Integrated aviation hybrid oil cooling system and aviation hybrid aircraft

Abstract

The application discloses an integrated aviation hybrid power oil cooling system and an aviation hybrid power aircraft, and belongs to the technical field of aviation hybrid power aircrafts. The integrated aviation hybrid power oil cooling system comprises a fan, a fan flow channel piece with an annular flow channel, an annular radiator, an oil supply and return pump set, a fan motor, a fan motor controller and an oil tank. The axial ends of the fan flow channel piece are connected with the fan and the annular radiator respectively, so that the annular flow channel is axially communicated with the fan and the annular radiator, and then the cooling airflow generated by the fan enters the annular radiator through the annular flow channel. The inner shaft hole of the fan flow channel piece further forms a hub installation space for installation. The fan motor and the oil supply and return pump set are arranged in the hub installation space respectively, two power output ends of the fan motor are connected with the fan and the oil supply and return pump set respectively, the oil tank is arranged in the shaft hole of the annular radiator, and the fan motor controller is connected with the fan flow channel piece. The overall structure of the application is compact and reasonable, the manufacturing and maintenance costs are low, the weight is small, and the utilization rate of the cooling airflow heat dissipation capacity is high.

Description

Technical Field

[0001] This invention relates to the field of aviation hybrid systems technology, and in particular, to an integrated aviation hybrid power lubricating oil cooling system. Furthermore, this invention also relates to an aviation hybrid aircraft having the aforementioned integrated aviation hybrid power lubricating oil cooling system. Background Technology

[0002] Aviation hybrid systems typically consist of an engine, a generator, and its controller. The engine drives the generator to generate electricity, which is then supplied to the propeller-driven motor to produce airflow that propels the aircraft. Currently, both the generator and its controller experience power losses, which are converted into heat. This heat must be carried away by a cooling medium and transferred to the refrigerant in a heat exchanger. Otherwise, the temperature of the generator and its controller will rise, affecting their performance. Furthermore, to meet the oil supply and return requirements of the generator's internal bearing cavities, a lubrication and cooling system for the generator and its controller is necessary. Flight platform power systems require efficient lubrication and cooling solutions. Traditional systems use separate designs for the lubrication cooling system (including oil pumps and oil filters) and the electric cooling devices (including fans and radiators), resulting in complex and heavy systems that are difficult to integrate to meet high-density requirements.

[0003] The current technical solution is operating as follows: Two independent systems: an oil cooling system and an electric cooling unit, which are connected by oil lines. Both systems include a drive motor and a controller. Both controllers are located in the cooler compartments of the flight platform and are equipped with cooling fans and related flow channels. They are connected to their respective drive motors via long cables.

[0004] The lubricating oil cooling system mainly consists of an electric oil pump, a drive motor and its controller, an oil filter, an oil tank, sensors, valves, and pipelines, and is installed on the side of the engine. The oil pump's supply stage draws oil from the oil tank, pressurizes it, and supplies it to the electric cooling unit via external pipelines. The cooled oil then returns to the system via external pipelines, enters the oil filter for filtration, and is then monitored by pressure / temperature sensors. Finally, the flow rate is regulated by a regulating valve before being supplied to the generator and its controller. The lubricating oil entering the generator and its controller is divided into two return paths: one path returns directly to the oil tank via pipeline, and the other path is the return oil from the two bearing cavities of the generator, drawn back to the oil tank by the two return stages in the oil pump.

[0005] The electric cooling system mainly includes a drive motor and its controller, a fan, a radiator, a temperature control valve, an air intake channel, and an exhaust channel. It is generally installed outside the engine compartment to facilitate the entry and exit of cooling airflow. The fan drive motor drives the fan to rotate and generate cooling airflow, which is supplied to the radiator to cool the lubricating oil.

[0006] The shortcomings of existing technical solutions are as follows: Size and weight issues: The lubricating oil cooling system, electric cooling device, and two drive motors and their controllers are all placed independently and far apart to meet their respective working conditions. This not only occupies a lot of space and is complicated to install, but also increases the system weight due to the connecting pipes and cables, and also limits the design flexibility of the flight platform. Independent system configuration increases costs: Using two independent systems, each driven by a separate set of motors and controllers, increases manufacturing and maintenance costs; High heat dissipation costs: The electric fan consumes a lot of power to generate cooling airflow, but the heat dissipation capacity of the airflow is not fully utilized, resulting in wasted power consumption; at the same time, in order to meet the operating temperature requirements of the controllers of both the oil pump and the fan drive motor, a heat dissipation structure, drive fan and corresponding airflow channels are also configured on the controller, which increases the system cost. Summary of the Invention

[0007] This invention provides an integrated aviation hybrid power lubricating oil cooling system and an aviation hybrid aircraft to solve the technical problems of existing systems, such as large space occupation, complex installation, increased system weight due to interconnecting pipes and cables, limited design flexibility of flight platforms, increased manufacturing and maintenance costs due to the use of two independent systems, and wasted power due to the underutilization of cooling airflow generated by electric fans.

[0008] The technical solution adopted in this invention is as follows: An integrated aviation hybrid power lubricating oil cooling system for generator controller and generator oil supply and return and heat dissipation includes: a fan for generating cooling airflow; a fan flow channel component that is hollow cylindrical and has an axially extending annular flow channel inside; an annular radiator arranged in an annular shape; a supply and return oil pump set for oil supply and return; a fan motor with two opposing power output ends; a fan motor controller connected to the fan motor; and an oil tank for holding lubricating oil. The axial ends of the fan flow channel component are respectively connected to the fan and the annular radiator, so that the annular flow channel axially connects the fan and the annular radiator, thereby allowing the cooling airflow generated by the fan to enter the annular radiator through the annular flow channel. The inner shaft hole of the fan flow channel component also forms a hub mounting space for installation. The fan motor and the supply and return oil pump set are respectively disposed in the hub mounting space, and the two power output ends of the fan motor are respectively connected to the fan and the supply and return oil pump set. The oil tank is installed in the shaft hole of the annular radiator, and the fan motor controller is connected to the fan flow channel component.

[0009] Furthermore, the fan flow channel component is cone-shaped, with its small-diameter end connected to the fan and its large-diameter end connected to the annular heat sink. The inner diameter of the annular flow channel also gradually increases along the direction of the cooling airflow, so that the outlet end of the annular flow channel is matched and connected to the annular heat sink.

[0010] Furthermore, the inner ring surface of the upstream section of the annular flow channel near the fan is provided with multiple air ducts spaced apart in a circumferential direction to introduce the cooling airflow in the annular flow channel into the hub mounting space; the downstream section of the annular flow channel is also provided with multiple support plates spaced apart in a circumferential direction, at least some of which are hollow support plates with hollow holes connecting the hub mounting space and the external space, and the hollow support plates are used to allow the cooling airflow in the hub mounting space to be discharged outward through the hollow holes.

[0011] Furthermore, the fan motor controller is connected to the outer ring surface of the fan flow channel component, and the heat dissipation fins of the fan motor controller are inserted into the annular flow channel after passing through the outer ring surface of the fan flow channel component.

[0012] Furthermore, the oil supply and return pump assembly includes an oil supply pump connected to the oil tank to pump lubricating oil from the oil tank into the annular radiator; an oil filter is also installed on the outer ring surface of the annular radiator, the oil filter is connected to the generator controller through a first oil supply pipe, the generator controller is connected to the generator through a second oil supply pipe, the fan motor is also connected to the first oil supply pipe through a third oil supply pipe, and the fan motor is also connected to the oil tank through a first return oil pipe; a first lubricating oil pressure and temperature combination sensor and a flow regulating valve are also connected sequentially in the first oil supply pipe.

[0013] Furthermore, the oil supply pump is connected to the annular radiator through the internal flow path in the oil tank, and the annular radiator is also connected to the oil filter through its internal flow path; the first oil supply pipe is integrated and arranged on the outer ring surface of the fan flow channel component; the third oil supply pipe enters and exits the hub mounting space through the hollow hole of the hollow support plate.

[0014] Furthermore, the oil supply and return pump assembly also includes a first return oil pump and a second return oil pump arranged side by side. The first return oil pump is connected to the front bearing cavity of the generator through a second return oil pipe, and the second return oil pump is connected to the rear bearing cavity of the generator through a third return oil pipe. The first and second return oil pumps are also connected to the lubricating oil tank through a return oil main pipe. Each of the second and third return oil pipes is also equipped with a return oil filter screen. A magnetic debris detection signal is also installed in the return oil main pipe.

[0015] Furthermore, the lubricating oil tank is also connected to the generator's cooling return oil circuit via a fourth return oil pipe, and the fourth return oil pipe is also connected in sequence to a second lubricating oil pressure and temperature combination sensor and a pressure regulating valve.

[0016] Furthermore, the front and rear bearing cavities of the generator are respectively connected to external ventilation pipes, and the exhaust end of the external ventilation pipes extends close to the oil tank; a vent plug is also connected to the oil tank to allow the oil and gas inside the oil tank to be discharged outward.

[0017] According to another aspect of the invention, an aviation hybrid aircraft is also provided, having an integrated aviation hybrid power lubricating oil cooling system as described above.

[0018] The present invention has the following beneficial effects: Considering the problem that existing solutions involve two separate systems—the oil cooling system and the electric cooling unit—which are distributed separately, significantly increasing system weight and operating costs, this application's integrated aviation hybrid oil cooling system integrates the oil cooling system and the electric cooling unit. It adds fan flow channel components to connect and conduct the fan and annular radiator. The radiator is designed as an annular shape, not only matching the annular flow channel of the fan flow channel components but also utilizing the inner shaft hole of the annular radiator to install the oil tank. Furthermore, the inner shaft hole of the hollow cylindrical fan flow channel components forms a hub mounting space for installing the fan motor and the oil supply and return pump assembly. Therefore, the overall system structure of this application is compact and reasonable, requiring minimal installation space, and the overall layout is simple to install. It also greatly shortens the length of the pipes and cables connecting the structural components, thereby significantly reducing the system weight. This also makes the flight platform design more flexible. On the other hand, considering that the electric motors and their controllers account for a high proportion of the total cost and weight in the two independent systems, the system in this application uses only one fan motor and one fan motor controller. The outputs on both sides of the fan motor drive the oil supply and return pump group and the fan respectively, thereby reducing one electric motor and one controller, significantly reducing the system manufacturing and maintenance costs and system weight. In addition, in the system in this application, the annular radiator is designed in a ring shape and is installed in conjunction with the oil tank. The oil tank is placed at the center of the shaft hole of the annular radiator, which not only makes the overall structure compact, but also, because the annular radiator is placed on the oil supply line, the oil temperature in the oil tank is high. Therefore, the cooling airflow of the fan, which has been cooled by the annular radiator, and the oil in the oil tank can be cooled by the temperature difference between them, further improving the utilization rate of the cooling airflow cooling capacity.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a cross-sectional front view schematic diagram of an integrated aviation hybrid power lubricating oil cooling system according to a preferred embodiment of the present invention; Figure 2 yes Figure 1 Left view schematic diagram of the integrated aviation hybrid power lubricating oil cooling system; Figure 3 yes Figure 1Right view schematic diagram of the integrated aviation hybrid power lubricating oil cooling system; Figure 4 yes Figure 3 Schematic diagram of the cross-sectional structure in the middle BB direction; Figure 5 This is an enlarged schematic diagram of the integrated aviation hybrid power lubricating oil cooling system and some of its structures according to the present invention; Figure 6 yes Figure 5 Schematic diagram of the cross-sectional structure along the CC direction; Figure 7 This is a schematic diagram of the internal flow path of the integrated aviation hybrid power lubricating oil cooling system of the present invention. Figure 1 ; Figure 8 This is a schematic diagram of the internal flow path of the integrated aviation hybrid power lubricating oil cooling system of the present invention. Figure 2 ; Figure 9 This is a schematic diagram of the main structure of the integrated aviation hybrid power lubricating oil cooling system of the present invention; Figure 10 This is a schematic diagram of the integrated aviation hybrid power lubricating oil cooling system of the present invention.

[0021] Legend: 1. Generator controller; 2. Fan; 3. Fan flow channel components; 301. Annular flow channel; 302. Hub mounting space; 303. Air vent; 304. Support plate; 4. Circular radiator; 5. Oil supply and return pump assembly; 51. Oil supply pump; 52. First return pump; 53. Second return pump; 6. Fan motor; 7. Fan motor controller; 71. Heat sink fins; 8. Oil tank; 9. Oil filter; 10. First oil supply pipe; 11. Second oil supply pipe; 12. Third oil supply pipe; 13. First return oil pipe; 14. First oil pressure and temperature combination sensor; 15. Flow regulating valve; 16. Second return oil pipe; 17. Third return oil pipe; 18. Main return oil pipe; 19. Return oil filter screen; 20. Magnetic debris detector; 21. Fourth return oil pipe; 22. Second oil pressure and temperature combination sensor; 23. Pressure regulating valve; 24. External ventilation pipe; 25. Vent plug. Detailed Implementation

[0022] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0023] Those skilled in the art will understand that, unless specifically stated otherwise, the term "comprising" as used in this specification means the presence of the stated features, integers, steps, operations, components, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, and / or combinations thereof. It should be understood that when we say a component is "connected" to another component, it can be directly connected to the other component or connected via an intermediate component. The term "and / or" as used herein includes all or any unit and all combinations of one or more associated listed items. The terms "first" and "second," etc., in this specification and claims are used to distinguish different objects, not to describe a particular order.

[0024] Reference Figure 1 A preferred embodiment of the present invention provides an integrated aviation hybrid power lubricating oil cooling system for supplying and returning oil and dissipating heat from a generator controller 1 and a generator. The system includes: a fan 2 for generating cooling airflow; a fan flow channel component 3, which is hollow cylindrical and has an axially extending annular flow channel 301; an annular radiator 4; a supply and return oil pump assembly 5 for supplying and returning oil; a fan motor 6 with two opposing power output ends; a fan motor controller 7 connected to the fan motor 6; and an oil tank 8 for holding lubricating oil. The axial ends of the fan flow channel component 3 are respectively connected to the fan 2 and the annular radiator 4, so that the annular flow channel 301 axially connects the fan 2 and the annular radiator 4, thereby allowing the cooling airflow generated by the fan 2 to enter the annular radiator 4 through the annular flow channel 301. The inner shaft hole of the fan flow channel component 3 also forms a hub mounting space 302 for installation. The fan motor 6 and the oil supply and return pump group 5 are respectively installed in the hub mounting space 302, and the two power output ends of the fan motor 6 are respectively connected to the fan 2 and the oil supply and return pump group 5. The lubricating oil tank 8 is installed in the shaft hole of the annular radiator 4, and the fan motor controller 7 is connected to the fan flow channel component 3.

[0025] When the integrated aviation hybrid power lubricating oil cooling system of this application is working, after receiving the command from the fan motor controller 7, the fan motor 6 drives the fan 2 to rotate to do work on the air and form a cooling airflow. The cooling airflow enters the annular flow channel 301 of the fan flow channel 3, and then enters the annular radiator 4 under the guidance of the annular flow channel 301 to cool the lubricating oil in the annular radiator 4. At the same time, the fan motor 6 drives the fan 2 to rotate the oil supply and return pump group 5. On the one hand, it draws oil from the lubricating oil tank 8, and the pressurized lubricating oil enters the annular radiator 4 for cooling. After cooling, the lubricating oil is filtered and treated before entering the generator controller 1 to cool the generator controller 1. The lubricating oil that has cooled the generator controller 1 is then supplied to the generator. At the same time, as needed, the lubricating oil in the generator bearing cavity and the lubricating oil in the circuit can also be returned to the lubricating oil tank 8 under the action of the oil supply and return pump group 5, thereby realizing the oil supply, oil return and cooling of the generator.

[0026] Considering the problem that the existing solutions involve two separate systems, the lubricating oil cooling system and the electric cooling device, which significantly increase system weight and operating costs due to their dispersed arrangement, the integrated aviation hybrid lubricating oil cooling system of this application integrates the lubricating oil cooling system and the electric cooling device. A fan flow channel component 3 is added to connect and conduct the fan 2 and the annular radiator 4. The radiator 4 is designed as an annular shape, not only matching the annular flow channel 301 of the fan flow channel component 3, but also utilizing the inner shaft hole of the annular radiator 4 to install the lubricating oil tank 8. Furthermore, the inner shaft hole of the hollow cylindrical fan flow channel component 3 forms a hub mounting space 302 for installing the fan motor 6 and the oil supply and return pump assembly 5. The overall structure of this application system is compact and reasonable, requiring minimal installation space and simplifying installation. It also significantly reduces the length of connecting pipes and cables between structural components, thereby greatly reducing system weight and allowing for more flexible flight platform design. Furthermore, considering the high proportion of motors and their controllers in the total cost and weight of the two independent systems, this application system uses only one fan motor 6 and one fan motor controller 7. The outputs of the fan motor 6 drive the oil supply and return pump group 5 and the fan 2 respectively, thus reducing one motor and one controller, significantly lowering system manufacturing and maintenance costs and system weight. Additionally, in this application system, if... Figure 1 and Figure 2 As shown, the annular radiator 4 is designed in a ring shape and is installed in conjunction with the oil tank 8. The oil tank 8 is placed at the center of the shaft hole of the annular radiator 4, which not only makes the overall structure compact, but also, because the annular radiator 4 is placed on the oil supply line, the oil temperature in the oil tank 8 is high. Therefore, the cooling airflow of the fan 2, which has been cooled by the annular radiator 4, and the temperature difference between the airflow and the oil in the oil tank 8 can be used to cool the oil in the oil tank 8, further improving the utilization rate of the cooling airflow cooling capacity.

[0027] Preferably, such as Figure 1 As shown, the fan flow channel 3 is conical in shape, with its small-diameter end connected to the fan 2 and its large-diameter end connected to the annular radiator 4. The inner diameter of the annular flow channel 301 also gradually increases along the direction of the cooling airflow, so that the outlet end of the annular flow channel 301 is matched and connected to the annular radiator 4. This not only smoothly guides the cooling airflow into the annular radiator 4 to cool the lubricating oil, but also makes the overall structure compact and the layout reasonable. Furthermore, the cooling airflow used to cool the lubricating oil can be used to cool the lubricating oil in the oil tank 8, thereby improving the energy utilization rate of the cooling airflow. In addition, the oil tank 8 and the annular radiator 4 are designed as an integrated unit and have integrated connecting pipes between them.

[0028] Preferably, such as Figure 5 and Figure 6 As shown, the annular flow channel 301, near the upstream section of the fan 2, has multiple air intake holes 303 arranged circumferentially at intervals on its inner annular surface to introduce cooling airflow from the annular flow channel 301 into the hub mounting space 302. The downstream section of the annular flow channel 301 also has multiple support plates 304 arranged circumferentially at intervals. At least some of the support plates 304 are hollow support plates with hollow holes connecting the hub mounting space 302 and the external space. These hollow support plates allow cooling airflow from the hub mounting space 302 to be discharged outwards through the hollow holes. In this preferred embodiment, through the air intake holes 303 and the hollow support plates, air is drawn from the annular flow channel 301 into the hub mounting space 302. After cooling the fan motor 6 and the oil supply and return pump assembly 5, the cooling airflow is discharged from the hollow holes of the circumferentially distributed support plates 304, thereby further reducing the operating temperature of the fan motor 6 and thus reducing system costs.

[0029] During operation, after receiving the command from the fan motor controller 7, the fan motor 6 drives the fan 2 to rotate, doing work on the air and forming a cooling airflow. The cooling airflow enters the annular flow channel 301 of the fan flow channel component 3. At the front of the annular flow channel 301, the airflow passes through the circumferentially distributed air vents 303 and enters the hub mounting space 302. After cooling the fan motor 6 and the oil supply and return pump group 5, it is discharged from the support plate 304 of the fan flow channel component 3. The cooling airflow then enters the annular radiator 4 along the annular flow channel 301, cools the lubricating oil in the annular radiator 4, and flows over the surface of the lubricating oil tank 8, further cooling the lubricating oil in the lubricating oil tank 8.

[0030] Preferably, such as Figure 3 and Figure 4As shown, the fan motor controller 7 is connected to the outer ring surface of the fan flow channel component 3, and the heat dissipation fins 71 of the fan motor controller 7 pass through the outer ring surface of the fan flow channel component 3 and are installed in the annular flow channel 301. Since the ambient temperature and cooling conditions have a significant impact on the cost and weight of the fan motor 6, the oil supply and return pump group 5, and the fan motor controller 7, in this application, the fan motor 6 is lubricated and cooled by integrating relevant oil circuits. At the same time, the fan motor controller 7 is installed outside the fan flow channel component 3, and its heat dissipation fins are placed in the annular flow channel 301, thereby using the cooling airflow to cool the heat dissipation fins.

[0031] Optionally, such as Figure 9 and Figure 10 As shown, the oil supply and return pump assembly 5 includes an oil supply pump 51 connected to the oil tank 8 to pump lubricating oil from the oil tank 8 into the annular radiator 4. An oil filter 9 is also installed on the outer ring surface of the annular radiator 4. The oil filter 9 is connected to the generator controller 1 via a first oil supply pipe 10. The generator controller 1 is connected to the generator via a second oil supply pipe 11. The fan motor 6 is also connected to the first oil supply pipe 10 via a third oil supply pipe 12. The fan motor 6 is also connected to the oil tank 8 via a first return oil pipe 13. A first lubricating oil pressure and temperature combination sensor 14 and a flow regulating valve 15 are also sequentially connected in the first oil supply pipe 10.

[0032] Preferably, such as Figure 9 As shown, the oil supply pump 51 is connected to the annular radiator 4 through the internal flow path in the oil tank 8, and the annular radiator 4 is also connected to the oil filter 9 through its internal flow path. The first oil supply pipe 10 is integrated and arranged on the outer ring surface of the fan flow channel component 3. The third oil supply pipe 12 enters and exits the hub mounting space 302 through the hollow hole of the hollow support plate.

[0033] During operation, the fan motor 6 drives the fan 2 and simultaneously rotates the oil supply pump 51. The oil supply pump 51 draws oil from the lubricating oil tank 8. After being pressurized, the lubricating oil enters the annular radiator 4 through the internal flow path on the lubricating oil tank 8. After being cooled, the lubricating oil directly enters the lubricating oil filter 9 installed on the annular radiator 4. After being cooled and filtered, the lubricating oil passes through the lubricating oil temperature / pressure monitoring point, then through the first oil supply pipe 10 integrated on the fan flow channel component 3, and after the flow rate is regulated by the flow regulating valve 15, it enters the generator controller 1. After cooling the lubricating oil in the generator controller 1, it is supplied to the generator through an external pipeline. At the same time, before being supplied to the generator controller 1, the lubricating oil is also supplied to the fan motor 6 through the second oil supply pipe 11, where it is cooled, and then returned to the lubricating oil tank 8 through the first return oil pipe 13.

[0034] The workflow of this application system is as follows: Figure 7 and Figure 8As shown: a) Oil tank 8 to oil supply pump 51; b) Oil supply pump 51 to annular radiator 4; c) Annular radiator 4 to oil filter 9; d) Oil filter 9 to generator controller 1; e) Oil filter 9 to fan motor 6; f) Fan motor 6 to oil tank 8. By rationally arranging the locations of accessories and interfaces according to the upstream and downstream relationships in the system flow, the length of related pipelines and cables can be minimized, thereby further reducing the system weight.

[0035] Optionally, such as Figure 9 and Figure 10 As shown, the oil supply and return pump group 5 also includes a first return pump 52 and a second return pump 53 arranged side by side. The first return pump 52 is connected to the front bearing cavity of the generator through a second return pipe 16, and the second return pump 53 is connected to the rear bearing cavity of the generator through a third return pipe 17. The first return pump 52 and the second return pump 53 are also connected to the lubricating oil tank 8 through a return oil main pipe 18. Both the second return pipe 16 and the third return pipe are equipped with return oil filters 19. A magnetic debris detection signal 20 is also installed in the return oil main pipe 18.

[0036] Furthermore, such as Figure 9 and Figure 10 As shown, the lubricating oil tank 8 is also connected to the cooling return oil circuit of the generator through the fourth return oil pipe 21 for oil return. The fourth return oil pipe 21 is also connected in sequence to the second lubricating oil pressure and temperature combination sensor 22 and the pressure regulating valve 23.

[0037] During operation, the lubricating oil in the generator returns to the lubricating oil tank 8 in two parts. One part is pumped back to the lubricating oil tank 8 by the first return oil pump 52 and the second return oil pump 53. Before entering the first return oil pump 52 and the second return oil pump 53, it passes through the return oil filter screen 19 and then shares an outlet through the return oil main pipe 18. A magnetic debris detection signal 20 is installed at this outlet to monitor the wear debris in the return oil. The other part is the patrol oil, which returns directly to the lubricating oil tank 8 through the fourth return oil pipe 21. Before returning to the lubricating oil tank 8, it passes through the lubricating oil temperature / pressure monitoring point and the back pressure is adjusted by the pressure regulating valve 23 to meet the working pressure requirements of the internal lubrication points of the generator.

[0038] Preferably, such as Figure 10 As shown, the front and rear bearing cavities of the generator are also connected to external ventilation pipes 24, with the exhaust end of the external ventilation pipes 24 extending close to the oil tank 8 for ventilation of the generator's bearing cavities. A vent plug 25 is also connected to the oil tank 8 to allow oil and gas inside the oil tank 8 to be discharged outwards.

[0039] A preferred embodiment of the present invention also provides an aviation hybrid aircraft having an integrated aviation hybrid power lubricating oil cooling system as described above. Thus, the system of the present invention has a compact and reasonable overall structural layout, requiring no large installation space and simplifying installation. It also significantly shortens the length of pipes and cables connecting structural components, thereby greatly reducing system weight and making the flight platform design more flexible. Furthermore, by reducing one electric motor and one controller, the system manufacturing and maintenance costs and system weight are significantly reduced. Additionally, because the annular radiator 4 is placed on the oil supply line, the lubricating oil temperature in the lubricating oil tank 8 is high. Therefore, the temperature difference between the cooling airflow from the fan 2 (which has already been cooled by the annular radiator 4) and the lubricating oil in the lubricating oil tank 8 can be used to cool the lubricating oil in the lubricating oil tank 8, further improving the utilization rate of the cooling airflow's heat dissipation capacity.

[0040] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An integrated aviation hybrid power lubricating oil cooling system, characterized in that, For the supply and return of oil and cooling of the generator controller (1) and the generator, including: A fan (2) for generating cooling airflow, a fan flow channel component (3) having a hollow cylindrical shape and an annular flow channel (301) extending along the axial direction, an annular radiator (4) arranged in an annular shape, an oil supply and return pump assembly (5) for supplying and returning oil, a fan motor (6) having two power output ends arranged opposite to each other, a fan motor controller (7) connected to the fan motor (6), and an oil tank (8) for holding lubricating oil. The fan flow channel component (3) is connected to the fan (2) and the annular radiator (4) at both ends of the axial direction, so that the annular flow channel (301) is axially connected to the fan (2) and the annular radiator (4), thereby allowing the cooling airflow generated by the fan (2) to enter the annular radiator (4) through the annular flow channel (301). The inner shaft hole of the fan flow channel component (3) also forms a hub mounting space (302) for installation. The fan motor (6) and the oil supply and return pump group (5) are respectively installed in the hub mounting space (302), and the two power output ends of the fan motor (6) are respectively connected to the fan (2) and the oil supply and return pump group (5). The lubricating oil tank (8) is installed in the shaft hole of the annular radiator (4), and the fan motor controller (7) is connected to the fan flow channel component (3).

2. The integrated aviation hybrid power lubricating oil cooling system according to claim 1, characterized in that, The fan flow channel component (3) is cone-shaped, with its small diameter end connected to the fan (2) and its large diameter end connected to the annular heat sink (4). The inner diameter of the annular flow channel (301) also gradually increases along the direction of the cooling airflow, so that the outlet end of the annular flow channel (301) is matched and connected to the annular heat sink (4).

3. The integrated aviation hybrid power lubricating oil cooling system according to claim 1, characterized in that, The annular flow channel (301) has multiple air vents (303) arranged circumferentially at intervals on the inner annular surface of the upstream section near the fan (2) to introduce the cooling airflow in the annular flow channel (301) into the hub mounting space (302). The downstream section of the annular flow channel (301) is also provided with multiple support plates (304) arranged sequentially along the circumference. At least some of the support plates (304) are hollow support plates with hollow holes that connect the hub mounting space (302) and the external space. The hollow support plates are used to allow the cooling airflow in the hub mounting space (302) to be discharged to the outside through the hollow holes.

4. The integrated aviation hybrid power lubricating oil cooling system according to claim 1, characterized in that, The fan motor controller (7) is connected to the outer ring surface of the fan flow channel component (3), and the heat dissipation fins (71) of the fan motor controller (7) pass through the outer ring surface of the fan flow channel component (3) and are installed in the annular flow channel (301).

5. The integrated aviation hybrid power lubricating oil cooling system according to claim 3, characterized in that, The oil supply and return pump assembly (5) includes an oil supply pump (51) connected to the oil tank (8) to pump oil from the oil tank (8) into the annular radiator (4). An oil filter (9) is also installed on the outer ring surface of the annular radiator (4). The oil filter (9) is connected to the generator controller (1) through the first oil supply pipe (10). The generator controller (1) is connected to the generator through the second oil supply pipe (11). The fan motor (6) is also connected to the first oil supply pipe (10) through the third oil supply pipe (12). The fan motor (6) is also connected to the oil tank (8) through the first oil return pipe (13). The first oil supply pipe (10) is also connected in sequence to the first lubricating oil pressure and temperature combination sensor (14) and the flow regulating valve (15).

6. The integrated aviation hybrid power lubricating oil cooling system according to claim 5, characterized in that, The oil supply pump (51) is connected to the annular radiator (4) through the internal flow path in the oil tank (8), and the annular radiator (4) is also connected to the oil filter (9) through its internal flow path. The first oil supply pipe (10) is integrated and arranged on the outer ring surface of the fan flow channel component (3); The third oil supply pipe (12) enters and exits the hub mounting space (302) through the hollow hole of the hollow support plate.

7. The integrated aviation hybrid power lubricating oil cooling system according to claim 5, characterized in that, The oil supply and return pump group (5) also includes a first return pump (52) and a second return pump (53) arranged side by side. The first return pump (52) is also connected to the front bearing cavity of the generator through the second return pipe (16). The second return pump (53) is also connected to the rear bearing cavity of the generator through the third return pipe (17). The first return pump (52) and the second return pump (53) are also connected to the lubricating oil tank (8) through the return oil main pipe (18). The second return oil pipe (16) and the third return oil circuit are each equipped with a return oil filter (19). A magnetic chip detector (20) is also installed in the return oil main (18) pipeline.

8. The integrated aviation hybrid power lubricating oil cooling system according to claim 5, characterized in that, The lubricating oil tank (8) is also connected to the cooling return oil circuit of the generator through the fourth return oil pipe (21) for oil return. The fourth return oil pipe (21) is also connected in sequence to the second lubricating oil pressure and temperature combination sensor (22) and the pressure regulating valve (23).

9. The integrated aviation hybrid power lubricating oil cooling system according to claim 1, characterized in that, The front bearing cavity and the rear bearing cavity of the generator are also connected to external ventilation pipes (24), and the exhaust end of the external ventilation pipes (24) extends to the oil tank (8). The lubricating oil tank (8) is also connected to a vent plug (25) for the oil and gas in the lubricating oil tank (8) to be discharged outward.

10. A hybrid aircraft, characterized in that, It has an integrated aviation hybrid power lubricating oil cooling system as described in any one of claims 1-9.

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