the evaporator 25. The evaporator 25 also serves as a component of the second liquid cooling line, in which the pipes on the cold side of the evaporator 25 sequentially connect to the compressor 39, the condenser 23, and the expansion valve 24, transferring the heat absorbed by the refrigerant to the coolant on the cold side of the condenser 23. The condenser 23 also serves as a component of the third liquid cooling line, with the pipes on the cold side of the condenser 23 sequentially connecting to the fuel-liquid heat exchanger 21 and the liquid-air heat exchanger 22, transferring the heat absorbed by the coolant to the fuel on the cold side of the fuel-liquid heat exchanger 21. Figure 1 In the diagram, A represents air.
[0039] In some optional embodiments, the first fuel circuit and the second fuel circuit include multiple flow control valves and temperature sensors. Temperature sensors are installed in the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42 and the high-temperature fuel storage space 6. The fuel system based on the multi-temperature zone aircraft fuel tank also includes a controller 61 connected to each flow control valve and temperature sensor. The controller 61 is configured to control the opening degree of each flow control valve to control the fuel input and output flow of the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42 and the high-temperature fuel storage space 6.
[0040] refer to Figure 2 The controller 61 connects to various temperature sensors, flow control valves, electric fuel pumps, and other electronic components. It receives signals from each temperature sensor and controls the operation of the electric fuel pump, four-way valve, and flow control valve. The temperature sensors mainly include: temperature sensor 60 located in the high-temperature fuel storage space 6; temperature sensor 58 located in the low-temperature fuel storage space 34; temperature sensor 59 located in the medium-temperature fuel storage space 42; temperature sensor 57 located in the first fuel circuit; temperature sensors 53, 49-51, and 46-47 located in the second fuel circuit; temperature sensors 52 and 54-56 located in the cooling circuit; and temperature sensor 48 located before the engine 16.
[0041] In some alternative embodiments, the controller 61 is further configured to keep the fuel temperature in the low-temperature fuel storage space 34 below a first set temperature, such as 20°C or 30°C, to keep the fuel temperature in the medium-temperature fuel storage space 42 between the first set temperature and a second set temperature, where the second set temperature can be 60°C or 70°C, etc., and to keep the fuel temperature in the high-temperature fuel storage space 6 above the second set temperature. In this embodiment, the fuel temperature range within the three fuel storage spaces can be set as needed; this is not intended to limit the invention and is merely an example.
[0042] In some optional embodiments, the second fuel circuit, via a four-way valve 1, respectively supplies fuel back to the low-temperature fuel storage space 34, the medium-temperature fuel storage space 42, and the high-temperature fuel storage space 6. When the fuel temperature in the second fuel circuit monitored by the temperature sensor 46 before the four-way valve 1 is lower than the first set temperature, fuel is preferentially supplied to the low-temperature fuel storage space 34. When the fuel temperature in the second fuel circuit monitored by the temperature sensor 46 is higher than the second set temperature, fuel is preferentially supplied to the high-temperature fuel storage space 6. When the fuel temperature in the second fuel circuit monitored by the temperature sensor 46 falls between the first and second set temperatures, fuel is preferentially supplied to the medium-temperature fuel storage space 42. In this embodiment, the controller 61 controls the opening and closing of the valves on each pipeline connected to the four-way valve 1 based on the real-time measurement data of the temperature sensors 46, 58, 59, and 60, ensuring that the fuel temperature in each fuel storage space remains within a defined range. When the fuel temperature T46 measured by temperature sensor 46 is lower than the upper limit of the fuel temperature in the low-temperature fuel storage space 34, the fuel at the outlet of the air-fuel radiator 13 is preferentially sent to the low-temperature fuel storage space 34, and secondarily sent to the medium-temperature fuel storage space 42 or the high-temperature fuel storage space 6; when the fuel temperature T46 measured by temperature sensor 46 is lower than the upper limit of the fuel temperature in the medium-temperature fuel storage space 42, the fuel at the outlet of the air-fuel radiator 13 is preferentially sent to the medium-temperature fuel storage space 42, and secondarily sent to the high-temperature fuel storage space 6 or the low-temperature fuel storage space 34; when the fuel temperature T46 measured by temperature sensor 46 is higher than the upper limit of the fuel temperature in 42, the fuel at the outlet of the air-fuel radiator 13 is preferentially sent to the high-temperature fuel storage space 6, and secondarily sent to the medium-temperature fuel storage space 42 or the low-temperature fuel storage space 34.
[0043] In some alternative embodiments, the controller 61 is further configured to first supply fuel from the high-temperature fuel storage space 6 to the engine 16 via the fuel supply line, and then supply fuel to the engine 16 via the second fuel circuit. In this embodiment, the controller 61 controls the opening of flow control valves 12, 14, 44, and 17 according to the engine's real-time fuel flow and inlet temperature requirements, and prioritizes the use of fuel from the high-temperature fuel storage space 6.
[0044] In some alternative embodiments, the controller 61 is further configured to first supply fuel to the second fuel circuit using fuel from the medium-temperature fuel storage space 42, and then supply fuel to the second fuel circuit using fuel from the low-temperature fuel storage space 34 and the high-temperature fuel storage space 6. In this embodiment, the controller 61 controls the opening of the flow control valve 11 and the flow control valve 40 based on real-time measurement data from temperature sensors 49, 50, 51, 52, 53, 54, 58, and 59, ensuring that the fuel-side inlet / outlet temperatures of the fuel-lubricating oil radiator 19, the fuel-hydraulic oil radiator 20, and the fuel-liquid heat exchanger 21 do not exceed the usage limits, and preferentially uses fuel from the medium-temperature fuel storage space 42.
[0045] Compared with the prior art, this application has the following advantages:
[0046] (1) Improved performance. The design of storing fuel in temperature zones enables the tiered utilization of fuel, and at the same time, it can maximize the delivery of high-temperature fuel into the engine combustion chamber, which can effectively improve the utilization rate of the fuel heat sink.
[0047] (2) Improve heat dissipation capacity. The fuel system design method illustrated in this application can obtain low-temperature fuel and store it in the low-temperature fuel storage space of the airborne fuel tank, ensuring the immediacy of heat dissipation response to airborne equipment and effectively improving the overall heat dissipation capacity of the aircraft.
[0048] (3) Easy to implement. Since this application includes, but is not limited to, dividing a fuel tank into three independent storage spaces, or can be composed of multiple temperature zone storage spaces within two or more fuel tanks, it is easy to implement. At the same time, compared with the traditional aircraft fuel system, it only adds components such as a four-way valve, heat insulation material, flow control valve, three-way valve, temperature sensor and related fuel heat exchange pipelines, achieving the goal of improving the overall performance of the system at a relatively low cost.
[0049] (4) High versatility. Since this application includes, but is not limited to, dividing the aircraft fuel tank into storage spaces with three temperature zones, it can be used by selecting any two or more temperature zones from the multi-temperature zone aircraft fuel tank in combination with specific application scenarios; at the same time, it can be supplied by fuel in any one temperature zone storage space alone or by fuel in different temperature zone storage spaces mixed together, and different fuel supply methods can be flexibly switched, making it highly versatile.
[0050] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A fuel system based on a multi-temperature zone aircraft fuel tank, characterized in that, It includes multiple fuel storage spaces to store fuel at different temperatures. The low-temperature fuel separately forms a first fuel circuit, the high-temperature fuel supplies fuel to the engine, and the low-temperature fuel and high-temperature fuel are mixed to form a second fuel circuit. The second fuel circuit selectively supplies fuel to the engine or flows back to different fuel storage spaces according to the fuel temperature. Multiple fuel storage spaces include a low-temperature fuel storage space (34), a medium-temperature fuel storage space (42), and a high-temperature fuel storage space (6). The low-temperature fuel storage space (34) exchanges heat with the cooling pipe through a first fuel circuit, absorbing heat from the first fuel circuit. The low-temperature fuel storage space (34), the medium-temperature fuel storage space (42), and the high-temperature fuel storage space (6) are connected to a second fuel circuit through a flow control valve. The second fuel circuit includes multiple heat exchangers or radiators to heat the fuel. After the fuel is heated, it flows through a three-way valve (18). Selectively, a portion of the fuel is exported from the second fuel circuit and fed into the engine (16). The remaining fuel continues to be selectively distributed along the second fuel circuit into the low-temperature fuel storage space (34), the medium-temperature fuel storage space (42), and the high-temperature fuel storage space (6). Among the multiple heat exchangers or radiators, at least one fuel-liquid heat exchanger (21) is included to heat the fuel in the second fuel circuit by means of the heat absorbed by the cooling pipes from the first fuel circuit. The high-temperature fuel storage space (6) also includes a fuel supply line directly connected to the engine (16). The cooling pipeline includes a first liquid cooling pipeline, which absorbs the fuel heat of the first fuel circuit through a liquid-fuel radiator (27) and transfers the heat to a second liquid cooling pipeline through an evaporator (25). The second liquid cooling pipeline transfers the heat to a third liquid cooling pipeline through a condenser (23). The third liquid cooling pipeline transfers the heat to the second fuel circuit through a fuel-liquid heat exchanger (21).
2. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 1, characterized in that, The low-temperature fuel storage space (34), the medium-temperature fuel storage space (42) and the high-temperature fuel storage space (6) are formed by dividing the same fuel tank into multiple storage spaces.
3. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 2, characterized in that, The low-temperature fuel storage space (34), the medium-temperature fuel storage space (42) and the high-temperature fuel storage space (6) are separated by structural frame plates and heat insulation materials.
4. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 1, characterized in that, The second fuel circuit also includes a fuel-hydraulic oil radiator (20), a fuel-lubricating oil radiator (19), and an air-fuel radiator (13), wherein the fuel-liquid heat exchanger (21), the fuel-hydraulic oil radiator (20), and the fuel-lubricating oil radiator (19) are located before the three-way valve (18) of the second fuel circuit, and the air-fuel radiator (13) is located after the three-way valve (18) of the second fuel circuit.
5. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 1, characterized in that, The first fuel circuit and the second fuel circuit include multiple flow control valves and temperature sensors. Temperature sensors are provided in the low-temperature fuel storage space (34), the medium-temperature fuel storage space (42) and the high-temperature fuel storage space (6). The fuel system based on the multi-temperature zone aircraft fuel tank also includes a controller (61) connected to each flow control valve and temperature sensor. The controller (61) is configured to control the opening of each flow control valve to control the fuel input and output flow of the low-temperature fuel storage space (34), the medium-temperature fuel storage space (42) and the high-temperature fuel storage space (6).
6. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 5, characterized in that, The controller (61) is also configured to lower the fuel temperature of the low-temperature fuel storage space (34) below the first set temperature, lower the fuel temperature of the medium-temperature fuel storage space (42) between the first set temperature and the second set temperature, and lower the fuel temperature of the high-temperature fuel storage space (6) above the second set temperature.
7. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 6, characterized in that, The second fuel circuit supplies fuel back to the low-temperature fuel storage space (34), the medium-temperature fuel storage space (42), and the high-temperature fuel storage space (6) respectively through the four-way valve (1). When the fuel temperature in the second fuel circuit monitored by the temperature sensor (46) before the four-way valve (1) is lower than the first set temperature, the fuel is preferentially input into the low-temperature fuel storage space (34). When the fuel temperature in the second fuel circuit monitored by the temperature sensor (46) is higher than the second set temperature, the fuel is preferentially input into the high-temperature fuel storage space (6). When the fuel temperature in the second fuel circuit monitored by the temperature sensor (46) is between the first set temperature and the second set temperature, the fuel is preferentially input into the medium-temperature fuel storage space (42).
8. The fuel system based on a multi-temperature zone aircraft fuel tank as described in claim 6, characterized in that, The controller (61) is also configured to: First, fuel from the high-temperature fuel storage space (6) is supplied to the engine (16) through the fuel supply line, and then fuel is supplied to the engine (16) through the second fuel circuit. First, fuel from the medium-temperature fuel storage space (42) is used to supply fuel to the second fuel circuit, and then fuel from the low-temperature fuel storage space (34) and the high-temperature fuel storage space (6) is used to supply fuel to the second fuel circuit.