A propulsion system and aircraft

Abstract

The application discloses a propelling system and an aircraft, wherein the propelling system comprises a power generation system and a distributed system; the power generation system comprises a pre-ionization device and a magnetic fluid power generation device; the pre-ionization device can ionize gas to generate ionized gas; the magnetic fluid power generation device is suitable for the ionized gas to pass through; the distributed system comprises a plurality of propellers; any one of the propellers is electrically connected with the magnetic fluid power generation device. The magnetic fluid power generation device is used to replace an internal combustion engine to drive a generator to generate power; when the ionized gas passes through the magnetic fluid power generation device, the magnetic fluid power generation device can directly generate electric energy, so that the electric energy can be generated without mechanical conversion, the energy conversion efficiency is improved, and the electric energy is easy to transmit, that is, the energy transmission efficiency is also improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a propulsion system and an aircraft. Background Technology

[0002] A gas turbine engine, also known as a combustion turbine engine, draws in air from the external atmosphere through a compressor, compresses it stage by stage, and sends the compressed air to the combustion chamber to mix with injected fuel to produce high-temperature, high-speed combustion gas. This gas then enters the turbine to expand and do work. Gas turbine engines are widely used in aircraft, where they drive a turbine to provide power to the aircraft.

[0003] An aircraft is provided that includes a propulsion system comprising a pair of internal combustion engines, each of which drives a generator, each generator being electrically connected to multiple electric thrusters, each thruster comprising an electric motor and a propeller, the thrusters being located in front of the leading edge of the tail fin, such that during operation the airflow generated by the thrusters flows over the wing, thereby providing lift to the aircraft.

[0004] However, the propulsion system in the aforementioned aircraft uses an internal combustion engine to drive a generator to generate electrical energy, which means that internal energy is converted into electrical energy through a series of mechanical conversions. Therefore, the energy conversion efficiency is relatively low. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention lies in the propulsion system of existing aircraft, which uses an internal combustion engine to drive a generator to generate electrical energy, that is, converting internal energy into electrical energy through a series of mechanical conversions, thus resulting in low energy conversion efficiency.

[0006] Therefore, the present invention provides a propulsion system, comprising:

[0007] A power generation system, comprising a pre-ionization device and a magnetohydrodynamic (MHD) power generation device, wherein the pre-ionization device is capable of ionizing gas to generate ionized gas, and the MHD power generation device is adapted to allow the ionized gas to pass through.

[0008] A distributed system comprising multiple thrusters, each of which is electrically connected to the magnetohydrodynamic power generation device.

[0009] Optionally, in the aforementioned propulsion system, the power generation system further includes an ionization channel, which is connected to the magnetohydrodynamic power generation device. The pre-ionization device is capable of ionizing the gas passing through the ionization channel to generate the ionized gas.

[0010] Optionally, the aforementioned propulsion system further includes a gas chamber having an inlet and an outlet, the outlet being connected to the end of the ionization channel away from the magnetohydrodynamic power generation device, and the gas chamber being adapted to generate high-temperature, high-speed gas.

[0011] Optionally, the aforementioned propulsion system further includes:

[0012] An air compressor device, including at least one compressor, wherein the outlet of the air compressor device is connected to the air inlet;

[0013] An electric motor is connected to the compressor, and the magnetohydrodynamic power generation device is electrically connected to the electric motor.

[0014] Optionally, the propulsion system described above, the power generation system further includes an exhaust pipe, which is connected to the exhaust port of the magnetohydrodynamic power generation device.

[0015] Optionally, the aforementioned propulsion system further includes a power controller, which is electrically connected to the magnetohydrodynamic power generation device, the pre-ionization device, and the motor, respectively.

[0016] Optionally, the aforementioned propulsion system, the distributed system further includes:

[0017] A transmission bus, which is connected to the power controller;

[0018] An energy storage device, which is connected to the transmission bus.

[0019] Optionally, the aforementioned propulsion system, the distributed system further includes:

[0020] Several conveyor branches, each of which is connected to the conveyor bus;

[0021] Multiple frequency converters, wherein any one of the frequency converters is connected to one of the conveyor branches;

[0022] Multiple power converters, any one of which is electrically connected to one of the frequency converters.

[0023] Optionally, in the above-described propulsion system, the thruster includes:

[0024] A drive unit, the drive unit being electrically connected to one of the frequency converters;

[0025] A propeller, which is fixedly connected to the drive unit.

[0026] The present invention provides an aircraft, including an aircraft body and the aforementioned propulsion system, wherein the propulsion system is disposed on the aircraft body.

[0027] The technical solution provided by this invention has the following advantages:

[0028] 1. The propulsion system provided by the present invention includes a power generation system and a distributed system. The power generation system includes a pre-ionization device and a magnetohydrodynamic (MHD) power generation device. The pre-ionization device is capable of ionizing gas to generate ionized gas, and the MHD power generation device is adapted to allow the ionized gas to pass through. The distributed system includes multiple thrusters, and any one of the thrusters is electrically connected to the MHD power generation device.

[0029] The propulsion system of this structure uses a magnetohydrodynamic (MHD) generator to drive a generator instead of an internal combustion engine. When ionized gas passes through the MHD generator, it can directly generate electrical energy. Therefore, it can generate electrical energy without mechanical conversion, which improves energy conversion efficiency. In addition, the electrical energy is easy to transmit, which also improves energy transmission efficiency.

[0030] 2. The propulsion system provided by the present invention further includes a gas chamber having an air inlet and an air outlet. The air outlet is connected to the end of the ionization channel away from the magnetohydrodynamic power generation device. The gas chamber is suitable for generating high-temperature, high-speed gas. The magnetohydrodynamic power generation device can convert the thermal energy and kinetic energy of the high-temperature gas generated in the combustion chamber into electrical energy to drive the propeller and provide a power source for the distributed system.

[0031] 3. The propulsion system provided by this invention uses a magnetohydrodynamic (MHD) generator to produce direct current (DC). During power transmission, this reduces the impact of electromagnetic interference on the power and control systems. Furthermore, since DC power has no reactive power, the cables required for transmission are lighter than those required for AC power transmission. This reduces the overall mass of the propulsion system.

[0032] 4. The propulsion system provided by this invention requires real-time changes in the attitude of the aircraft, thus necessitating real-time adjustments to the propulsion system's power. The thruster is electrically driven, enabling it to operate at its optimal operating point and improving the propulsion system's efficiency. Furthermore, since the power generation system eliminates the need for mechanical conversion, fuel consumption is reduced, saving energy and enhancing the aircraft's endurance.

[0033] 5. The propulsion system provided by the present invention has a transmission bus connected to a power controller and an energy storage device connected to the transmission bus. The power on the transmission bus flows through a frequency converter and a power converter and is finally sent to the thruster. That is, a corresponding DC transmission type power framework is constructed, which realizes the decoupling of the magnetohydrodynamic power generation device and the thruster, so that the thruster can operate stably and efficiently. Attached Figure Description

[0034] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0035] Figure 1 A schematic diagram of the propulsion system provided by the present invention;

[0036] Figure 2 This is a schematic diagram of the magnetohydrodynamic device and distributed system provided by the present invention.

[0037] Explanation of reference numerals in the attached figures:

[0038] 11. Pre-ionization device; 12. Magnetohydrodynamic power generation device; 13. Ionization channel; 14. Compressor; 15. Motor; 16. Exhaust pipe;

[0039] 2. Distributed system; 21. Thruster; 211. Drive unit; 212. Propeller; 22. Transmission bus; 23. Energy storage device; 24. Transmission branch line; 25. Frequency converter; 26. Power converter;

[0040] 3. Gas chamber;

[0041] 4. Power controller. Detailed Implementation

[0042] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0044] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0045] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0046] Example 1

[0047] This embodiment provides a propulsion system, such as Figure 1 and Figure 2 As shown, the system includes a power generation system and a distributed system 2. The power generation system includes a pre-ionization device 11 and a magnetohydrodynamic (MHD) power generation device 12. The pre-ionization device 11 can ionize gas to generate ionized gas, which can pass through the MHD power generation device 12. The distributed system 2 includes four thrusters 21. As an alternative implementation, those skilled in the art can set different numbers of thrusters 21 as needed. The thrusters 21 are electrically connected to the MHD power generation device 12.

[0048] The propulsion system provided in this embodiment uses a magnetohydrodynamic (MHD) power generation device 12 to replace the internal combustion engine and drive the generator 15 to generate electricity. When ionized gas passes through the MHD power generation device 12, the MHD power generation device 12 can directly generate electrical energy. Therefore, it can generate electrical energy without mechanical conversion, which improves the energy conversion efficiency. In addition, the electrical energy is easy to transmit, which also improves the energy transmission efficiency.

[0049] like Figure 1As shown, the propulsion system provided in this embodiment includes an ionization channel 13 and an exhaust pipe 16. The ionization channel 13 is connected to the magnetohydrodynamic (MHD) power generation device 12. The pre-ionization device 11 can ionize the gas passing through the ionization channel 13 to generate ionized gas. The pre-ionization device 11 includes several resistance wires, some of which are wound around the outside of the pre-ionization channel 13 and some of which extend into the ionization channel 13. When high-temperature gas is introduced into the ionization channel 13, the pre-ionization device 11 supplies power, causing the resistance wires to heat up, thereby increasing the temperature inside the ionization channel 13 and causing the gas inside the ionization channel 13 to form plasma, which then becomes the working fluid of the MHD power generation device 12. The exhaust pipe 16 is connected to the exhaust port of the MHD power generation device 12 and is used to discharge the waste gas inside the MHD power generation device 12. The magnetohydrodynamic generator 12 generates direct current, which can reduce the impact of electromagnetic interference on the power and control systems during power transmission. Furthermore, since direct current does not have reactive power, the cables required for power transmission are lighter than those required for alternating current transmission, thereby reducing the mass of the propulsion system.

[0050] like Figure 1 As shown, the propulsion system provided in this embodiment also includes a gas chamber 3, a compressor 14, and a motor 15. The gas chamber 3 has an inlet and an outlet. The outlet is connected to the end of the ionization channel 13 away from the magnetohydrodynamic power generation device 12. The gas chamber 3 can generate high-temperature, high-speed gas. The compressor 14 includes three compressors connected in sequence. As an alternative implementation, those skilled in the art can adjust the number of compressors as needed. The outlet of the compressor 14 is connected to the inlet, and the inlet of the compressor 14 is connected to the outside. Each compressor is connected to a motor 15. The motor 15 operates the electric compressor. The compressor 14 can draw in a large amount of air and compress it sequentially. The compressed air is sent into the combustion chamber and mixed with the injected fuel to produce high-temperature, high-speed gas. The gas chamber 3 is suitable for generating high-temperature, high-speed gas; it converts the thermal energy and kinetic energy of the high-temperature gas generated in the combustion chamber into electrical energy to drive the motor 15, providing a power source for the distributed system 2.

[0051] like Figure 1 and Figure 2 As shown, the propulsion system provided in this embodiment also includes a power controller 4, which is electrically connected to the magnetohydrodynamic power generation device 12, the pre-ionization device 11 and the motor 15 respectively, that is, connected to the magnetohydrodynamic power generation device 12, the pre-ionization device 11 and the motor 15 through cables. The power controller 4 can realize the control of the magnetohydrodynamic power generation device 12, the pre-ionization device 11 and the motor 15.

[0052] like Figure 2As shown, the propulsion system provided in this embodiment, the distributed system 2, also includes a transmission bus 22, an energy storage device 23, four transmission branches 24, four frequency converters 25, four power converters 26, and four thrusters 21. The transmission bus 22 is connected to the power controller 4 and is a cable. The energy storage device 23 is connected to the transmission bus 22 and is a battery. As an alternative implementation, the energy storage device 23 can be a device or method for storing electrical energy. Any one of the four transmission branches 24 is connected to the transmission bus 22, and the connection positions are different. The transmission branch 24 is also a cable. Any one of the four frequency converters 25 is connected to its corresponding transmission branch 24. The frequency converter 25 is a DC-AC frequency converter 25, which can convert DC power into AC power. Any one of the power converters 26 is electrically connected to one frequency converter 25, that is, the power converter 26 and the frequency converter 25 are connected through a cable. The power converter 26 adjusts the current frequency according to the attitude of the aircraft. The thruster 21 includes a drive unit 211 and a propeller 212. Alternatively, the thruster 21 may also include an electric motor and a turbofan. The drive unit 211 is connected to one of the power converters 26 via a cable, and the propeller 212 is fixedly connected to the drive unit 211. The drive unit 211 can drive the propeller 212 to rotate. The transmission bus 22 is connected to the power controller 4, and the energy storage device 23 is connected to the transmission bus 22. The power on the transmission bus 22 flows through the frequency converter 25 and the power converter 26, and is finally sent to the thruster 21. The magnetohydrodynamic power generation device 12 cannot control the thruster 21 by changing the engine speed to adjust the current frequency. By adjusting the thruster 21 through the power converter 26, the power generation system and the electric motor can be decoupled. The current frequency on the electric motor side can be adjusted separately, improving the working efficiency of the propulsion system. That is, a corresponding DC transmission power framework is constructed, realizing the decoupling of the magnetohydrodynamic power generation device 12 and the thruster 21, enabling the thruster 21 to operate stably and efficiently.

[0053] The propulsion system provided in this embodiment works as follows:

[0054] When the power generation system is started for the first time, the energy storage device 23 provides electrical energy and inputs current to the motor 15 through the power controller 4. The motor 15 drives the air compressor 14 to work. The air compressor 14 draws in air from the external atmosphere and compresses it step by step. The compressed air is sent to the combustion chamber and mixed with the fuel injected into the combustion chamber to produce high-temperature and high-speed gas. At the same time, the energy storage device powers the pre-ionization device 11 through the power controller 4. The pre-ionization device 11 works and ionizes the high-temperature and high-speed gas passing through the ionization channel 13 to form plasma, which becomes the working fluid of the magnetohydrodynamic power generation device 12. When the magnetohydrodynamic power generation device 12 enters a certain working state, the motor 15, the pre-ionization device 11 and the distributed system 2 are all powered by the magnetohydrodynamic power generation device 12.

[0055] Once the magnetohydrodynamic (MHD) power generation device 12 reaches a certain state, the electrical energy generated by it is transmitted to each frequency converter 25 via the power controller 4 and the transmission bus 22. The frequency converter 25 converts the DC power into AC power and then transmits it to the power converter via cable. The power converter adjusts the rotational speed of the thruster 21 according to the aircraft's status. When the electrical output power of the MHD power generation device 12 is greater than the flight power, the excess electrical energy can be stored in the energy storage device. When the electrical output power of the MHD power generation device 12 is less than the flight power, the energy storage device 23 can provide power to the propulsion system simultaneously with the MHD power generation device 12. This ensures that the propulsion system operates stably at its optimal operating point, improves system reliability, and reduces fuel consumption.

[0056] Example 2

[0057] This embodiment provides an aircraft, including the thruster 21 system in embodiment 1 and the aircraft body, with the thruster system disposed on the aircraft body.

[0058] The aircraft provided in this embodiment has a thruster 21 that can be controlled independently, which improves control precision.

[0059] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A propulsion system, characterized in that, include: A power generation system comprising a pre-ionization device (11) and a magnetohydrodynamic power generation device (12), wherein the pre-ionization device (11) is capable of ionizing gas to generate ionized gas, and the magnetohydrodynamic power generation device (12) is adapted to allow the ionized gas to pass through; A distributed system (2) comprising multiple thrusters (21), each of which is electrically connected to the magnetohydrodynamic power generation device (12); The power generation system also includes an ionization channel (13), which is connected to the magnetohydrodynamic power generation device (12). The pre-ionization device (11) can ionize the gas passing through the ionization channel (13) to generate the ionized gas. The pre-ionization device (11) includes several resistance wires, some of which are wound around the outside of the pre-ionization channel (13) and some of which extend into the ionization channel (13). When high-temperature gas is introduced into the ionization channel (13), the pre-ionization device (11) supplies power, causing the resistance wires to heat up, thereby increasing the temperature inside the ionization channel (13). It also includes a gas chamber (3), which has an inlet and an outlet. The outlet is connected to the end of the ionization channel (13) away from the magnetohydrodynamic power generation device (12). The gas chamber (3) is suitable for generating high-temperature, high-speed gas.

2. The propulsion system according to claim 1, characterized in that, Also includes: The air compressor (14) includes at least one compressor, and the outlet of the air compressor (14) is connected to the air inlet; The motor (15) is connected to the compressor, and the magnetohydrodynamic generator (12) is electrically connected to the motor (15).

3. The propulsion system according to claim 2, characterized in that, The power generation system also includes an exhaust pipe (16), which is connected to the exhaust port of the magnetohydrodynamic power generation device (12).

4. The propulsion system according to claim 2 or 3, characterized in that, It also includes a power controller (4), which is electrically connected to the magnetohydrodynamic power generation device (12), the pre-ionization device (11) and the motor (15).

5. The propulsion system according to claim 4, characterized in that, The distributed system (2) also includes: A transmission bus (22) is connected to the power controller (4); An energy storage device (23) is connected to the transmission bus (22).

6. The propulsion system according to claim 5, characterized in that, The distributed system (2) also includes: A plurality of conveying branches (24), each of which is connected to the conveying bus (22); Multiple frequency converters (25), any one of the frequency converters (25) is connected to one of the conveyor branches (24); Multiple power converters (26), any one of the power converters (26) being electrically connected to one of the frequency converters (25).

7. The propulsion system according to claim 6, characterized in that, The thruster (21) includes: A drive unit (211) is electrically connected to one of the frequency converters (25); The propeller (212) is fixedly connected to the drive unit (211).

8. An aircraft, characterized in that, It includes an aircraft body and a propulsion system as described in any one of claims 1-7, wherein the propulsion system is mounted on the aircraft body.

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