Electric paddle fan aero-engine device with high-speed tail jet power generation function

Abstract

The invention provides an electric paddle fan aero-engine device with a high-speed tail jet power generation function. The electric paddle fan aero-engine device comprises an air inlet, a duct, an exhaust port, a fan assembly, an electric core machine assembly, a paddle fan assembly, a generator assembly and a rotating assembly, wherein the fan assembly, the electric core machine assembly, the paddle fan assembly, the generator assembly and the rotating assembly are arranged in the duct. The ducts comprise a single duct and a double duct, the double duct comprises an outer duct and an inner duct, and the outer duct and the inner duct are shunted at the rear end of the fan assembly and converged at the front end of the paddle fan assembly; the power core machine assembly is located in front of the inner duct at the rear end of the fan assembly. The paddle fan assembly is located in the middle of the inner duct. A first rotating cylinder and a second rotating cylinder of the rotating assembly respectively rotate to form a 90-degree direction, a 90-degree angle is formed between an air inlet and an air outlet, and horizontal power is switched to vertical power; fuel oil power is replaced by electric power, the acting force angle of a paddle fan can be changed by combining a rotating mechanism, vertical and horizontal power switching is provided, and high-speed jet gas kinetic energy is recycled for power generation by combining with a high-performance turbine generator set.

Description

Technical Field

[0001] The present invention relates to the technical field of power-driven aero-engine engines, and particularly relates to a power propeller fan aero-engine device with high-speed tail jet power generation. Background Art

[0002] There are many types of modern aero-engine engines, mainly fuel-powered, and are used as power for different aircraft. The mainstream aero-engines include: (1) Turbojet engine.

[0003] Working principle: Air enters the engine through the intake duct, is compressed by the compressor and then enters the combustion chamber, mixes with fuel and burns to produce high-temperature and high-pressure gas. The gas pushes the turbine to rotate, and at the same time is ejected at high speed from the tail nozzle, generating a reaction force to push the aircraft forward.

[0004] Features: It can provide strong thrust during high-speed flight, with fast flight speed and high ceiling, but it has poor economy, high fuel consumption rate and high noise during subsonic flight.

[0005] Application scenarios: It was widely used in civil airliners and military aircraft in the early days. Now it has been basically replaced by turbofan engines in the civil field and is mainly used in military aircraft for high-speed propulsion, such as fighter jets, reconnaissance aircraft, etc.

[0006] (2) Turbofan engine.

[0007] Working principle: Based on the turbojet engine, a fan and an outer bypass duct are added. After air enters the engine, a part of the air enters the outer bypass duct directly through the fan and is discharged backward to generate thrust; another part of the air enters the core duct, passes through components such as the compressor, combustion chamber, and turbine, and has the same working principle as a traditional turbojet engine. Finally, the high-temperature gas mixes with the air in the outer bypass duct and is discharged.

[0008] Features: It has the characteristics of high efficiency, low noise, low fuel consumption, environmental protection, etc. The higher the bypass ratio, the better the economy and propulsion efficiency.

[0009] Application scenarios: It is the mainstream power device for modern civil airliners and large transport aircraft, and is also widely used in some military aircraft such as large refueling aircraft and early warning aircraft.

[0010] (3) Turboprop engine.

[0011] Working principle: Combines a turbine gas turbine and a propeller, uses the power of the turbine to drive the propeller to rotate to generate thrust, and at the same time a small amount of jet will be generated at the tail of the engine to generate auxiliary thrust.

[0012] Features: It has high efficiency and good economy at low-speed flight, and has the advantages of low noise and low fuel consumption, but its flight speed is relatively slow.

[0013] Application scenarios: Suitable for short - range regional transportation, regional airliners, feeder airliners, and some small transport aircraft with high economic requirements, etc.

[0014] (4) Turboshaft engine.

[0015] Working principle: By increasing the number of turbines, the energy in the combustion airflow is converted into the energy of turbine rotation. The power is mainly output by the turboshaft to drive the rotor of the helicopter or other equipment that requires shaft power.

[0016] Features: Focus on providing pure power output, not relying on jet propulsion, with the characteristics of high power, small volume, and light weight.

[0017] Application scenarios: Mainly used in helicopters, and can also be applied to some ground vehicles or other equipment that require shaft power.

[0018] (5) Propfan engine.

[0019] Working principle: The propfan engine belongs to the gas turbine engine, and its working process is basically similar to that of the turboprop engine. Air enters the engine through the intake device, is compressed in the compressor, and the pressure and temperature are increased; the compressed air enters the combustion chamber, mixes with fuel and burns to form high - temperature and high - pressure gas; the gas expands fully in the turbine, converting most of the available energy of the gas into turbine mechanical work, and the turbine drives the compressor and the propfan to rotate; finally, the gas is discharged from the exhaust device, generating a small amount of thrust, and the main propulsion force is generated by the high - speed rotation of the propfan.

[0020] Features: The propfan engine is an innovative design that combines the characteristics of turboprop and turbofan, with the characteristics of high fuel efficiency, high flight speed, high propulsion efficiency, and high take - off and landing performance.

[0021] Application scenarios: Suitable for feeder airliners, transport aircraft, patrol aircraft, special operation aircraft, future large - scale UAVs, etc.

[0022] (6) Rotor - shaped UAV.

[0023] Composition and principle: Composed of a battery, an electronic speed controller (ESC), a motor, and a propeller, belonging to electric power. The battery provides electrical energy, controls the speed and rotation direction of the motor according to the instructions of the flight control system. The motor drives the propeller to rotate at high speed, and the propeller generates a reaction force by pushing air downward to provide lift and thrust for the UAV, thus realizing flight.

[0024] Features: It has the advantages of simple structure, easy maintenance, quick start, sensitive response, low noise, and no pollution. However, the energy density of the battery is relatively low, resulting in a limited endurance time for the UAV, generally about dozens of minutes.

[0025] Application scenarios: Widely used in consumer rotor UAVs, such as aerial photography UAVs, entertainment UAVs, etc., and also applicable to some small professional UAVs with low requirements for endurance, flexible operation and low noise, such as UAVs in the fields of urban security monitoring, indoor inspection, etc.

[0026] In view of the above mainstream aeroengines, electric aircraft technology, as the future development direction of the aviation industry, has a broad market prospect in the future because it greatly reduces the emissions of carbon dioxide and other pollutants, reduces the noise of the aircraft, and improves the efficiency of the aircraft. Its core technologies are high-efficiency and high power-to-weight ratio electric engine technology and high-energy density battery technology. The breakthrough of the core technology plays a crucial role in the future development of electric aviation. In particular, the low-altitude economy is a rapidly developing field in the future, and electric aircraft technology is the key carrier for the development of the low-altitude economy. The core of electric aircraft technology is electric propulsion technology. Summary of the Invention

[0027] In view of this, the purpose of the present invention is to propose a power propeller fan aeroengine device with high-speed tail jet power generation. According to the working principles and technical characteristics of turbofan engines and propeller fan engines, further integrate the working principles and technical advantages of turbofan engines and propeller fan engines, as well as the technical advantages of high-performance generators, further integrate the compressor technology of turbofan engines and the turbine drive technology of propeller fan engines, and use the electric power mode to replace the fuel power working mode to form a new power propeller fan aeroengine device technology and method; further integrate a 90-degree rotation mechanism that can change the angle of the propeller fan force to provide vertical and horizontal power switching; and further combine with a high-performance turbogenerator set to recover the kinetic energy of the high-speed tail jet for power generation, forming a new integrated device technology and method of a power propeller fan aeroengine and a tail jet turbine generator. This new type of aviation power device will be used as a new power for future electric aircraft.

[0028] To achieve the above object, the present invention provides the following technical solutions: Based on the above object, in the first aspect, the present invention provides a power propeller fan aeroengine device with high-speed tail jet power generation, including an air inlet, a duct, an exhaust port, and a fan assembly, a power core engine assembly, a propeller fan assembly, a generator assembly, and a rotation assembly provided in the duct; The duct includes a single duct and a double duct, and the double duct includes an inner duct and an outer duct; The fan assembly includes a fan fairing and a fan; The power core engine assembly includes a medium-pressure compressor, a high-pressure compressor, a compressor rotating shaft, a compressor differential, a compressor turbine group, a compressor motor, and a compressor motor fairing; The propeller fan assembly includes a propeller fan turbine fairing, a propeller fan turbine group, a propeller fan rotating shaft, and a double-row contra-rotating propeller blade driver; The generator assembly includes a generator turbine, a generator, and a tail fairing; The rotating assembly includes a front-end connecting flange, a first rotating cylinder, a first rotating cylinder gear, a connecting cylinder, a third rotating cylinder gear, a second rotating cylinder, a rear-end connecting flange, a first rotating cylinder drive motor, a first rotating cylinder drive motor reducer, a first rotating cylinder drive rack, a second rotating cylinder drive motor, a second rotating cylinder drive motor reducer, and a second rotating cylinder drive rack.

[0029] As a further aspect of the present invention, the air inlet is located at the front entrance of the duct, and the exhaust outlet is located at the rear exit of the duct; Air is inhaled from the air inlet, flows through the duct passage, and is discharged from the exhaust outlet; the air forms a flowing air current through the limited passages of the air inlet, the duct, and the exhaust outlet; after the high-speed and high-pressure air current is discharged from the exhaust outlet, a small amount of thrust is generated.

[0030] As a further aspect of the present invention, the inner duct and the outer duct are branched at the rear end of the fan assembly and converge at the front end of the propeller fan assembly; after the air enters the double duct, a part of the air enters the outer duct through the fan and is directly ejected backward to generate a driving force; another part of the air enters the inner duct, and the air after entering the inner duct is compressed by the compressor to form a high-speed and high-pressure air current; wherein, the air flow rate of the outer duct is greater than that of the inner duct, and the fan significantly increases the total air flow rate of the engine, thereby enhancing the thrust.

[0031] As a further aspect of the present invention, the fan fairing is installed at the front end of the fan to play a guiding role; The rear end of the fan is connected to the fan drive shaft of the compressor rotating shaft of the power core engine assembly. The fan is a low-pressure and low-speed air flow compression mechanism, and the rotation of the fan is used to suck a large amount of air from the outside into the duct.

[0032] As a further aspect of the present invention, the medium-pressure compressor, high-pressure compressor, compressor rotating shaft, compressor differential, compressor turbine group, compressor motor, and compressor motor fairing of the power core engine assembly are sequentially connected and placed in the single duct or the inner duct; The rear ends of the medium-pressure compressor and the high-pressure compressor are respectively connected to the medium-pressure compressor drive shaft and the high-pressure compressor drive shaft of the compressor rotating shaft; the medium-pressure compressor is a multi-stage medium-pressure and medium-speed air flow compression mechanism, and the high-pressure compressor is a multi-stage high-pressure and high-speed air flow compression mechanism; after the air is gradually compressed by the medium-pressure compressor and the high-pressure compressor, a high-speed and high-pressure air current is formed, and this air current has a very high speed and kinetic energy.

[0033] The compressor rotating shaft includes a fan drive shaft, an intermediate-pressure compressor drive shaft, and a high-pressure compressor drive shaft. The compressor rotating shaft is a concentric multi-shaft sleeve-type rotating shaft structure. The rear end of the compressor rotating shaft is connected to the interfaces of the fan drive shaft, the intermediate-pressure compressor drive shaft, and the high-pressure compressor drive shaft at the output end of the compressor differential. The compressor rotating shaft is a rotational power transmission mechanism. The front end of the compressor differential is connected to the compressor rotating shaft, and the rear end is connected to the compressor turbine group. It is used to convert the rotational power input by the compressor turbine group into three output rotational powers of the fan, the intermediate-pressure compressor, and the high-pressure compressor and output them to the compressor rotating shaft. The compressor differential is a rotational power distribution mechanism.

[0034] The front end of the compressor turbine group is connected to the compressor differential, and the rear end is coupled to the turbine shaft of the compressor motor. The compressor turbine group is a conversion mechanism that converts the kinetic energy of air flow into rotational power. After the air is compressed step by step by the fan, the intermediate-pressure compressor, and the high-pressure compressor, a high-speed and high-pressure air flow with very high speed and kinetic energy is formed. This high-speed and high-pressure air flow is converted into rotational power by the compressor turbine group and output to the compressor differential. On the other hand, since there is no combustion chamber in the electric core engine component, the part of the energy that generates high-pressure gas by fuel combustion in the traditional core engine is output by the resultant force of the rotational power of the compressor motor and the rotational power output by the compressor turbine group to compensate for the rotational power generated by the energy of fuel combustion. Theoretically, as long as the electrical energy generated by the compressor motor is the same as the energy of fuel combustion, the total rotational power output by the compressor turbine group is the same. The front end of the compressor motor is coupled to the turbine shaft of the compressor turbine group and is used to output the resultant force of the rotational power converted from electrical energy and the rotational power of the compressor turbine group. The compressor motor is a high-performance motor, such as a magnetic levitation bearingless motor or a superconducting motor. The rear end of the compressor motor is connected to the compressor motor fairing, and the compressor motor fairing plays a role in guiding the flow.

[0035] As a further solution of the present invention, the propeller fan turbine fairing, the propeller fan turbine group, the propeller fan rotating shaft, and the double-row contra-rotating propeller blade driver are sequentially connected by the propeller fan rotating shaft. The propeller fan turbine fairing is installed at the front end of the propeller fan turbine group and plays a role in guiding the flow. The rear end of the propeller fan turbine group is connected to the propeller fan turbine group and provides rotational power for the double-row contra-rotating propeller blade driver.

[0036] As a further aspect of the present invention, the double-row contra-rotating propeller blade driver includes a double-row contra-rotating propeller blade power gear, a double-row contra-rotating propeller blade drive gear, an annular propeller blade connector support rib, an annular propeller blade connector, a propeller fan assembly blade, and a propeller fan assembly cover; The double-row contra-rotating propeller blade power gear is fixed on the propeller fan rotating shaft and is composed of back-to-back double 45-degree helical gears, which are respectively engaged and connected with the double-row contra-rotating propeller blade drive gear; the outer edges of the double-row contra-rotating propeller blade drive gears are respectively connected to multiple fan-shaped distributed groups of the annular propeller blade connector support ribs; the outer edges of the two groups of annular propeller blade connector support ribs are respectively connected to the inner edges of two of the annular propeller blade connectors; the outer edges of the two annular propeller blade connectors are respectively connected to two groups of contra-rotating propeller fan assembly blades; The propeller fan turbine group rotates and transmits the rotational power to the double-row contra-rotating propeller blade power gear on the double-row contra-rotating propeller blade driver through the propeller fan rotating shaft. The double-row contra-rotating propeller blade power gear vertically transmits the power to the double-row contra-rotating propeller blade drive gear. The double-row contra-rotating propeller blade drive gear drives the propeller fan assembly blades on the annular propeller blade connectors of the annular propeller blade connector support ribs, driving the two groups of propeller fan assembly blades to rotate in left-handed and right-handed rotations respectively, canceling out the reaction torque.

[0037] As a further aspect of the present invention, when the propeller fan assembly switches from horizontal power to vertical power, the first rotating cylinder and the second rotating cylinder respectively rotate to form a 90-degree orientation, and the air inlet and the air outlet present a 90-degree angle, switching the horizontal power to vertical power.

[0038] As a further aspect of the present invention, the front connecting flange and the rear connecting flange are respectively fixed at both ends of the engine main body; the first rotating cylinder drive rack and the second rotating cylinder drive rack respectively drive the first rotating cylinder gear and the third rotating cylinder gear through the first rotating cylinder drive motor reducer and the second rotating cylinder drive motor reducer, realizing a 90-degree directional rotation of the propeller fan assembly.

[0039] As a further aspect of the present invention, the generator assembly includes a generator turbine, a generator, and a tail fairing; the generator turbine is installed on the front rotating shaft of the generator, the generator is placed inside the tail fairing, and the generator is a high-performance generator, such as a magnetic levitation bearingless generator or a superconducting generator.

[0040] Compared with the prior art, a power propeller fan aeroengine device with high-speed tail jet power generation proposed by the present invention has the following beneficial effects: 1. By replacing fuel combustion with electric drive and directly driving the turbine group using the electric core engine components (compressor motor), the heat energy loss during the fuel combustion process of traditional engines is eliminated, and the energy conversion efficiency is improved; the generator components use the high-speed exhaust gas to drive the turbine to generate electricity, converting the originally wasted air flow kinetic energy into electrical energy, realizing the recycling of energy, reducing the overall energy consumption, and achieving the recovery of exhaust gas kinetic energy for power generation; moreover, the compressor turbine group, propeller fan turbine group, and generator turbine extract the air flow kinetic energy step by step, maximizing the utilization of air flow energy and enhancing the overall system efficiency.

[0041] 2. The present invention cancels the torque by two sets of counter-rotating blades, reduces energy loss, and at the same time increases the air flow rate per unit time, so the propulsion efficiency is higher than that of traditional single-row propeller fans. Through the multi-stage compression and acceleration of the medium-pressure / high-pressure compressor and turbine components, the air flow speed in the core duct reaches high speed and high pressure, and the large-flow air in the bypass duct acts synergistically, significantly enhancing the total thrust; the proportion of the air flow in the bypass duct is greater than that in the core duct, and it is directly accelerated and discharged to generate additional thrust, which is suitable for high-subsonic cruise requirements.

[0042] 3. The compressor rotating shaft adopts a sleeve structure, integrating the drive fan, compressor, and turbine, reducing the number of mechanical transmission components, and reducing the weight and friction loss; the electric core engine, propeller fan assembly, and generator assembly are independently installed, facilitating maintenance and upgrading; the rotating assembly adopts a gear-driven motor structure to achieve a 90-degree rotation function, simplifying the complexity of the traditional tilting mechanism; the generator turbine blades and propeller fans can use high-temperature-resistant composite materials, and the turbine disk and blade disk are integrally formed, reducing the moment of inertia and meeting the requirements of structural lightweight and compactness. Completely relying on electric drive, it eliminates pollutants such as CO2 and NOx generated by fuel combustion, conforming to the development trend of green aviation. The generator assembly adopts a five-degree-of-freedom magnetic levitation bearingless generator or superconducting generator device, eliminating mechanical friction noise, suitable for the urban air mobility (UAM) scenario. The single-duct type is suitable for short-range high-maneuver requirements, and the double-duct type meets the long-range high-thrust requirements. Through modular design, rapid configuration can be achieved.

[0043] These aspects or other aspects of the present application will be more clearly understood in the following description of the embodiments. It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present application. Brief Description of the Drawings

[0044] To more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following will briefly introduce the drawings required for use in the description of the exemplary embodiments or related technologies. The drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation to the present invention. In the drawings: Figure 1Schematic structural diagram of a dual-ducted electric propfan aeroengine device with high-speed tail jet power generation in the present invention.

[0045] Figure 2 Schematic structural diagram of a single-ducted electric propfan aeroengine device with high-speed tail jet power generation in the present invention.

[0046] Figure 3 Schematic structural diagram of a dual-ducted electric propfan aeroengine device in the present invention.

[0047] Figure 4 Schematic structural diagram of a single-ducted electric propfan aeroengine device in the present invention.

[0048] Figure 5 Schematic structural diagram of the 90-degree rotation structure of the propfan in the single-ducted electric propfan aeroengine device of the present invention.

[0049] Figure 6 Schematic structural diagram of the propfan assembly in the electric propfan aeroengine device with high-speed tail jet power generation of the present invention.

[0050] Figure 7 Schematic structural diagram of the rotation mechanism of the propfan assembly in the electric propfan aeroengine device with high-speed tail jet power generation of the present invention. Description of the drawings: 1 - Air inlet, 2 - Fan fairing, 3 - Fan, 4 - Medium-pressure compressor, 5 - High-pressure compressor, 6 - Compressor rotating shaft, 7 - Compressor differential, 8 - Compressor turbine group, 9 - Compressor motor, 10 - Compressor motor fairing, 11 - Single duct, 111 - Inner duct, 112 - Outer duct, 13 - Propfan turbine fairing, 14 - Propfan turbine group, 15 - Double-row contra-rotating blade driver, 16 - Generator turbine, 17 - Generator, 18 - Tail fairing, 19 - Exhaust port; 51 - Propfan rotating shaft, 52 - Propfan turbine disk, 53 - Propfan turbine blade, 54 - Ring blade connector, 55 - Propfan assembly blade, 56 - Ring blade connector support rib, 57 - Double-row contra-rotating blade drive gear, 58 - Double-row contra-rotating blade power gear, 59 - Propfan assembly cover; 61 - Front-end connection flange, 62 - First rotating cylinder, 63 - First rotating cylinder gear, 64 - Connection cylinder, 65 - Third rotating cylinder gear, 66 - Second rotating cylinder, 67 - Rear-end connection flange, 68 - First rotating cylinder drive motor, 69 - First rotating cylinder drive motor reducer, 610 - First rotating cylinder drive rack, 611 - Second rotating cylinder drive motor, 612 - Second rotating cylinder drive motor reducer, 613 - Second rotating cylinder drive rack. Detailed implementation manners

[0052] Next, in combination with the accompanying drawings and specific embodiments, the present application will be further described. It should be noted that, on the premise of no conflict, the following-described embodiments or technical features can be arbitrarily combined with each other to form new embodiments.

[0053] To make the objectives, technical solutions, and advantages of the present invention clearer and more understandable, the following further elaborates on the embodiments of the present invention in combination with specific embodiments and with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0054] It should be noted that all the expressions using "first" and "second" in the embodiments of the present invention are used to distinguish two non-identical entities or non-identical parameters with the same name. It can be seen that "first" and "second" are only for the convenience of expression and should not be construed as a limitation on the embodiments of the present invention. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or device that includes a series of steps or units inherently includes other steps or units.

[0055] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in combination with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts fall within the scope of protection of the present application.

[0056] The flowchart shown in the accompanying drawings is only an example illustration, and does not necessarily include all the content and operations / steps, nor does it necessarily execute in the described order. For example, some operations / steps can also be decomposed, combined, or partially merged. Therefore, the actual execution order may change according to the actual situation.

[0057] Next, some embodiments of the present application will be described in detail in combination with the accompanying drawings. Without conflict, the following embodiments and the features in the embodiments can be combined with each other.

[0058] See Figures 1-4 As shown, an embodiment of the present invention provides a power pusher-fan aeroengine device with high-speed exhaust gas power generation, which is characterized by including an air inlet 1, a duct, an exhaust port 19, and a fan assembly, a power core engine assembly, a pusher-fan assembly, a generator 17 assembly, and a rotating assembly disposed in the duct; The duct includes a single duct 11 and a double duct, and the double duct includes an inner duct 111 and an outer duct 112; The fan assembly includes a fan cowling 2 and a fan 3; The power core component includes a medium-pressure compressor 4, a high-pressure compressor 5, a compressor rotating shaft 6, a compressor differential 7, a compressor turbine group 8, a compressor motor 9, and a compressor motor fairing 10; The propeller fan component includes a propeller fan turbine fairing 13, a propeller fan turbine group 14, a propeller fan rotating shaft 51, and a double-row contra-rotating propeller blade driver 15; The generator component includes a generator turbine 16, a generator 17, and a tail fairing 18; The rotating component includes a front-end connecting flange 61, a first rotating cylinder 62, a first rotating cylinder gear 63, a connecting cylinder 64, a third rotating cylinder gear 65, a second rotating cylinder 66, a rear-end connecting flange 67, a first rotating cylinder driving motor 68, a first rotating cylinder driving motor reducer 69, a first rotating cylinder driving rack 610, a second rotating cylinder driving motor 611, a second rotating cylinder driving motor reducer 612, and a second rotating cylinder driving rack 613.

[0059] In this embodiment, the air inlet 1 is located at the front entrance of the duct, and the exhaust port 19 is located at the rear exit of the duct; air is inhaled from the air inlet 1, flows through the duct passage, and is discharged from the exhaust port 19; the air forms a flowing air current through the limited passages of the air inlet 1, the duct, and the exhaust port 19; after the high-speed and high-pressure air current is discharged from the exhaust port 19, a small amount of thrust is generated.

[0060] In this embodiment, the inner duct 111 and the outer duct 112 are branched at the rear end of the fan assembly and converge at the front end of the propeller fan assembly; after the air enters the double duct, a part of the air enters the outer duct 112 through the fan and is directly ejected backward to generate a driving force; the other part of the air enters the inner duct 111, and the air entering the inner duct 111 is compressed by the compressor to form a high-speed and high-pressure air current; among them, the air flow rate of the outer duct 112 is greater than that of the inner duct 111, and the fan significantly increases the total air flow rate of the engine, thereby increasing the thrust.

[0061] In this embodiment, the fan fairing 2 is installed at the front end of the fan 3 to play a guiding role; the rear end of the fan 3 is connected to the fan drive shaft of the compressor rotating shaft 6 of the power core component, the fan 3 is a low-pressure and low-speed air compression mechanism, and the fan 3 rotates to suck a large amount of air from the outside into the duct.

[0062] In this embodiment, the medium-pressure compressor 4, high-pressure compressor 5, compressor rotating shaft 6, compressor differential 7, compressor turbine set 8, compressor motor 9 and compressor motor fairing 10 of the power core component are sequentially connected and placed in the single duct 11 or the inner duct 111; the rear ends of the medium-pressure compressor 4 and the high-pressure compressor 5 are respectively connected to the medium-pressure compressor drive shaft and the high-pressure compressor drive shaft of the compressor rotating shaft 6; the medium-pressure compressor 4 is a multi-stage medium-pressure and medium-speed air compression mechanism, and the high-pressure compressor 5 is a multi-stage high-pressure and high-speed air compression mechanism; after the air is compressed step by step by the medium-pressure compressor 4 and the high-pressure compressor 5, a high-speed and high-pressure air flow is formed, and this air flow has a very high speed and kinetic energy.

[0063] The compressor rotating shaft 6 includes a fan drive shaft, a medium-pressure compressor drive shaft, and a high-pressure compressor drive shaft. The compressor rotating shaft 6 is a concentric multi-shaft sleeve-type rotating shaft structure; the rear end of the compressor rotating shaft 6 is connected to the interfaces of the fan drive shaft, the medium-pressure compressor drive shaft, and the high-pressure compressor drive shaft at the output end of the compressor differential 7; the compressor rotating shaft 6 is a rotational power transmission mechanism. The front end of the compressor differential 7 is connected to the compressor rotating shaft 6, and the rear end is connected to the compressor turbine set 8. It converts the rotational power input by the compressor turbine set 8 into three output rotational powers of the fan 3, the medium-pressure compressor 4, and the high-pressure compressor 5 and outputs them to the compressor rotating shaft 6; the compressor differential 7 is a rotational power distribution mechanism.

[0064] The front end of the compressor turbine set 8 is connected to the compressor differential 7, and the rear end is coupled to the turbine shaft of the compressor motor 9; the compressor turbine set 8 is a conversion mechanism that converts the kinetic energy of the air flow into rotational power; after the air is compressed step by step by the fan 3, the medium-pressure compressor 4, and the high-pressure compressor 5, a high-speed and high-pressure air flow with a very high speed and kinetic energy is formed; this high-speed and high-pressure air flow is converted into rotational power by the compressor turbine set 8 and output to the compressor differential 7.

[0065] On the other hand, since there is no combustion chamber in the power core component, the energy that generates high-pressure gas by fuel combustion in the traditional core engine is output by the combined force of the rotational power of the compressor motor 9 and the rotational power output by the compressor turbine set 8 to compensate for the rotational power generated by the energy of fuel combustion; theoretically, as long as the electrical energy generated by the compressor motor 9 is the same as the energy of fuel combustion, the total rotational power output by the compressor turbine set 8 is the same. The front end of the compressor motor 9 is coupled to the turbine shaft of the compressor turbine set 8, and the rotational power converted from electrical energy and the rotational power of the compressor turbine set 8 are combined and output; the compressor motor 9 is a high-performance motor, such as a magnetic levitation bearingless motor or a superconducting motor; the rear end of the compressor motor 9 is connected to the compressor motor fairing 10, and the compressor motor fairing 10 serves as a flow guide.

[0066] See Figure 6 As shown, in this embodiment, the propeller fan turbine fairing 13, the propeller fan turbine set 14, the propeller fan rotating shaft 51, and the double-row contra-rotating propeller blade driver 15 of the propeller fan assembly are sequentially connected by the propeller fan rotating shaft 51; the propeller fan turbine fairing 13 is installed at the front end of the propeller fan turbine set 14 and serves as a flow guide; the rear end of the propeller fan turbine set 14 is connected to the propeller fan turbine set 14 to provide rotational power for the double-row contra-rotating propeller blade driver 15.

[0067] In this embodiment, the double-row contra-rotating propeller blade driver 15 includes a double-row contra-rotating propeller blade power gear 58, a double-row contra-rotating propeller blade drive gear 57, an annular propeller blade connector support rib 56, an annular propeller blade connector 54, a propeller fan assembly blade 55, and a propeller fan assembly cover 59. The double-row contra-rotating propeller blade power gear 58 is fixed on the propeller fan rotating shaft 51 and is composed of back-to-back double 45-degree helical gears, which are respectively engaged with the double-row contra-rotating propeller blade drive gear 57; the outer edge of the double-row contra-rotating propeller blade drive gear 57 is respectively connected to multiple fan-shaped distributed groups of the annular propeller blade connector support ribs 56; the outer edges of the two groups of annular propeller blade connector support ribs 56 are respectively connected to the inner edges of the two annular propeller blade connectors 54; the outer edges of the two annular propeller blade connectors 54 are respectively connected to two groups of contra-rotating propeller fan assembly blades 55.

[0068] When the propeller fan turbine set 14 rotates, the rotational power is transmitted to the double-row contra-rotating propeller blade power gear 58 on the double-row contra-rotating propeller blade driver 15 through the propeller fan rotating shaft 51. The double-row contra-rotating propeller blade power gear 58 vertically transmits the power to the double-row contra-rotating propeller blade drive gear 57. The double-row contra-rotating propeller blade drive gear 57 drives the propeller fan assembly blades 55 on the annular propeller blade connectors 54 of the annular propeller blade connector support ribs 56, driving the two groups of propeller fan assembly blades to rotate in left and right rotations respectively, canceling the reaction torque with each other.

[0069] See Figure 5 and Figure 7As shown, in this embodiment, the rotating assembly includes a front-end connecting flange 61, a first rotating cylinder 62, a first rotating cylinder gear 63, a connecting cylinder 64, a third rotating cylinder gear 65, a second rotating cylinder 66, a rear-end connecting flange 67, a first rotating cylinder driving motor 68, a first rotating cylinder driving motor reducer 69, a first rotating cylinder driving rack 610, a second rotating cylinder driving motor 611, a second rotating cylinder driving motor reducer 612, and a second rotating cylinder driving rack 613. When the paddle fan assembly switches from horizontal power to vertical power, the first rotating cylinder 62 and the second rotating cylinder 66 rotate respectively to form a 90-degree orientation, and the air inlet 1 and the exhaust port 19 present a 90-degree angle, switching the horizontal power to vertical power.

[0070] In this embodiment, the front-end connecting flange 61 and the rear-end connecting flange 67 are respectively fixed to both ends of the engine body; the first rotating cylinder driving rack 610 and the second rotating cylinder driving rack 613 respectively drive the first rotating cylinder gear 63 and the third rotating cylinder gear 65 through the first rotating cylinder driving motor reducer 69 and the second rotating cylinder driving motor reducer 612, realizing a 90-degree directional rotation of the paddle fan assembly.

[0071] In this embodiment, the generator assembly includes the generator turbine 16, the generator 17, and the tail fairing 18; the generator turbine 16 is installed on the front rotating shaft of the generator 17, and the generator 17 is placed inside the tail fairing 18; the generator 17 is a high-performance generator, such as a magnetic levitation bearingless generator or a superconducting generator.

[0072] The above are the exemplary embodiments disclosed by the present invention. However, it should be noted that various changes and modifications can be made without departing from the scope of the embodiments disclosed by the present invention defined by the claims. The functions, steps, and / or actions of the method claims according to the disclosed embodiments herein do not need to be executed in any specific order. In addition, although the elements disclosed by the embodiments of the present invention can be described or claimed in individual form, they can also be understood as plural unless explicitly limited to the singular.

[0073] It should be understood that, as used in the present invention, unless the context clearly supports an exception, the singular form "a" is also intended to include the plural form. It should also be understood that the "and / or" used in the present invention refers to any and all possible combinations including one or more of the related listed items. The serial numbers of the disclosed embodiments of the present invention above are only for description and do not represent the advantages or disadvantages of the embodiments.

[0074] Those of ordinary skill in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope (including the claims) of the disclosure of the embodiments of the present invention is limited to these examples; under the concept of the embodiments of the present invention, the technical features in the above embodiments or different embodiments can also be combined, and there are many other variations in different aspects of the embodiments of the present invention as described above, which are not provided in detail for the sake of brevity. Therefore, any omission, modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present invention shall be included within the protection scope of the embodiments of the present invention.

Claims

1. A power paddle fan aeroengine device with high-speed tail jet power generation, characterized in that, It includes an air inlet (1), a duct, an exhaust port (19), and a fan assembly, an electric core engine assembly, a propeller fan assembly, a generator assembly, and a rotating assembly disposed within the duct; The duct includes a single duct (11) and a dual duct, and the dual duct includes an inner duct (111) and an outer duct (112); The fan assembly includes a fan fairing (2) and a fan (3); The electric core engine assembly includes an intermediate-pressure compressor (4), a high-pressure compressor (5), a compressor rotating shaft (6), a compressor differential (7), a compressor turbine group (8), a compressor motor (9), and a compressor motor fairing (10). The intermediate-pressure compressor (4), high-pressure compressor (5), compressor rotating shaft (6), compressor differential (7), compressor turbine group (8), compressor motor (9), and compressor motor fairing (10) of the electric core engine assembly are sequentially connected and disposed within the single duct (11) or the inner duct (111); The propeller fan assembly includes a propeller fan turbine fairing (13), a propeller fan turbine group (14), a propeller fan rotating shaft (51), and a double-row contra-rotating propeller blade driver (15); The generator assembly includes a generator turbine (16), a generator (17), and a tail fairing (18); The rotating assembly includes a front-end connecting flange (61), a first rotating cylinder (62), a first rotating cylinder gear (63), a connecting cylinder (64), a third rotating cylinder gear (65), a second rotating cylinder (66), a rear-end connecting flange (67), a first rotating cylinder driving motor (68), a first rotating cylinder driving motor reducer (69), a first rotating cylinder driving rack (610), a second rotating cylinder driving motor (611), a second rotating cylinder driving motor reducer (612), and a second rotating cylinder driving rack (613).

2. The power paddle fan aeroengine device with high-speed tail jet power generation according to claim 1, characterized in that, The air inlet (1) is located at the front entrance of the duct, and the exhaust port (19) is located at the rear exit of the duct; Air is inhaled from the air inlet (1), flows through the duct passage, and is discharged from the exhaust port (19); the air forms a flowing air current through the limited passages of the air inlet (1), the duct, and the exhaust port (19).

3. The power paddle fan aeroengine device with high-speed tail jet power generation as described in claim 1, characterized in that, The inner duct (111) and the outer duct (112) are split at the rear end of the fan assembly and converge at the front end of the propeller fan assembly, and the air flow rate of the outer duct (112) is greater than that of the inner duct (111).

4. The power paddle fan aero-engine device with high-speed tail jet power generation according to claim 3, characterized in that, The fan fairing (2) is installed at the front end of the fan (3) to play a guiding role; The rear end of the fan (3) is connected to the fan drive shaft of the compressor rotating shaft (6) of the electric core engine assembly. The fan (3) is a low-pressure and low-speed air compression mechanism, and the fan (3) rotates to suck a large amount of air from the outside into the duct.

5. The power paddle fan aero-engine device with high-speed tail jet power generation according to claim 1, characterized in that, The rear ends of the medium-pressure compressor (4) and the high-pressure compressor (5) are respectively connected to the medium-pressure compressor drive shaft and the high-pressure compressor drive shaft of the compressor rotating shaft (6); the medium-pressure compressor (4) is a multi-stage medium-pressure and medium-speed air compression mechanism, and the high-pressure compressor (5) is a multi-stage high-pressure and high-speed air compression mechanism; after the air is gradually compressed by the medium-pressure compressor (4) and the high-pressure compressor (5), a high-speed and high-pressure air flow is formed. The compressor rotating shaft (6) includes a fan drive shaft, a medium-pressure compressor drive shaft, and a high-pressure compressor drive shaft. The compressor rotating shaft (6) is a concentric multi-shaft sleeve-type rotating shaft structure; the rear end of the compressor rotating shaft (6) is connected to the interfaces of the fan drive shaft, the medium-pressure compressor drive shaft, and the high-pressure compressor drive shaft at the output end of the compressor differential (7); the compressor rotating shaft (6) is a rotational power transmission mechanism. The front end of the compressor differential (7) is connected to the compressor rotating shaft (6), and the rear end is connected to the compressor turbine group (8). It is used to convert the rotational power input by the compressor turbine group (8) into three output rotational powers of the fan (3), the medium-pressure compressor (4), and the high-pressure compressor (5) and output them to the compressor rotating shaft (6); the compressor differential (7) is a rotational power distribution mechanism. The front end of the compressor turbine group (8) is connected to the compressor differential (7), and the rear end is coupled to the turbine shaft of the compressor motor (9); the compressor turbine group (8) is a conversion mechanism that converts the kinetic energy of the air flow into rotational power; after the air is gradually compressed by the fan (3), the medium-pressure compressor (4), and the high-pressure compressor (5), a high-speed and high-pressure air flow with high speed and kinetic energy is formed. The high-speed and high-pressure air flow is converted into rotational power by the compressor turbine group (8) and output to the compressor differential (7). The front end of the compressor motor (9) is coupled to the turbine shaft of the compressor turbine group (8) and is used to combine the rotational power converted from electrical energy with the rotational power of the compressor turbine group (8) and output the resultant force; the compressor motor (9) is a high-performance motor. The rear end of the compressor motor (9) is connected to the compressor motor fairing (10), and the compressor motor fairing (10) serves a guiding function.

6. The power paddle fan aero-engine device with high-speed tail jet power generation according to claim 5, characterized in that, The propeller fan turbine fairing (13), the propeller fan turbine group (14), and the double-row contra-rotating propeller blade driver (15) of the propeller fan assembly are sequentially connected by the propeller fan rotating shaft (51). The propeller fan turbine fairing (13) is installed at the front end of the propeller fan turbine group (14) and serves a guiding function. The rear end of the propeller fan turbine group (14) is connected to the propeller fan turbine group (14) and provides rotational power for the double-row contra-rotating propeller blade driver (15).

7. The power paddle fan aero-engine device with high-speed tail jet power generation according to claim 6, characterized in that, The double-row contra-rotating propeller blade driver (15) includes a double-row contra-rotating propeller blade power gear (58), a double-row contra-rotating propeller blade drive gear (57), an annular propeller blade connector support rib (56), an annular propeller blade connector (54), the propeller fan assembly blade (55), and the propeller fan assembly fairing (59). The double-row contra-rotating blade power gear (58) is fixed on the paddle fan rotating shaft (51) and consists of back-to-back double 45-degree helical gears, which are respectively engaged and connected with the double-row contra-rotating blade drive gear (57); the outer edges of the double-row contra-rotating blade drive gears (57) are respectively connected with two groups of the annular blade connector support ribs (56) distributed in a fan-shaped manner; the outer edges of the two groups of annular blade connector support ribs (56) are respectively connected with the inner edges of the two annular blade connectors (54); the outer edges of the two annular blade connectors (54) are respectively connected with two groups of contra-rotating paddle fan assembly blades (55). The paddle fan turbine group (14) rotates to transmit the rotational power to the double-row contra-rotating blade power gear (58) on the double-row contra-rotating blade driver (15) through the paddle fan rotating shaft (51). The double-row contra-rotating blade power gear (58) is used to vertically transmit the power to the double-row contra-rotating blade drive gear (57). The double-row contra-rotating blade drive gear (57) drives the paddle fan assembly blades (55) on the annular blade connectors (54) of the annular blade connector support ribs (56), driving the two groups of paddle fan assembly blades to rotate in left-handed and right-handed rotations respectively to cancel the reaction torque.

8. The power paddle fan aeroengine device with high-speed tail jet power generation as claimed in claim 1, wherein When the paddle fan assembly switches from horizontal power to vertical power, the first rotating cylinder (62) and the second rotating cylinder (66) rotate to form a 90-degree orientation respectively, and the air inlet (1) and the exhaust port (19) present a 90-degree angle to switch the horizontal power to vertical power.

9. The power paddle fan aero-engine device with high-speed tail jet power generation according to claim 8, characterized in that The front connecting flange (61) and the rear connecting flange (67) are respectively fixed at both ends of the engine body; the first rotating cylinder drive rack (610) and the second rotating cylinder drive rack (613) respectively drive the first rotating cylinder gear (63) and the third rotating cylinder gear (65) through the first rotating cylinder drive motor reducer (69) and the second rotating cylinder drive motor reducer (612).

10. The power paddle fan aeroengine device with high-speed tail jet power generation according to claim 1, characterized in that, The generator turbine (16) is installed on the front rotating shaft of the generator (17), and the generator (17) is placed in the tail fairing (18). The generator (17) is a high-performance generator.

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