WO2021164549A1 - Moteur d'aéronef à réaction entraîné par énergie électrique et aéronef associé - Google Patents

Moteur d'aéronef à réaction entraîné par énergie électrique et aéronef associé Download PDF

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Publication number
WO2021164549A1
WO2021164549A1 PCT/CN2021/075031 CN2021075031W WO2021164549A1 WO 2021164549 A1 WO2021164549 A1 WO 2021164549A1 CN 2021075031 W CN2021075031 W CN 2021075031W WO 2021164549 A1 WO2021164549 A1 WO 2021164549A1
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Prior art keywords
stage
jet
fan
wheel disc
engine
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PCT/CN2021/075031
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English (en)
Chinese (zh)
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王镇辉
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王镇辉
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Publication of WO2021164549A1 publication Critical patent/WO2021164549A1/fr

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan

Definitions

  • the invention belongs to the field of aeroengines, and relates to an electric energy-driven jet aeroengine and an aircraft.
  • the traditional fuel-fueled turbojet engine taking its most commonly used turbofan engine as an example, its power source is the internal energy released by the combustion of the fuel in the combustion chamber to heat the air and expand and accelerate. Due to the intrinsic limitation of the thermodynamic cycle, its thermal efficiency is compared. Low, pushing the turbine to drive the compressor and fan to do work through the central drive shaft. Of the energy and power consumed, about 60% is used to drive the compressor to compress air and about 20% is used to drive the fan to do work on the air. Only about 20% is finally used to heat the air to accelerate its discharge. The thermal efficiency of the existing turbofan jet engine can only reach 40%-46%.
  • the efficiency of the existing fuel turbojet engine is also closely related to the flight speed.
  • the efficiency of the turbojet engine is higher when flying at supersonic high speed, but the efficiency drops sharply when flying at subsonic low speed.
  • the fuel economy is very bad; while the turbofan engine with a large bypass ratio has good thermal efficiency in the subsonic range, and has good fuel economy, but it is difficult or impossible to fly at supersonic speed; a turbine with a small bypass ratio
  • the fan engine has partially improved its efficiency at subsonic speeds, but its efficiency under low-speed conditions is still low, and at the expense of some high-speed performance.
  • the existing technology In order to improve the efficiency of fuel jet engines in high, medium and low speed domains ranging from supersonic, high subsonic speeds to medium and low subsonic speeds, the existing technology has designed variable cycle jet engines for improvement, but its technical difficulty It is extremely large, and its reliability has significantly deteriorated. It is still a technology that a very few countries can master, and it has not been widely used. That is, the existing fuel turbojet engine cannot or is extremely difficult to achieve high efficiency at the same time in the high, medium, and low full speed range from supersonic, high subsonic speed to mid-low subsonic speed, resulting in a waste of energy. , The high cost of flight.
  • the purpose of the present invention is to provide a multi-mode, wide-speed range, and high-efficiency electric power-driven jet aero engine and aircraft.
  • the invention is based on the aerodynamics under subsonic and supersonic speed conditions, the principle of aviation propulsion and power, the principle of aeroengine, the principle of aviation vane machine, the principle of axial compressor, the principle of intake port under subsonic and supersonic speed and Exhaust duct principle, etc., based on full consideration of scientific feasibility and engineering feasibility, creatively designed a practical jet aero engine driven by electric energy to realize the aerodynamic power plant from supersonic, high subsonic to high subsonic speed.
  • the multi-mode, wide-speed range, and high-efficiency electric energy-driven jet aeroengine of the present invention adopts the following technical solutions:
  • An electric energy-driven jet aeroengine including a jet core engine; the jet core engine includes a compressor, the compressor is used to decelerate and boost the intake air flow, and also includes electric energy used to provide power to the compressor Drive mechanism.
  • the jet core engine further includes an accelerator arranged behind the compressor along the intake direction, and the accelerator is used for accelerating boost pressure or accelerating pressure maintaining or accelerating decompression of the intake air flow; the compressor, The front and back of the accelerator are connected in one piece;
  • the jet core aircraft also includes an electric power drive mechanism for providing power to the accelerator.
  • an outer duct is formed between the outer circumference of the jet core aircraft and the outer casing, and a single-stage or multi-stage fan is provided in the outer duct on the outer circumference of the jet core aircraft and/or at the front end of the jet core aircraft;
  • It also includes an electric power drive mechanism for providing power to the fan, and any stage fan is directly or drively connected to the electric power drive mechanism.
  • the jet core engine is provided with an intake duct system on the front side of the air intake direction, and an exhaust duct system is provided on the rear side.
  • the compressor includes single-stage or multi-stage elementary stages, and each elementary stage in the compressor is arranged one after the other along the axial flow direction of the intake air; any elementary stage includes movers arranged alternately back and forth. Stages and single-stage stators; any single-stage mover is directly or drivingly connected to the electric power drive mechanism.
  • the mover single stage in the air intake direction, is in front and the stator single stage is arranged alternately in sequence.
  • the compressor and the accelerator each include a single-stage or multi-stage elementary stage, and each elementary stage in the compressor and the accelerator is arranged one after another along the axial flow direction of the intake air; any elementary stage includes The mover single-stage and the static single-stage alternately arranged back and forth; any single-stage mover is directly or drivingly connected to the electric power drive mechanism.
  • the single stage of the mover includes a plurality of blades extending radially outward along the central axis, and the blade height edges of the plurality of blades are all connected to the outer wheel disc;
  • the electric energy driving mechanism is directly or in a transmission connection with the single-stage outer wheel disk of the mover for driving the outer wheel disk to move in its surrounding direction;
  • the single stator stage includes a plurality of blades extending radially outward along the central axis; the blade height edges of the plurality of blades in the single stator stage are all connected to the shell base, and/or, the plurality of blades in the single stator stage The root of the blade is connected to the middle base.
  • the roots of the multiple blades in the mover single stage are connected to the inner wheel disc; the mover single-stage inner wheel disc is rotatably nested or connected to the intermediate base.
  • the movable single stage in front and the stator single stage is arranged alternately in sequence.
  • stator single stage and the mover single stage are alternately arranged back and forth in sequence along the intake direction.
  • the fan includes a plurality of blades extending radially outward along a central axis, and the blade height edges of the plurality of blades in the fan are all connected to an outer disk;
  • the electric energy driving mechanism is directly or in a transmission connection with the outer wheel disk of the fan for driving the outer wheel disk to move in its surrounding direction.
  • the roots of a plurality of blades in the fan are connected to an inner disc; the inner disc of the fan is rotatably nested on the outer circumference of the jet core machine.
  • the electric power drive mechanism includes a plurality of rotors arranged on the outer wheel disc of each mover single stage or fan, and also includes a plurality of rotors arranged on the outer periphery of the outer wheel disc and on the side of the housing base far away from the outer wheel disc.
  • a stator, the positions of the stator and the rotor are arranged in one-to-one correspondence;
  • the rotor is an induction coil or a permanent magnet
  • An energized coil is surrounded on the stator, and the energized coil is used to pass an alternating current to drive the rotor, and then drive the outer wheel disk connected with the rotor to move around.
  • the electric power drive mechanism includes a plurality of rotors arranged on the inner wheel disc of each mover single stage or fan, and also includes a middle base arranged on the inner circumference of the inner disc and close to the side of the inner disc A plurality of stators, the stators and the rotors are arranged in a one-to-one correspondence;
  • the rotor is an induction coil or a permanent magnet
  • An energized coil surrounds the stator, and the energized coil is used to pass an alternating current to drive the rotor, and then drive the inner wheel disc connected to the rotor to move around.
  • the inclination angle of the plurality of blades in the fan can be adjusted.
  • the blade is hinged to the outer wheel disc at one end close to the outer wheel disc;
  • the blade is hinged on the outer edge end of the outer wheel disc connected with an angle connecting rod, the other end of the angle connecting rod away from the blade is hinged with the synchronous rotating ring, and the synchronous rotating ring is on one side of the outer wheel disc along the outer wheel disc.
  • the axis directions are arranged in parallel, and the synchronization swivel and the outer wheel disc are connected by a rotation synchronization mechanism;
  • the rotation synchronization mechanism includes a fixed block arranged on the outer wheel disc, and an adjustment block arranged on the synchronizing swivel.
  • the fixed block and the adjustment block are connected as a whole through the adjustable distance of the bolt assembly.
  • intake guide vanes are arranged between the intake duct system and the compressor; and exhaust rectifying vanes are arranged between the accelerator and the exhaust duct system.
  • an intake air flow adjustment mechanism is provided in the intake duct system and/or the inner duct air intake and/or the outer duct air intake for adjusting the ratio of the intake and exhaust flow of the inner and outer ducts.
  • the invention also discloses an aircraft, which includes the aforementioned electric energy-driven jet aeroengine.
  • the electrical energy-driven jet aeroengine provided by the present invention has a simple structure and is easy to maintain, and has high efficiency in a wide speed range from zero to subsonic low speed to supersonic high speed, thereby greatly reducing flight costs; and Electricity itself is a secondary energy or intermediate energy, which is very conducive to the conversion of various clean and environment-friendly energy sources, and can achieve low-carbon or carbon-free, green and environmentally friendly energy consumption and utilization.
  • the aero engine of the present invention adopts the independent drive, parallel and independent design of the external duct fan and the internal duct jet core machine which are different from the prior art, so it can realize the pure jet mode and pure fan
  • the operation of multiple modes of mode and its mixed mode adopts different applicable modes according to different flight speeds, so as to achieve high efficiency at the same time in the full speed range of high, medium and low speeds from supersonic, high subsonic to medium and low subsonic speeds.
  • the pure fan mode is used to achieve high efficiency at low speeds
  • the hybrid mode is used in the high subsonic phase to achieve economical cruising at medium speeds
  • the pure jet mode is used in the high-altitude supersonic cruise phase to ensure Thrust and high efficiency at supersonic high speed.
  • the single-stage independent drive of each level of the mover reduces the power output requirements of the single-stage mover, and greatly reduces the difficulty of design and manufacturing.
  • the total temperature and total pressure of the air flow continue to increase step by step, which is easy to accumulate into huge power, and it is easy to realize a large thrust engine.
  • the tip of the mover blade that is, the edge of the blade height
  • the root of the blade are respectively connected to the outer wheel disc and the inner wheel disc, because both ends are airtightly connected, and there is no gap in the middle, so there is no Tip loss
  • the blade root of the mover blade is fixed on the central drive shaft, there is a certain gap between the tip and the casing, which brings different tip loss, so it can achieve better than traditional fuel jet engine.
  • the single-stage mover of each stage in the present invention mainly adopts the edge drive mode design, which changes the traditional axis drive mode, so that the drive mechanism changes from being concentrated in the axis area to being dispersed to the edge area, which greatly reduces
  • the overall thickness of the single-stage drive structure of the stage mover enables the single-stage electric drive mechanism of each stage mover to be seamlessly installed into the engine casing without significantly increasing the thickness of the casing, which is suitable for the drive mechanism and the various stages of the mover.
  • the fundamental requirement of single-stage integration while having the advantages of large rotating torque, fast speed, high efficiency, simple structure, easy maintenance, high reliability, long life, low noise and so on.
  • the electric power drive structure is integrated with the single-stage movers of each stage.
  • the single-stage movers of all levels can be driven independently, easy to control and coordinated, which greatly expands the design working state range of the engine, and greatly improves the surge margin of the engine.
  • the electrical energy-driven jet aviation engine provided by the present invention also realizes complete integration and compatibility with other original structures, functions, and performances of traditional fuel jet engines, such as being fully compatible with the original subsonic or supersonic speed
  • the sonic inlet system, the tail nozzle, which is also the exhaust system, and most other mechanisms can basically be used directly, thus greatly reducing the amount of modification.
  • the rotation direction and inclination angle of the fan blades in the electric-power-driven jet aeroengine provided by the present invention are adjustable, which can realize the real "reverse thrust", which can greatly shorten the landing and roll distance of traditional fixed-wing aircraft, or
  • the vertical take-off and landing fixed-wing aircraft can realize functions such as air deceleration "brake” and reverse flight in the air. This is something that traditional fuel jet engines cannot truly achieve.
  • the maximum operating temperature of the system of the engine of the present invention is significantly lower than that of the traditional fuel jet engine by more than 600-800°C, which greatly reduces the strict requirements on materials, and also greatly reduces the requirements on the cooling system. Design and manufacture are difficult, and the manufacturing cost is greatly reduced.
  • the exhaust gas temperature is greatly reduced, on the one hand, the efficiency is greatly improved, and on the other hand, the technical realization difficulty of the adjustable tail nozzle and the vector type tail nozzle is greatly reduced, and the vector engine is easy to realize.
  • Fig. 1 is a schematic diagram of the basic structure of the jet core aircraft of the jet aeroengine driven by electric energy according to the present invention
  • FIG. 2 is a sectional view of the basic structure of the jet core aircraft of the jet aero engine driven by electric energy according to the present invention
  • 3a and 3b are schematic diagrams (including cross-sectional views) of a single-stage mover dual-driven by the outer ring and the inner ring of the jet core aircraft of the electric-powered jet aeroengine according to the present invention
  • 4a and 4b are structural schematic diagrams (including cross-sectional views) of the single-stage mover driven only by the outer ring of the jet core aircraft of the electric jet aeroengine according to the present invention
  • Fig. 5 is a schematic diagram (section view) of the single-stage stator of the jet core aircraft of the jet aeroengine driven by electric energy according to the present invention
  • FIG. 6 is a schematic diagram of the overall appearance of the jet core aircraft of the jet aero engine driven by electric energy according to the present invention
  • FIG. 7 is a schematic diagram 1 of the structural disassembly of the jet core aircraft of the jet aeroengine driven by electric energy according to the present invention
  • Fig. 8 is a second schematic diagram of the structural disassembly of the jet core aircraft of the jet aeroengine driven by electric energy according to the present invention.
  • Figure 9 is a basic structural section of the internal duct jet core engine plus external ducted fan of the electric energy-driven jet aero engine according to the present invention.
  • Figure 10 is a schematic diagram of the overall appearance of the internal duct jet core engine plus external ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • Figure 11 is a front view of the internal duct jet core engine plus external ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • Figure 12 is a rear view of the internal duct jet core engine plus external ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • Figure 13 is a front view of the basic structure of the fan rotor part of the internal duct jet core engine plus external ducted fan of the electric energy-driven jet aeroengine according to the present invention
  • Fig. 14 is a side view of the basic structure of the fan rotor part of the inner channel jet core engine plus the outer ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • Fig. 15 is the disassembly diagram 1 of the basic structure of the inner channel jet core engine plus the outer ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • 16 is the disassembly diagram 2 of the basic structure of the inner channel jet core engine plus the outer ducted fan of the electric energy-driven jet aeroengine according to the present invention
  • Fig. 17 is the disassembly diagram 3 of the basic structure of the inner channel jet core engine plus the outer ducted fan of the electric energy-driven jet aero-engine according to the present invention
  • 3-jet core machine 30-element level, 30a-stator single stage, 30b-mover single stage, 300-blade, 301-outer disc, 302-inner disc, 31-compressor, 32-accelerator ;
  • A-intake system B-exhaust system.
  • each figure only schematically shows the parts related to the technical solution of the present invention, and they do not necessarily represent the final actual structure of the product as a product.
  • an electric power-driven jet aero engine including a jet core aircraft;
  • the jet core aircraft includes two methods:
  • the jet core engine 3 includes a compressor 31 for decelerating and supercharging the intake air flow; the engine also includes an electric power driving mechanism 4 for providing power to the jet core engine 3. Therefore, the compressor is driven by the electric energy drive mechanism to decelerate and boost the intake air flow, so that the total temperature and total pressure of the air flow are gradually increased, and the exhaust speed is greater than the intake speed to generate the thrust required for flight.
  • the jet core engine 3 includes a compressor 31 and an accelerator 32 arranged in order along the intake direction.
  • the compressor 31 is used to counter the intake air flow. Decelerating and supercharging, the accelerator 32 is used to accelerate the supercharging/holding/depressurizing of the intake air flow; the compressor 31 and the accelerator 32 are connected in an integrated manner; Powered electric energy drive mechanism4. Therefore, the combination of the two basic structures of the compressor and the accelerator is used as the jet core engine 3 of the engine.
  • the total pressure is increased step by step, and finally the exhaust velocity is greater than the intake velocity to generate the thrust required for flight.
  • jet core 3 two different setting forms are provided for the jet core 3, and the combination of compressor, compressor and accelerator can be freely selected according to needs.
  • the jet core engine 3 is provided with an intake duct system A on the front side of the air intake direction, and an exhaust duct system B is provided on the rear side.
  • the electrical energy-driven jet aviation engine provided in this embodiment is different from the traditional fuel turbojet engine, in that the combustion chamber and turbine of the traditional fuel turbojet engine are eliminated; the power consumed by the 31 part of the front stage compressor is not driven by the turbine
  • the passive work is the active work from its own electric energy drive mechanism, which consumes electric energy.
  • the electric energy drive mechanism decelerates and pressurizes the higher-speed intake air flow, which is the efficient acceleration and increase of the downstream accelerator 32.
  • the compressed air flow creates conditions, and at the same time makes the total temperature and total pressure of the original intake air flow "store” first, and gradually increases the total temperature and total pressure by doing work on the intake air flow step by step; the latter part of the accelerator part , Through its own electric energy drive mechanism, accelerate and continue to pressurize the air flow after the previous compressor is pressurized and decelerated, so that the total temperature and pressure of the air flow continue to increase step by step; finally, the compressor and the accelerator do work
  • the air flow after the total temperature and total pressure has been greatly increased passes through the tail nozzle, which is the exhaust duct system, and is fully expanded and accelerated and then discharged into the atmosphere. During this air expansion and acceleration process, the reaction force causes the engine to generate thrust. That is, the basic working principle of the jet core aircraft in the present invention to generate jet propulsion.
  • Figs. 9-12 it is an electric energy-driven jet aeroengine.
  • the difference between this embodiment and the first embodiment is that the specific configuration of an external duct fan is added. .
  • an outer duct is formed between the outer circumference of the jet core 3 and the outer casing 1, and the outer duct on the outer circumference of the jet core is inside and/or jet
  • a single-stage or multi-stage fan 5 is installed at the front end of the core machine;
  • It also includes an electric power driving mechanism 4 for providing power to the fan 5, and any stage fan 5 is directly or drivingly connected to the electric power driving mechanism 4.
  • an external duct fan is added to the inner duct jet core machine, so that multiple modes of pure jet mode, pure fan mode and mixed modes can be realized.
  • the jet core engine 3 is provided with an intake duct system A on the front side of the air intake direction, and an exhaust duct system B is provided on the rear side.
  • a single-stage or multi-stage fan with an outer duct is added.
  • the fan is driven by electric energy to form an electric energy-driven jet fan engine, which greatly improves the thrust and propulsion efficiency of the engine.
  • the external duct fan and the internal duct jet core engine in this embodiment are no longer the traditional passive drive and front-to-rear tandem type, but independently drive and actively drive each other.
  • Parallel and parallel type fans can be arranged on any part of the outer casing 1 of the casing, including the front, middle, and rear ends.
  • the fan 5 is arranged in the middle of the outer casing 1 of the jet core machine) .
  • the exhaust flow rate ratio can be adjusted by changing the speed of the external duct fan, changing the speed of the compressor and/or the accelerator, etc., which will not be described in detail here; it can also be adjusted by the angle adjustable and openable and closable blades and gears.
  • the high-efficiency speed range is greatly widened, and at the same time, it can achieve the speed from zero to medium and low subsonic speeds (0 ⁇ 0.5 Mach), then to high subsonic speeds (0.7 ⁇ 0.9 Mach) to higher supersonic speeds (1.7 ⁇ Very high propulsion efficiency is achieved in the wide speed range of Mach 3 (Mach 0 to Mach 3).
  • the true "reverse thrust" of the engine can be realized very easily by changing the direction of rotation of the fan or changing the angle of the fan blades. These are unimaginable and impossible for traditional fuel jet engines. .
  • three high-efficiency working modes are realized: one is the pure fan mode, which mainly works in the low subsonic low-speed section, suitable for take-off and landing, etc. In the near-earth phase, this mode can also realize the true "reverse thrust" of the engine by changing the direction of fan rotation or changing the angle of the fan blades; the second is the mixed mode of jet and fan, which mainly works at mid-to-high subsonic speeds and spans.
  • the third is the pure jet mode, which mainly works in the higher supersonic speed domain, and is suitable for the high-altitude supersonic cruise phase.
  • the outer casing of the outer duct or the air intake system in this embodiment also includes auxiliary air intakes or auxiliary air intake devices, which are activated during low-speed phases such as take-off and landing and "reverse thrust" phases to increase intake air. Air volume to further improve the thrust size and efficiency at low speeds.
  • the shell base of the endotrache in this embodiment also includes an auxiliary air venting device, which is used to reduce the amount of intake air when flying at high speeds such as supersonic speed and the amount of air intake is excessive, so that the thrust generated by the engine is maintained within the required range .
  • the exhaust method of the inner duct and the outer duct in this embodiment is usually that the two are mixed and then discharged into the atmosphere, but it also includes the unusual situation where the two are discharged into the atmosphere separately.
  • the combination of the inner channel jet core machine and the outer channel fan forms a multi-mode, and the reason why high efficiency can be achieved in a wide speed range is as follows:
  • the thrust, propulsion efficiency, and total efficiency of aviation jet engines can be known as follows:
  • F is generated by the jet engine thrust level
  • C p is the air flow to the engine
  • V in is the intake of the engine speed
  • V out is the speed of the engine exhaust gas.
  • the intake speed is approximately equal to the airplane's flight speed (airspeed), which means that only when the engine's exhaust speed exceeds the airplane's flight speed can thrust be produced.
  • ⁇ p is the propulsion efficiency of the engine
  • V in the intake of the engine speed V out is the speed of the engine exhaust gas.
  • the above formula shows that the closer the engine exhaust speed is to the flight speed of the aircraft, the higher the propulsion efficiency.
  • ⁇ is the total efficiency
  • ⁇ e is the energy conversion efficiency.
  • thermal efficiency which is about 40 to 46%.
  • electric energy driven jet engine of the present invention it is electrical efficiency.
  • ⁇ p is the propulsion efficiency of the engine. This first shows that the energy conversion efficiency of electric-driven jet aeroengines is more than twice that of traditional fuel-fueled jet aeroengines. The former has much higher energy conversion efficiency than the latter. At the same time, this also shows that the decline in propulsion efficiency will also lead to a decline in overall efficiency, which in turn leads to more energy consumption, shorter voyages, higher costs, and a decline in fuel economy.
  • the combination of the inner duct jet core engine and the outer duct fan in this example, and the independent parallel parallel design of the inner and outer ducts can independently adjust the respective intake and exhaust flow rates of the inner and outer ducts.
  • the exhaust flow rate so that the inner duct high-speed airflow and the outer duct low-speed airflow can be mixed in any ratio, and can be adjusted to meet the thrust requirements, the closest flight speed, and any speed less than or equal to the maximum exhaust speed of the jet core aircraft.
  • the final exhaust flow rate mixed by the internal and external ducts can greatly improve the propulsion efficiency and achieve high propulsion efficiency in the full speed range, while non-traditional fuel jet engines can only achieve high propulsion efficiency at a certain speed.
  • the energy conversion efficiency of electric-powered jet aeroengines is twice or more higher than that of traditional fuel jet aeroengines; according to the above formula (3), this example can achieve a high total Efficiency greatly improves energy economy, greatly reduces flight costs, and greatly increases range. At the same time, it realizes the advantages of multi-mode, wide speed range and high efficiency that traditional fuel jet engines cannot or are extremely difficult to achieve. .
  • the present invention is an electric energy-driven jet aeroengine.
  • the difference between this embodiment and the first embodiment lies in the specific structure of the jet core aircraft 3, which is shown in conjunction with FIGS. 3 to 5.
  • the compressor 31 includes a single-stage or multi-stage elementary stage, and each of the compressors 31
  • the elementary stages 30 are arranged in sequence along the axial flow of the intake air; any elementary stage includes a single mover stage 30b and a single stator stage 30a that are alternately arranged back and forth; any single mover stage 30b is directly connected to the electric power drive mechanism. Or drive connection.
  • the compressor 31 and the accelerator 32 each include a single-stage or multi-stage elementary stage 30, and the compressor 31 and the accelerator 32 are Each elementary stage is arranged in sequence along the axial flow direction of the intake air; any elementary stage 30 includes a single mover stage 30b and a single stator stage 30a that are alternately arranged back and forth; any single mover stage 30b is associated with an electric power drive mechanism 4 Direct or drive connection;
  • the single mover stage 30b includes a plurality of blades 300 extending radially outward along the central axis 2, and the blade height edges of the plurality of blades 300 in the single mover stage 30b are all connected with an inner hollow outer disk 301;
  • the electric energy driving mechanism is directly or in a transmission connection with the outer wheel disk 301 of the mover single-stage 30b for driving the outer wheel disk 301 to move in its surrounding direction;
  • the stator single stage 30a includes a plurality of blades 300 extending radially outward along the central axis 2, and the blade height edges of the plurality of blades 300 in the stator single stage 30a are connected to the housing base, and/or the stator The roots of the multiple blades 300 in the single stage 30a are connected to the intermediate base.
  • the housing base and the intermediate base are connected and fixed by a supporting mechanism or other similar mechanisms in the prior art.
  • the roots of the plurality of blades 300 in the single mover stage 30b are connected to the hollow inner disk 302.
  • the inner wheel 302 of the mover single stage 30b is rotatably nested or connected to the middle base.
  • the blade 300 of the single-stage mover 30b is driven to rotate by an electric power drive mechanism; wherein the single-stage mover blade 300 is hermetically connected with both ends of the outer disc 301 and the inner disc 302, and the stator single-stage blade 300
  • the edge of the blade height is connected to the shell base, and the root is connected to the middle base. Both ends of the stator single-stage blade 300 are also airtightly connected. There are no gaps, so there is no tip loss.
  • -Type engine with higher supercharging ratio and higher efficiency.
  • the blades 300 of the stator single-stage 30a are peeled from the housing base.
  • the blade height of the stator single-stage blade 300 is It is connected to the housing base, that is, the stator single stage 30a is integrated with the outer housing.
  • the electric power drive mechanism 4 includes a plurality of rotors 40a arranged on the outer wheel disk 301 of each mover single stage 30b, and the plurality of rotors 40a can be evenly distributed on the outer side of the outer wheel disk 301, It also includes a plurality of stators 41a arranged on the outer circumference of the outer wheel disc 301 and on the housing base on the side away from the outer wheel disc 301, and the positions of the stator 41a and the rotor 40a are arranged in one-to-one correspondence;
  • the rotor 40a is an induction coil or a permanent magnet.
  • the magnetic properties of adjacent rotors 40a are opposite.
  • two or more adjacent rotors 40a can also be used as a group.
  • the rotor 40a is magnetically opposite.
  • the stator 41a surrounds an energized coil (not shown in the figure), and the energized coil can pass an alternating current to drive the rotor 40a, and then drive the outer wheel disk 301 connected to the rotor 40a to move around; when the rotor 40a is a permanent magnet
  • the electric energy driving mechanism 4 can drive the outer wheel disk 301 to move in its surrounding direction in the driving mode of a DC motor.
  • the principle of the DC motor will not be repeated here; when the rotor 40a is an induction coil, the electric energy driving mechanism 4 can be asynchronous AC
  • the driving mode of the motor drives the outer wheel disk 301 to move in its surrounding direction, and the principle of the asynchronous AC motor will not be repeated here.
  • the outer wheel disk 301 at the edge of the single-stage 30b blade of the mover is driven.
  • the blade 300 is driven to rotate, thus forming an edge drive mode, which changes the traditional axis drive mode, so that the drive mechanism is changed from being concentrated in the axis area to being dispersed to the edge area, which greatly reduces the single stage 30b of each mover.
  • the overall thickness of the driving mechanism makes it possible for the electric power driving mechanism 4 of the single-stage 30b of each mover to be seamlessly fitted into the housing base (that is, the receiver base) without significantly increasing the thickness of the housing, so this solution It meets the fundamental requirements of the integration of the drive mechanism and the single-stage 30b of the movers at all levels, and has the advantages of large rotating torque, fast speed, high efficiency, simple structure, easy maintenance, high reliability, long life, and low noise.
  • the mover single stage 30b and the stator single stage 30a are fixed on the central shaft and the casing, specifically, the two ends of the stator single stage 30a are respectively fixed on the housing base and the middle base, and the mover The single stage 30b is rotatably nested or connected to the middle base of the jet core machine, so that the mover single stage 30b and the stator single stage 30a are alternately arranged back and forth at a certain interval.
  • the electric power drive mechanism 4 further includes a plurality of rotors 42a arranged on the inner disc 302 of each mover single stage 30b far away from the blades, and also includes a plurality of rotors 42a arranged on the inner circumference of the inner disc 302 and close to the inner circumference of the inner disc 302.
  • a plurality of stators 43a on the middle base on one side of the inner wheel disk 302, the stators 43a and the rotor 42a are arranged in a one-to-one correspondence;
  • the rotor 42a is an induction coil or a permanent magnet.
  • the magnetic properties of adjacent rotors 42a are opposite. Specifically, two or more adjacent rotors 42a can also be used as a group.
  • the rotor 42a has opposite magnetic properties;
  • the stator 43a is surrounded by an energized coil (not shown in the figure), and the energized coil is used to pass an alternating current to drive the rotor 42a, and then drive the inner wheel disk 302 connected to the rotor 42a to move around; when the rotor When 42a is a permanent magnet, the electric energy driving mechanism 4 can drive the inner wheel 302 to move in its surrounding direction in the driving mode of a DC motor.
  • the principle of the DC motor will not be repeated here; when the rotor 42a is an induction coil, it is driven by electric energy
  • the mechanism 4 can be driven by an asynchronous AC motor to drive the inner wheel 302 to move in its surrounding direction. The principle of the asynchronous AC motor will not be repeated here.
  • the electric power driving mechanism 4 is connected to the inner wheel disk 302 of the mover single-stage 30b for driving the inner wheel disk 302 to move in its surrounding direction.
  • the inner ring drive (or inner wheel drive) of the mover single stage 30b can also be performed at the same time. That is, the inner wheel 302 is driven to move in its surrounding direction.
  • the inner wheel disk 302 rotates in its own ring direction after being driven by the electric power driving mechanism 4, and at the same time drives the blade 300 to rotate when rotating.
  • a separate inner ring driving mode can also be used to realize the rotation of the blade 300 to generate airflow.
  • each mover single stage 30b can be configured independently to drive each mover single stage 30b independently; or, there are also the following situations: corresponding to several mover stages
  • the stages 30b are combined and configured by the same electric power driving mechanism 4, so that the electric power driving mechanism 4 is synchronously drivingly connected with several moving sub-stages 30b, and driving several moving sub-single stages 30b in combination.
  • the moving single stage 30b is in front and the stator single stage 30a is alternately arranged in the air intake direction.
  • the air flow cross section of each elementary stage 30 in the compressor 31 converges step by step.
  • the air flow cross section refers to the cross section of the air flow channel perpendicular to the axial flow direction.
  • the blades of the single stage 30b of each mover perform work on the passing air, accelerate it, increase its dynamic pressure, and increase the total temperature and total pressure of the airflow.
  • the stator blades of each stage in the compressor play the role of rectifier and expansion and boost, so that the dynamic pressure of the gas increased by the single-stage blades of the mover is converted into static pressure, and at the same time, the airflow speed is slowed down; specifically, in the compressor 31
  • the air flow cross section converges step by step in the following three forms and any combination thereof: a.
  • the outer diameter of the ducted air flow section does not change step by step, and the inner diameter is gradually larger.
  • the stator single stage 30a is in front and the mover single stage 30b is alternately arranged in the air intake direction. More preferably, the airflow cross section of each elementary stage 30 in the accelerator 32 expands step by step.
  • the blades of each stator single-stage 30a in the accelerator 32 play the role of rectifier and expansion and pressurization.
  • the front-stage airflow expands and pressurizes and decelerates, creating better conditions for the next-stage mover single-stage blades to accelerate the airflow more efficiently.
  • the speed decreases
  • the dynamic pressure decreases
  • the static pressure increases.
  • the dynamic pressure is converted to static pressure, and the total temperature and total pressure remain basically unchanged.
  • the single-stage blades of the stage mover act to perform work on the passing air, accelerate it, increase its dynamic pressure, and make the total temperature and total pressure of the air flow continue to increase step by step.
  • the stator single stage 30a is in the front, and the mover single stage 30b is alternately arranged at the rear.
  • the first expansion pressurizes and decelerates, and the latter accelerates to increase the dynamic pressure, so that the mover single stage 30b is more efficient for low-speed airflow.
  • the air flow cross section in the accelerator 32 is expanded step by step in the following three forms and any combination thereof: a.
  • the inner diameter of the duct air flow section does not change step by step, and the outer diameter increases step by step; b. the duct air flow
  • the inner diameter of the section becomes smaller step by step, and the outer diameter does not change step by step;
  • c The inner diameter of the ducted air flow section gradually becomes smaller and the outer diameter becomes larger step by step.
  • the arrangement of the mover single stage 30b in the front and the stator single stage 30a in the back can also be used; the air flow cross section of each elementary stage in the accelerator can also be changed step by step. form.
  • the inclination angle of the blade 300 of the single mover stage 30b and/or the single stage 30a of the stator 30 of any one of the compressor 31 and the accelerator 32 can be adjusted.
  • the fan 5 includes a fan that extends radially outward along the central axis 2.
  • Two blades 500, the blade height edges of the plurality of blades 500 are all connected to the hollow outer wheel disc 501;
  • the electric power driving mechanism 4 is connected to the outer wheel disk 501 of the fan for driving the outer wheel disk 501 to move in its surrounding direction, and the inner wheel disk 502 of the fan is rotatably nested on the outer circumference of the jet core machine 3.
  • the electric power driving mechanism 4 includes a plurality of rotors 40b arranged on the outer disc 501 of each stage of the fan 5, the plurality of rotors 40b can be evenly distributed on the outer side of the outer disc 501, and further includes a plurality of rotors 40b arranged on the outer disc 501 A plurality of stators 41b on the outer periphery of the housing base on the side away from the outer wheel disc 501, and the positions of the stators 41b and the rotor 40b are arranged in a one-to-one correspondence;
  • the rotor 40b is an induction coil or a permanent magnet.
  • the magnetic properties of adjacent rotors 40b are opposite.
  • two or more adjacent rotors 40b can also be used as a group, and each adjacent group of The rotor 40b is magnetically opposite.
  • the stator 41b surrounds an energized coil (not shown in the figure), and the energized coil can be supplied with alternating current to drive the rotor 40b, and then drive the outer wheel disk 501 connected to the rotor 40b to move around; when the rotor 40b is a permanent magnet , The electric energy driving mechanism 4 can drive the outer wheel disk 501 to move in its surrounding direction in the driving mode of a DC motor.
  • the principle of the DC motor will not be repeated here; when the rotor 40b is an induction coil, the electric energy driving mechanism 4 can be asynchronous AC
  • the driving mode of the electric motor drives the outer wheel disk 501 to move in its surrounding direction, and the principle of the asynchronous AC motor will not be repeated here.
  • the outer wheel disk 501 at the blade height edge of the fan blade is driven.
  • the blade 500 is driven to rotate at time, so an edge drive mode is formed, that is, the outer ring drive of the fan 5 is realized.
  • the roots of a plurality of blades are connected to an inner hollow disc 502; the inner disc 502 of the fan is rotatably nested on the outer circumference of the jet core.
  • the electric power drive mechanism 4 further includes a plurality of rotors 42b arranged on the inner wheel disc 502 of each stage of the fan 5, and also includes a plurality of rotors 42b arranged on the inner circumference of the inner wheel disc 502 and a side close to the inner disc 502
  • a plurality of stators 43b on the middle base of the, the stators 43b and the rotor 42b are arranged in a one-to-one correspondence;
  • the rotor 42b is an induction coil or a permanent magnet.
  • the magnetic properties of adjacent rotors 42b are opposite. Specifically, two or more adjacent rotors 42b can also be used as a group.
  • the rotor 42b has opposite magnetic properties;
  • the stator 43b is surrounded by an energized coil (not shown in the figure), and the energized coil is used to pass an alternating current to drive the rotor 42b, and then drive the inner wheel disk 502 connected to the rotor 42b to move around; when the rotor When 42b is a permanent magnet, the electric power driving mechanism 4 can drive 502 to move in its surrounding direction in the driving mode of a DC motor.
  • the principle of the DC motor will not be repeated here; when the rotor 42b is an induction coil, the electric power driving mechanism 4 can The driving mode of an asynchronous AC motor is used to drive the inner wheel 502 to move in its surrounding direction. The principle of the asynchronous AC motor will not be repeated here.
  • the electric energy driving mechanism is connected with the inner wheel 502 of the mover single stage 30b to drive the inner wheel 502 to move in its surrounding direction.
  • the fan in addition to the aforementioned method of driving the fan in the outer ring, that is, the outer wheel 501, the fan can also be driven in the inner ring at the same time, that is, the inner wheel 502 is driven to move in its surrounding direction.
  • the inner roulette 502 rotates in its own ring direction after being driven by the electric power driving mechanism 4, and at the same time drives the blade 500 to rotate when it rotates.
  • a separate inner ring driving method can also be used to realize the rotation of the blade 500 to generate airflow.
  • the inclination angle of the plurality of blades 500 in the fan 5 can be adjusted.
  • the specific structure of the blades in the fan 5 to realize the adjustable inclination angle is as follows:
  • the blade 500 is hinged to the outer wheel disk 501 at one end close to the outer wheel disk 501; specifically, a plurality of rotating rods 50 are connected to the inner side of the outer wheel disk 501, and the rotating rods 50 are arranged on the outer wheel disk 501 in the radial direction of the outer wheel disk 501.
  • a plurality of rotating rods 50 are connected to the inner disc 502
  • the blades are sleeved on the rotating rod 50
  • the blades 500 are rotatably connected to the rotating rod 50 along the axial direction of the rotating rod 50, thereby realizing that the blade 500 is hinged to Outer roulette 501;
  • the blade 500 is hinged with an angle link 51 on the outer edge end connected to the closed outer 501, and the other end of the angle link 50 away from the blade 500 is hinged with a synchronization swivel 52, and the synchronization swivel 52 is on the outer wheel.
  • One side of the disk 501 is arranged in parallel along the axial direction of the outer wheel disk, and the synchronization swivel 52 and the outer wheel disk 501 are connected by a rotation synchronization mechanism;
  • the rotation synchronization mechanism includes a fixed block 53 arranged on the outer wheel disc 501 and an adjustment block 54 arranged on the synchronizing swivel 52.
  • the fixed block 53 and the adjustment block 54 are connected in an adjustable distance through a bolt assembly. .
  • the distance between the fixing block 53 and the adjusting block 54 is adjusted by the bolt assembly, so that the distance between the outer wheel disc and the synchronous rotating ring is changed, so that the hinged blade 500 can be driven to rotate along the angle link 51
  • the rod 50 rotates, thereby changing the inclination angle or the rotation direction of the outer edge end of the blade 500.
  • the specific structure for adjusting the inclination angle of the blade 500 includes but is not limited to the above-mentioned solutions.
  • the flow rate of the outer duct can be adjusted by adjusting the fan speed, thereby changing the magnitude of the thrust; the rotation direction of the fan 5 can be changed to realize the reversal of the thrust direction, that is, "reverse thrust” ".
  • the flow rate of the outer duct can be adjusted by adjusting the speed of the fan 5 and the blade angle of the fan 5, thereby changing the thrust; the rotation direction of the fan 5 can be changed or the fan 5 can be changed.
  • the way of changing the blade angle is not affected by the inertia, and the response is faster for changing the flow velocity, the magnitude and the way of the thrust.
  • the function of the central shaft 2 in the above-mentioned embodiment is to fix the structural components such as the mover single-stage 30b, the static single-stage 30a, and the electric power drive mechanism.
  • the central shaft 2 can be fixed or Can be set in the form of rotation.
  • FIG. 1 it is an electric power-driven jet aeroengine.
  • the air inlet system and/or the internal passage enter
  • An intake air flow adjustment mechanism is arranged in the air and/or the outer duct to adjust the ratio of the intake and exhaust flow of the inner and outer ducts.
  • the intake air flow adjustment mechanism in this embodiment may adopt an angle adjustable and openable intake guide vane or baffle; or adopt a multi-fish scale adjustment mechanism similar to an adjustable tail nozzle.
  • inlet guide vanes are arranged at the front end of the inner duct inlet and the outer duct inlet.
  • the inclination angle of the guide vanes can be adjusted and can be opened and closed, so as to change the intake and exhaust into the inner duct and the outer duct. flow.
  • the aforementioned air flow adjustment mechanism is a structure commonly used in the prior art, and of course, other flow adjustment structures that can realize the flow ratio of the inner and outer ducts can also be used.
  • the intake air flow adjustment mechanism in this embodiment can be arranged at multiple positions in the casing.
  • the openable and closable guide vanes can be reused at the outer duct, and it can also be used at the inlet lip of the inner duct.
  • the adjustable baffle in the supersonic inlet can also be used to adjust the air flow of the inner duct and the outer duct.
  • the intake system in this embodiment is divided into two categories: subsonic intake and supersonic intake.
  • the subsonic inlet or supersonic inlet of traditional jet aircraft is used.
  • the tail nozzle exhaust system
  • the tail nozzle adopts a convergent tail nozzle, including a fixed convergent tail Nozzle and adjustable convergent tail nozzle.
  • the designed maximum flight speed is higher supersonic speed (>1.5 ⁇ 1.7 Mach)
  • the tail nozzle adopts the fixed type first convergence and then expansion type tail nozzle and the adjustable type first convergence and then expansion type tail nozzle.
  • the tail nozzle uses a vector nozzle, it becomes a vector jet engine.
  • the invention also discloses an aircraft, which includes the electric energy-driven jet aero engine of any of the foregoing embodiments.

Abstract

La présente invention concerne un moteur d'aéronef à réaction entraîné par énergie électrique, le moteur comprenant un moteur à noyau à réaction (3) comprenant un compresseur de gaz (31) et un accélérateur (32) disposés successivement dans une direction d'entrée de gaz, le compresseur de gaz (31) étant utilisé pour la décélération et la mise sous pression de l'écoulement d'air d'entrée, l'accélérateur (32) étant utilisé pour l'accélération et la mise sous pression/le maintien de la pression/la mise hors pression de l'écoulement d'air d'entrée, et le compresseur de gaz (31) et l'accélérateur (32) étant reliés d'un seul tenant dans une direction avant-arrière ; et comprenant en outre un mécanisme d'entraînement par énergie électrique (4) permettant d'alimenter en énergie le compresseur de gaz (31) et l'accélérateur (32). De plus, un ventilateur (5) à étage unique ou à étages multiples est disposé dans un conduit externe au niveau de la périphérie externe du moteur à noyau à réaction (3) ; un étage quelconque du ventilateur (5) est en liaison directe ou de transmission avec le mécanisme d'entraînement par énergie électrique (4). La conception relativement indépendante du ventilateur dans le conduit externe, et du moteur à noyau à réaction dans le conduit interne, permet d'obtenir un fonctionnement en mode purement réaction, en mode purement ventilateur et en mode mixte du mode purement réaction et du mode purement ventilateur, lesdits modes étant respectivement appropriés pour des vitesses de vol élevées, moyennes et faibles, afin d'obtenir un haut rendement dans un domaine à plein régime. Par conséquent, le moteur d'aéronef à réaction entraîné par énergie électrique présente les avantages d'un domaine à modes multiples et à vitesses variables et d'un haut rendement. La présente invention concerne également un aéronef comprenant le moteur d'aéronef à réaction entraîné par énergie électrique.
PCT/CN2021/075031 2020-02-17 2021-02-03 Moteur d'aéronef à réaction entraîné par énergie électrique et aéronef associé WO2021164549A1 (fr)

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CN114973902A (zh) * 2022-04-14 2022-08-30 西北工业大学 一种教学用航空发动机低压涡轮模型及装配方法
CN117235891A (zh) * 2023-09-27 2023-12-15 南京航空航天大学 一种并联多模块宽速域鼓包可调进气道设计方法

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TWI776218B (zh) * 2020-08-31 2022-09-01 台灣晉陞太空股份有限公司 火箭推進器的電動機及燃料動力混合系統
CN112360815B (zh) * 2020-11-10 2022-05-24 沈观清 用于多级涵道风扇的可调节定片机构及该机构的控制系统
WO2022185164A1 (fr) * 2021-03-03 2022-09-09 Whisper Aero Inc. Ventilateur de propulseur et système d'entraînement
CN113060290A (zh) * 2021-04-29 2021-07-02 陕西北斗金箭航空科技有限公司 一种电动推进器
CN114103572B (zh) * 2021-12-30 2023-08-22 北京国家新能源汽车技术创新中心有限公司 一种双涵道混合动力装置、飞行汽车以及控制方法
CN114458613B (zh) * 2022-02-17 2022-10-28 集美大学 一种超音速轴流压气机的流量调节方法及装置

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