Airflow high lift device and vector control device for outer duct of aviation turbofan engine

Abstract

The invention provides an aviation turbofan engine outer duct airflow high lift device and a vector control device, and belongs to the technical field of aerospace. The outer duct airflow high lift device of the aviation turbofan engine comprises an outer mounting ring, an inner fixing ring and an airflow high lift assembly. And the two airflow lift augmentation assemblies comprise lift augmentation front edge plates, the two lift augmentation front edge plates are fixedly connected with the opposite faces, in the transverse direction, of the outer mounting ring and the inner fixing ring correspondingly, and one sides of the two lift augmentation front edge plates are rotationally connected with lift augmentation rear edge plates. According to the high-bypass-ratio turbofan engine, the lift augmentation assembly and the direction control surface are additionally arranged on the outer duct of the high-bypass-ratio turbofan engine, airflow distribution and the vector direction in the outer duct are accurately regulated and controlled, collaborative optimization of thrust and lift force of the engine is achieved, and therefore the overall efficiency and fuel economy of the engine are improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace, and more specifically, to an aerospace turbofan engine outer duct airflow lift enhancement device and a vector control device. Background Art

[0002] As the global aviation market continues to expand and competition intensifies, the need to improve flight efficiency and reduce operating costs has become increasingly apparent. Take fuel consumption as an example. High fuel costs are an important part of airline operating costs. If the performance of aircraft engines cannot meet the requirements, the aircraft will need more fuel to complete the mission, thereby increasing the operating costs of airlines. In addition, high fuel consumption also means higher carbon emissions, which is contrary to the global environmental protection trend. Increasingly stringent environmental regulations have also posed new challenges to aircraft engine technology. Improving engine efficiency is imperative.

[0003] In the field of civil aviation, turbofan engines are more widely used. Most medium and long-range civil aviation trunk passenger aircraft use high bypass ratio turbofan engines. For high bypass ratio turbofan engines, more than 75%-80% of the thrust is generated by the external bypass airflow, and the thrust generated by the internal bypass airflow accounts for only a small part. At present, turbojet engines make relatively little use of the external bypass airflow, and the utilization and conversion rate of the external bypass airflow needs to be improved. Summary of the invention

[0004] In order to make up for the above shortcomings, the present application provides an aviation turbofan engine external duct airflow lift enhancement device and a vector control device, aiming to improve the current turbojet engine's relatively less utilization of the external duct airflow, and the problem that the utilization and conversion rate of the external duct airflow need to be improved.

[0005] On the one hand, an embodiment of the present application provides an airflow enhancement device for an outer duct of an aviation turbofan engine, comprising an outer mounting ring, an inner fixing ring and an airflow enhancement assembly.

[0006] The two airflow lift enhancement components include lift enhancement leading edge plates, which are respectively fixedly connected to the opposite surfaces of the outer mounting ring and the inner fixed ring in the transverse direction, and one side of the two lift enhancement leading edge plates is rotatably connected to a lift enhancement trailing edge plate.

[0007] In a specific embodiment, the two lift-enhancing leading edge panels have the same shape as an aircraft wing.

[0008] In a specific embodiment, the two lift-enhancing leading edge plates are symmetrically fixedly connected to opposite surfaces of the outer mounting ring and the inner fixing ring in the transverse direction.

[0009] In a specific embodiment, a first rotating shaft is fixedly connected to one side of the lift-enhancing leading edge plate close to the lift-enhancing trailing edge plate, and the lift-enhancing trailing edge plate is rotatably connected to the first rotating shaft.

[0010] On the other hand, an embodiment of the present application further provides an aviation turbofan engine outer duct vector control device, including the above-mentioned aviation turbofan engine outer duct airflow lift enhancement device and vector control component.

[0011] The vector control component includes a front arc plate, and the two front arc plates are respectively fixedly connected to the vertically opposite surfaces of the outer mounting ring and the inner fixed ring. One side of the two front arc plates is rotatably connected to a rear arc plate, and the two front arc plates form a rudder surface on the side away from the rear arc plate.

[0012] In a specific embodiment, the shape of the two front curved panels is the same as that of the vertical tail of the aircraft.

[0013] In a specific embodiment, the two front arc-shaped plates are asymmetrically fixedly connected to opposite surfaces of the outer mounting ring and the inner fixing ring in a vertical direction.

[0014] In a specific embodiment, a second rotating shaft is fixedly connected to one side of the front arc-shaped plate close to the rear arc-shaped plate, and the rear arc-shaped plate is rotatably connected to the second rotating shaft.

[0015] Beneficial effects:

[0016] 1. By adding airflow lift enhancement components and rudder surfaces to the outer duct of a high bypass ratio turbofan engine, the airflow distribution and vector direction in the outer duct can be precisely controlled to achieve coordinated optimization of engine thrust and lift, thereby improving the overall efficiency and fuel economy of the engine.

[0017] 2. The airflow lift-enhancing component adopts a unique lower arc airfoil design, combined with the variable angle adjustment of the lift-enhancing trailing edge plate, which effectively improves the lift performance of the engine. This design enables the engine to maintain a high lift coefficient in various flight conditions, thereby optimizing flight performance.

[0018] 3. The rudder surface installed in the outer duct can achieve fine-tuning of the flight direction by precisely controlling its deflection angle. This design is equivalent to integrating a miniature vector engine inside the engine, which greatly enhances the maneuverability and controllability of the aircraft. Improve engine efficiency: By optimizing airflow distribution and vector control, the thrust and lift output of the engine are effectively improved. This collaborative optimization method enables the engine to generate greater thrust and lift at the same power, thereby significantly improving the overall efficiency of the engine. Reduce fuel consumption: The improvement of engine efficiency directly leads to a reduction in fuel consumption. Under the same range, the amount of fuel required by the aircraft is reduced, which not only reduces operating costs, but also reduces the impact on the environment, which is in line with the development concept of green aviation. Improve flight performance: The introduction of airflow lift enhancement components and vector control components enables the aircraft to perform better flight performance in various stages such as take-off, climb, cruise and landing. This not only improves the safety and comfort of flight, but also enables the aircraft to adapt to more flight missions and scenarios, broadening the scope of application of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the implementation methods of the present application, the drawings required for use in the implementation methods will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 It is a schematic structural diagram of the first perspective of an aviation turbofan engine outer duct airflow lift enhancement device and a vector control device provided in an embodiment of the present application;

[0021] Figure 2 A schematic diagram of the structure of the second perspective of the outer duct airflow lift-enhancing device and the vector control device of the aviation turbofan engine provided in the embodiment of the present application;

[0022] Figure 3 A schematic diagram of the structure of an airflow enhancement component provided in an embodiment of the present application;

[0023] Figure 4 A schematic diagram of the structure of a vector control component provided in an embodiment of the present application.

[0024] In the figure: 1-external mounting ring; 2-inner fixed ring; 3-airflow lift enhancement assembly; 31-lift enhancement leading edge plate; 32-lift enhancement trailing edge plate; 33-first rotating shaft; 34-first sleeve; 4-vector control assembly; 41-front arc plate; 42-rear arc plate; 43-second rotating shaft; 44-second sleeve. DETAILED DESCRIPTION

[0025] The technical solutions in the embodiments of the present application will be described below in conjunction with the drawings in the embodiments of the present application.

[0026] See also Figure 1-Figure 4 The present application provides an airflow lift enhancement device for an outer duct of an aviation turbofan engine, comprising an outer mounting ring 1, an inner fixing ring 2 and an airflow lift enhancement component 3. The present application is installed in the outer duct of a high bypass ratio aviation turbofan engine.

[0027] See also Figure 1 , Figure 2 and Figure 3 The two airflow lift enhancement components 3 include lift enhancement leading edge plates 31, which are fixedly connected to the opposite surfaces of the outer mounting ring 1 and the inner fixed ring 2 in the transverse direction, and one side of the two lift enhancement leading edge plates 31 is rotatably connected to the lift enhancement trailing edge plate 32. The shape of the two lift enhancement leading edge plates 31 is the same as that of the aircraft wing. The two lift enhancement leading edge plates 31 are symmetrically fixedly connected to the opposite surfaces of the outer mounting ring 1 and the inner fixed ring 2 in the transverse direction. The lift enhancement leading edge plate 31 is fixedly connected to a first rotating shaft 33 on one side close to the lift enhancement trailing edge plate 32. Specifically, one end of the first rotating shaft 33 is fixedly connected to the outer wall of the inner fixed ring 2 to increase the stability of the first rotating shaft 33 and the lift enhancement trailing edge plate 32. The lift enhancement trailing edge plate 32 is rotatably connected to the first rotating shaft 33. Specifically, the two ends of the lift enhancement trailing edge plate 32 on the side close to the first rotating shaft 33 are fixedly connected to the first sleeve 34, and the two first sleeves 34 are rotatably connected to the two ends of the first rotating shaft 33. Among them, the airflow lift-enhancing component 3 imitates the streamlined design of the wing of a civil aircraft. The lower arc-shaped airfoil of the lift-enhancing leading edge plate 31 can effectively guide the airflow. Through the guidance of the guide blades, the airflow will generate upward lift when it flows through the lift-enhancing leading edge plate 31, so that the turbofan engine can provide additional upward lift for the aircraft while providing traditional thrust, thereby enhancing the aircraft's climbing ability and maneuverability. The lift-enhancing trailing edge plate 32 has a similar function to the flap of the aircraft wing. The lift-enhancing trailing edge plate 32 can be adjusted in real time according to the flight state to adapt to the lift requirements at different flight speeds and altitudes. When flying at low speed, the angle can be increased to increase the lift coefficient and improve the climbing efficiency; while when flying at high speed, the trailing edge angle can be reduced to reduce resistance and maintain the stability of high-speed flight. By installing two airflow lift-enhancing components 3 in the outer duct, the performance of the high bypass ratio turbofan engine has been significantly improved. It can not only provide greater thrust for the aircraft, but also optimize the flight trajectory and performance of the aircraft by generating additional lift. This innovative design not only improves the aircraft's climbing ability and maneuverability, but also reduces fuel consumption and emissions, further improving the aircraft's economy and environmental performance.

[0028] See also Figure 1-Figure 4The embodiment of the present application further provides an aviation turbofan engine outer duct vector control device, including the above aviation turbofan engine outer duct airflow lift enhancement device and vector control component 4.

[0029] See also Figure 1 , Figure 2 and Figure 4 The vector control assembly 4 includes a front arc plate 41, two front arc plates 41 are respectively fixedly connected to the vertically opposite surfaces of the outer mounting ring 1 and the inner fixed ring 2, and one side of the two front arc plates 41 is rotatably connected to the rear arc plate 42, and the side of the two front arc plates 41 away from the rear arc plate 42 forms a rudder surface. The shape of the two front arc plates 41 is the same as that of the vertical tail of the aircraft. The two front arc plates 41 are respectively asymmetrically fixedly connected to the vertically opposite surfaces of the outer mounting ring 1 and the inner fixed ring 2. A second rotating shaft 43 is fixedly connected to the side of the front arc plate 41 close to the rear arc plate 42, and specifically, one end of the second rotating shaft 43 is fixedly connected to the outer side wall of the inner fixed ring 2. The rear arc plate 42 is rotatably connected to the second rotating shaft 43, and specifically, the two ends of the side of the rear arc plate 42 close to the second rotating shaft 43 are fixedly connected to the second sleeve 44, and the two second sleeves 44 are respectively rotatably connected to the two ends of the second rotating shaft 43. Among them, the design inspiration of the vector control component 4 comes from the vertical tail and rudder surface at the tail of the aircraft. They not only have similar appearance and functions, but also show great potential in improving engine performance. This set of vector control components 4, called "external duct vector rudder system", is installed on the inner wall of the engine's external duct, forming a structure similar to the control surface of the tail of the aircraft. The rudder surface is connected by a set of precise transmission devices, which can accurately control the angle and speed of its left and right deflection. When the engine is running, the airflow in the external duct will be affected by these rudder surfaces, resulting in slight changes in flow direction. By accurately controlling the deflection of the rudder surface, the distribution and direction of the airflow in the external duct can be effectively adjusted, thereby realizing vector control of the engine thrust. It can not only improve the thrust performance of the engine, but also improve its thrust distribution, making the aircraft more stable and flexible during flight. Specifically, when it is necessary to change the flight direction of the aircraft, the control system will issue an instruction to drive the rudder surface to deflect accordingly through the transmission device. With the deflection of the rudder surface, the airflow in the external duct will change its flow direction accordingly, generating a tiny thrust vector component. This component, combined with the main thrust of the engine, acts together on the aircraft, allowing it to fine-tune the direction of flight without changing the magnitude of the main thrust.

[0030] Working principle of the external bypass airflow lift device and vector control device of the aviation turbofan engine:

[0031] The airflow lift-enhancing assembly 3 imitates the streamlined design of the wing of a civil aircraft. The lower arc-shaped airfoil of the lift-enhancing leading edge plate 31 can effectively guide the airflow. Through the guidance of the guide blades, the airflow will generate upward lift when it flows through the lift-enhancing leading edge plate 31, so that the turbofan engine can provide additional upward lift for the aircraft while providing traditional thrust, thereby enhancing the aircraft's climbing ability and maneuverability. The lift-enhancing trailing edge plate 32 has a similar function to the flap of the aircraft wing. The lift-enhancing trailing edge plate 32 can be adjusted in real time according to the flight state to adapt to the lift requirements at different flight speeds and altitudes. When flying at low speed, the angle can be increased to increase the lift coefficient and improve the climbing efficiency; while when flying at high speed, the trailing edge angle can be reduced to reduce resistance and maintain the stability of high-speed flight. By installing two airflow lift-enhancing assemblies 3 in the outer duct, the performance of the high bypass ratio turbofan engine has been significantly improved. It can not only provide greater thrust for the aircraft, but also optimize the flight trajectory and performance of the aircraft by generating additional lift. This innovative design not only improves the aircraft's climbing ability and maneuverability, but also reduces fuel consumption and emissions, further improving the aircraft's economy and environmental protection. The design inspiration of the vector control component 4 comes from the vertical tail and rudder surface at the tail of the aircraft. They not only have similar appearance and functions, but also show great potential in improving engine performance. This set of vector control components 4, called the "external duct vector rudder system", is installed on the inner wall of the engine's external duct, forming a structure similar to the aircraft's tail control surface. The rudder surface is connected by a set of precise transmission devices, which can accurately control the angle and speed of its left and right deflection. When the engine is running, the airflow in the external duct will be affected by these rudder surfaces, resulting in subtle changes in flow direction. By accurately controlling the deflection of the rudder surface, the distribution and direction of the airflow in the external duct can be effectively adjusted, thereby realizing vector control of the engine thrust. It can not only improve the engine's thrust performance, but also improve its thrust distribution, making the aircraft more stable and flexible during flight. Specifically, when the aircraft's flight direction needs to be changed, the control system will issue a command to drive the rudder surface to deflect accordingly through the transmission device. As the rudder surface deflects, the airflow in the outer duct will change direction and generate a tiny thrust vector component. This component is combined with the main thrust of the engine and acts on the aircraft together, enabling it to fine-tune the flight direction without changing the magnitude of the main thrust. By adding an airflow lift-enhancing component 3 and a rudder surface to the outer duct of a high bypass ratio turbofan engine, the airflow distribution and vector direction in the outer duct can be precisely controlled to achieve coordinated optimization of engine thrust and lift, thereby improving the overall efficiency and fuel economy of the engine. The airflow lift-enhancing component 3 adopts a unique lower arc airfoil design, combined with the variable angle adjustment of the lift-enhancing trailing edge plate 32, which effectively improves the lift performance of the engine. This design enables the engine to maintain a high lift coefficient in a variety of flight conditions, thereby optimizing flight performance.The rudder surface installed in the outer duct can achieve fine-tuning of the flight direction by precisely controlling its deflection angle. This design is equivalent to integrating a micro vector engine inside the engine, which greatly enhances the maneuverability and controllability of the aircraft. Improve engine efficiency: By optimizing airflow distribution and vector control, the thrust and lift output of the engine are effectively improved. This collaborative optimization method enables the engine to generate greater thrust and lift at the same power, thereby significantly improving the overall efficiency of the engine. Reduce fuel consumption: The improvement of engine efficiency directly leads to a reduction in fuel consumption. Under the same range, the amount of fuel required by the aircraft is reduced, which not only reduces operating costs, but also reduces the impact on the environment, which is in line with the development concept of green aviation. Improve flight performance: The introduction of the airflow lift enhancement component 3 and the vector control component 4 enables the aircraft to exhibit better flight performance in various stages such as take-off, climb, cruise and landing. This not only improves the safety and comfort of flight, but also enables the aircraft to adapt to more flight missions and scenarios, broadening the scope of application of the aircraft.

[0032] The above description is only an embodiment of the present application and is not intended to limit the scope of protection of the present application. For those skilled in the art, the present application may have various changes and variations. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application should be included in the scope of protection of the present application. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings.

Claims

1. An aircraft turbofan engine outer duct airflow lift enhancement device, characterized in that: include An outer mounting ring (1), an inner fixing ring (2) and an airflow lift-enhancing assembly (3), wherein two of the airflow lift-enhancing assemblies (3) comprise lift-enhancing leading edge plates (31), the two lift-enhancing leading edge plates (31) being respectively fixedly connected to opposite surfaces of the outer mounting ring (1) and the inner fixing ring (2) in a transverse direction, and one side of the two lift-enhancing leading edge plates (31) is rotatably connected to a lift-enhancing trailing edge plate (32).

2. The aircraft turbofan engine outer duct airflow lift-increasing device according to claim 1, characterized in that: The shapes of the two lift-enhancing leading edge panels (31) are the same as those of aircraft wings.

3. The airflow enhancement device for the outer bypass of an aviation turbofan engine according to claim 1, characterized in that: The two lift-enhancing leading edge plates (31) are symmetrically fixedly connected to opposite surfaces of the outer mounting ring (1) and the inner fixing ring (2) in the transverse direction.

4. The aircraft turbofan engine outer duct airflow lift-increasing device according to claim 1, characterized in that: A first rotating shaft (33) is fixedly connected to one side of the lift-enhancing leading edge plate (31) close to the lift-enhancing trailing edge plate (32), and the lift-enhancing trailing edge plate (32) is rotatably connected to the first rotating shaft (33).

5. An aviation turbofan engine bypass vector control device, characterized in that: include The aircraft turbofan engine outer duct airflow lift enhancement device and vector control component (4) as described in claims 1-4; The vector control assembly (4) comprises a front arc plate (41), wherein two front arc plates (41) are respectively fixedly connected to the vertically opposite surfaces of the outer mounting ring (1) and the inner fixing ring (2), one side of the two front arc plates (41) is rotatably connected to a rear arc plate (42), and a side of the two front arc plates (41) away from the rear arc plate (42) forms a rudder surface.

6. The aircraft turbofan engine bypass vector control device according to claim 5, characterized in that: The shapes of the two front curved plates (41) are the same as the vertical tail of the aircraft.

7. The aircraft turbofan engine bypass vector control device according to claim 5, characterized in that: The two front arc-shaped plates (41) are respectively asymmetrically fixedly connected on opposite surfaces of the outer mounting ring (1) and the inner fixing ring (2) in a vertical direction.

8. The aircraft turbofan engine bypass vector control device according to claim 5, characterized in that: A second rotating shaft (43) is fixedly connected to one side of the front arc-shaped plate (41) close to the rear arc-shaped plate (42), and the rear arc-shaped plate (42) is rotatably connected to the second rotating shaft (43).

9. The aircraft turbofan engine bypass vector control device according to claim 8, characterized in that: The two ends of the rear arc-shaped plate (42) on one side close to the second rotating shaft (43) are fixedly connected to second sleeves (44), and the two second sleeves (44) are rotatably connected to the two ends of the second rotating shaft (43) respectively.

10. The aircraft turbofan engine bypass vector control device according to claim 5, characterized in that: The outer side wall of the outer mounting ring (1) is provided with a mounting groove.

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