Piston turbine power generation system based on double-rotor motor

Abstract

The invention provides a piston turbine power generation system based on a double-rotor motor. The system comprises an internal combustion engine, the double-rotor motor and a turbine engine. Wherein the double-rotor motor comprises an inner rotor, a stator and an outer rotor which are arranged from inside to outside, the inner rotor is provided with an inner shaft interface, and the outer rotor is provided with an outer shaft interface; wherein a first mechanical shaft of the internal combustion engine is directly connected with the outer rotor through the outer shaft connector, and a second mechanical shaft of the turbine engine is directly connected with the inner rotor through the inner shaft connector, so that energy transfer between the internal combustion engine and / or the turbine engine and the double-rotor motor is achieved. By means of the system, the problem that an existing fuel oil power generation system is difficult to consider high power-to-weight ratio, high efficiency and low cost at the same time is solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fuel power generation system, in particular to a piston turbine power generation system based on a double rotor motor. BACKGROUND

[0002] The flying car and the unmanned aerial vehicle are the main carriers for developing low-altitude economy, and currently mainly adopt the battery power system, which has problems of small load and short voyage. The fuel power generation system can greatly improve the load and voyage of the flying car and the unmanned aerial vehicle. The fuel power generation system mainly has two types of internal combustion engine power generation system and gas turbine power generation system. The internal combustion engine power generation system composed of an internal combustion engine (including a gasoline engine and a diesel engine) and a generator has advantages of high power generation efficiency and low cost, but has a low power-to-weight ratio, and is difficult to meet the high efficiency demand scenario of the flying car and the unmanned aerial vehicle. The gas turbine power generation system composed of a gas turbine engine and a generator has a high power-to-weight ratio, but has low efficiency and high cost, and is difficult to meet the long endurance and large-scale application requirements of the low-altitude load carrying equipment. SUMMARY

[0003] In view of the above problems, the present application provides a piston turbine power generation system based on a double rotor motor to solve the problem that the existing fuel power generation system is difficult to balance high power-to-weight ratio, high efficiency and low cost.

[0004] To solve the above problems, the present application provides a piston turbine power generation system based on a double rotor motor, which adopts the technical scheme of: A piston turbine power generation system based on a double rotor motor, the system comprising an internal combustion engine, a double rotor motor and a turbine engine; wherein the double rotor motor comprises an inner rotor, a stator and an outer rotor arranged from inside to outside, and an inner shaft interface is arranged on the inner rotor, and an outer shaft interface is arranged on the outer rotor; Wherein the first mechanical shaft of the internal combustion engine is directly connected with the outer rotor through the outer shaft interface, and the second mechanical shaft of the turbine engine is directly connected with the inner rotor through the inner shaft interface, so as to realize energy transmission between the internal combustion engine and / or the turbine engine and the double rotor motor.

[0005] As one of the preferred schemes, the moment of inertia of the inner rotor is set to be less than the moment of inertia of the outer rotor, and the torque of the inner rotor is set to be less than the torque of the outer rotor.

[0006] As one of the preferred schemes, the internal combustion engine comprises any one of a gasoline engine, a diesel engine, a hydrogen-ammonia internal combustion engine and a rotor engine.

[0007] As one of the preferred solutions, the turbine engine comprises a compressor, a turbine and a combustion chamber, the combustion chamber being in communication with the compressor and the turbine respectively, and the compressor, the turbine and the inner rotor being coaxially connected through the second mechanical shaft.

[0008] As one of the preferred solutions, the system further comprises a first clutch and a second clutch; wherein the first clutch is arranged on the first mechanical shaft for switching on and off the energy transmission between the internal combustion engine and the dual rotor motor; the second clutch is arranged on the second mechanical shaft for switching on and off the energy transmission between the turbine engine and the dual rotor motor.

[0009] As one of the preferred solutions, the system further comprises a transmission arranged on the first mechanical shaft for matching the rotational speed of the first mechanical shaft and the outer rotor.

[0010] As one of the preferred solutions, the system further comprises a motor controller connected with the dual rotor motor, the first clutch, the second clutch and the transmission respectively, for controlling the dual rotor motor, the first clutch, the second clutch and the transmission to be in corresponding working states according to the target demand working condition.

[0011] As one of the preferred solutions, the dual rotor motor is configured to switch between a motor and a generator; When the dual rotor motor is a motor, the electric energy of the dual rotor motor is converted into mechanical energy of the turbine engine; When the dual rotor motor is a generator, the mechanical energy of the turbine engine and / or the internal combustion engine is converted into electric energy of the dual rotor motor.

[0012] As one of the preferred solutions, the internal combustion engine is connected between the compressor and the combustion chamber through an intake branch, and is connected between the turbine and the combustion chamber through an exhaust branch.

[0013] As one of the preferred solutions, the system further comprises a turbine motor connected between the compressor and the turbine.

[0014] Compared with the prior art, the present application has the following advantages: The piston turbine power generation system based on a double rotor motor provided by the embodiment of the application comprises an internal combustion engine, a double rotor motor and a turbine engine; wherein the double rotor motor comprises an inner rotor, a stator and an outer rotor arranged from inside to outside, and an inner shaft interface is arranged on the inner rotor, and an outer shaft interface is arranged on the outer rotor; wherein a first mechanical shaft of the internal combustion engine is directly connected with the outer rotor through the outer shaft interface, and a second mechanical shaft of the turbine engine is directly connected with the inner rotor through the inner shaft interface, so as to realize energy transmission between the internal combustion engine and / or the turbine engine and the double rotor motor.

[0015] By adopting the technical scheme of the application, the turbine engine, the internal combustion engine and the double rotor motor are mechanically coupled to form a turbine compound power generation system, the turbine engine is used to output power when high-power output is required, the internal combustion engine is used to output power when high-efficiency operation is required, both of them share one double rotor motor, and are coupled through a transmission mechanism, so that the system has the characteristics of high power-to-weight ratio, high efficiency and low cost. The inner rotor and the outer rotor of the double rotor motor are directly mechanically connected with the turbine engine and the internal combustion engine, power is directly outputted by mechanical connection, the mechanical coupling path is shorter, the intermediate electrical conversion link is omitted, energy conversion loss is eliminated, and the comprehensive efficiency of the system is improved. The double rotor motor independently drives the internal combustion engine and the turbine engine through the inner rotor and the outer rotor, power sources can be quickly switched, independent power source active power generation and collaborative compound power generation are supported, the energy of the internal combustion engine and the turbine engine is decoupled and cooperated, the system structure is highly integrated, the volume and weight of the system are reduced, and the variable operating condition requirements of low-load operating equipment are met. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical scheme of the application, the drawings needed to be used in the description of the application will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without any creative labor on the basis of these drawings.

[0017] Figure 1 Fig. 1 is a system composition schematic diagram of the piston turbine power generation system based on a double rotor motor provided by the embodiment one of the application; Figure 2 Fig. 2 is a system composition schematic diagram of the piston turbine power generation system based on a double rotor motor provided by the embodiment two of the application; Figure 3 Fig. 3 is a system composition schematic diagram of the piston turbine power generation system based on a double rotor motor provided by the embodiment three of the application; Figure 4 Fig. 4 is a system composition schematic diagram of the piston turbine power generation system based on a double rotor motor provided by the embodiment four of the application.

[0018] Explanation of reference signs: 1. Turbine engine; 11. Compressor; 12. Combustion chamber; 13. Turbine; 14. Turbine motor; 2. Dual rotor motor; 21. Outer rotor; 22. Stator; 23. Inner rotor; 3. Second clutch; 4. First clutch; 5. Internal combustion engine; 6. Transmission. Detailed Implementation

[0019] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0020] Low-altitude transport equipment such as drones and flying cars are influenced by factors such as mission requirements, flight modes, atmospheric conditions, and terrain conditions. Their operating conditions encompass a variety of complex and variable scenarios, including vertical takeoff and landing (VTOL), short takeoff and landing (STOVL), acceleration and climb, hovering, cruise, and emergency response, and they typically operate under varying power demands. Different application scenarios place different requirements on fuel power systems and energy management. For example, takeoff, hovering, and rapid maneuvering require high power output per unit mass, necessitating instantaneous high power output to support VTOL and hovering. In contrast, high-dynamic flight conditions such as cruise demand high fuel system efficiency and low fuel consumption to extend range. Furthermore, for the low-altitude economy to achieve large-scale commercialization, the requirements for power systems far exceed those for ground vehicles. Traditional internal combustion engine power generation systems and gas turbine power generation systems each have their limitations and cannot adequately adapt to diverse operating conditions and application scenarios.

[0021] It is evident that, in order to address the payload and range issues faced by the development of low-altitude transport equipment such as drones and flying cars, there is an urgent need to develop fuel-powered power generation systems that combine high power-to-weight ratio, high efficiency, and low cost.

[0022] Reference Figure 1 and Figure 2 As shown, Figure 1 and Figure 2 Two piston turbine power generation systems based on dual-rotor motors provided by this invention are shown respectively. In the first aspect, this invention provides a turbine composite power system based on a dual-rotor motor, the system comprising an internal combustion engine 5, a dual-rotor motor 2, and a turbine engine 1; wherein, the dual-rotor motor 2 includes an inner rotor 23, a stator 22, and an outer rotor 21 arranged from the inside out, with an inner shaft interface on the inner rotor 23 and an outer shaft interface on the outer rotor 21; wherein, the first mechanical shaft of the internal combustion engine 5 is directly connected to the outer rotor 21 through the outer shaft interface, and the second mechanical shaft of the turbine engine 1 is directly connected to the inner rotor 23 through the inner shaft interface, thereby realizing energy transfer between the internal combustion engine 5 and / or the turbine engine 1 and the dual-rotor motor 2.

[0023] In the present embodiment, the internal combustion engine 5 serves as a first power source, responsible for converting fuel chemical energy into mechanical energy and outputting a first power through a first mechanical shaft. The turbine engine 1 serves as a second power source, utilizing high-temperature and high-pressure gas generated by fuel combustion to drive the turbine 13 to rotate and output a second power through a second mechanical shaft. In some embodiments, the dual-rotor motor 2 has both motor and generator modes, so that the second mechanical shaft can serve as an input shaft to input the electric power output by the dual-rotor motor 2 to the turbine engine 1 through the second mechanical shaft.

[0024] The dual-rotor motor 2 generally includes an inner rotor 23, an outer rotor 21, and a stator 22. The inner rotor 23 is located inside the stator 22, and the outer rotor 21 is located outside the stator 22. The stator 22 is composed of an iron core, an outer winding, an inner winding, and a magnetic shield support. The magnetic shield support is rotatably connected to the rotating shaft of the outer rotor 21 through a stator support bearing, and the inner rotor 23 is supported on the stator 22 through a bearing. The inner and outer sides of the magnetic shield support are respectively provided with the outer winding and the inner winding.

[0025] In the present embodiment, the dual-rotor motor 2 is a commonly used dual-rotor motor 2. For the sake of simplicity, the specific structure of the dual-rotor motor 2 will not be described in detail in the present application, and the relevant structure and working principle can be referred to relevant technical documents. The improvement of the present embodiment lies in that an inner shaft interface is formed on the rotating shaft of the inner rotor 23, and an outer shaft interface is formed on the rotating shaft of the outer rotor 21. The inner shaft interface is configured to connect the inner rotor 23 and the second mechanical shaft of the turbine engine 1, so as to transmit power between the dual-rotor motor 2 and the turbine engine 1 through the inner shaft interface. The outer shaft interface is configured to connect the outer rotor 21 and the first mechanical shaft of the internal combustion engine 5, so as to transmit power between the dual-rotor motor 2 and the internal combustion engine 5 through the outer shaft interface. Therefore, the two mechanical shaft interfaces on the dual-rotor motor 2 can realize independent transmission of the energy of the two mechanical shafts.

[0026] In this way, compared with the conventional hybrid power system, the gas path coupling between the internal combustion engine 5 and the turbine engine 1 is required, for example, the turbine 13 drives the generator by recovering part of the exhaust energy of the internal combustion engine 5 through electrification. The electrical coupling is limited by the exhaust flow and temperature of the internal combustion engine 5, the energy conversion level is high, the power transmission path is long, and the energy conversion loss is large. In the present system, the inner and outer rotors of the dual-rotor motor 2 are directly mechanically connected to the turbine engine 1 and the internal combustion engine 5, the mechanical connection directly outputs power, the mechanical coupling path is shorter, the intermediate electrical conversion link is omitted, the energy conversion loss is eliminated, and the overall efficiency of the system is improved.

[0027] Furthermore, to achieve individual or combined power generation today, the turbine engine 1 and the internal combustion engine 5 need to be equipped with their own corresponding generators to generate electricity independently. Then, an electrical conversion device is used to integrate the generated electricity from the internal combustion engine 5 and the turbine engine 1 to achieve synergistic power generation. This results in high system complexity, large overall weight, and complex equipment structure. This system uses a dual-rotor motor 2, driven independently by the inner and outer rotors, allowing for rapid switching of power sources. This achieves decoupling and synergistic energy transfer between the internal combustion engine 5 and the turbine engine 1, resulting in a highly integrated system structure that reduces system size and weight.

[0028] As a specific explanation of this embodiment, the system can use the turbine engine 1 and the internal combustion engine 5 separately or simultaneously under different operating conditions. In the first operating condition, the mechanical energy output by the internal combustion engine 5 is directly transmitted to the outer rotor 21 through the first mechanical shaft. The rotation of the outer rotor 21 drives the stator 22 to generate electricity. At the same time, the turbine engine 1 is in a non-working state, and the second mechanical shaft stops rotating, thereby realizing the energy transfer between the internal combustion engine 5 and the dual-rotor motor 2 independently, so as to output the first power of the internal combustion engine 5 independently. Here, the first operating condition can be understood as a high-efficiency operating condition such as cruising or low load.

[0029] In the second operating condition, the mechanical energy output by the turbine engine 1 is directly transmitted to the inner rotor 23 through the second mechanical shaft. The rotation of the inner rotor 23 drives the stator 22 to generate electricity. At the same time, the internal combustion engine 5 is in a non-operating state, and the first mechanical shaft stops rotating, thus realizing the energy transfer between the turbine engine 1 and the dual-rotor motor 2 independently, so as to output the second power of the turbine engine 1 independently. The second operating condition can be understood as a high-power operating condition such as takeoff, climb, and acceleration.

[0030] In the third operating condition, the mechanical energy output by the internal combustion engine 5 is directly transferred to the outer rotor 21 through the first mechanical shaft, while the mechanical energy output by the turbine engine 1 is directly transferred to the inner rotor 23 through the second mechanical shaft. The inner and outer rotors rotate simultaneously, driving the stator 22 to generate electricity, thereby realizing the energy transfer between the internal combustion engine 5 and the turbine engine 1 and the dual-rotor motor 2, outputting the combined power of the internal combustion engine 5 and the turbine engine 1. The third operating condition can be understood as full-power operation conditions such as full-load takeoff, steep ascent, forced landing, emergency avoidance, and long-endurance high-load operation.

[0031] Therefore, this invention mechanically couples a turbine engine 1, an internal combustion engine 5, and a dual-rotor motor 2 to form a turbine-based composite power generation system. When high power output is required, the turbine engine 1 provides the output; when high efficiency is required, the internal combustion engine 5 provides the output. Both share a single dual-rotor motor and are coupled through a transmission mechanism, resulting in a high power-to-weight ratio, high efficiency, and low cost. This system can quickly switch power modes, supporting independent active power generation and collaborative composite power generation. Specifically, the internal combustion engine 5 can drive the outer rotor 21 to generate electricity, the turbine engine 1 can drive the inner rotor 23 to generate electricity, or both can generate electricity in combination. Energy scheduling can match the needs of flight missions and meet the variable operating conditions of low-altitude transport equipment. This system is particularly suitable for applications requiring short-term high-power output and long-term low-power output, such as high-power vertical takeoff and landing and high-efficiency cruise operation of drones and flying cars.

[0032] In addition to the three operating conditions mentioned above, this system can also include a turbine engine starting condition. In this embodiment, the dual-rotor motor 2 is configured to switch between electric motor and generator modes. When the dual-rotor motor 2 is an electric motor, its electrical energy is converted into the mechanical energy of the turbine engine 1. When the dual-rotor motor 2 is a generator, the mechanical energy of the turbine generator and / or the internal combustion engine 5 is converted into the electrical energy of the dual-rotor motor 2. The dual-rotor motor 2 used in this embodiment is an integrated electric-generator motor. In electric mode, the motor operates as an engine, with power supplied to the inner winding of the stator 22. The outer winding is de-energized, and the inner winding is energized to drive the inner rotor 23 to rotate, transferring the mechanical energy of the inner rotor 23 to the second mechanical shaft of the turbine engine 1, thereby starting the turbine engine 1. After the turbine engine 1 starts, the dual-rotor motor 2 can switch to generator mode.

[0033] In power generation mode, the motor operates as a generator. The turbine engine 1 drives the inner rotor 23 to rotate via the second mechanical shaft, outputting power matching the second or third operating condition. Turbine power generation or combined power generation is achieved through changes in the magnetic field of the stator 22. The internal combustion engine 5 drives the outer rotor 21 to rotate via the first mechanical shaft, outputting power matching the first or third operating condition. Piston power generation or combined power generation is achieved through changes in the magnetic field of the stator 22.

[0034] Therefore, the dual-rotor motor 2 in this embodiment integrates starting and power generation, avoiding the complex structure of traditional fuel hybrid systems that require the simultaneous configuration of generators and motors, thus simplifying system complexity.

[0035] It is understandable that in electric mode, the power supply for the input inner winding can be an external power source, such as a power battery. In some embodiments, the dual-rotor motor 2 can function as both a generator and a motor. The internal combustion engine 5 drives the outer rotor 21 to generate electricity, while the electrical energy directly drives the inner rotor 23 to rotate for air intake. Therefore, a power battery is not required, resulting in higher system integration.

[0036] As a further explanation of this embodiment, the moment of inertia of the inner rotor 23 is set to be less than that of the outer rotor 21, and the torque of the inner rotor 23 is set to be less than that of the outer rotor 21. It is known that the internal combustion engine 5 operates at low speeds and high torque; therefore, the outer rotor 21, with its large moment of inertia and high torque, is connected to the first mechanical shaft of the internal combustion engine 5, so that the output characteristics of the internal combustion engine 5 match the rotational characteristics of the outer rotor 21, stabilizing the output of the internal combustion engine 5. The turbine engine 1 outputs at extremely high speeds and with relatively low torque; therefore, the inner rotor 23, with its small moment of inertia and low torque, is connected to the second mechanical shaft of the turbine engine 1 to improve the response speed of the turbine 13, and simultaneously, in electric mode, to transiently increase the intake pressure. Therefore, in this embodiment, the inner rotor 23 and outer rotor 21 are assigned to suitable mechanical shafts according to their mechanical characteristics of difference in moment of inertia and torque, matching the power requirements of both transient and steady-state operating conditions.

[0037] Based on the above embodiments, by employing pure mechanical coupling, the outer shaft interface of the outer rotor 21 of the dual-rotor motor 2 can serve as a universal interface. For example, the outer rotor 21 of the dual-rotor motor 2 can be connected to the crankshaft drive of different types of internal combustion engines 5 via standardized flanges, splines, or couplings, making it compatible with the mechanical shafts of various types of internal combustion engines 5 and adaptable to the power-torque-speed characteristics of different types of internal combustion engines 5, such as any one of gasoline engines, diesel engines, hydrogen-ammonia internal combustion engines, and rotary engines. Therefore, the pure mechanical coupling power transmission proposed in this system can establish a modular architecture, achieving fuel compatibility and power platform universality. Through the pure mechanical coupling of multi-fuel engine models with the dual-rotor motor 2, under different internal combustion engine 5 driving conditions, there is no need to reconstruct the power system architecture or change the electrical control strategy (unlike gas-line coupled hybrid systems, which require redesigning the supporting hardware and adjusting the electronic control strategy), allowing a transition from traditional combustion engines to zero-carbon fuel engines. Modularization further reduces the R&D and manufacturing costs for automakers.

[0038] Furthermore, the system also includes a transmission 6, which is mounted on the first mechanical shaft to match the rotational speeds of the first mechanical shaft and the outer rotor 21. The outer rotor 21 of the dual-rotor motor 2 is connected to the internal combustion engine 5 via the first clutch 4. The transmission 6 can be added according to the rotational speed of the internal combustion engine 5 and the rotational speed of the outer rotor 21. The transmission 6 can adjust the speed ratio between the first mechanical shaft and the outer rotor 21. When adapting to different types of internal combustion engines 5 (gasoline engine, diesel engine, hydrogen-ammonia internal combustion engine, rotary engine), the optimal torque of the internal combustion engine 5 is different. Therefore, by setting the transmission 6 on the first mechanical shaft, the transmission ratio can be adjusted according to the torque characteristics of different internal combustion engines 5, so as to better match the rotational speed characteristics of various internal combustion engines 5, while the internal combustion engine 5 always operates in the optimal fuel economy range.

[0039] As an improvement in another embodiment, the turbine engine 1 includes a compressor 11, a turbine 13, and a combustion chamber 12. The combustion chamber 12 is connected to both the compressor 11 and the turbine 13, and the compressor 11, turbine 13, and inner rotor 23 are coaxially connected via a second mechanical shaft. The turbine engine 1 includes a compressor 11, a turbine 13, and a combustion chamber 12. The compressor 11 compresses air and supplies it to the combustion chamber 12, where the air and fuel are mixed and burned to produce high-temperature, high-pressure gas. The turbine 13 utilizes the expansion of the gas to perform work and output mechanical energy. The compressor 11 and turbine 13 are generally coaxially mounted. The compressor 11, turbine 13, and inner rotor 23 are all mounted on the same rotating shaft and share the second mechanical shaft for power transmission. Therefore, mechanical energy is transmitted along the second mechanical shaft, driving the inner rotor 23 to rotate, thereby driving the dual-rotor motor 2 to generate electricity.

[0040] Furthermore, referring to Figure 3 As shown, Figure 3 This embodiment demonstrates a piston turbine power generation system based on a dual-rotor motor. An internal combustion engine 5 is connected between the compressor 11 and the combustion chamber 12 via an intake branch, and between the turbine 13 and the combustion chamber 12 via an exhaust branch. In this embodiment, the internal combustion engine 5 has an air inlet and an air outlet. The air inlet is connected to the outlet of the compressor 11 via the intake branch, and the air outlet is connected to the outlet of the combustion chamber 12 via the exhaust branch. Therefore, a portion of the high-pressure air compressed by the compressor 11 is sent to the combustion chamber 12 to supply air to the turbine engine side, while the other portion is sent to the internal combustion engine 5 via the intake branch. The compressor 11 pressurizes the internal combustion engine 5, increasing its operating pressure. Simultaneously, the exhaust gas from the internal combustion engine 5 merges with the combustion gas from the combustion chamber 12 before entering the turbine 13.

[0041] Furthermore, referring to Figure 4 As shown, Figure 4 This embodiment demonstrates a piston turbine power generation system based on a dual-rotor motor. The system also includes a turbine motor 14 connected between the compressor 11 and the turbine 13. In this embodiment, the turbine motor 14 is mounted on a second mechanical shaft, positioned between the compressor 11 and the turbine 13. Therefore, the turbine motor 14 can serve as an auxiliary motor, electrically driving the second mechanical shaft to rotate during startup to assist in starting the turbine engine 1, and also driving the second mechanical shaft to rotate during operation to assist in pressurization.

[0042] As a further improvement to this embodiment, the system also includes a first clutch 4 and a second clutch 3; wherein, the first clutch 4 is disposed on the first mechanical shaft and is used to switch the energy transmission between the internal combustion engine 5 and the dual rotor motor 2; the second clutch 3 is disposed on the second mechanical shaft and is used to switch the energy transmission between the turbine engine 1 and the dual rotor motor 2.

[0043] Specifically, the first clutch 4 and the second clutch 3 can selectively isolate the power source. By disengaging / engaging the clutches, the system can quickly cut off / connect the power transmission of the internal combustion engine 5 or the turbine engine 1, achieving rapid power switching under different operating conditions. In the first operating condition, the first clutch 4 is engaged and the second clutch 3 is disengaged, allowing the internal combustion engine 5 to drive the dual-rotor motor 2 to generate electricity, while the turbine engine 1 does not participate in operation. In the second operating condition, the first clutch 4 is disengaged and the second clutch 3 is engaged, allowing the turbine engine 1 to drive the dual-rotor motor 2 to generate electricity, while the internal combustion engine 5 does not participate in operation. In the third operating condition, the first clutch 4 is engaged and the second clutch 3 is engaged, allowing both the internal combustion engine 5 and the turbine engine 1 to jointly drive the dual-rotor motor 2 to generate electricity. In the turbine engine starting condition, the first clutch 4 is disengaged and the second clutch 3 is engaged, allowing the dual-rotor motor 2 to start the turbine engine 1. Therefore, by setting the first clutch 4 and the second clutch 3, the adaptability to different operating conditions is rapidly improved.

[0044] As a specific illustration of the above embodiments, the system also includes a motor controller, which is connected to the dual rotor motor 2, the first clutch 4, the second clutch 3 and the transmission 6 respectively, and is used to control the dual rotor motor 2, the first clutch 4, the second clutch 3 and the transmission 6 to be in the corresponding working state according to the target demand working conditions.

[0045] Flying cars and drones have different power output requirements under different flight conditions. The motor controller allocates power according to the flight phase (takeoff, climb, cruise, descent) and controls the system to switch between the first operating condition, the second operating condition, the third operating condition, and the turbine engine starting condition. Simultaneously, it controls the dual-rotor motor 2 to freely switch between electric motor and generator modes. For example, in the first operating condition, the motor controller controls the dual-rotor motor 2 to be in generator mode, engages the first clutch 4, and disengages the second clutch 3, allowing the internal combustion engine 5 to directly drive the outer rotor 21, outputting the first power. The transmission 6 is then controlled to be in high gear (reducing the speed of the internal combustion engine 5 and minimizing friction loss), matching the speed of the internal combustion engine 5 to the optimal fuel efficiency point to meet cruise requirements and improve fuel efficiency. The other operating conditions are described above and will not be elaborated further in this embodiment.

[0046] In conjunction with the above embodiments, the present invention provides four preferred embodiments for illustrative purposes: Example 1: Please refer to it again. Figure 1 The air passages of the compressor 11, combustion chamber 12, and turbine 13 are connected in sequence to form a turbine engine 1. The second mechanical shaft of the turbine engine 1 is connected to the inner rotor 23 of the dual-rotor motor 2 via a second clutch 3. The first mechanical shaft of the internal combustion engine 5 is connected to a first clutch 4, and the other end of the first clutch 4 is connected to the outer rotor 21 of the dual-rotor motor 2.

[0047] The system can operate under four target demand conditions: turbine engine start-up condition, first operating condition, second operating condition, and third operating condition.

[0048] When the system is operating in turbine engine start-up mode, the second clutch 3 is engaged and the first clutch 4 is disengaged. The dual rotor motor 2 operates in drive mode, with the inner rotor 23 rotating, driving the compressor 11 and turbine 13 to rotate, thus starting the turbine engine 1.

[0049] When the system is operating in the first operating condition (high-efficiency operating condition), the second clutch 3 is disengaged and the first clutch 4 is engaged. The dual-rotor motor 2 operates in generator mode, the internal combustion engine 5 runs, driving the outer rotor 21 of the motor to rotate and output electrical energy.

[0050] When the system operates in the second operating condition (high-power operating condition), the second clutch 3 is engaged and the first clutch 4 is disengaged. The dual-rotor motor 2 operates in power generation mode, and the turbine 13 drives the inner rotor 23 to rotate, outputting electrical energy.

[0051] When the system is operating in the third operating condition (full power operating condition), the second clutch 3 is engaged and the first clutch 4 is engaged. The dual rotor motor 2 operates in power generation mode, with the turbine 13 driving the inner rotor 23 to rotate and the internal combustion engine 5 driving the outer rotor 21 to rotate, outputting electrical energy.

[0052] Example 2: Please refer to it again. Figure 2 The compressor 11, combustion chamber 12, and turbine 13 are sequentially connected to form a turbine engine 1. The second mechanical shaft of the turbine engine 1 is connected to the inner rotor 23 of the dual-rotor motor 2 via a second clutch 3. The first mechanical shaft of the internal combustion engine 5 is connected to the low-speed end of the transmission 6. The high-speed end of the transmission 6 is connected to the outer rotor 21 of the dual-rotor motor 2 via a first clutch 4.

[0053] The system can operate under four target demand conditions: turbine engine start-up condition, first operating condition, second operating condition, and third operating condition.

[0054] When the system is operating in turbine engine start-up mode, the second clutch 3 is engaged and the first clutch 4 is disengaged. The dual rotor motor 2 operates in drive mode, with the inner rotor 23 rotating, driving the compressor 11 and turbine 13 to rotate, thus starting the turbine engine 1.

[0055] When the system is operating in the first operating condition (high-efficiency operating condition), the second clutch 3 is disengaged and the first clutch 4 is engaged. The dual-rotor motor 2 operates in generator mode. The output of the internal combustion engine 5 is accelerated by the transmission 6 and drives the outer rotor 21 of the motor to rotate, thus outputting electrical energy.

[0056] When the system operates in the second operating condition (high-power operating condition), the second clutch 3 is engaged and the first clutch 4 is disengaged. The dual-rotor motor 2 operates in power generation mode, and the turbine 13 drives the inner rotor 23 to rotate, outputting electrical energy.

[0057] When the system is operating in the third operating condition (full power operating condition), the second clutch 3 is engaged and the first clutch 4 is engaged. The dual rotor motor 2 operates in power generation mode. The turbine 13 drives the inner rotor 23 to rotate. The output of the internal combustion engine 5 is accelerated by the transmission 6 and drives the outer rotor 21 of the motor to rotate, thus outputting electrical energy.

[0058] Example 3: Please refer to it again. Figure 3 Unlike embodiment 2, the internal combustion engine 5 is connected to the turbine engine 1 through an intake branch and an exhaust branch.

[0059] When the system is operating in the third operating condition (full power operating condition), the second clutch 3 is engaged and the first clutch 4 is engaged. The dual rotor motor 2 operates in power generation mode. The turbine 13 drives the second mechanical shaft to rotate, which in turn drives the inner rotor 23 to rotate. At the same time, the compressor 11 assists in supercharging the internal combustion engine 5. The output of the internal combustion engine 5 is accelerated by the transmission 6 and drives the outer rotor 21 to rotate, outputting electrical energy.

[0060] Example 4: Please refer to it again. Figure 4 Unlike embodiment 3, a turbine motor is installed on the second mechanical shaft between the compressor 11 and the turbine 13.

[0061] When the system is operating in the turbine engine start-up condition, the second clutch 3 is engaged and the first clutch 4 is disengaged. The dual rotor motor 2 operates in drive mode, the inner rotor 23 rotates, and at the same time the turbine motor 14 drives the second mechanical shaft to rotate, which together drive the compressor 11 and the turbine 13 to rotate, thus starting the turbine engine 1.

[0062] When the system is operating in the third operating condition (full power operating condition), the second clutch 3 is engaged and the first clutch 4 is engaged. The dual rotor motor 2 operates in power generation mode. The turbine 13 and the turbine motor 14 jointly drive the second mechanical shaft to rotate, which in turn drives the inner rotor 23 to rotate. At the same time, the compressor 11 assists in supercharging the internal combustion engine 5. The output of the internal combustion engine 5 is accelerated by the transmission 6 and then drives the outer rotor 21 of the motor to rotate, outputting electrical energy.

[0063] It should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0064] It should also be noted that, in this document, the terms "upper," "lower," "left," "right," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention 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 the invention. Furthermore, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations, nor should they be construed as indicating or implying relative importance. Moreover, the term "comprising" or any other variation thereof is intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements, but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device.

[0065] The foregoing has provided a detailed description of a piston turbine power generation system based on a dual-rotor motor provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of aiding understanding this application, and the content of this specification should not be construed as limiting this application. Furthermore, those skilled in the art will recognize that various modifications may occur in the specific implementation methods and application scope based on this application. It is neither necessary nor possible to exhaustively list all implementation methods here, and any obvious variations or modifications derived therefrom are still within the protection scope of this application.

Claims

1. A piston turbine power generation system based on a dual-rotor motor, characterized in that, The system includes an internal combustion engine, a dual-rotor motor, and a turbine engine; wherein, the dual-rotor motor includes an inner rotor, a stator, and an outer rotor arranged from the inside out, and the inner rotor is provided with an inner shaft interface, and the outer rotor is provided with an outer shaft interface; The first mechanical shaft of the internal combustion engine is directly connected to the outer rotor through the outer shaft interface, and the second mechanical shaft of the turbine engine is directly connected to the inner rotor through the inner shaft interface, so as to realize the energy transfer between the internal combustion engine and / or the turbine engine and the dual rotor motor.

2. The piston turbine power generation system based on a dual-rotor motor according to claim 1, characterized in that, The moment of inertia of the inner rotor is set to be less than that of the outer rotor, and the torque of the inner rotor is set to be less than that of the outer rotor.

3. The piston turbine power generation system based on a dual-rotor motor according to claim 1, characterized in that, The internal combustion engine includes any one of a gasoline engine, a diesel engine, a hydrogen-ammonia internal combustion engine, and a rotary engine.

4. A piston turbine power generation system based on a dual-rotor motor according to claim 1, characterized in that, The turbine engine includes a compressor, a turbine, and a combustion chamber. The combustion chamber is connected to the compressor and the turbine, respectively, and the compressor, the turbine, and the inner rotor are coaxially connected via a second mechanical shaft.

5. A piston turbine power generation system based on a dual-rotor motor according to any one of claims 1-4, characterized in that, The system also includes a first clutch and a second clutch; wherein the first clutch is disposed on the first mechanical shaft and is used to switch the energy transfer between the internal combustion engine and the dual rotor motor; the second clutch is disposed on the second mechanical shaft and is used to switch the energy transfer between the turbine engine and the dual rotor motor.

6. A piston turbine power generation system based on a dual-rotor motor according to claim 5, characterized in that, The system also includes a transmission mounted on the first mechanical shaft for matching the rotational speeds of the first mechanical shaft and the outer rotor.

7. A piston turbine power generation system based on a dual-rotor motor according to claim 6, characterized in that, The system also includes a motor controller, which is connected to the dual-rotor motor, the first clutch, the second clutch, and the transmission respectively, and is used to control the dual-rotor motor, the first clutch, the second clutch, and the transmission to be in corresponding working states according to the target operating conditions of the aircraft.

8. A piston turbine power generation system based on a dual-rotor motor according to claim 1, characterized in that, The dual-rotor motor is configured to switch between electric motor and generator; When the dual-rotor motor is an electric motor, the electrical energy of the dual-rotor motor is converted into the mechanical energy of the turbine engine; When the dual-rotor motor is a generator, the mechanical energy of the turbine generator and / or the internal combustion engine is converted into the electrical energy of the dual-rotor motor.

9. A piston turbine power generation system based on a dual-rotor motor according to claim 4, characterized in that, The internal combustion engine is connected between the compressor and the combustion chamber via an intake branch, and between the turbine and the combustion chamber via an exhaust branch.

10. A piston turbine power generation system based on a dual-rotor motor according to claim 9, characterized in that, The system also includes a turbine motor connected between the compressor and the turbine.

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