An engine and an aircraft

Abstract

The application belongs to the technical field of aviation aircraft, and particularly relates to an engine and an aviation aircraft. The application provides an engine, which comprises: a detonation power assembly arranged in a cavity between an inner rotor and an outer rotor, a power generation assembly for generating power after the inner rotor and / or the outer rotor is driven to rotate, a center shaft provided with an energy storage part, the power generation assembly is electrically connected with the energy storage part, and the energy storage part can drive the inner rotor to rotate. The application further provides an aviation aircraft comprising the above engine. The thrust generated by combustion of the detonation power assembly drives the inner rotor and the outer rotor to rotate, power generation is performed through the power generation assembly, and energy is stored in the energy storage part, so that the loss of energy efficiency is avoided; when greater power is required, the energy storage part drives the inner rotor to rotate, and the inner rotor and the detonation power assembly are jointly driven, so that the stability of the engine in high-speed operation is improved; and the technical defects that the detonation power device has poor stability and large efficiency loss are solved.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, and particularly relates to an engine and an aircraft. Background Technology

[0002] Detonation propulsion devices are a new type of jet propulsion device based on the principle of detonation combustion. Fuel and oxidizer are mixed to form a combustible mixture, which is then triggered by an initiation device to generate detonation, producing immense pressure and high temperature. The resulting high-temperature, high-pressure detonation combustion products are discharged at high speed through the tail nozzle, thus generating thrust. Compared to common slow-burning combustion, it has a higher heat release rate, faster combustion wave propagation speed, and a higher self-pressurization effect of the burned gas. Common detonation propulsion devices include rotating detonation engines (RDE), pulse detonation engines (PDE), and oblique detonation engines (ODE), serving as the main propulsion system for rockets, missiles, aircraft, and other spacecraft.

[0003] Traditional detonation power devices have three main drawbacks: 1. Low engineering applicability: Rotary detonation combustion is a near-continuous process, requiring solutions to problems such as difficulty initiating liquid fuel, narrow detonation boundaries, unstable combustion, and short duration; 2. Unstable detonation mode: This leads to problems such as unstable speed, efficiency loss, load imbalance, structural strength issues, shock wave losses, and total pressure losses on the power unit platform; 3. Adaptability issues of detonation to upstream and downstream components: Difficulty in matching with upstream and downstream engine components.

[0004] Therefore, developing an engine and aircraft to address the technical shortcomings of existing detonation power devices, such as poor stability and significant efficiency loss, has become an urgent problem for those skilled in the art. Summary of the Invention

[0005] Therefore, it is necessary to address the technical shortcomings of existing detonation power devices, such as poor stability and significant efficiency loss, and to provide an engine and aircraft.

[0006] This application provides an engine, which includes: a detonation force assembly, an inner rotor, an outer rotor, a central shaft, and a power generation assembly;

[0007] The inner rotor is coupled to the central shaft, the outer rotor is disposed outside the inner rotor, a cavity is provided between the outer rotor and the inner rotor, and the detonation force assembly is disposed in the cavity for driving the inner rotor and / or the outer rotor to rotate;

[0008] The power generation component includes: a stator and a fourth permanent magnet. The stator is hinged to the central shaft. The outer rotor is an annular structure. The annular outer wall of the outer rotor is provided with a plurality of first grooves. The fourth permanent magnet is embedded in the first grooves. The fourth permanent magnet is matched with the stator to generate electricity.

[0009] The central shaft is provided with an energy storage unit, and the power generation component is electrically connected to the energy storage unit. The energy storage unit provides power to drive the inner rotor to rotate.

[0010] In one embodiment, the stator includes: a stator core, a coil winding, and a frame. The coil winding is disposed inside the stator core and is embedded in a slot of the stator core. The stator core and the coil winding are fixed to the frame, and the frame is hinged to the central shaft.

[0011] In one embodiment, the power generation assembly further includes: a third permanent magnet and a longitudinally suspended stator, the longitudinally suspended stator being fixed to the central shaft, the outer wall surface of the outer rotor being provided with a third groove wound in an annular shape, the third permanent magnet being embedded in the third groove, the third permanent magnet being matched with the longitudinally suspended stator for suspending the outer rotor in the longitudinal direction.

[0012] In one embodiment, the power generation component further includes: a second permanent magnet and an axially suspended stator, the axially suspended stator being fixed to the central shaft, the end face of the outer rotor being provided with a second groove, the second permanent magnet being embedded in the second groove, the second permanent magnet being matched with the axially suspended stator for axially suspending the outer rotor.

[0013] In one embodiment, the annular sidewall of the outer rotor is provided with several air-cooled cavities.

[0014] In one embodiment, the inner rotor includes rotor blades and a cylindrical ring, the rotor blades being coupled to the central shaft.

[0015] In one embodiment, the outer wall of the inner rotor is provided with an external spiral thread, and the inner wall of the outer rotor is provided with an internal spiral thread, wherein the external spiral thread and the internal spiral thread interact.

[0016] In one embodiment, the engine further includes: a first permanent magnet, wherein the end face of the inner wall of the stator is provided with a stator groove, the first permanent magnet is disposed in the stator groove, and the first permanent magnet is matched with the coil winding for suspending the coil winding.

[0017] In one embodiment, a portion of the inner wall of the outer rotor is provided with the internal spiral thread, and a portion of the outer wall of the inner rotor is provided with the external spiral thread.

[0018] This application also provides an aircraft comprising the engine described in any of the above claims.

[0019] In summary, this application provides an engine comprising: a detonation force assembly, an inner rotor, an outer rotor, a central shaft, and a power generation assembly; the inner rotor is coupled to the central shaft, the outer rotor is disposed outside the inner rotor, a cavity is provided between the outer rotor and the inner rotor, the detonation force assembly is disposed in the cavity, and is used to drive the inner rotor and / or the outer rotor to rotate; the power generation assembly comprises: a stator and a fourth permanent magnet, the stator is hinged to the central shaft, the outer rotor is an annular structure, the annular outer wall of the outer rotor is provided with a plurality of first grooves, the fourth permanent magnet is embedded in the first grooves, and the fourth permanent magnet is matched with the stator to generate electricity; the central shaft is provided with an energy storage unit, the power generation assembly is electrically connected to the energy storage unit, and the energy storage unit supplies energy to drive the inner rotor to rotate. This application also provides an aircraft including the above-described engine. This application provides an engine and aircraft in which the thrust generated by the combustion of the detonation force assembly drives the inner and outer rotors to rotate, and then generates electricity through a power generation assembly and stores the energy in an energy storage unit, thus avoiding energy efficiency loss. When more power is needed, the energy storage unit drives the inner rotor to rotate, working together with the detonation force assembly to improve the stability of the engine at high speeds. This solves the technical defects of existing detonation force devices, such as poor stability and large efficiency loss. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0021] Figure 1 A three-dimensional structural schematic diagram of an engine provided in the technical solution of this application embodiment;

[0022] Figure 2 A schematic cross-sectional view of the left side of an engine provided in the technical solution of this application embodiment;

[0023] Figure 3 This application provides a schematic diagram of the stator structure in an engine according to an embodiment of the present application.

[0024] Figure 4 A side sectional view of the stator in an engine provided in an embodiment of this application;

[0025] Figure 5This application provides a schematic diagram of the structure of an outer rotor in an engine.

[0026] Figure 6 A side cross-sectional view of an outer rotor equipped with permanent magnets in an engine provided in an embodiment of this application;

[0027] Figure 7 This application provides a schematic diagram of the structure of an inner rotor in an engine.

[0028] Figure 8 A side sectional view of the inner rotor in an engine provided in an embodiment of this application;

[0029] The components include an axially suspended stator 1, a longitudinally suspended stator 2, a first permanent magnet 3, a second permanent magnet 4, a third permanent magnet 5, a fourth permanent magnet 6, an air-cooled cavity 7, an outer rotor 8, an inner spiral thread 9, an outer spiral thread 10, an inner rotor 11, a central shaft 12, rotor blades 13, and a stator 14. Detailed Implementation

[0030] This application provides an engine and an aircraft to address the technical defects of existing detonation power devices, such as poor stability and significant efficiency loss.

[0031] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0032] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, 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, and therefore should not be construed as a limitation of this application.

[0033] 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 at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0034] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0035] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0036] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0037] Please see Figure 1 and Figure 2This application provides an engine, including: a detonation force assembly, an inner rotor 11, an outer rotor 8, a central shaft 12, and a power generation assembly; the inner rotor 11 is coupled to the central shaft 12, the outer rotor 8 is disposed outside the inner rotor 11, a cavity is provided between the outer rotor 8 and the inner rotor 11, the detonation force assembly is disposed in the cavity, and is used to drive the inner rotor 11 and / or the outer rotor 8 to rotate; the power generation assembly includes: a stator 14 and a fourth permanent magnet 6, the stator 14 is hinged to the central shaft 12, the outer rotor 8 is an annular structure, the annular outer wall of the outer rotor 8 is provided with a plurality of first grooves, the fourth permanent magnet 6 is embedded in the first grooves, and the fourth permanent magnet 6 is matched with the stator 14 to generate electricity; the central shaft 12 is provided with an energy storage part, the power generation assembly is electrically connected to the energy storage part, and the energy storage part supplies energy to drive the inner rotor 11 to rotate.

[0038] In the technical solution provided in this application embodiment, the power generated by the combustion of the detonation force assembly is the main power source of the engine. When the engine is in a steady-state flight condition, there will be a certain amount of energy waste in the combustion of the detonation force assembly. At this time, the power generated by the combustion can drive the outer rotor 8 and the inner rotor 11 to rotate. When rotating, they interact with the power generation assembly to generate electrical energy, which is stored in the energy storage section. The energy of the detonation force assembly is stored in the form of electrical energy, avoiding energy waste and reducing the energy efficiency loss of the detonation force assembly.

[0039] When the engine is in takeoff or high-speed operation, it needs to provide greater thrust. At this time, the thrust generated by the combustion of the knock force component can be used efficiently. At the same time, the electrical energy stored in the energy storage unit drives the inner rotor 11 to rotate and generate thrust. At this time, the engine thrust comes from the knock force component and the rotation of the inner rotor 11. The two thrusts work together to provide power, effectively improving the engine performance, especially the working stability at high speeds, and expanding the engine speed range.

[0040] Please refer to this section for further information. Figure 3 and Figure 4 In an engine provided in this application embodiment, the stator 14 includes a stator core, a coil winding, and a frame. The coil winding is disposed inside the stator core and is embedded in a slot in the stator core. The stator core and the coil winding are fixed to the frame, and the frame is hinged to the central shaft 12. The hinge between the frame and the central shaft 12 provides a stable mounting reference for the stator 14. The stator core and the coil winding cooperate with the fourth permanent magnet 6 to generate electricity.

[0041] Please see here. Figure 5 and Figure 6To simplify the engine structure by suspending and fixing the stator 14 in the longitudinal direction, and eliminating the need to fix the stator 14 in the longitudinal direction, the power generation component of the engine provided in this application embodiment further includes: a third permanent magnet 5 and a longitudinally suspended stator 2. The longitudinally suspended stator 2 is fixed to the central shaft 12. The outer wall surface of the outer rotor 8 is provided with a third groove that is wound in an annular shape. The third permanent magnet 5 is embedded in the third groove. The third permanent magnet 5 matches the longitudinally suspended stator 2 and is used to suspend the outer rotor 8 in the longitudinal direction.

[0042] Similarly, in order to suspend and fix the stator 14 in the axial direction and simplify the structure of the engine, without the need to fix the stator 14 in the axial direction, the power generation component of the engine provided in this application embodiment further includes: a second permanent magnet 4 and an axially suspended stator 1. The axially suspended stator 1 is fixed to the central shaft 12. The end face of the outer rotor 8 is provided with a second groove. The second permanent magnet 4 is embedded in the second groove. The second permanent magnet 4 matches the axially suspended stator 1 and is used to suspend the outer rotor 8 in the axial direction.

[0043] To further optimize the technical solution, in the technical solution provided in this application embodiment, the annular sidewall of the outer rotor 8 is provided with several air-cooled cavities 7. The air-cooled cavities 7 cool the heat generated by the detonation combustion assembly through airflow, preventing high temperature from affecting the permanent magnets of the power generation assembly.

[0044] Please see here. Figure 7 and Figure 8 In the technical solution provided in this application embodiment, the inner rotor 11 includes rotor blades 13 and a cylindrical ring, with the rotor blades 13 coupled to the central shaft 12. When the engine is in a steady-state flight condition, the cylindrical ring rotates to generate electricity. When the engine is in a takeoff or high-speed operation condition, the energy storage unit drives the rotor blades 13 to rotate, which together with the detonation combustion assembly generates driving force to ensure stable engine operation.

[0045] In order to more efficiently utilize the power of the detonation combustion assembly to drive the inner rotor 11 and / or the outer rotor 8 to rotate, the outer wall of the inner rotor 11 is provided with an external spiral thread 10, and the inner wall of the outer rotor 8 is provided with an internal spiral thread 9, with the external spiral thread 10 and the internal spiral thread 9 interacting.

[0046] An engine provided in this application embodiment further includes: a first permanent magnet 3; a stator groove is provided on the end face of the inner wall of the stator 14; the first permanent magnet 3 is disposed in the stator groove; the first permanent magnet 3 is matched with the coil winding and is used to suspend the coil winding. The magnetic levitation force generated by the first permanent magnet 3 and the coil winding can effectively suspend and fix the coil winding, further simplifying the structure of the engine.

[0047] In the technical solution provided in this application embodiment, a portion of the inner wall of the outer rotor 8 is provided with an internal spiral thread 9, and a portion of the outer wall of the inner rotor 11 is provided with an external spiral thread 10. The detonation combustion assembly burns in the cavity between the outer rotor 8 and the inner rotor 11. After the portion without the internal spiral thread 9 and the external spiral thread 10 is fully burned to generate a detonation wave, it interacts with the external spiral thread 10 and the internal spiral thread 9 to drive the inner rotor 11 and the outer rotor 8 to rotate.

[0048] The engine provided in this application embodiment effectively utilizes the propagation characteristics of continuous detonation waves by coupling magnetic levitation technology, rim motor technology and continuous detonation technology. It also achieves the integration of the detonation combustion component and the turbine through a novel design concept that replaces the traditional turbine with a spiral thread, thus realizing the coupling of the detonation combustion component and the transmission turbine. This proposes a new detonation engine structure, which can provide a new route for the integrated design of future flight propulsion systems.

[0049] The detonation combustion component is levitated and rotated by a magnetically levitated central axis, which not only integrates the detonation combustion component with the rotor, but also meets the requirements of low noise and environmental friendliness. The hybrid magnetically levitated central axis control scheme realizes the controllable charging and discharging function, which not only provides part of the energy supply for the energy storage unit, but also effectively utilizes the ineffective work done by the detonation combustion component during combustion, making the energy use efficiency higher.

[0050] Based on the above advantages, the engine provided in this application embodiment can be used as the core power structure of an aircraft and installed in the aircraft.

[0051] In summary, this application provides an engine comprising: a detonation force assembly, an inner rotor, an outer rotor, a central shaft, and a power generation assembly; the inner rotor is coupled to the central shaft, the outer rotor is disposed outside the inner rotor, a cavity is provided between the outer rotor and the inner rotor, the detonation force assembly is disposed in the cavity, and is used to drive the inner rotor and / or the outer rotor to rotate; the power generation assembly comprises: a stator and a fourth permanent magnet, the stator is hinged to the central shaft, the outer rotor is an annular structure, the annular outer wall of the outer rotor is provided with a plurality of first grooves, the fourth permanent magnet is embedded in the first grooves, and the fourth permanent magnet is matched with the stator to generate electricity; the central shaft is provided with an energy storage unit, the power generation assembly is electrically connected to the energy storage unit, and the energy storage unit supplies energy to drive the inner rotor to rotate. This application also provides an aircraft including the above-described engine. This application provides an engine and aircraft in which the thrust generated by the combustion of the detonation force assembly drives the inner and outer rotors to rotate, and then generates electricity through a power generation assembly and stores the energy in an energy storage unit, thus avoiding energy efficiency loss. When more power is needed, the energy storage unit drives the inner rotor to rotate, working together with the detonation force assembly to improve the stability of the engine at high speeds. This solves the technical defects of existing detonation force devices, such as poor stability and large efficiency loss.

[0052] The technical features of the embodiments described above can be combined arbitrarily. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as the combination of these technical features does not contradict each other, it should be considered within the scope of this specification. Furthermore, other implementation methods can be derived from the above embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.

[0053] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An engine, characterized in that, The engine includes: a knock force assembly, an inner rotor, an outer rotor, a central shaft, and a power generation assembly; The inner rotor is coupled to the central shaft, the outer rotor is disposed outside the inner rotor, a cavity is provided between the outer rotor and the inner rotor, and the detonation force assembly is disposed in the cavity for driving the inner rotor and / or the outer rotor to rotate; The power generation component includes: a stator and a fourth permanent magnet. The stator is hinged to the central shaft. The outer rotor is an annular structure. The annular outer wall of the outer rotor is provided with a plurality of first grooves. The fourth permanent magnet is embedded in the first grooves. The fourth permanent magnet is matched with the stator to generate electricity. The central shaft is provided with an energy storage unit, and the power generation component is electrically connected to the energy storage unit. The energy storage unit can supply power to drive the inner rotor to rotate.

2. The engine according to claim 1, characterized in that, The stator includes a stator core, a coil winding, and a frame. The coil winding is disposed inside the stator core and is embedded in a slot in the stator core. The stator core and the coil winding are fixed to the frame, and the frame is hinged to the central shaft.

3. The engine according to claim 1, characterized in that, The power generation component further includes: a third permanent magnet and a longitudinally suspended stator. The longitudinally suspended stator is fixed to the central shaft. The outer wall surface of the outer rotor is provided with a third groove that is wound in an annular shape. The third permanent magnet is embedded in the third groove. The third permanent magnet matches the longitudinally suspended stator and is used to suspend the outer rotor in the longitudinal direction.

4. The engine according to claim 3, characterized in that, The power generation assembly further includes: a second permanent magnet and an axially suspended stator. The axially suspended stator is fixed to the central shaft. The end face of the outer rotor is provided with a second groove. The second permanent magnet is embedded in the second groove. The second permanent magnet matches the axially suspended stator and is used to axially suspend the outer rotor.

5. The engine according to claim 3 or 4, characterized in that, The annular sidewall of the outer rotor is provided with several air-cooled cavities.

6. The engine according to claim 1, characterized in that, The inner rotor includes rotor blades and a cylindrical ring, wherein the rotor blades are coupled to the central shaft.

7. The engine according to claim 1, characterized in that, The outer wall of the inner rotor is provided with an external spiral thread, and the inner wall of the outer rotor is provided with an internal spiral thread, with the external spiral thread and the internal spiral thread interacting.

8. The engine according to claim 2, characterized in that, The engine further includes: a first permanent magnet, wherein the end face of the inner wall of the stator is provided with a stator groove, the first permanent magnet is disposed in the stator groove, and the first permanent magnet is matched with the coil winding for suspending the coil winding.

9. The engine according to claim 7, characterized in that, A portion of the inner wall of the outer rotor is provided with the inner spiral thread, and a portion of the outer wall of the inner rotor is provided with the outer spiral thread.

10. An aircraft, characterized in that, The aircraft includes the engine as described in any one of claims 1 to 9.

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