Distributed intelligent cooling system and cooling method for aviation heavy oil engine

Abstract

The invention discloses a distributed intelligent cooling system and method for an aviation heavy oil engine. The system comprises a distributed cooling loop, an intelligent flow adjusting device, a miniature radiator, an additional cooling branch and a cooling water pump. Parallel cooling branches of the distributed cooling loop independently cool different parts of the engine, efficient heat exchange is achieved through the miniature radiator, and the intelligent flow adjusting device adjusts the flow according to the temperature of cooling liquid. The additional cooling branch enhances the heat dissipation capacity under special working conditions, and the number of the miniature radiators can be dynamically adjusted. The cooling method comprises the steps of collecting cooling liquid temperature signals, comparing threshold values, adjusting the opening degree of the electric flow adjusting valve and independently cooling all the air cylinders. And in the cold start stage, flow is reduced to accelerate preheating, alarm is triggered under extreme working conditions, and redundant branches are switched. The problems that a traditional cooling system is uneven in heat dissipation, large in weight, poor in adaptability and the like are solved, and the heat dissipation efficiency, reliability and environmental adaptability are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation heavy oil engine cooling, and in particular to a distributed intelligent cooling system and a cooling method for an aviation heavy oil engine. Background Art

[0002] With the rapid development of general aviation and low-altitude economy, aviation heavy oil engines have gradually become the core power units of small aircraft and UAVs due to their low fuel consumption, high power density and long endurance. However, the high power density and long-term high-load operation characteristics have led to a sharp increase in the heat generation of aviation heavy oil engines, and their thermal management faces severe challenges. Especially in plateaus, low pressure and extreme temperature environments, the efficiency and reliability of the engine cooling system directly determine the power performance and safety. In addition, the strict requirements of aviation engines on power-to-weight ratio, volume and weight make it difficult for traditional cooling systems to take into account both efficient heat dissipation and lightweight design. An innovative cooling technology is urgently needed to break through the existing bottleneck.

[0003] At present, the cooling technology of aircraft engines mainly includes two methods: air cooling and liquid cooling. The air-cooled system dissipates heat through air convection, but its heat dissipation capacity is limited and it is difficult to meet the heat load requirements of high-power density engines. The liquid-cooled system achieves efficient heat dissipation through coolant circulation. The existing technology mostly adopts a centralized cooling structure, that is, a single cooling circuit covers the entire engine. For example, the patent with publication number CN102678253A proposes a distributed liquid cooling system, which cools the cylinder head, cylinder block and other parts respectively through multiple sets of cooling devices, but it relies on heater-assisted temperature control and does not consider the special requirements of aircraft engines for weight and reliability. Another patent with publication number CN109209600A designs a parallel forced cooling and windward cooling system, which adjusts the cooling flow through the control valve group to optimize energy consumption, but the additional valve group structure reduces the system reliability and is not adapted to the plateau and closed working conditions of aircraft engines.

[0004] The existing technology has the following main problems: (1) Limitations of centralized cooling systems: Traditional liquid cooling systems use a single cooling circuit. When the engine is running at high load, the heat distribution is uneven, which can easily lead to local overheating or insufficient cooling capacity. In addition, the system is large in size and weight, making it difficult to meet the lightweight requirements of aircraft engines.

[0005] (2) Insufficient adaptability of existing distributed systems: Although some distributed cooling technologies optimize heat dissipation efficiency through multi-branch design, they rely on complex control valve groups or external heating devices, which increases system complexity and failure rate and cannot meet the high reliability requirements of aircraft engines.

[0006] (3) Poor adaptability to extreme environments: Existing technologies are mostly designed for normal temperature and pressure environments, and do not fully consider the impact of aviation conditions such as plateau low pressure and extreme temperatures on heat dissipation performance, resulting in a significant decrease in the efficiency of the cooling system at high altitudes or in closed environments.

[0007] In summary, the existing aviation heavy fuel oil engine cooling technology has obvious defects in meeting the requirements of efficient, stable and reliable cooling. An innovative cooling system is urgently needed to break through these bottlenecks and ensure the high performance operation, safety and stability of aviation heavy fuel oil engines. Summary of the invention

[0008] Purpose of the invention: In order to overcome the deficiencies of the prior art, the present invention provides a distributed intelligent cooling system and cooling method for aviation heavy fuel engines, which optimizes the coolant distribution through distributed cooling loops and parallel-connected micro-radiators to reduce the weight and volume of the system; combines an intelligent flow regulating device to regulate the coolant flow in real time to improve heat dissipation efficiency and reliability; and utilizes additional cooling branches and dynamic adjustment mechanisms to enhance adaptability to high altitudes, extreme temperatures and high load conditions, while shortening the engine preheating time through flow control in the cold start phase, thereby solving the technical problems of uneven heat dissipation, excessive weight, poor environmental adaptability of traditional centralized cooling systems, and insufficient reliability of existing distributed systems.

[0009] Technical solution: In order to achieve the above-mentioned purpose, the present invention provides a distributed intelligent cooling system for aviation heavy oil engines, including: a distributed cooling circuit, an intelligent flow regulating device, a micro radiator, an additional cooling branch, and a cooling water pump. The distributed cooling circuit includes a plurality of cooling branches arranged in parallel, and the cooling branches are respectively connected to the engine cylinders for independently cooling different parts of the engine; the micro radiator is arranged in the cooling branch for realizing efficient heat exchange in a compact space. The micro radiator is suitable for compact space and can be flexibly arranged in the limited space of the aircraft engine without occupying too much space resources, which is helpful to optimize the overall structural design of the engine and improve space utilization; the intelligent flow regulating device includes a temperature A temperature sensor, an electric flow control valve and an intelligent cooling control unit, wherein the temperature sensor monitors the coolant temperature in real time and transmits a signal to the intelligent cooling control unit, and the intelligent cooling control unit controls the electric flow control valve to adjust the coolant flow according to the signal, thereby avoiding excessive circulation of the coolant, reducing unnecessary energy consumption, and reducing the energy consumption of the engine to a certain extent, thereby improving fuel economy; the additional cooling branch is connected in parallel to the high-temperature return water main, and is equipped with a micro radiator and an electronic fan to enhance the heat dissipation capacity under high load, high altitude or closed environment; the cooling water pump is connected to the engine crankshaft to provide power for the coolant circulation, thereby ensuring that the coolant continues to flow in the entire cooling system and realizing effective heat transfer.

[0010] Furthermore, in the distributed intelligent cooling system for aviation heavy fuel engines described in this application, the number of micro radiators can be dynamically adjusted based on the engine operating environment, and micro radiators can be added in series or in parallel to adapt to the cooling requirements in high altitude or low temperature environments. By adding micro radiators in series or in parallel, the system can more accurately match the cooling requirements of the engine in different environments. In high altitude environments, the air density decreases and the cooling efficiency decreases. Adding a radiator in series can increase the cooling travel and time of the coolant; in low temperature environments, adding a radiator in parallel can expand the cooling area to ensure that the engine is always at the optimal operating temperature.

[0011] Furthermore, in the distributed intelligent cooling system for aviation heavy oil engines described in the present application, the intelligent cooling control unit is also equipped with an abnormal alarm module. When the coolant flow, temperature or pressure exceeds the threshold, the alarm is triggered and the flow is automatically adjusted or the electronic fan is started. The automatic monitoring, alarm and adjustment functions of the system cooperate with each other to enhance the reliability and stability of the cooling system.

[0012] Furthermore, in the distributed intelligent cooling system of an aviation heavy oil engine described in the present application, the parallel design of the cooling branch includes a low-temperature water inlet branch and a high-temperature water return branch, which are respectively connected to the engine cooling water inlet and the high-temperature water outlet to ensure the consistency of the cooling temperature of each cylinder. The cooling branch adopts a parallel design so that each cylinder can have a relatively independent cooling cycle path. The low-temperature water inlet branch transports the low-temperature coolant to the engine cooling water inlet to provide the low-temperature medium required for cooling each cylinder; the high-temperature water return branch collects the high-temperature coolant from the engine high-temperature water outlet to form a complete circulation process. Through this parallel low-temperature water inlet branch and high-temperature water return branch design, it can be ensured that the coolant is distributed to each cylinder with a relatively uniform flow rate and temperature. The coolant conditions received by each cylinder are similar, thereby ensuring that the cooling temperature of each cylinder remains consistent, avoiding the overall performance of the engine being affected by insufficient or excessive cooling of individual cylinders.

[0013] Further, in the present application, a distributed intelligent cooling system for an aviation heavy oil engine is described, wherein the micro radiator adopts a fin plate structure, including a radiator inlet, a radiator main pipe, a radiator branch pipe, a radiator fin and a radiator outlet. The radiator fins of the fin plate micro radiator adopt a high thermal conductivity composite material, and the distribution density of the radiator branch pipe is optimized based on the engine heat load distribution. The micro radiator uses a fin plate structure, which can significantly increase the contact area between the coolant and the air. The coolant flows in from the radiator inlet and is distributed to each radiator branch pipe through the radiator main pipe. In the process of flowing through the branch pipe, the heat is quickly transferred to the surrounding air with the help of the radiator fins, and finally flows out from the radiator outlet to achieve efficient heat exchange. The distribution density of the radiator branch pipe is optimized according to the engine heat load distribution. In the area where the engine heat load is high, the distribution density of the branch pipe is increased so that more coolant can flow through the area to enhance the heat dissipation effect; and in the area where the heat load is low, the branch pipe density is appropriately reduced, so as to reasonably distribute the coolant flow and improve the heat dissipation efficiency of the entire cooling system.

[0014] Furthermore, the distributed intelligent cooling system for aviation heavy oil engines described in the present application also includes a radiator interconnection pipeline, which is used to connect the engine's built-in radiator with the additional micro-radiator to form a multi-stage heat dissipation network. The radiator interconnection pipeline connects the engine's built-in radiator with the additional micro-radiator to form a multi-stage heat dissipation structure. The coolant can flow through different radiators in sequence. After multiple heat dissipation treatments, the temperature of the coolant can be more effectively reduced, and the heat dissipation capacity of the entire cooling system can be enhanced. The interconnection pipeline provides a channel for the coolant to flow from the engine's built-in radiator to the additional micro-radiator, or to flow in the opposite direction, ensuring that the coolant can circulate smoothly in the multi-stage heat dissipation network, so that each radiator can fully play its role.

[0015] Furthermore, in a distributed intelligent cooling system for an aviation heavy oil engine described in the present application, the adjustment logic of the electric flow control valve includes: when the coolant temperature is lower than a first preset threshold value, reducing the flow rate to shorten the engine preheating time, allowing the engine to reach a suitable operating temperature more quickly, and allowing the engine to enter an efficient operation state as soon as possible; when the coolant temperature is higher than a second preset threshold value, increasing the flow rate to allow more low-temperature coolant to enter the engine, accelerating heat dissipation or starting an additional micro radiator and electronic fan to enhance heat dissipation.

[0016] The present invention also provides a cooling method for an aviation heavy oil engine, based on the above-mentioned distributed intelligent cooling system for an aviation heavy oil engine, comprising the following steps: S1: collect coolant temperature signals in real time through temperature sensors; S2: The intelligent cooling control unit compares the temperature signal with a first preset threshold and a second preset threshold; S3: Dynamically adjust the opening of the electric flow control valve according to the comparison results, specifically including: If the temperature is below a first threshold, reducing the coolant flow rate to accelerate engine warm-up; If the temperature is higher than the second threshold, the flow rate is increased or an additional micro radiator and an electronic fan are started for forced heat dissipation; S4: Cool each cylinder independently through parallel cooling branches to ensure temperature balance; Furthermore, the cooling method of an aviation heavy fuel engine described in the present application also includes: during the cold start phase of the engine, shortening the preheating time by reducing the coolant flow; in extreme environments or overload conditions, triggering an alarm and switching to a redundant cooling branch to maintain heat dissipation capacity.

[0017] It can be seen from the above technical solution that the present invention has the following beneficial effects: The distributed intelligent cooling system for aviation heavy oil engines described in the present invention independently cools different parts of the engine through multiple cooling branches arranged in parallel in a distributed cooling circuit, thereby solving the problem of uneven heat distribution in traditional centralized cooling systems, which easily leads to local overheating or insufficient cooling, and at the same time reduces the volume and weight of the system; by setting a micro radiator in the cooling branch, using a fin plate structure and fins made of high thermal conductivity composite materials, efficient heat exchange is achieved in a compact space, and the branch pipe density is optimized based on the engine heat load distribution, the coolant flow is reasonably distributed, and the heat dissipation efficiency is improved; the coolant temperature is monitored in real time through an intelligent flow regulating device and the electric flow regulating valve is adjusted The opening degree can accelerate preheating during cold start and enhance heat dissipation at high temperature, thereby improving fuel economy and engine life; the heat dissipation capacity is enhanced under high load, high altitude or closed environment through additional cooling branches; the engine's built-in radiator and additional micro-radiator are connected through radiator interconnection pipes to form a multi-level heat dissipation network, which can more effectively reduce the coolant temperature; the coolant parameters are monitored in real time through the abnormal alarm module of the intelligent cooling control unit, and an alarm is triggered and automatically adjusted when the threshold is exceeded, thereby enhancing the reliability and stability of the system; the number of micro-radiators can be dynamically adjusted based on the engine working environment to accurately match the heat dissipation requirements in different environments, thereby improving the adaptability of the system in extreme environments.

[0018] A cooling method for an aviation heavy oil engine described in the present invention collects coolant temperature signals in real time through a temperature sensor to provide a data basis for subsequent intelligent adjustment; compares the temperature signal with a preset threshold through an intelligent cooling control unit, and dynamically adjusts the opening of an electric flow control valve according to the comparison result, thereby reducing the flow rate to accelerate preheating during cold start, increasing the flow rate at high temperature or starting additional heat dissipation equipment to force heat dissipation, thereby ensuring that the engine can quickly enter and maintain an efficient operating state; independently cools each cylinder through a parallel cooling branch to ensure that the cooling temperature of each cylinder is consistent, thereby improving the overall performance of the engine; shortens the preheating time by reducing the coolant flow rate during the cold start phase of the engine, and triggers an alarm and switches to a redundant cooling branch under extreme environments or overload conditions, thereby enhancing the stability and reliability of the engine under special conditions, and ensuring the high-performance operation and safe and stable operation of the aviation heavy oil engine in complex environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of a distributed intelligent cooling system for an aviation heavy fuel oil engine; Figure 2 It is the control logic of a distributed intelligent cooling system for aviation heavy fuel oil engines; Figure 3 This is a schematic diagram of the micro radiator structure.

[0020] Explanation of the markings in the specification: 1-high-temperature return water branch, 2-high-temperature return water main, 3-additional cooling branch, 4-additional micro radiator, 5-electronic fan, 6-cooling temperature control unit, 7-temperature sensor, 8-engine built-in radiator, 9-radiator connecting pipeline, 10-electric flow regulating valve, 11-low-temperature cooling water circuit, 12-cooling water pump, 13-engine low-temperature water inlet pipeline, 14-engine cooling water inlet, 15-low-temperature water inlet branch, 16-engine high-temperature water outlet, 17-engine cylinder, 18-radiator inlet, 19-radiator main pipe, 20-radiator branch, 21-radiator fins, 22-radiator mounting bracket, 23-radiator outlet, 24-intelligent cooling control unit. DETAILED DESCRIPTION

[0021] Example 1 This embodiment provides a specific implementation of a distributed intelligent cooling system for aviation heavy fuel oil engines. Figures 1 to 3 Describe in detail the system's composition, connection relationships and control logic.

[0022] 1. System structure (1) Distributed cooling circuit: It includes a low-temperature water inlet branch 15 and a high-temperature water return branch 1 arranged in parallel, which are respectively connected to the engine cooling water inlet 14 and the engine high-temperature water outlet 16. Each engine cylinder 17 corresponds to an independent cooling branch. The low-temperature water inlet branch 15 distributes the coolant evenly to each cylinder through a splitter, and the high-temperature water return branch 1 collects the high-temperature coolant of each cylinder through the high-temperature water return main pipe 2.

[0023] (2) Micro radiator 4: Fin plate structure (see Figure 3 ), including radiator inlet 18, radiator main pipe 19, radiator branch pipe 20, radiator fin 21 and radiator outlet 23. The radiator fin is made of high thermal conductivity aluminum alloy composite material, and the branch pipe distribution density is optimized according to the engine heat load distribution. The branch pipe density in the area with high heat load is increased by 30%.

[0024] (3) Intelligent flow control device: including temperature sensor 7, electric flow control valve 10 and intelligent cooling control unit 24. The temperature sensor 7 is installed in the high-temperature return water main pipe 2 and the low-temperature cooling water circuit 11 to monitor the coolant temperature in real time; the electric flow control valve 10 is set at the entrance of the low-temperature water inlet branch 15, and the opening is controlled by the intelligent cooling control unit 24 according to the temperature signal.

[0025] (4) Additional cooling branch 3: connected in parallel to the high-temperature return water main pipe 2, equipped with an additional micro radiator 4 and an electronic fan 5. The additional micro radiator 4 is connected to the engine's own radiator 8 through a radiator connecting pipe 9 to form a multi-level heat dissipation network.

[0026] (5) Cooling water pump 12: It is connected to the engine crankshaft through a belt drive. The speed is adjusted synchronously with the engine speed to ensure that the coolant circulation flow rate matches the engine load.

[0027] 2. Control logic and workflow (1) Cold start phase: When the engine is started, the coolant temperature is lower than the first preset threshold (60°C), and the intelligent cooling control unit 24 controls the electric flow control valve 10 to reduce its opening to 30%, thereby limiting the coolant flow and accelerating engine preheating.

[0028] The coolant in the low-temperature cooling water circuit 11 enters the engine cylinder 17 through the engine low-temperature water inlet pipe 13, absorbs heat, and returns to the micro radiator 4 through the high-temperature return water branch 1.

[0029] (2) Normal working conditions: When the temperature sensor 7 detects that the coolant temperature is in the range of 60°C to 90°C, the opening of the electric flow control valve 10 is adjusted to 70% to 100% to maintain normal heat dissipation requirements.

[0030] Each engine cylinder 17 achieves temperature balance through an independent cooling branch, and the temperature difference is controlled within ±2°C.

[0031] (3) High load or high altitude conditions: If the coolant temperature exceeds the second preset threshold (90°C), the intelligent cooling control unit 24 triggers the following operations: a. The opening degree of the electric flow regulating valve 10 is increased to 100%, and the additional micro radiator 4 and the electronic fan 5 are started at the same time.

[0032] b. The additional cooling branch 3 is opened, and the high-temperature coolant is diverted to the additional micro radiator 4, and the heat dissipation is enhanced through the fin plate structure.

[0033] c. If the temperature continues to rise to 95°C, the abnormal alarm module triggers an audible and visual alarm and automatically switches to the redundant cooling branch.

[0034] (4) Extreme low temperature environment: In an environment of -30°C, the cooling path of the coolant is extended by connecting an additional micro radiator 4 in series to avoid overcooling; at the same time, the speed of the electronic fan 5 is reduced to prevent excessive heat dissipation.

[0035] 3. Dynamic adjustment and redundancy design Adjustment of the number of micro radiators: In high altitude areas (>4000 meters above sea level), the heat dissipation area is increased by 40% by connecting two additional micro radiators 4 in series; in low temperature environments (<-20°C), 4 additional micro radiators are connected in parallel to expand the heat dissipation area while reducing the heat dissipation intensity.

[0036] Redundant branch switching: When the main cooling branch fails, the intelligent cooling control unit 24 automatically switches to the backup branch and calls the engine's built-in radiator 8 for emergency cooling through the radiator connecting pipe 9.

[0037] 4. Optimization of radiator structure The radiator branches 20 of the micro radiator 4 are designed with staggered distribution, and the branch spacing is 5 mm in the high temperature zone and 10 mm in the low temperature zone; the surface of the radiator fin 21 is sprayed with a nano-ceramic coating to improve the heat radiation efficiency.

[0038] 5. Implementation Effect The warm-up time during the cold start phase is shortened by 40%, allowing the engine to quickly reach the optimal operating temperature.

[0039] Under high-load conditions, the heat dissipation efficiency is improved by 35%, and the cylinder temperature difference is controlled within ±2°C.

[0040] At an altitude of 5000 meters, the system maintains a stable heat dissipation capacity without power attenuation through the coordinated work of the additional heat sink and the electronic fan 5.

[0041] Example 2 This embodiment provides a specific implementation step of a cooling method for an aviation heavy fuel oil engine: (1) Temperature signal acquisition: The temperature of the coolant in the high-temperature return water main 2 and the low-temperature cooling water circuit 11 is collected in real time by the temperature sensor 7, with a sampling frequency of 10 Hz.

[0042] (2) Threshold comparison and adjustment: The intelligent cooling control unit 24 compares the temperature signal with the preset threshold (60°C, 90°C): If the temperature is <60℃, control the electric flow control valve 10% to 30% opening, reduce the flow rate to accelerate preheating.

[0043] If the temperature is >90°C, the valve opening is controlled to 100%, and the additional micro radiator 4 and the electronic fan 5 are started.

[0044] (3) Independent cooling control: Each cylinder 17 is cooled independently through parallel cooling branches (15, 1), and a splitter is used to ensure that the flow deviation of each branch is less than 5%.

[0045] (4) Handling of extreme working conditions: When the coolant temperature exceeds 95°C or the pressure is abnormal, an alarm is triggered and the redundant branch is switched. At the same time, a multi-level cooling network is called through the radiator connecting pipeline 9.

[0046] Explanation of the attached figure: Figure 1 In the middle, the high-temperature return water branch 1 is connected in parallel with the additional cooling branch 3 to form a main and auxiliary dual heat dissipation channel.

[0047] Figure 2 The control logic diagram shows the closed-loop control process of temperature signal → threshold comparison → valve adjustment → heat dissipation enhancement.

[0048] Figure 3 In the schematic diagram of the micro radiator structure, the density distribution of the radiator branch pipes 20 corresponds one to one with the engine heat load area.

[0049] The above embodiments are exemplary, and their purpose is to illustrate the technical concept and features of the present invention so that people familiar with the technology in this field can understand the content of the present invention and implement it accordingly, and they cannot be used to limit the protection scope of the present invention. Any equivalent changes or modifications made according to the spirit of the present invention should be included in the protection scope of the present invention.

Claims

1. A distributed intelligent cooling system for aviation heavy oil engines, characterized in that: include: A distributed cooling circuit, the distributed cooling circuit comprising a plurality of cooling branches arranged in parallel, the cooling branches being respectively connected to the engine cylinders for independently cooling different parts of the engine; A micro radiator, which is arranged in a cooling branch and is used to achieve efficient heat exchange in a compact space; An intelligent flow regulating device, the intelligent flow regulating device comprising a temperature sensor, an electric flow regulating valve and an intelligent cooling control unit, the temperature sensor monitors the coolant temperature in real time and transmits a signal to the intelligent cooling control unit, and the intelligent cooling control unit controls the electric flow regulating valve to adjust the coolant flow according to the signal; An additional cooling branch, which is connected in parallel to the high-temperature return water main and is equipped with a micro radiator and an electronic fan to enhance the heat dissipation capacity under high load, high altitude or closed environment; A cooling water pump is connected to the engine crankshaft to provide power for coolant circulation.

2. The distributed intelligent cooling system for aviation heavy fuel oil engines according to claim 1 is characterized in that: The number of the micro radiators can be dynamically adjusted based on the engine operating environment, and the heat dissipation requirements can be adapted by adding micro radiators in series or in parallel in high altitude or low temperature environments.

3. The distributed intelligent cooling system for aviation heavy oil engines according to claim 1 is characterized in that: The intelligent cooling control unit is also equipped with an abnormal alarm module, which triggers an alarm and automatically adjusts the flow or starts the electronic fan when it detects that the coolant flow, temperature or pressure exceeds a threshold.

4. The distributed intelligent cooling system for aviation heavy fuel oil engines according to claim 1 is characterized in that: The parallel design of the cooling branches includes a low-temperature water inlet branch and a high-temperature water return branch, which are respectively connected to the engine cooling water inlet and high-temperature water outlet to ensure the consistency of the cooling temperature of each cylinder.

5. The distributed intelligent cooling system for aviation heavy fuel oil engines according to claim 1 is characterized in that: The micro radiator adopts a fin plate structure, including a radiator inlet, a radiator main pipe, a radiator branch pipe, a radiator fin and a radiator outlet. The radiator fins of the fin plate micro radiator are made of high thermal conductivity composite materials, and the distribution density of the radiator branch pipe is optimized based on the engine heat load distribution.

6. The distributed intelligent cooling system for aviation heavy fuel oil engines according to claim 1 is characterized in that: It also includes a radiator connecting pipeline for connecting the engine's own radiator with the additional micro radiator to form a multi-level heat dissipation network.

7. The distributed intelligent cooling system for aviation heavy fuel oil engines according to claim 1 is characterized in that: The regulation logic of the electric flow control valve includes: when the coolant temperature is lower than a first preset threshold, reducing the flow to shorten the engine preheating time; when the coolant temperature is higher than a second preset threshold, increasing the flow or starting an additional micro radiator and an electronic fan to enhance heat dissipation.

8. A cooling method for an aviation heavy fuel oil engine, based on the distributed intelligent cooling system for an aviation heavy fuel oil engine according to any one of claims 1 to 7, characterized in that: The following steps are involved: S1: collect coolant temperature signals in real time through temperature sensors; S2: The intelligent cooling control unit compares the temperature signal with a first preset threshold and a second preset threshold; S3: Dynamically adjust the opening of the electric flow control valve according to the comparison results, specifically including: If the temperature is below a first threshold, reducing the coolant flow rate to accelerate engine warm-up; If the temperature is higher than the second threshold, the flow rate is increased or an additional micro radiator and an electronic fan are started for forced heat dissipation; S4: Each cylinder is cooled independently through parallel cooling branches to ensure temperature balance.

9. The cooling method of an aviation heavy oil engine according to claim 8, characterized in that: Also includes: During the cold start phase of the engine, the warm-up time is shortened by reducing the coolant flow; In extreme environments or overload conditions, an alarm is triggered and the system switches to the redundant cooling branch to maintain heat dissipation capacity.

Images