A thrust fan and engine

Abstract

The embodiment of the present application provides a thrust fan and an engine, the thrust fan comprises: a casing, a hub and an annular track arranged in the casing, the annular track is located between the hub and the inner side wall of the casing, the annular track keeps a static state relative to the casing, further comprising: a plurality of first blades located between the hub and the annular track, and arranged on the hub so as to drive each of the plurality of first blades to rotate around the hub, a plurality of second blades located between the annular track and the casing, and a plurality of first electromagnetic coupling components located between the first end of the plurality of second blades and the annular track, which electromagnetically couples the first end of the second blade and the annular track, so that the corresponding second blade is suspended between the annular track and the inner side wall of the casing and rotates around the annular track. The technical scheme can reduce the flutter generated by high-speed unsteady flow, ensure the efficiency of the thrust fan, and reduce abnormal vibration and noise.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to a thrust fan and engine. Background Technology

[0002] In turbofan engines, the thrust fan is a key component that generates the engine's main thrust and simultaneously provides compressed airflow to the core engine and bypass duct. In high-speed unsteady flow, the thrust fan is prone to flutter, which leads to a sharp drop in thrust fan efficiency, accompanied by strong abnormal vibrations and noise, as well as high-cycle fatigue failure of the blades, and may even cause blade breakage and catastrophic damage. Summary of the Invention

[0003] To address the technical problems, this application provides a thrust fan and engine to reduce flutter caused by high-speed unsteady flow, ensure thrust fan efficiency, reduce abnormal vibration and noise, and prevent blade fatigue damage.

[0004] In a first aspect, embodiments of this application provide a thrust fan, including: a casing and a hub and an annular track disposed within the casing, the annular track being located between the hub and the inner wall of the casing, the annular track remaining stationary relative to the casing, and the thrust fan further including: Multiple first blades are located between the hub and the annular track, and are arranged on the hub along the circumferential direction of the hub. The hub is used to drive each of the multiple first blades to rotate around the hub. Multiple second blades, located between the annular track and the inner wall of the casing, having a first end near the annular track and a second end near the inner wall of the casing; and, Multiple first electromagnetic coupling components, corresponding to multiple second blades, are located between the first ends of the multiple second blades and the annular track. The multiple first electromagnetic coupling components surround the annular track. The first electromagnetic coupling components are used to electromagnetically couple the first ends of the second blades to the annular track, so that the corresponding second blades are suspended between the annular track and the inner wall of the casing and rotate around the annular track.

[0005] Secondly, embodiments of this application also provide an engine, including: a thrust fan as described in the first aspect.

[0006] In one or more technical solutions of this application embodiment, a plurality of first blades are located between the hub and the annular track, and the plurality of first blades are arranged on the hub along the circumferential direction of the hub, so that the hub can drive each of the plurality of first blades to rotate around the hub; while a plurality of second blades are located between the annular track and the inner sidewall of the casing, and a plurality of first electromagnetic coupling components are located between the first ends of the plurality of second blades and the annular track. Therefore, the first electromagnetic coupling components can electromagnetically couple the first ends of the second blades to the annular track, so that the second blades are suspended between the annular track and the inner sidewall of the casing and rotate around the annular track.

[0007] As can be seen, the thrust fan of this application embodiment can divide the blades into two groups using a ring track to reduce the spanwise height of each group of blades, thereby ensuring the aeroelastic stability of the blades and preventing flutter. Therefore, the thrust fan of this application embodiment has high efficiency, reduces abnormal vibration and noise, prevents blade fatigue damage, and avoids catastrophic damage caused by blade breakage.

[0008] Furthermore, as the multiple second blades rotate around the annular track, multiple first electromagnetic coupling components can magnetically levitate the second blades between the annular track and the inner wall of the casing. This reduces frictional losses and increases the rotational speed of the multiple second blades, thereby increasing the thrust of the thrust fan and maximizing the specific strength and damping characteristics of the material. Moreover, without changing the hub speed, the speed of the multiple second blades can be electromagnetically controlled to maximize the thrust density of the fan, overcoming the physical limitations of traditional single rotor speed on thrust output.

[0009] In addition, the thrust fan of this application embodiment does not require the addition of a damping device to suppress blade flutter, does not increase blade weight, does not interfere with airflow channels, and introduces additional aerodynamic losses, thereby ensuring the engine thrust-to-weight ratio and efficiency, making the engine less prone to wear and performance degradation under high-speed, centrifugal force environments, thereby improving the long-term service reliability of the engine. Attached Figure Description

[0010] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments of this application and are configured to explain this application, but do not constitute an undue limitation of this application. In the drawings: Figure 1 A schematic diagram of the thrust fan according to an embodiment of this application is shown; Figure 2 A cross-sectional schematic diagram of a thrust fan according to an embodiment of this application is shown; Figure 3 A schematic diagram of the blade segmentation of a thrust fan according to an embodiment of this application is shown; Figure 4A Detailed structural diagrams of the first and third electromagnetic coupling components according to embodiments of this application are shown. Figure 1 ; Figure 4B A detailed structural schematic diagram of the second electromagnetic coupling component according to an embodiment of this application is shown. Figure 1 ; Figure 5A Detailed structural diagrams of the first and third electromagnetic coupling components according to embodiments of this application are shown. Figure 2 ; Figure 5B A detailed structural schematic diagram of the second electromagnetic coupling component according to an embodiment of this application is shown. Figure 2 ; Figure 6A A schematic diagram of the limiting structure of the first electromagnetic coil in an embodiment of this application is shown; Figure 6B A schematic diagram of the limiting structure of the second and third electromagnetic coils in an embodiment of this application is shown; Figure 6C A schematic diagram showing the details of the limiting structure of the second electromagnetic coil in an embodiment of this application is shown; Figure 7 A schematic diagram of the heat dissipation structure of the first electromagnetic component and the third electromagnetic component according to an embodiment of this application is shown; Figure 8 A schematic diagram of the installation structure of the annular track according to an embodiment of this application is shown. Detailed Implementation

[0011] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0012] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0013] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise expressly specified. "Several" means one or more, unless otherwise expressly specified.

[0014] In the description of this application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0015] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0016] A turbofan engine mainly consists of five core components: the air intake, the compression system, the combustion chamber, the turbine, and the exhaust nozzle. The compression system comprises a thrust fan and a compressor. As a key component that generates the engine's main thrust and simultaneously provides compressed airflow to the core engine and the bypass duct, the safety and reliability of the fan have always been a focus of research.

[0017] Due to their high aspect ratio, complex swept-back shape, and the use of lightweight composite materials, thrust fan blades are prone to flutter, aerodynamic forces coupled with elastic deformation, in high-speed unsteady flow. Flutter can cause a sharp drop in thrust fan efficiency, resulting in a significant decrease in thrust. It is also accompanied by strong abnormal vibrations and noise, and can lead to high-cycle fatigue failure of the thrust fan blades, or even blade breakage and catastrophic damage.

[0018] In engineering, common methods for suppressing blade flutter in thrust fans can be divided into two main categories: one is to improve the aerodynamic / structural design of the thrust fan, such as optimizing the three-dimensional blade shape, increasing the blade thickness or chord length, to suppress flutter from the root cause; the other is to add damping devices to directly dissipate vibration energy through physical means, thus suppressing flutter from the perspective of its consequences. Examples include installing damping rings on the blades of a thrust fan to convert mechanical energy into heat energy, or adding dampers, buffers, etc.

[0019] However, adding damping devices to suppress blade flutter increases blade weight and may interfere with airflow channels, introducing additional aerodynamic losses, thus reducing the engine's thrust-to-weight ratio and efficiency. Furthermore, under high-speed, centrifugal force conditions, friction surfaces may experience wear and performance degradation, thereby reducing long-term service reliability.

[0020] To address the aforementioned problems, this application provides a thrust fan and engine. The thrust fan adopts a radially partitioned fan blade structure to solve the root cause problem by dividing the fan blades with higher spanwise height into two segments, thereby shortening the spanwise height of the thrust fan blades, ensuring the aeroelastic stability of the blades, and preventing flutter.

[0021] This application provides an engine including a thrust fan. The blades of the thrust fan have high aeroelastic stability, which can prevent flutter. The engine can be a turbofan engine, which can be applied to various aircraft, such as military aircraft, civilian aircraft, and drones, but is not limited to these.

[0022] Optionally, taking a turbofan engine as an example, the engine may include a thrust fan that can be rotatably connected to the turbine shaft, so that the turbine shaft (such as a low-pressure turbine shaft) can drive the thrust fan to rotate, and the thrust fan can electromagnetically control the speed of the blades in the region away from the turbine shaft without changing the speed of the turbine shaft, so as to maximize the thrust density of the fan and break through the physical limitation of the traditional single rotor speed (or turbine shaft speed) on thrust output.

[0023] This application also provides a thrust fan. Figure 1 A schematic diagram of the thrust fan according to an embodiment of this application is shown. Figure 2 A cross-sectional schematic diagram of a thrust fan according to an embodiment of this application is shown. Figure 1 and Figure 2 As shown, the thrust fan 100 may include a casing 101 and a hub 102 and an annular track 103 disposed within the casing 101. The annular track 103 is located between the hub 102 and the inner wall of the casing 101. The annular track 103 remains stationary relative to the casing 101.

[0024] The thrust fan 100 of this application embodiment may further include: a first group of blades and a second group of blades, wherein the first group of blades includes a plurality of first blades 104 and the second group of blades includes a plurality of second blades 105. Optionally, the total length of the first blades 104 and the second blades 105 in the spanwise direction may be equal to or slightly greater than the spanwise direction of blades in the related art. Therefore, even if the blades of the thrust fan 100 are divided into two groups, the airflow of the fan will not be affected. Optionally, the number of the first blade 104 and the second blade 105 can be the same or different. For example, the number of the second blade 105 can be higher than the number of the first blade 104. Therefore, the number of the first blade 104 and the second blade 105 can be flexibly set according to the usage requirements to achieve the aerodynamic structural layout design of the thrust fan 100.

[0025] For example, Figure 3 A schematic diagram of the blade segments of a thrust fan according to an embodiment of this application is shown. Figures 1-3 As shown, the blades in the related technology can be divided into two segments, a first blade 104 and a second blade 105, along the radial direction of the casing 101. The thrust fan 100 blades of this application embodiment can be divided into two segments along the radial direction: a lower half fan blade and an upper half fan blade. The lower half fan blade is the first blade 104, and the upper half fan blade is the second blade 105. The two can be manufactured and installed independently.

[0026] The first set of blades includes a plurality of first blades 104 which can be located between the hub 102 and the annular track 103 and are disposed on the hub 102 along the circumferential direction of the hub 102, so that the hub 102 is used to drive each of the plurality of first blades 104 to rotate around the hub 102.

[0027] Optionally, the hub 102 can be mounted on the turbine shaft, so that the turbine shaft can drive the hub 102 to rotate during rotation. The root end of the first blade 104 can be fixedly connected to the hub through a dovetail groove or a fir tree tenon, and is evenly arranged along the circumference of the hub.

[0028] Optionally, the tips of the plurality of first blades 104 in the first set of blades have a first gap with the surface of the annular track 103 near the hub 102. In this way, when the hub 102 drives each of the plurality of first blades 104 to rotate around the hub 102, the annular track 103 will not interfere with the tips of each of the plurality of first blades 104, thereby reducing friction loss and increasing the rotational speed of the plurality of first blades 104, and increasing the thrust of the thrust fan 100.

[0029] The second set of blades includes a plurality of second blades 105 located between the annular track 103 and the inner wall of the casing 101, each of the plurality of second blades 105 having a first end near the annular track 103 and a second end near the inner wall of the casing 101.

[0030] The thrust fan 100 of this embodiment may further include a plurality of first electromagnetic coupling components corresponding to a plurality of second blades 105. The plurality of first electromagnetic coupling components may be located between the first ends of the plurality of second blades 105 and the annular track 103, and the plurality of first electromagnetic coupling components surround the annular track 103.

[0031] In this embodiment of the application, the second blade 105 corresponds one-to-one with the first electromagnetic coupling component. For any first electromagnetic coupling component, it can be used to electromagnetically couple the first end of the second blade 105 with the annular track 103, so that the corresponding second blade 105 is suspended between the annular track 103 and the inner wall of the casing 101, and rotates around the annular track 103.

[0032] Optionally, by dividing the overall blades of the thrust fan 100 into a first group of structures and a second group of structures that are radially segmented along the casing 101, the centrifugal load borne by a single blade can be significantly reduced. This allows both the first blade 104 and the second blade 105 to be manufactured using advanced composite materials (such as resin-based composite materials, ceramic-based composite materials, etc.) with higher specific strength but lower density. This provides a favorable structural platform for further lightweighting and efficiency improvement of fan blades in the future.

[0033] For example, the second blade 105 may be made of a low-density composite material or titanium alloy to reduce the centrifugal load in the second end region of the second blade 105, while utilizing the high specific strength and good damping characteristics of the composite material to further suppress vibration.

[0034] Optionally, each of the plurality of second blades 105 included in the second set of blades has a second gap between its first end and the surface of the annular track 103 near the inner wall of the casing 101. This way, during the rotation of the corresponding second blade 105 driven by the first electromagnetic coupling assembly, the annular track 103 will not interfere with the first end of the second blade 105, thereby reducing frictional losses and increasing the rotational speed of the plurality of second blades 105, thus increasing the thrust of the thrust fan 100.

[0035] Optionally, each of the plurality of second blades 105 in the second set of blades has a second end with a third gap between its second end and the surface of the annular track 103 near the inner wall of the annular track 103. This way, during the rotation of the corresponding second blade 105 driven by the first electromagnetic coupling assembly, the casing 101 will not interfere with the first end of the second blade 105, thereby reducing frictional losses and increasing the rotational speed of the plurality of second blades 105, thus increasing the thrust of the thrust fan 100. It should be understood that the aerodynamic efficiency of the thrust fan 100 can also be improved by increasing the number of blades to reduce the gap between two blades.

[0036] As can be seen, the thrust fan 100 of this embodiment can divide the blades into two groups using the annular track 103 to reduce the spanwise height (cantilever length) of each group of blades. Compared with the integral blades under the same diameter of the inference fan, this structure can effectively improve the structural stiffness and natural frequency of each group of blades. It can not only reduce the flutter problem caused by aeroelastic coupling of long blades under high-speed rotation conditions from the root, thereby ensuring the aeroelastic stability of the blades, preventing flutter, and enhancing the operational safety under high-speed conditions, but also significantly reduce the deformation of the blades under unsteady aerodynamic loads. Therefore, the thrust fan 100 of this embodiment has high efficiency, reduces abnormal vibration and noise, prevents blade fatigue failure, and avoids catastrophic damage caused by blade breakage.

[0037] Furthermore, during the rotation of multiple second blades 105 around the annular track 103, multiple first electromagnetic coupling components can magnetically levitate the multiple second blades 105 between the annular track 103 and the inner wall of the casing 101. This allows the second blades 105 to levitate between the annular track 103 and the inner wall of the casing 101 under the action of the first electromagnetic coupling components. This transforms the mechanical connection into a non-mechanical connection, reducing frictional losses and increasing the rotational speed of the multiple second blades 105, thereby increasing the thrust of the thrust fan 100 and maximizing the specific strength and damping characteristics of the material. Moreover, without changing the rotational speed of the hub 102, the speed of the multiple second blades 105 can be actively controlled electromagnetically. Since the tip linear velocity (the linear velocity of the second end of the second blade 105) contributes significantly to the total thrust of the fan, the thrust density of the fan can be maximized, breaking through the physical limitation of thrust output by the traditional single rotor speed. This also enables adjustable thrust of the thrust fan 100, thereby improving the efficiency, safety, and controllability of the aero-engine.

[0038] In other words, the rotational speed of the second blade 105 can be controlled by the first electromagnetic coupling component, making the difference in rotational speed between the second blade 105 and the first blade 104, i.e., the rotational speed, controllable, thus achieving a flexible match between engine economy and power. For example, under high thrust demand conditions such as takeoff, climb, and go-around, the rotational speed of the upper fan blades can be increased rapidly and independently, enabling the fan to output high thrust in a short time to meet maneuverability or safety requirements. Conversely, under low thrust demand conditions such as cruise and holding, the electromagnetic drive power of the first electromagnetic coupling component can be reduced or cut off, allowing the second blade 105 to operate synchronously or with low slip with the first blade 104, significantly reducing the electromagnetic energy consumption of the first electromagnetic coupling component and effectively improving fuel economy. Therefore, in the thrust fan 100 of this application embodiment, by controlling the rotational speeds of the first blade 104 and the second blade 105 in zones, "flexible adjustment" of engine thrust output can be achieved, breaking through the technical bottleneck of "difficulty in balancing thrust and fuel consumption" in traditional engines across the entire operating range, and significantly improving the engine's operability and efficiency in different flight phases.

[0039] In addition, the thrust fan 100 of this application embodiment does not require the addition of a damping device to suppress blade flutter, does not increase blade weight, does not interfere with airflow channels, and introduces additional aerodynamic losses, thereby ensuring the engine thrust-to-weight ratio and efficiency, making the engine less prone to wear and performance degradation under high-speed, centrifugal force environments, thereby improving the long-term service reliability of the engine.

[0040] In one possible implementation, for any first electromagnetic coupling component, Figure 4ADetailed structural diagrams of the first and third electromagnetic coupling components according to embodiments of this application are shown. Figure 1 , Figure 5A Detailed structural diagrams of the first and third electromagnetic coupling components according to embodiments of this application are shown. Figure 2 .like Figure 4A and Figure 5A As shown, the first electromagnetic coupling assembly includes a first electromagnetic coil 1061A and two first permanent magnets 1062A. The first electromagnetic coil 1061A is disposed at the first end of the corresponding second blade 105, so that the position of the first electromagnetic coil 1061A changes as the second blade 105 rotates. Therefore, the first electromagnetic coil 1061A can be used as a mover. The two first permanent magnets 1062A are disposed along the axial direction of the annular track 103 on the surface of the annular track 103 near the inner sidewall of the casing 101. Since the annular track 103 remains stationary, the position of the first permanent magnets 1062A does not change, and they can be used as stators.

[0041] Optionally, the first permanent magnets 1062A included in the multiple first electromagnetic coupling components can be combined into a permanent magnet array, and the first permanent magnets 1062A can be selected from high-temperature resistant neodymium iron boron (NdFeB) or samarium cobalt (SmCo) permanent magnet materials, with an operating temperature of up to 150℃~350℃, and their surfaces can be coated with a corrosion-resistant protective layer, such as a nickel-copper-nickel plating layer or an epoxy resin layer.

[0042] The magnetic poles of adjacent first permanent magnets 1062A in the plurality of first electromagnetic coupling components are opposite, so that the magnetic poles of the first permanent magnets 1062A in the plurality of first electromagnetic coupling components can be arranged in an alternating polarity along the circumferential direction of the annular track 103 to enhance the air gap magnetic flux density and reduce leakage magnetic flux. The first electromagnetic coil 1061A is located between the two first permanent magnets 1062A, one of the two first permanent magnets 1062A is opposite to the input end of the first electromagnetic coil 1061A, and the other is opposite to the output end of the first electromagnetic coil 1061A.

[0043] For example, the first permanent magnets 1062A included in the multiple first electromagnetic coupling components can be arranged in a permanent magnet array along the circumferential direction of the ring track 103 in an alternating manner of N poles and S poles, forming a fixed magnetic channel.

[0044] When the first electromagnetic coil 1061A is energized, it is an electromagnet that can be precisely controlled. Therefore, according to the principle that like poles repel and unlike poles attract, by precisely controlling the on / off state and direction of the current flowing into the first electromagnetic coil 1061A, the coil can obtain a continuous and powerful directional thrust on the track formed by the magnetic field.

[0045] Optionally, to facilitate control of the first electromagnetic coupling component, the thrust fan 100 may also include an electronic control system, which can be electrically connected to the first electromagnetic coil 1061A via a first lead. A lead channel may be provided inside the second blade 105, and the first lead can be electrically connected to the electronic control system along the lead channel provided inside the second blade 105.

[0046] When the electronic control system provides a first alternating current signal to the first electromagnetic coil 1061A included in each of the first electromagnetic coupling components through the first lead, the first electromagnetic coil 1061A included in each of the first electromagnetic coupling components generates a rotating magnetic field in response to the first alternating current signal, and interacts with the first permanent magnet 1062A included in each of the first electromagnetic coupling components to generate a circumferential electromagnetic force, which drives the multiple second blades 105 to rotate.

[0047] Optionally, the electronic control system can also refer to the turbine shaft speed and a preset speed difference to determine the frequency and phase of the first alternating current signal, so that the rotating magnetic field generated by the first electromagnetic coil 1061A of each first electromagnetic coupling component responds to the first alternating current signal and cooperates with the first permanent magnet to indirectly control the magnitude and direction of the circumferential electromagnetic force, so that the speed difference between the first blade 104 and the second blade 105 meets the preset speed difference value. Therefore, the electronic control system of this embodiment can set a preset speed difference according to actual requirements, so that the first blade 104 and the second blade 105 can operate synchronously, at an increased speed, or at a decreased speed.

[0048] Optionally, the first electromagnetic coil 1061A can be embedded in the corresponding second blade 105 as the first end of the coupling end face. The first electromagnetic coil 1061A can also be wound with high-temperature resistant enameled wire (such as polyimide insulated copper wire) and encapsulated in a thin-walled shell made of titanium alloy, high thermal conductivity epoxy resin, or ceramic matrix composite material, and the thin-walled shell is integrally formed with the second blade 105. In this case, there is a second gap between the surface of the thin-walled shell facing the annular track 103 and the surface of the annular track 103 near the casing 101 to avoid mechanical contact between the two.

[0049] Figure 6A A schematic diagram of the limiting structure of the first electromagnetic coil in an embodiment of this application is shown. Figure 4A , Figure 5A and 6A As shown, in order to facilitate the installation of the first permanent magnet 1062A and limit the first electromagnetic coil 1061A, the surface of the annular track 103 near the inner wall of the casing 101 has two first outer limiting tracks 1071A surrounding the annular track 103 and a plurality of first limiting sliders 1072A spaced apart around the annular track 103.

[0050] Each of the two first outer limiting tracks 1071A is distributed along the axial direction of the annular track 103. Optionally, the casing 101 has an air inlet side and an air outlet side, and their distribution direction can be the axial direction of the annular track 103. It can be considered that the two first outer limiting tracks 1071A surrounding the annular track 103 are arranged along the distribution direction of the air inlet side and the air outlet side on the surface of the annular track 103 near the inner wall of the casing 101.

[0051] Multiple first limiting sliders 1072A are located between two first outer limiting tracks 1071A. These multiple first limiting sliders 1072A are used to move along the circumferential direction of the annular track 103 near the inner wall of the casing 101 during the rotation of the multiple second blades 105. At this time, there is a gap between the two first outer limiting tracks 1071A and the first limiting sliders 1072A, and the first limiting sliders 1072A are in contact with the surface of the annular track 103 near the inner wall of the casing 101, but relative movement is possible.

[0052] Two adjacent first limiting sliders 1072A, two first outer limiting tracks 1071A, and the surface of the annular track 103 near the inner wall of the casing 101 form a first receiving space, within which a first electromagnetic coil 1061A is located. A first permanent magnet 1062A corresponds one-to-one with a first outer limiting track 1071A. Each of two first permanent magnets 1062A is located within one of the corresponding first outer limiting tracks 1071A and is connected to the first electromagnetic coil 1061A included in the two adjacent first electromagnetic coupling components of the first limiting slider 1072A.

[0053] Optionally, the first outer limiting track 1071A can be an annular groove formed on the inner wall of the annular track 103 near the housing 101, or it can be an annular cavity (with magnetic conduction function) on the surface of the annular track 103 near the inner wall of the housing 101.

[0054] As can be seen, in the thrust fan 100 of this application embodiment, the first permanent magnet 1062A can be accurately positioned by the limiting effect of the first outer limiting rail 1071A, so that the first permanent magnet 1062A can couple with the first electromagnetic coil 1061A to form an axial magnetic field force with stable direction and speed, ensuring the stability of the second blade 105 in rotation trajectory and rotational attitude. Furthermore, the first end of the second blade 105 is limited by the first limiting slider 1072A in the circumferential direction of the annular track 103 and by the first outer limiting rail 1071A in the axial direction of the casing 101, which can reduce the vibration position of the second blade 105 during rotation, thereby further enhancing the dynamic stability of the second blade 105 and meeting the safe operation requirements under higher speed and greater thrust conditions.

[0055] Optional, Figure 7 A schematic diagram of the heat dissipation structure of the first electromagnetic component and the third electromagnetic component according to an embodiment of this application is shown. Figure 5A and Figure 7 As shown, considering that the first electromagnetic coupling assembly operates under high speed and high power density conditions, the resistive heating and eddy current loss of the first electromagnetic coil 1061A are significant. One or more first airflow channels H1 are provided on the first outer limiting track 1071A. The axial direction of these first airflow channels H1 can be the same as the axial direction of the casing 101. For example, multiple first airflow channels H1 are provided on the first outer limiting track 1071A, and these multiple first airflow channels H1 can be spaced apart along the circumferential direction of the first outer limiting track 1071A.

[0056] The thrust fan 100 of this application embodiment can connect the first housing space containing the first electromagnetic coil 1061A with the external space through the first airflow channel H1. Therefore, when the first electromagnetic coupling component is working, the heat generated by the first electromagnetic coil 1061A can be discharged from the first housing space through the first airflow channel H1. Of course, the cooling airflow can also enter the first housing space through the first airflow channel H1 to cool the first electromagnetic coupling coil contained in the first housing space.

[0057] In one possible implementation, such as Figures 1-3 As shown, the thrust fan 100 of this application embodiment further includes: a plurality of second electromagnetic coupling components corresponding to a plurality of second blades 105, which may be located between the second ends of the plurality of second blades 105 and the inner sidewall of the casing 101, and the plurality of second electromagnetic coupling components are circumferentially disposed on the inner sidewall of the casing 101 around the annular track 103.

[0058] For any second electromagnetic coupling component, it can be used to electromagnetically couple the second end of the second blade 105 to the inner wall of the casing 101, so that there is a gap between the second end of the corresponding second blade 105 and the inner wall of the casing 101, and the second blade 105 rotates around the annular track 103. When the hub 102 drives multiple first blades 104 to rotate, it can also be driven and accelerated by the first electromagnetic coupling component at the first end and the second electromagnetic coupling component at the second end of the second blade 105. Moreover, by cooperating with the first electromagnetic coupling component and the second electromagnetic coupling component, the second blade 105 can achieve independent acceleration to adapt to different working scenarios.

[0059] Optional, Figure 4B A detailed structural schematic diagram of the second electromagnetic coupling component according to an embodiment of this application is shown. Figure 1 , Figure 5BA detailed structural schematic diagram of the second electromagnetic coupling component according to an embodiment of this application is shown. Figure 2 .like Figures 1-3 , Figure 4B and Figure 5B The second electromagnetic coupling assembly includes a second electromagnetic coil 1061B and two second permanent magnets 1062B. The second electromagnetic coil 1061B is disposed at the second end corresponding to the second blade 105, such that the position of the second electromagnetic coil 1061B changes as the second blade 105 rotates. Therefore, the second electromagnetic coil 1061B can be used as a mover. The two second permanent magnets 1062B are disposed on the inner side wall of the casing 101 along the axial direction of the annular track 103, while the casing 101 remains stationary. Therefore, the position of the second permanent magnets 1062B does not change, and they can be used as stators.

[0060] In one example, the second permanent magnet 1062B can be referred to the previous description of the first permanent magnet 1062A. The second permanent magnet 1062B is covered with a wear-resistant coating to cope with the friction that may occur between it and the second electromagnetic coil 1061B due to the extremely small contact. The second electromagnetic coil 1061B can be encapsulated in a thin-walled housing and disposed at the second end of the second blade 105. The specific details of the thin-walled housing can be referred to the description of the first electromagnetic coil 1061A, and there is a gap between the surface of the thin-walled housing near the inner sidewall of the housing 101 and the inner sidewall of the housing 101.

[0061] In a plurality of second electromagnetic coupling components, the magnetic poles of two adjacent second permanent magnets 1062B are opposite. A second electromagnetic coil 1061B is located between two second permanent magnets 1062B. One of the two second permanent magnets 1062B is opposite to the input end of the second electromagnetic coil 1061B, and the other is opposite to the output end of the second electromagnetic coil 1061B. This arrangement allows the magnetic poles of the second permanent magnets 1062B in the plurality of second electromagnetic coupling components to be arranged in an alternating polarity along the circumferential direction of the annular track 103, thereby enhancing the air gap magnetic flux density and reducing leakage magnetic flux.

[0062] For example, the second permanent magnets 1062B included in the multiple second electromagnetic coupling components can be arranged in a permanent magnet array along the circumferential direction of the ring track 103 in an alternating manner of N poles and S poles, forming a fixed magnetic channel.

[0063] When the second electromagnetic coil 1061B is energized, it becomes a precisely controllable electromagnet. Therefore, for a given second blade 105, an alternating current signal with the same phase and frequency can be supplied to the first electromagnetic coil 1061A and the second electromagnetic coil 1061B corresponding to that second blade 105. At this time, the first electromagnetic coil 1061A can cooperate with the first permanent magnet 1062A to rotate the second blade 105, while the second electromagnetic coil 1061B can generate a circumferential electromagnetic field along the annular track 103, and cooperate with the second permanent magnet to generate a circumferential electromagnetic force, i.e., a tangential driving force, to accelerate the second blade 105. This driving method can be independent of the rotational speed of the first blade 104, achieving independent acceleration of the blade tip region (when the first blade 104 and the second blade 105 are considered as one blade, the second blade 105 can be considered as the blade tip region of that blade).

[0064] Optionally, the electronic control unit in this embodiment can also be electrically connected to the first electromagnetic coil 1061A and the second electromagnetic coil 1061B. When a failure occurs in the first electromagnetic coupling component corresponding to a certain second blade 105, the electronic control unit can adjust the control strategy and rely on the second electromagnetic coupling component corresponding to the second blade 105 to maintain the rotation function of the second blade 105, thereby achieving fault isolation and degraded operation. When a failure occurs in the second electromagnetic coupling component corresponding to a certain second blade 105, the electronic control unit can adjust the control strategy and rely on the first electromagnetic coupling component corresponding to the second blade 105 to maintain the rotation function of the second blade 105, thereby achieving fault isolation and degraded operation.

[0065] As can be seen, in the thrust fan 100 of this application embodiment, a first electromagnetic coupling component is added between the annular track 103 and the inner wall of the casing 101, and a second electromagnetic coupling component is added between the second ends of the plurality of second blades 105 and the inner wall of the casing 101. This redundant design can effectively avoid the risk of thrust loss of the thrust fan 100 due to the failure of a single electromagnetic coupling component, and is especially suitable for the field of aero-engines where safety requirements are extremely high.

[0066] Optional, Figure 6B A schematic diagram of the limiting structure of the second and third electromagnetic coils in an embodiment of this application is shown. Figure 6C A detailed schematic diagram of the limiting structure of the second electromagnetic coil in an embodiment of this application is shown. Figures 1-3 , Figure 4B , Figure 5B , Figure 6B and Figure 6CAs shown, in order to facilitate the installation of the second permanent magnet 1062B and limit the second electromagnetic coil 1061B, the inner wall of the casing 101 has two second outer limiting rails 1071B surrounding the annular rail 103 and a plurality of second limiting sliders 1072B spaced apart around the annular rail 103.

[0067] Each of the two second outer limiting tracks 1071B is distributed along the axial direction of the annular track 103. Optionally, the casing 101 has an air inlet side and an air outlet side, and their distribution direction can be the axial direction of the annular track 103. It can be considered that the two second outer limiting tracks 1071B are arranged on the inner wall of the casing 101 along the distribution direction of the air inlet side and the air outlet side.

[0068] Multiple second limiting sliders 1072B are located between two second outer limiting tracks 1071B. These sliders move along the circumferential direction of the annular track 103 on the inner wall of the casing 101 during the rotation of the multiple second blades 105. At this time, there is a gap between the two second outer limiting tracks 1071B and the second limiting sliders 1072B, and the second limiting sliders 1072B are in contact with the inner wall of the casing 101, but relative movement is possible.

[0069] Two adjacent second limiting sliders 1072B, two second outer limiting rails 1071B, and the inner wall of the casing 101 form a second receiving space. The second electromagnetic coil 1061B is located in the second receiving space, thereby embedding the second electromagnetic coil 1061B assembly in the second receiving space. The second permanent magnet 1062B corresponds one-to-one with the second outer limiting rail 1071B. Each of the two second permanent magnets 1062B is located in one of the corresponding two second outer limiting rails 1071B and is connected to the second electromagnetic coil 1061B included in the two adjacent second electromagnetic coupling assemblies of the second limiting slider 1072B.

[0070] Optionally, the second outer limiting track 1071B may include an annular groove provided on the inner sidewall of the housing 101, with the openings of the annular grooves of the two second outer limiting tracks 1071B facing each other. For example, the opening of the annular groove of the second outer limiting track 1071B near the air inlet side may face the air outlet side, while the opening of the annular groove of the second outer limiting track 1071B near the air outlet side may face the air inlet side. When the second permanent magnet 1062B is provided in the annular groove, the second permanent magnet 1062B may face the end of the second electromagnetic coil 1061B to facilitate electromagnetic coupling between the two.

[0071] Optional, Figure 8 A schematic diagram of the installation structure of the ring track according to an embodiment of this application is shown. Figure 8As shown, the annular track 103 can be fixed to the inner wall of the casing 101. At this time, the thrust fan 100 also includes multiple connecting members 108. The end face of the annular track 103 can be perpendicular to the axial direction of the casing 101. It can be the end face of the annular track 103 facing the air inlet side or the end face of the annular track 103 facing the air outlet side.

[0072] Each of the plurality of connecting members 108 has a first connecting end and a second connecting end. The first connecting end is connected to the end face of the annular track 103, and the second connecting end is connected to the inner wall of the casing 101. The two second permanent magnets 1062B are located on the same side of the second connecting end. For example, the connecting member 108 can be integrally formed with the casing 101, or it can be connected by welding or bolting. In this way, when the connecting member 108 connects the annular track 103 to the inner wall of the casing 101, it will not affect the rotation of the second blade 105.

[0073] As can be seen, in the thrust fan 100 of this application embodiment, the second permanent magnet 1062B can be accurately positioned by the limiting effect of the second outer limiting rail 1071B, so that the second permanent magnet 1062B can couple with the second electromagnetic coil 1061B to form an axial magnetic field force with stable direction and speed, ensuring the stability of the second blade 105 in rotation trajectory and rotational attitude. Furthermore, the second end of the second blade 105 is limited by the second limiting slider 1072B in the circumferential direction of the annular track 103 and by the second outer limiting rail 1071B in the axial direction of the casing 101, which can reduce the vibration position of the second blade 105 during rotation, thereby further enhancing the dynamic stability of the second blade 105 and meeting the safe operation requirements under higher speed and greater thrust conditions.

[0074] Optionally, considering that the first electromagnetic coupling assembly operates under high speed and high power density conditions, resulting in significant resistive heating and eddy current losses in the second electromagnetic coil 1061B, one or more second airflow channels can be provided on the second outer limiting rail. The axial direction of these second airflow channels can be the same as the axial direction of the casing 101. For example, multiple second airflow channels can be provided on the second outer limiting rail, and these channels can be spaced apart along the circumferential direction of the second outer limiting rail.

[0075] The thrust fan 100 of this application embodiment can connect the second housing space containing the second electromagnetic coil 1061B with the external space through the second airflow channel. Therefore, when the second electromagnetic coupling component is working, the heat generated by the second electromagnetic coil 1061B can be discharged from the second housing space through the second airflow channel. Of course, the cooling airflow can also enter the second housing space through the second airflow channel to cool the second electromagnetic coil 1061B contained in the second housing space.

[0076] In addition, the cooling airflow can come from the airflow flowing behind the second blade 105 (the side closer to the air outlet), which can be introduced into the annular track 103 through the connecting member 108, and enter the second accommodating space through the airflow channel opened by the first outer annular track 103 to cool the second electromagnetic coil 1061B in the second accommodating space.

[0077] In one possible implementation, such as Figures 1-3 As shown, the thrust fan 100 of this embodiment may further include: a plurality of third electromagnetic coupling components corresponding to a plurality of first blades 104, located on the surface of the annular track 103 near the hub 102 and the tips of the plurality of first blades 104. The plurality of third electromagnetic coupling components surround the annular track 103.

[0078] In this embodiment, the first blade 104 corresponds one-to-one with the third electromagnetic coupling component. For any third electromagnetic coupling component, it can be used to electromagnetically couple the tip of the first blade 104 to the annular track 103 to adjust the rotational speed of the first blade 104. In this case, during the rotation of the first blade 104 driven by the turbine shaft (low-pressure turbine shaft) hub 102, the third electromagnetic coupling component can be used to increase the rotational speed of the corresponding first blade 104 and reduce the mechanical losses generated by the low-pressure turbine shaft driving the hub 102 to rotate.

[0079] Optional, such as Figures 1-3 , Figure 4A and Figure 5A As shown, the third electromagnetic coupling assembly includes a third electromagnetic coil 1061C and two third permanent magnets 1062C. The third electromagnetic coil 1061C is located at the tip of the corresponding first blade 104, so that the position of the third electromagnetic coil 1061C changes as the first blade 104 rotates. Therefore, the third electromagnetic coil 1061C can be used as a mover. The two third permanent magnets 1062C are located along the axial direction of the annular track 103 on the surface of the annular track 103 near the hub 102. Since the annular track 103 remains stationary, the position of the third permanent magnets 1062C does not change, and they can be used as stators.

[0080] In one example, the third permanent magnets 1062C included in multiple third electromagnetic coupling components can be combined into a permanent magnet array, and the third permanent magnets 1062C can be selected from high-temperature resistant neodymium iron boron (NdFeB) or samarium cobalt (SmCo) permanent magnet materials, with an operating temperature of up to 150℃~350℃, and their surfaces can be coated with a corrosion-resistant protective layer, such as a nickel-copper-nickel plating or an epoxy resin layer.

[0081] In the plurality of third electromagnetic coupling components, the magnetic poles of two adjacent third permanent magnets 1062C are opposite, allowing the magnetic poles of the third permanent magnets 1062C included in the plurality of third electromagnetic coupling components to be arranged in an alternating polarity along the circumferential direction of the annular track 103, thereby enhancing the air gap magnetic flux density and reducing leakage flux. The third electromagnetic coil 1061C is located between the two third permanent magnets 1062C, with one of the two third permanent magnets 1062C facing the input terminal of the third electromagnetic coil 1061C and the other facing the output terminal of the third electromagnetic coil 1061C.

[0082] For example, the third permanent magnets 1062C included in the multiple third electromagnetic coupling components can form a permanent magnet array along the circumferential direction of the ring track 103 in a manner where the N poles and S poles are alternately arranged, forming a fixed magnetic channel.

[0083] When the third electromagnetic coil 1061C is energized, it is an electromagnet that can be precisely controlled. Therefore, according to the principle that like poles repel and unlike poles attract, by precisely controlling the on / off state and direction of the current flowing into the third electromagnetic coil 1061C, the coil can obtain a continuous and powerful directional thrust on the track formed by the magnetic field.

[0084] Optionally, to facilitate the control of the first electromagnetic coupling component, the electronic control system can be electrically connected to the third electromagnetic coil 1061C via the third lead. A lead channel can be provided inside the first blade 104, and the third lead can be electrically connected to the electronic control system along the lead channel provided inside the first blade 104.

[0085] The electronic control system can refer to the rotational speed of the turbine shaft to set the frequency and phase of the third alternating current signal, and then send the third alternating current signal to the third electromagnetic coil 1061C included in each third electromagnetic coupling component. The third electromagnetic coil 1061C can generate a rotating magnetic field in response to the third alternating current signal and interact with the third permanent magnet 1062C included in each third electromagnetic coupling component to generate a circumferential electromagnetic force. This circumferential electromagnetic force drives multiple first blades 104 to rotate.

[0086] like Figure 4A , Figure 5A and Figure 6B As shown, in order to facilitate the installation of the third permanent magnet 1062C and limit the first electromagnetic coil 1061A, the surface of the annular track 103 near the inner wall of the hub 102 has two inner limiting tracks 1071C surrounding the annular track 103 and a plurality of third limiting sliders 1072C distributed at intervals around the annular track 103.

[0087] Each of the two inner limiting rails 1071C is distributed along the axial direction of the annular track 103. When the distribution direction of the air inlet and air outlet sides of the casing 101 is the axial direction of the annular track 103, the two inner limiting rails 1071C are arranged on the surface of the annular track 103 near the hub 102 along the distribution direction of the air inlet and air outlet sides. A plurality of third limiting sliders 1072C are used to move along the circumferential direction of the annular track 103 on the surface of the annular track 103 near the hub 102 during the rotation of the plurality of first blades 104.

[0088] Multiple third limiting sliders 1072C are located between the two inner limiting tracks 1071C. At this time, there is a gap between the two second outer limiting tracks 1071B and the second limiting sliders 1072B, and the third limiting sliders 1072C are in contact with the surface of the annular track 103 near the hub 102, but relative movement is possible.

[0089] Two adjacent third limiting sliders 1072C, two inner limiting rails 1071C, and the surface of the annular rail 103 near the hub 102 form a third accommodating space. A third electromagnetic coil 1061C is located in the third accommodating space. Each of the two second permanent magnets 1062B is located in one of the corresponding inner limiting rails 1071C and is connected to the third electromagnetic coils 1061C included in the two adjacent third electromagnetic coupling components of the third limiting sliders 1072C.

[0090] Optionally, when the thrust fan 100 includes a first electromagnetic coupling component and a second electromagnetic coupling component, the surface of the annular track 103 near the hub 102 is provided with two inner limiting tracks 1071C and the surface of the annular track 103 near the inner wall of the casing 101 is provided with two first outer limiting tracks 1071A, so that the annular track 103, the first outer limiting tracks 1071A and the inner limiting tracks 1071C form an H-shaped structure.

[0091] Optionally, the inner limiting track 1071C may include an annular groove provided on the inner wall of the casing 101, and the openings of the annular grooves included in the two second outer limiting tracks 1071B are opposite to each other. For example, the opening of the annular groove included in the inner limiting track 1071C near the air inlet side may face the air outlet side, while the opening of the annular groove included in the inner limiting track 1071C near the air outlet side may face the air inlet side. When the third permanent magnet 1062C is provided in the annular groove, the third permanent magnet 1062C may face the end of the third electromagnetic coil 1061C to facilitate electromagnetic coupling between the two.

[0092] Optionally, considering that the third electromagnetic coupling component operates under high speed and high power density conditions, resulting in significant resistive heating and eddy current losses in the third electromagnetic coil 1061C, one or more third airflow channels H3 are provided on the third limiting rail. The axial direction of these third airflow channels H3 can be the same as the axial direction of the casing 101. For example, multiple third airflow channels H3 are provided on the inner limiting rail 1071C, and these multiple third airflow channels H3 can be spaced apart along the circumferential direction of the inner limiting rail 1071C.

[0093] The thrust fan 100 of this application embodiment can connect the third housing space containing the third electromagnetic coil 1061C with the external space through the third airflow channel H3. Therefore, when the third electromagnetic coupling component is working, the heat generated by the third electromagnetic coil 1061C can be discharged from the third housing space through the third airflow channel H3. Of course, the cooling airflow can also enter the third housing space through the third airflow channel H3 to cool the third electromagnetic coupling coil contained in the third housing space.

[0094] As can be seen, the blades in the thrust fan 100 of this embodiment can be divided into two groups to shorten the cantilever length (i.e., spanwise height) of each group of blades, increase stiffness, and improve aeroelastic stability, thereby effectively suppressing flutter. Simultaneously, the design of multiple electromagnetic coupling components can reduce frictional losses caused by traditional mechanical transmission, improving fan efficiency; and by controlling the rotational speed of the upper and lower fan blades separately through current, the different speeds maximize the thrust of the thrust fan 100, making the thrust fan 100 more convenient and flexible to operate.

[0095] It is understood that the actions and steps described in the above embodiments and accompanying drawings can be performed in different orders to achieve the technical effects expected in this application, and are not limited to the order described in the above embodiments and accompanying drawings.

[0096] The embodiments of this application have been described above. However, these embodiments are merely illustrative and not intended to limit the scope of this application. The scope of this application is defined by the appended claims and their equivalents. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this application, and all such substitutions and modifications should fall within the scope of this application.

Claims

1. A thrust fan, characterized in that, include: The thrust fan further includes: a casing, a hub and an annular track disposed within the casing, the annular track being located between the hub and the inner wall of the casing, the annular track remaining stationary relative to the casing; and the thrust fan also includes: Multiple first blades are located between the hub and the annular track, and are disposed on the hub along the circumferential direction of the hub. The hub is used to drive each of the multiple first blades to rotate around the hub. A plurality of second blades, located between the annular track and the inner wall of the casing, having a first end near the annular track and a second end near the inner wall of the casing; and, A plurality of first electromagnetic coupling components corresponding to the plurality of second blades are located between the first ends of the plurality of second blades and the annular track. The plurality of first electromagnetic coupling components surround the annular track. The first electromagnetic coupling components are used to electromagnetically couple the first ends of the second blades to the annular track, so that the corresponding second blades are suspended between the annular track and the inner wall of the casing and rotate around the annular track.

2. The thrust fan according to claim 1, characterized in that, The first electromagnetic coupling assembly includes a first electromagnetic coil and two first permanent magnets. The first electromagnetic coil is disposed at a first end corresponding to the second blade, and the two first permanent magnets are disposed on the surface of the annular track near the inner wall of the casing along the axial direction of the annular track. In the plurality of first electromagnetic coupling components, the magnetic poles of two adjacent first permanent magnets are opposite, the first electromagnetic coil is located between the two first permanent magnets, one of the two first permanent magnets is opposite to the input end of the first electromagnetic coil, and the other is opposite to the output end of the first electromagnetic coil.

3. The thrust fan according to claim 2, characterized in that, The surface of the annular track near the inner wall of the casing has two first outer limiting tracks surrounding the annular track and a plurality of first limiting sliders spaced apart around the annular track. Each of the two first outer limiting tracks is distributed along the axial direction of the annular track, and the plurality of first limiting sliders are located between the two first outer limiting tracks. The plurality of first limiting sliders are used to move along the circumferential direction of the annular track on the surface of the annular track near the inner wall of the casing during the rotation of the plurality of second blades. The surfaces of two adjacent second limiting sliders, the two first outer limiting tracks, and the annular track near the inner wall of the casing form a first accommodating space, and the first electromagnetic coil is located in the first accommodating space; each of the two first permanent magnets is disposed in one of the corresponding two first outer limiting tracks, and is connected to the first electromagnetic coils of the two adjacent first electromagnetic coupling components of the first limiting slider.

4. The thrust fan according to claim 1, characterized in that, The thrust fan further includes: a plurality of second electromagnetic coupling components corresponding to the plurality of second blades, located between the second ends of the plurality of second blades and the inner wall of the casing, the plurality of second electromagnetic coupling components being circumferentially disposed on the inner wall of the casing around the annular track, the second electromagnetic coupling components being used to electromagnetically couple the second ends of the second blades to the inner wall of the casing, such that there is a gap between the second ends of the second blades and the inner wall of the casing, and the second blades rotating around the annular track.

5. The thrust fan according to claim 4, characterized in that, The second electromagnetic coupling assembly includes a second electromagnetic coil and two second permanent magnets. The second electromagnetic coil is disposed at the second end corresponding to the second blade, and the two second permanent magnets are disposed on the inner side wall of the casing along the axial direction of the annular track. In the plurality of second electromagnetic coupling components, the magnetic poles of two adjacent second permanent magnets are opposite, the second electromagnetic coil is located between the two second permanent magnets, one of the two second permanent magnets is opposite to the input end of the second electromagnetic coil, and the other is opposite to the output end of the second electromagnetic coil.

6. The thrust fan according to claim 5, characterized in that, The inner wall of the casing has two second outer limiting tracks surrounding the annular track and a plurality of second limiting sliders spaced apart around the annular track, each of the two second outer limiting tracks being distributed along the axial direction of the annular track; The plurality of second limiting sliders are located between the two second outer limiting rails, and the plurality of second limiting sliders are used to move along the circumferential direction of the annular rails on the inner wall of the casing during the rotation of the plurality of second blades; The two adjacent second limiting sliders, the two second outer limiting tracks, and the inner wall of the casing form a second accommodating space. The second electromagnetic coil is located in the second accommodating space. Each of the two second permanent magnets is located in one of the corresponding two second outer limiting tracks and is connected to the second electromagnetic coils of the two adjacent second electromagnetic coupling components of the second limiting slider.

7. The thrust fan according to any one of claims 1 to 6, characterized in that, The thrust fan further includes: a plurality of third electromagnetic coupling components corresponding to the plurality of first blades, located on the surface of the annular track near the hub and at the tips of the plurality of first blades; The plurality of third electromagnetic coupling components surround the annular track, and the third electromagnetic coupling components are used to electromagnetically couple the tip of the first blade to the annular track in order to adjust the rotational speed of the first blade.

8. The thrust fan according to claim 7, characterized in that, The third electromagnetic coupling assembly includes a third electromagnetic coil and two third permanent magnets. The third electromagnetic coil is located at the tip corresponding to the first blade, and the two third permanent magnets are located on the surface of the annular track near the hub, along the axial direction of the annular track. In the plurality of third electromagnetic coupling components, the magnetic poles of two adjacent third permanent magnets are opposite, the third electromagnetic coil is located between the two third permanent magnets, one of the two third permanent magnets is opposite to the input end of the third electromagnetic coil, and the other is opposite to the output end of the third electromagnetic coil.

9. The thrust fan according to claim 8, characterized in that, The surface of the annular track near the inner wall of the hub has two inner limiting tracks surrounding the annular track and a plurality of third limiting sliders spaced apart around the annular track. Each of the two inner limiting tracks is distributed along the axial direction of the annular track, and the plurality of third limiting sliders are used to move along the circumferential direction of the annular track on the surface of the annular track near the hub during the rotation of the plurality of first blades. The plurality of third limiting sliders are located between the two inner limiting tracks. Two adjacent third limiting sliders, the two inner limiting tracks, and the annular track near the surface of the hub form a third accommodating space. The third electromagnetic coil is located in the third accommodating space. Each of the two third permanent magnets is located in one of the corresponding inner limiting tracks and is connected to the third electromagnetic coils included in the two adjacent third electromagnetic coupling components of the plurality of third limiting sliders.

10. An engine, characterized in that, include: Includes the thrust fan as described in any one of claims 1 to 9.

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