Hybrid power engine and aviation aircraft

Abstract

The invention belongs to the technical field of aviation aircrafts, and particularly relates to a hybrid power engine and an aviation aircraft. The invention provides a hybrid power engine which comprises a detonation combustion chamber, a center shaft and a power generation assembly, the power generation assembly comprises a stator, an outer rotor and fourth permanent magnets, the stator is hinged to the center shaft, the outer rotor is of an annular structure, a plurality of first grooves are formed in the annular outer wall of the outer rotor, and the fourth permanent magnets are embedded in the first grooves; the fourth permanent magnet is matched with the stator for power generation; the detonation combustion chamber is arranged in the outer rotor and drives the outer rotor to rotate; the center shaft is provided with an energy storage part, and the power generation assembly is electrically connected with the energy storage part. The invention further provides an aviation aircraft comprising the hybrid power engine. According to the engine, the detonation combustion chamber combusts to drive the outer rotor to rotate to generate electricity, redundant power of the detonation combustion chamber generates electricity through the power generation assembly and then is stored in the energy storage part, waste of redundant energy is avoided, and the energy storage part can also be used for providing driving power.

Description

Technical Field

[0001] The present application belongs to the field of aviation technology, and in particular relates to a hybrid power engine and an aviation aircraft. Background Art

[0002] A detonation power device is a device that uses high-temperature, high-pressure gas generated by detonation combustion to generate thrust or power. It generally includes: rotating detonation engines, pulse detonation engines, detonation wave rotor engines and other types.

[0003] In the existing technology, the detonation power device has the following main defects, including: 1. The engineering applicability of the detonation power device is low, and the rotating detonation combustion is approximately a continuous process, which requires solving problems such as difficulty in detonating liquid fuel, narrow detonation boundary, unstable combustion, and short duration; 2. The detonation mode is unstable, which correspondingly brings problems such as unstable speed, efficiency loss, load imbalance, structural strength, shock wave loss and total pressure loss to the power unit platform; 3. The adaptability of detonation to upstream and downstream components. Like the detonation mode, it faces the characteristics of detonation itself, such as pressure forward transmission, unstable combustion process, uneven flow, high temperature and high pressure exhaust, and supersonic flow, which brings huge engineering and technical challenges to the matching of upstream and downstream components of the engine.

[0004] Therefore, developing a hybrid engine and aircraft to solve the technical defects of the existing technology, such as poor applicability, poor operating stability and poor adaptability of upstream and downstream components, has become an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0005] Based on this, it is necessary to provide a hybrid power engine and aircraft to address the technical defects of the existing technology, such as poor applicability, poor operating stability and poor adaptability of upstream and downstream components of the detonation force device.

[0006] The present application provides a hybrid engine, comprising: a detonation combustion chamber, a central shaft, and a power generation assembly, wherein the power generation assembly comprises: a stator, an outer rotor, and a fourth permanent magnet, wherein the stator is hingedly connected to the central shaft, the outer rotor is an annular structure, and the annular outer wall of the outer rotor is provided with a plurality of first grooves, wherein the fourth permanent magnet is embedded in the first grooves, and the fourth permanent magnet and the stator are matched to generate electricity;

[0007] The detonation combustion chamber is arranged inside the outer rotor, and the detonation combustion chamber drives the outer rotor to rotate;

[0008] The central axis is provided with an energy storage part, and the power generation component is electrically connected to the energy storage part.

[0009] In one embodiment, the stator includes: a stator core, a coil winding and a machine base. The coil winding is provided inside the stator core, and the coil winding is embedded in the slot of the stator core. The stator core and the coil winding are fixed to the machine base, and the machine base is hinged to the center axis.

[0010] In one embodiment, the base is a cross-shaped structure.

[0011] In one embodiment, the power generation component also includes: a third permanent magnet and a longitudinally suspended stator, the longitudinally suspended stator is fixed to the central axis, the outer wall surface of the outer rotor is provided with a third groove in a ring shape, the third permanent magnet is embedded in the third groove, and the third permanent magnet is 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 is fixed to the central axis, the end surface of the outer rotor is provided with a second groove, the second permanent magnet is embedded in the second groove, and the second permanent magnet is matched with the axially suspended stator for axially suspending the outer rotor.

[0013] In one embodiment, the annular side wall of the outer rotor is provided with a plurality of air cooling cavities.

[0014] In one embodiment, the inner wall of the outer rotor is provided with an internal thread.

[0015] In one embodiment, the hybrid engine further includes: a first permanent magnet, a stator groove is provided on the end surface of the inner wall of the stator, the first permanent magnet is arranged in the stator groove, and the first permanent magnet matches the coil winding and is used to suspend the coil winding.

[0016] In one embodiment, a portion of the inner wall of the outer rotor is provided with the internal thread.

[0017] The present application also provides an aircraft, which includes any one of the hybrid power engines described above.

[0018] In summary, the present application provides a hybrid engine comprising: a detonation combustion chamber, a central shaft, and a power generation assembly. The power generation assembly comprises: a stator, an outer rotor, and a fourth permanent magnet. The stator is hingedly connected to the central shaft. The outer rotor is an annular structure. The outer annular wall of the outer rotor is provided with a plurality of first grooves. The fourth permanent magnet is embedded in the first grooves and matches the stator to generate electricity. The detonation combustion chamber is disposed within the outer rotor and drives the outer rotor to rotate. The central shaft is provided with an energy storage unit, and the power generation assembly is electrically connected to the energy storage unit. The present application also provides an aircraft including the hybrid engine described above. In the hybrid engine and aircraft provided by the present application, combustion in the detonation combustion chamber drives the outer rotor to rotate and generate electricity. Excess power from the detonation combustion chamber is generated by the power generation assembly and then stored in the energy storage unit. This not only avoids the waste of excess energy, but also allows the energy storage unit to provide driving power when necessary. This addresses the technical shortcomings of prior art detonation power devices, such as poor applicability, poor operational stability, and poor adaptability of upstream and downstream components. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without any creative work.

[0020] Figure 1 A schematic diagram of the three-dimensional structure of a hybrid engine in the technical solution provided in the embodiment of the present application;

[0021] Figure 2 A schematic diagram of the left side cross-sectional structure of a hybrid engine in the technical solution provided in an embodiment of the present application;

[0022] Figure 3 A schematic diagram of the three-dimensional structure of a stator in a hybrid engine provided in an embodiment of the present application;

[0023] Figure 4 A schematic side cross-sectional view of a stator in a hybrid engine provided in an embodiment of the present application;

[0024] Figure 5 A schematic diagram of the three-dimensional structure of an outer rotor in a hybrid engine provided in an embodiment of the present application;

[0025] Figure 6 A schematic side cross-sectional view of an outer rotor in a hybrid engine provided in an embodiment of the present application;

[0026] Figure 7 A schematic diagram of the three-dimensional structure of a detonation combustion chamber in a hybrid engine provided in an embodiment of the present application;

[0027] Figure 8 A schematic diagram of the internal cross-sectional structure of a detonation combustion chamber in a hybrid engine provided in an embodiment of the present application;

[0028] Among them, there are 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 cooling cavity 7, an outer rotor 8, an internal thread 9, a detonation combustion chamber 10, a central shaft 11 and a stator 12. DETAILED DESCRIPTION

[0029] The embodiments of the present application provide a hybrid power engine and aircraft to address the technical defects of the prior art, such as poor applicability, poor operating stability, and poor adaptability of upstream and downstream components of the detonation power device.

[0030] To make the above-mentioned objects, features, and advantages of the present application more clearly understood, the specific embodiments of the present application are described in detail below with reference to the accompanying drawings. The following description sets forth many specific details to facilitate a full understanding of the present application. However, the present application can be implemented in many other ways than those described herein, and those skilled in the art can make similar improvements without violating the scope of the present application. Therefore, the present application is not limited to the specific embodiments disclosed below.

[0031] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0032] 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 the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. Throughout the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0033] In this application, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0034] In this application, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0035] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be an intermediate element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be an intermediate 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 implementation methods.

[0036] See also Figure 1 、 Figure 2 、 Figure 7 as well as Figure 8 An embodiment of the present application provides a hybrid engine, including: a detonation combustion chamber 10, a central shaft 11 and a power generation component, the power generation component including: a stator 12, an outer rotor 8 and a fourth permanent magnet 6, the stator 12 is hinged to the central shaft 11, 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 matches the stator 12 to generate electricity; the detonation combustion chamber 10 is arranged inside the outer rotor 8, and the detonation combustion chamber 10 drives the outer rotor 8 to rotate; the central shaft 11 is provided with an energy storage part, and the power generation component is electrically connected to the energy storage part.

[0037] In the technical solution provided in the embodiment of the present application, the combustion in the detonation combustion chamber 10 provides the main power source for the hybrid engine. At the same time, in the power generation component, the stator 12 is hinged to the central shaft 11 to provide a stable installation structure foundation. When the detonation combustion chamber 10 arranged inside the outer rotor 8 burns, a part of the energy generated by the combustion drives the outer rotor 8 to rotate. At this time, the fourth permanent magnet 6 on the outer wall of the outer rotor 8 rotates accordingly, matching with the stator 12 to complete power generation, and a part of the energy in the combustion process of the detonation combustion chamber 10 is used to generate electrical energy through magnetic field rotation.

[0038] The power generation component is electrically connected to the energy storage part arranged on the central axis 11. The electric energy generated by the power generation component is stored in the energy storage part. The energy storage part can serve as another power source of the hybrid engine, and together with the power generated during combustion in the detonation combustion chamber 10, it can serve as the power source of the hybrid engine.

[0039] In the technical solution provided in the embodiment of the present application, when the engine is in a steady-state flight condition, there will be a certain amount of waste in the energy generated by the combustion in the detonation combustion chamber 10. At this time, the power generated by the combustion can drive the outer rotor 8 to rotate and then generate electricity and store it in the energy storage part. The excess combustion energy is stored in the form of electrical energy, which avoids energy waste and effectively improves the energy utilization rate of the detonation combustion chamber 10.

[0040] When the engine is in takeoff or high-speed operation, greater thrust is required. At this time, the thrust generated by the combustion in the detonation combustion chamber 10 can be efficiently utilized. At the same time, the electrical energy stored in the energy storage unit can also be used as a power source for the engine to generate thrust. At this time, the thrust of the engine comes from the combustion in the detonation combustion chamber 10 and the energy supply of the energy storage unit. The detonation combustion chamber 10 and the energy storage unit jointly provide power, which effectively improves the performance of the engine, especially the working stability at high speed, and broadens the speed range of the engine.

[0041] Based on this, an embodiment of the present application provides a hybrid engine that solves the technical defects in the prior art of the detonation power device, such as poor applicability, poor operating stability, and poor adaptability of upstream and downstream components.

[0042] See further here Figure 3 and Figure 4 In a hybrid engine provided in an embodiment of the present application, stator 12 includes a stator core, coil windings, and a base. The stator core is provided with coil windings embedded in slots within the stator core. The stator core and coil windings are fixed to the base, which is hinged to the central shaft 11. The hinged connection between the base and the central shaft 11 provides a stable mounting base for stator 12. The stator core and coil windings cooperate with the fourth permanent magnet 6 to generate electricity.

[0043] To further optimize the technical solution and better guide the air entering the hybrid engine to ensure sufficient combustion during the operation of the detonation combustion chamber 10, in the technical solution provided in the embodiment of the present application, the engine base is a cross-shaped structure.

[0044] See here Figure 5 and Figure 6 In order to suspend and fix the stator 12 in the longitudinal direction and simplify the structure of the hybrid engine, it is not necessary to fix the stator 12 in the longitudinal direction. In an engine provided in an embodiment of the present application, the power generation component also includes: a third permanent magnet 5 and a longitudinally suspended stator 2. The longitudinally suspended stator 2 is fixed to the central axis 11. The outer wall surface of the outer rotor 8 is provided with a third groove in the shape of a ring. 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.

[0045] Similarly, in order to axially suspend and fix the stator 12 and simplify the structure of the hybrid engine, it is not necessary to fix the stator 12 in the axial direction. In a hybrid engine provided in an embodiment of the present application, the power generation component also includes: a second permanent magnet 4 and an axially suspended stator 1, the axially suspended stator 1 is fixed to the central axis 11, 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, and the second permanent magnet 4 is matched with the axially suspended stator 1 for axially suspending the outer rotor 8.

[0046] To further optimize the technical solution, in the technical solution provided in the embodiment of the present application, the annular sidewall of the outer rotor 8 is provided with a plurality of air cooling cavities 7. The air cooling cavities 7 cool the heat generated by the detonation combustion chamber 10 through airflow, preventing the high temperature from affecting the permanent magnets of the power generation assembly.

[0047] In order to more efficiently convert the heat energy of combustion in the detonation combustion chamber 10 into kinetic energy and utilize the generated power to effectively drive the outer rotor 8 to rotate, the inner wall of the outer rotor 8 is provided with an internal thread 9.

[0048] A hybrid engine provided in an embodiment of the present application further includes a first permanent magnet 3 . A stator 12 groove is defined on the end surface of the inner wall of the stator 12 . The first permanent magnet 3 is disposed in the stator groove and matches the coil winding to suspend the coil winding. The magnetic levitation force generated by the first permanent magnet 3 and the coil winding effectively suspends and secures the coil winding, further simplifying the structure of the hybrid engine.

[0049] In the technical solution provided by the embodiment of the present application, a portion of the inner wall of the outer rotor 8 is provided with internal threads 9. A detonation combustion chamber 10 burns in the cavity inside the annular structure of the outer rotor 8. After the portion without the internal threads 9 fully burns to generate a detonation wave, the outer rotor 8 is driven to rotate.

[0050] A hybrid engine provided in an embodiment of the present application couples magnetic levitation technology and rim motor technology with continuous detonation technology, effectively utilizes the propagation characteristics of continuous detonation waves, and realizes the integration of detonation combustion components and turbines through a new concept design of replacing traditional turbines with spiral threads, realizes the coupling of detonation combustion chambers and transmission turbines, and proposes a new detonation engine structure, which can provide a new route for the design of future integrated flight propulsion systems.

[0051] The detonation combustion assembly is suspended and rotated through the magnetic levitation center axis, which not only completes the integration of the detonation combustion chamber and the outer rotor, but also meets the low-noise and environmentally friendly requirements; the hybrid magnetic levitation center axis control scheme is used to achieve controllable charging and discharging functions, which not only provides partial energy supply for the energy storage unit, but also effectively utilizes the ineffective work done by the detonation combustion assembly during combustion, making energy use more efficient.

[0052] Based on the above advantages, the hybrid engine provided in the embodiment of the present application can be used as the core power structure of an aircraft and installed in the aircraft.

[0053] In summary, the present application provides a hybrid engine comprising: a detonation combustion chamber, a central shaft, and a power generation assembly. The power generation assembly comprises: a stator, an outer rotor, and a fourth permanent magnet. The stator is hingedly connected to the central shaft. The outer rotor is an annular structure. The outer annular wall of the outer rotor is provided with a plurality of first grooves. The fourth permanent magnet is embedded in the first grooves and matches the stator to generate electricity. The detonation combustion chamber is disposed within the outer rotor and drives the outer rotor to rotate. The central shaft is provided with an energy storage unit, and the power generation assembly is electrically connected to the energy storage unit. The present application also provides an aircraft including the hybrid engine described above. In the hybrid engine and aircraft provided by the present application, combustion in the detonation combustion chamber drives the outer rotor to rotate and generate electricity. Excess power from the detonation combustion chamber is generated by the power generation assembly and then stored in the energy storage unit. This not only avoids the waste of excess energy, but also allows the energy storage unit to provide driving power when necessary. This addresses the technical shortcomings of prior art detonation power devices, such as poor applicability, poor operational stability, and poor adaptability of upstream and downstream components.

[0054] The technical features of the above-described embodiments may be combined in any manner. To simplify the description, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there are no conflicts in the combination of these technical features, they should be considered to be within the scope of this specification. Furthermore, other implementations can be derived from the above-described embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.

[0055] The above-described embodiments merely represent several implementation methods of the present application. 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 a person of ordinary skill in the art may make various modifications and improvements without departing from the spirit of the present application, and these modifications and improvements fall within the scope of protection of the present application. Therefore, the scope of protection of the present patent application shall be determined by the appended claims.

Claims

1. A hybrid engine, characterized in that: The hybrid engine includes: a detonation combustion chamber, a central shaft, and a power generation assembly, wherein the power generation assembly includes: a stator, an outer rotor, 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 and the stator are matched to generate electricity. The detonation combustion chamber is arranged inside the outer rotor, and the detonation combustion chamber drives the outer rotor to rotate; The central axis is provided with an energy storage part, and the power generation component is electrically connected to the energy storage part.

2. The engine according to claim 1, characterized in that The stator includes: a stator core, a coil winding and a machine base. The coil winding is provided inside the stator core and embedded in the slots of the stator core. The stator core and the coil winding are fixed to the machine base, and the machine base is hinged to the central axis.

3. The hybrid engine according to claim 2, characterized in that: The machine base is a cross-shaped structure.

4. The hybrid engine according to claim 1, characterized in that: The power generation component also includes: a third permanent magnet and a longitudinally suspended stator, the longitudinally suspended stator is fixed to the central axis, the outer wall surface of the outer rotor is provided with a third groove in a ring shape, the third permanent magnet is embedded in the third groove, and the third permanent magnet is matched with the longitudinally suspended stator for suspending the outer rotor in the longitudinal direction.

5. The hybrid engine according to claim 4, characterized in that: The power generation component also includes: a second permanent magnet and an axially suspended stator, the axially suspended stator is fixed to the central axis, the end surface of the outer rotor is provided with a second groove, the second permanent magnet is embedded in the second groove, and the second permanent magnet is matched with the axially suspended stator for axially suspending the outer rotor.

6. The hybrid engine according to claim 3, characterized in that: The annular side wall of the outer rotor is provided with a plurality of air cooling cavities.

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

8. The hybrid engine according to claim 2, characterized in that: The hybrid engine further includes: a first permanent magnet; a stator groove is provided on the end surface of the inner wall of the stator; the first permanent magnet is disposed in the stator groove; the first permanent magnet matches the coil winding and is used to suspend the coil winding.

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

10. An aircraft, characterized in that: The aircraft comprises the hybrid engine according to any one of claims 1 to 9.

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