CN111237084A - Electric-driven jet aircraft engine and aircraft - Google Patents

Electric-driven jet aircraft engine and aircraft Download PDF

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Publication number
CN111237084A
CN111237084A CN202010095452.8A CN202010095452A CN111237084A CN 111237084 A CN111237084 A CN 111237084A CN 202010095452 A CN202010095452 A CN 202010095452A CN 111237084 A CN111237084 A CN 111237084A
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China
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stage
wheel disc
jet
fan
electric energy
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CN202010095452.8A
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Chinese (zh)
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王镇辉
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Individual
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Priority to CN202010095452.8A priority Critical patent/CN111237084A/en
Publication of CN111237084A publication Critical patent/CN111237084A/en
Priority to PCT/CN2021/075031 priority patent/WO2021164549A1/en
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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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses an electric energy driven jet aircraft engine and an aircraft, wherein the engine comprises a jet core engine; the air compressor is used for decelerating and pressurizing the inlet air flow, and the accelerator is used for accelerating and pressurizing/maintaining pressure/reducing the inlet air flow; the compressor and the accelerator are integrally connected front and back; the electric energy driving mechanism is used for providing power for the air compressor and the accelerator. In addition, a single-stage or multi-stage fan is arranged in an outer duct at the periphery of the jet core machine; any stage of fan is directly or in transmission connection with the electric energy driving mechanism. Due to the relatively independent design of the outer ducted fan and the inner ducted jet core machine, the operation of multiple modes of a pure jet mode, a pure fan mode and a mixed mode can be realized, and the jet core machine is respectively suitable for high, medium and low flight speeds to realize high efficiency in a full speed domain, so that the electric-driven jet aircraft engine has the advantages of multiple modes, wide speed domain and high efficiency.

Description

Electric-driven jet aircraft engine and aircraft
Technical Field
The invention belongs to the field of aircraft engines, and relates to an electric-driven jet aircraft engine and an aircraft.
Background
Conventional jet aircraft power plants use primarily fuel-fired turbojet engines. The traditional fuel turbine jet engine is limited by the essence of thermodynamic cycle, has the inherent defects of low heat efficiency, carbon emission, atmospheric pollution, high noise, high manufacturing difficulty, high cost and the like, and in the 21 st century of pursuing energy efficient utilization, paying attention to environmental friendliness and paying attention to the cost of traffic economy, vehicles are increasingly motorized, and a practical design scheme or product of an electric energy-driven jet engine does not appear in the world.
The conventional fuel oil turbojet engine, taking the most commonly used turbofan engine as an example, has a power source that the internal energy released by combustion of fuel in a combustion chamber heats air to expand and accelerate, is limited by the nature of thermodynamic cycle, has low thermal efficiency, pushes a turbine to drive a compressor and a fan to do work through a central transmission shaft, and in the energy effectively utilized and consumed power, about 60% of the energy is used for driving the compressor to compress air to do work, about 20% of the energy is used for driving the fan to do work on air, and only about 20% of the energy is finally used for heating air to accelerate the air to be discharged. The highest thermal efficiency of the existing turbofan jet engine can only reach 40% -46%.
Moreover, the efficiency of the existing fuel turbojet engine is also greatly related to the flight speed, for example, the efficiency of the turbojet engine is higher when the turbojet engine flies at a supersonic speed at a high speed, and the efficiency of the turbojet engine is sharply reduced when the turbojet engine flies at a subsonic speed at a low speed, so that the fuel economy is very poor; the turbofan engine with a large bypass ratio has good thermal efficiency in a subsonic stage and good fuel economy, but is difficult or impossible to carry out supersonic flight; turbofan engines with small bypass ratios partially improve their efficiency at subsonic speeds, but are also less efficient at low speeds, at the expense of partially high speed performance. In order to improve the efficiency of a fuel oil jet engine in high, medium and low different speed domains from supersonic speed, high subsonic speed to medium and low subsonic speed, a variable cycle jet engine is designed and improved in the prior art, but the technical difficulty is extremely high, the reliability is obviously poor, the variable cycle jet engine is still a technology which can be mastered by few countries, and the variable cycle jet engine is not widely applied. That is, the conventional fuel turbojet engine cannot or is very difficult to achieve high efficiency in the full speed range of high, medium and low from supersonic speed, high subsonic speed to medium and low subsonic speed, which results in energy waste and high flight cost.
Therefore, there is a strong need in the art for a multi-mode, wide speed range, high efficiency, electrically powered jet aircraft engine.
Disclosure of Invention
In view of the above-mentioned deficiencies of the prior art, it is an object of the present invention to provide a multimode, wide speed range, high efficiency electrically driven jet aircraft engine and aircraft. The invention is based on the air thermal dynamics, aviation propulsion and power principles, aviation engine principles, aviation vane machine principles, axial flow compressor principles, air inlet channel principles and exhaust channel principles under subsonic and supersonic speed conditions, and the like, on the basis of fully considering scientific feasibility and engineering feasibility, the practical jet aeroengine driven by electric energy is creatively designed, so as to realize high-efficiency full electric propulsion of the aviation power device under the condition of full speed range from supersonic speed, high subsonic speed to medium-low subsonic speed, and further, the construction of the electric-driven jet plane is realized, so that in the future which is not too far away, people can take the electric-driven jet plane to carry out long-distance, high-efficiency, time-saving, cost-saving and low-carbon or carbon-free, low-noise and environment-friendly flight to realize daily traffic.
The invention relates to a multi-mode, wide-speed-range and high-efficiency electric-driven jet aircraft engine, which adopts the following technical scheme:
an electric-driven jet aircraft engine comprises a jet core engine; the jet core machine comprises a gas compressor, wherein the gas compressor is used for decelerating and pressurizing inlet flow and also comprises an electric energy driving mechanism used for providing power for the gas compressor.
Preferably, the jet core machine further comprises an accelerator arranged behind the gas compressor along the gas inlet direction, and the accelerator is used for accelerating and pressurizing or accelerating and maintaining pressure or accelerating and decompressing the gas inlet flow; the compressor and the accelerator are integrally connected front and back;
the jet core machine further comprises an electric energy driving mechanism for providing power for the accelerator.
Preferably, an outer duct is formed between the periphery of the jet core machine and the outer shell, and a single-stage or multi-stage fan is arranged in the outer duct at the periphery of the jet core machine and/or at the front end of the jet core machine;
the fan motor also comprises an electric energy driving mechanism used for providing power for the fan, and any stage of fan is directly or in transmission connection with the electric energy driving mechanism.
Preferably, the front side of the jet core machine along the air inlet direction is provided with an air inlet channel system, and the rear side is provided with an air outlet channel system.
Preferably, the compressor comprises a single-stage or multi-stage element stage, and each element stage in the compressor is sequentially arranged in the front and back direction along the axial flow direction of the air inlet; any element level comprises a rotor single level and a stator single level which are alternately arranged front and back; and any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism.
Furthermore, the rotor single-stage is arranged in front of the stator single-stage in the air compressor along the air inlet direction, and the stator single-stage is arranged in back of the air compressor in turn.
Furthermore, the airflow cross sections of each elementary stage in the compressor converge step by step.
Preferably, the gas compressor and the accelerator both comprise single-stage or multi-stage element stages, and the element stages in the gas compressor and the accelerator are sequentially arranged in the front-back direction along the axial flow direction of the gas inlet; any element level comprises a rotor single level and a stator single level which are alternately arranged front and back; and any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism.
Further, the rotor single stage comprises a plurality of blades extending outwards in the radial direction of the central shaft, and the edges of the blade heights of the plurality of blades are connected with an outer wheel disc;
the electric energy driving mechanism is directly or in transmission connection with the rotor single-stage outer wheel disc and is used for driving the outer wheel disc to move along the surrounding direction of the outer wheel disc;
the stator single stage includes a plurality of vanes extending radially outward along a central axis; the blade height edges of a plurality of blades in the stator single stage are connected with the shell base, and/or the roots of the blades in the stator single stage are connected with the middle base.
Furthermore, the roots of a plurality of blades in the rotor single stage are connected with the inner wheel disc; the rotor single-stage inner wheel disc is rotatably nested or connected to the middle base.
Furthermore, the rotor single-stage is arranged in front of the stator single-stage in the air compressor along the air inlet direction, and the stator single-stage is arranged in back of the air compressor in turn.
Furthermore, the airflow cross sections of each elementary stage in the compressor converge step by step.
Furthermore, the stator single-stage and the rotor single-stage in the accelerator are sequentially and alternately arranged back and forth along the air inlet direction.
Furthermore, the airflow section of each element stage in the accelerator is gradually expanded or unchanged.
Further, the fan comprises a plurality of blades extending outwards along the radial direction of the central shaft, and the high edges of the blades in the fan are connected with the outer wheel disc;
the electric energy driving mechanism is directly or in transmission connection with an outer wheel disc of the fan and is used for driving the outer wheel disc to move along the surrounding direction of the outer wheel disc.
Further, the roots of a plurality of blades in the fan are connected with the inner wheel disc; the inner wheel disc of the fan can be rotatably nested on the periphery of the jet core machine.
Furthermore, the electric energy driving mechanism comprises a plurality of rotors arranged on an outer wheel disc of each stage of mover single stage or fan, and a plurality of stators arranged on the periphery of the outer wheel disc and on a shell base far away from one side of the outer wheel disc, wherein the stators and the rotors are arranged in one-to-one correspondence;
the rotor is an induction coil or a permanent magnet;
the stator is surrounded by an electrified coil, and the electrified coil is used for introducing alternating current to drive the rotor and then drive an outer wheel disc connected with the rotor to move in a surrounding manner.
Furthermore, the electric energy driving mechanism comprises a plurality of rotors arranged on an inner wheel disc of each stage of mover single stage or fan, and a plurality of stators arranged on the inner circumference of the inner wheel disc and on a middle base close to one side of the inner wheel disc, wherein the stators and the rotors are arranged in one-to-one correspondence;
the rotor is an induction coil or a permanent magnet;
an electrified coil is arranged on the stator in a surrounding mode and used for being electrified with alternating current to drive the rotor and then drive an inner wheel disc connected with the rotor to move in a surrounding mode.
Further, the inclination angle of the plurality of blades in the fan is adjustable.
Furthermore, one end of each blade close to the outer wheel disc is hinged to the outer wheel disc;
the blade is hinged with an angle connecting rod on the end part of the outer edge connected with the outer wheel disc, the other end of the angle connecting rod, which is far away from the blade, is hinged with a synchronous rotating ring, the synchronous rotating ring is arranged on one side of the outer wheel disc in parallel along the axial direction of the outer wheel disc, and the synchronous rotating ring is connected with the outer wheel disc through a rotating synchronous mechanism;
the rotating synchronous mechanism comprises a fixed block arranged on the outer wheel disc and an adjusting block arranged on the synchronous rotating ring, and the fixed block and the adjusting block are connected into a whole in a distance-adjustable mode through a bolt assembly.
Preferably, an air inlet guide vane is arranged between the air inlet system and the air compressor; and an exhaust rectifying blade is arranged between the accelerator and the exhaust passage system.
Preferably, an intake flow adjusting mechanism is arranged at the intake position of the inner duct and/or the intake position of the outer duct in the intake passage system and/or used for adjusting the intake and exhaust flow ratio of the inner duct and the outer duct.
The invention also discloses an aircraft which comprises the electric energy driven jet aircraft engine.
The invention has at least the following significant advantages:
1) the electric energy driving jet aircraft engine provided by the invention has the advantages that the structure is simple, the maintenance is easy, the high efficiency is realized in a wide speed range from zero speed to subsonic low-speed section to supersonic high-speed section, and the like, so that the flying cost is greatly reduced; and the electric energy is secondary energy or intermediate energy, so that the conversion of various clean environment-friendly energy sources is facilitated, and low-carbon or carbon-free and environment-friendly energy consumption and utilization can be realized.
2) The aero-engine of the invention adopts the design of independent driving, parallel connection and mutual independence of the outer duct fan and the inner duct jet core machine different from the prior art, thus realizing the operation of various modes of a pure jet mode, a pure fan mode and a mixed mode thereof, and adopting different correspondingly applicable modes according to different flight speeds, thereby simultaneously realizing high efficiency in a full speed range from supersonic speed, high subsonic speed to different speeds of high, medium and low subsonic speeds. A pure fan mode is used in the taking-off and landing stage, so that high efficiency at low speed is realized; a mixed mode is adopted at a high subsonic speed stage, and high economical cruising at a medium speed is realized; and a pure jet mode is used in the high-altitude supersonic cruise stage, so that the thrust and the high efficiency of the supersonic speed at high speed are ensured. The high efficiency is realized, and the pure fan mode is used in the taking-off and landing stage, and the part of the jet core machine can be completely closed, so that the noise caused by the blades rotating at high speed and the sound of air flow above the subsonic speed and atmospheric friction are completely eliminated, the noise is greatly reduced, the noise pollution is avoided, the disturbance to the citizen is avoided, and the comprehensive popularization of the airplane is facilitated.
3) In the aircraft engine, the fan and the jet core engine are respectively and independently driven, are in parallel connection and are relatively independent, so that the air flows of the inner duct and the outer duct are mutually independent, the respective air inlet and exhaust flow and the exhaust flow rate of the two ducts can be properly adjusted and proportioned according to the flight speed, and the functions similar to that of a fuel variable-cycle jet engine can be easily realized, so that the efficiency in a wide speed range from zero speed to subsonic speed and supersonic speed is further remarkably improved.
4) According to the invention, the rotors of all stages are independently driven in a single stage, so that the power output requirement on the single stage of the single stage rotor is reduced, the design and manufacturing difficulty is greatly reduced, and on the other hand, the elementary stages of all stages are matched step by step to ensure that the total temperature and the total pressure of airflow are continuously increased step by step and are easy to accumulate into huge power, so that a large-thrust engine is easy to realize.
5) The blade tip (namely the edge of the blade height) and the blade root of the rotor blade are respectively connected with the outer wheel disc and the inner wheel disc, and both ends are hermetically connected, and no gap exists in the middle, so that blade tip loss does not exist.
6) The invention mainly adopts the edge driving mode design to change the traditional axis driving mode, so that the driving mechanism is changed from being concentrated in the axis area to be dispersed to the edge area, the integral thickness of the single-stage driving structure of each stage of the rotor is greatly reduced, and the single-stage electric driving mechanism of each stage of the rotor can be seamlessly arranged in the engine casing without obviously increasing the thickness of the casing, thereby adapting to the fundamental requirement of the integration of the driving mechanism and the single stage of the rotor.
7) Compared with the mode of centralized driving of the middle driving shaft of the traditional fuel oil turbine jet engine, the electric energy driving structure in the invention is integrated with each stage of rotor in a single stage, thereby omitting the complex designs of a heavy transmission shaft, a speed change mechanism, a clutch mechanism and the like, greatly reducing the weight of the engine, greatly improving the thrust-weight ratio of the engine, simultaneously greatly simplifying the design and greatly improving the reliability and the safety. Meanwhile, each stage of rotor single stage can realize independent driving, is easy to control and act cooperatively, greatly widens the designed working state interval of the engine, and greatly improves the surge margin of the engine.
8) The electric energy driving jet aero-engine provided by the invention also realizes complete fusion and complete compatibility with other original structures, functions and performances of the traditional fuel jet aero-engine, for example, the electric energy driving jet aero-engine is completely compatible with most other mechanisms such as an original subsonic or supersonic air inlet system, a tail nozzle which is an exhaust system and the like, and can be basically and directly used, thereby greatly reducing the change amount.
9) The blade rotating direction and the inclination angle of the fan in the electric-driven jet aircraft engine provided by the invention are adjustable, so that the reverse thrust can be realized in the true sense, the landing and sliding distance of the traditional fixed-wing aircraft can be greatly shortened, or the functions of air deceleration, braking, air reverse flight and the like of the vertical take-off and landing fixed-wing aircraft can be realized. This is not really possible with conventional fuel-injected engines.
10) Compared with the traditional fuel oil jet engine, the maximum system operation temperature of the engine is greatly reduced by more than 600-800 ℃, the severe requirement on materials is greatly reduced, the requirement on a cooling system is also greatly reduced, the design and manufacturing difficulty is greatly reduced, and the manufacturing cost is greatly reduced. The temperature of the tail gas is greatly reduced, so that the efficiency is greatly improved, the technical realization difficulty of the adjustable tail spray pipe and the vector type tail spray pipe is greatly reduced, and the vector engine is easy to realize.
Drawings
FIG. 1 is a schematic diagram of the basic configuration of a jet core engine of an electrically powered jet aircraft engine of the present invention;
FIG. 2 is a cross-sectional view of the basic structure of a jet core engine of an electrically powered jet aircraft engine of the present invention;
fig. 3a and 3b are schematic structural diagrams (including sectional views) of the single-stage mover driven by the outer ring and the inner ring of the jet core engine of the jet aircraft engine driven by electric energy according to the invention;
fig. 4a and 4b are schematic structural diagrams (including sectional views) of a single-stage mover driven only by an outer ring of a jet core engine of an electrically-driven jet aircraft engine according to the present invention;
FIG. 5 is a schematic structural view (in cross-section) of a single stage stator of a jet core engine of an electrically powered jet aircraft engine of the present invention;
FIG. 6 is a schematic overall appearance of a jet core engine of an electrically powered jet aircraft engine of the present invention;
FIG. 7 is a first exploded view of a jet core engine of an electrically driven jet aircraft engine according to the present invention;
FIG. 8 is a second schematic disassembled structure view of a jet core engine of an electrically driven jet aircraft engine of the present invention;
FIG. 9 is a cross-sectional view of the basic structure of an inner ducted jet core engine and an outer ducted fan of the electrically driven jet aircraft engine of the present invention;
FIG. 10 is a schematic view of the overall appearance of an inner ducted jet core engine and an outer ducted fan of an electrically driven jet aircraft engine according to the present invention;
FIG. 11 is a front view of an inner ducted jet core engine plus an outer ducted fan of an electrically powered jet aircraft engine of the present invention;
FIG. 12 is a rear view of an inner ducted jet core engine plus an outer ducted fan of an electrically driven jet aircraft engine of the present invention;
FIG. 13 is a front elevational view of the basic construction of the fan rotor section in the inner ducted jet core plus outer ducted fan of the electrically powered jet aircraft engine of the present invention;
FIG. 14 is a side view of the basic structure of the fan rotor section in the endoprosthesis jet core plus extraducted fan of the electrically powered jet aircraft engine of the present invention;
FIG. 15 is a first exploded view of the basic structure of an inner ducted jet core engine and an outer ducted fan of an electrically driven jet aircraft engine according to the present invention;
FIG. 16 is a second exploded view of the basic structure of the inner ducted jet core engine and the outer ducted fan of the electric-powered jet aircraft engine of the present invention;
FIG. 17 is a third exploded view of the basic structure of an inner ducted jet core engine and an outer ducted fan of the electric-powered jet aircraft engine of the present invention;
1-an outer housing; 2-central axis;
3-jet core machine, 30-element level, 300-blade, 301-outer wheel disc, 302-inner wheel disc, 31-compressor, 32-accelerator;
4-electric drive mechanism, 40a/40b/42a/42 b-rotor, 41a/41b/43a/43 b-stator;
5-fan, 500-blade, 501-outer wheel disc, 502-inner wheel disc;
50-rotating rod, 51-angle connecting rod, 52-synchronous rotating ring, 53-adjusting block and 54-fixing block;
a-an air inlet channel system; b-an exhaust passage system.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the specific embodiments. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
For the sake of simplicity, the drawings only schematically show the parts relevant to the solution of the invention, and they do not necessarily represent the final actual structure of the product.
According to one embodiment of the invention, an electrically driven jet aircraft engine comprises a jet core engine; the jet core machine comprises two modes:
the first method comprises the following steps: the jet core machine 3 comprises a compressor 31, wherein the compressor 31 is used for decelerating and pressurizing the inlet air flow; the engine also comprises an electric power drive mechanism 4 for powering the jet core machine 3. Therefore, the electric energy driving mechanism drives the air compressor to decelerate, pressurize and apply power to the air inlet flow, so that the total temperature and the total pressure of the air flow are increased step by step, and the air exhaust speed is greater than the air inlet speed to generate thrust required by flight.
And the second method comprises the following steps: as shown in fig. 1-2 and fig. 6-8, the jet core machine 3 includes a compressor 31 and an accelerator 32 sequentially arranged along an air intake direction, the compressor 31 is used for decelerating and pressurizing the air intake flow, and the accelerator 32 is used for accelerating, pressurizing/maintaining pressure/reducing pressure of the air intake flow; the compressor 31 and the accelerator 32 are integrally connected front and back; the engine also comprises an electric power drive mechanism 4 for powering the jet core machine 3. Therefore, the combination of two basic structures of the compressor and the accelerator is used as the jet core machine 3 of the engine, the air flow firstly performs deceleration pressurization work by the compressor, then performs acceleration pressurization work by the accelerator, the total temperature and total pressure of the air flow are gradually increased, and finally the exhaust speed is greater than the intake speed to generate thrust required by flight.
In the embodiment, two different arrangement forms are provided for the jet core machine 3, and the combination of the compressor, the compressor and the accelerator can be freely selected according to requirements.
On the basis of the embodiment, the front side of the jet core machine 3 along the air inlet direction is provided with an air inlet channel system A, and the rear side is provided with an air outlet channel system B.
The jet aircraft engine driven by electric energy provided by the embodiment is different from a traditional fuel turbine jet engine, and a combustion chamber and a turbine of the traditional fuel turbine jet engine are eliminated; the power consumed by the front-stage compressor 31 part is not passive work driven by a turbine, but active work from an electric energy driving mechanism of the front-stage compressor, the electric energy is consumed, the high-speed intake air flow is decelerated and pressurized through the electric energy driving mechanism, conditions are created for the high-efficiency acceleration and pressurization of the rear-stage accelerator 32, meanwhile, the total temperature and the total pressure of the original intake air flow are firstly stored, and the total temperature and the total pressure of the intake air flow are increased step by step through the step-by-step work on the intake air flow; the rear-stage accelerating machine part accelerates and continuously boosts the air flow after the boosting and decelerating of the front-stage compressor through an electric energy driving mechanism of the rear-stage accelerating machine part so as to continuously increase the total temperature and the total pressure of the air flow step by step; and finally, the air flow after the total temperature and the total pressure are greatly increased after the air compressor and the accelerator do work is fully expanded and accelerated through a tail nozzle, namely an exhaust passage system, and then is exhausted into the atmosphere, and the engine generates thrust through reaction force in the air expansion and acceleration process. That is, the jet core engine of the present invention produces the basic operating principle of jet propulsion.
According to another embodiment of the present invention, as shown in fig. 9 to 12, an electric-driven jet aircraft engine is provided, and the present embodiment is different from the first embodiment in that a specific arrangement of an extraducted fan is added.
On the basis of the first embodiment, in the embodiment, an outer duct is formed between the periphery of the jet core machine 3 and the outer shell 1, and a single-stage or multi-stage fan 5 is arranged in the outer duct of the periphery of the jet core machine and/or at the front end of the jet core machine;
the fan is characterized by further comprising an electric energy driving mechanism 4 for providing power for the fan 5, and any stage of fan 5 is directly or in transmission connection with the electric energy driving mechanism 4.
In this embodiment, the outer ducted fan is added on the basis of the inner ducted jet core machine, so that various modes of a pure jet mode, a pure fan mode and a mixed mode thereof can be realized.
On the basis of the embodiment, the front side of the jet core machine 3 along the air inlet direction is provided with an air inlet channel system A, and the rear side is provided with an air outlet channel system B.
On the basis of the electric energy driven jet aero-engine, the single-stage or multi-stage fan of the outer duct is added, the fan is driven by electric energy, the electric energy driven jet aero-engine is formed, and the thrust and the propulsion efficiency of the engine are greatly improved. But is completely different from the traditional fuel turbine jet engine, the outer ducted fan and the inner ducted jet core engine in the embodiment are not driven and connected in series in front and back in the traditional way, but are respectively independently and actively driven and parallelly connected (the fans can be arranged at any position on the outer shell 1 of the casing, including the front end, the middle part and the rear end, in the example, as shown in fig. 9, the fan 5 is arranged at the middle part of the outer shell 1 of the jet core machine), so that the air flows of the inner duct and the outer duct are independent and do not interfere with each other, the exhaust speed of the inner duct jet core machine and the exhaust speed of the outer duct fan can be freely adjusted according to the requirement, that is, the ratio of the exhaust flow rates of the inner and outer ducts is changed, for example, the adjustment is performed by changing the rotating speed of the fan of the outer duct, changing the rotating speed of the compressor and/or the accelerator, and the like, which is not described in detail herein; the air flow flowing into the inner duct and the outer duct can be changed very easily through the adjustable and openable blades, baffles or a plurality of fish scales and other adjusting mechanisms of the similar adjustable tail nozzles, namely the air intake and exhaust flow ratio of the inner duct and the outer duct is changed; even completely shutting down the inner ducted jet core machine (at low speed, especially at low subsonic speed and takeoff and landing stages) or completely shutting down the outer ducted fan (at high speed, especially at higher supersonic speeds), while greatly reducing noise and avoiding noise pollution. Therefore, the high-efficiency speed range is greatly expanded, and meanwhile, the extremely high propelling efficiency is realized from zero speed to medium and low subsonic speeds (Mach 0-0.5), and then to high subsonic speeds (Mach 0.7-0.9) to high supersonic speeds (Mach 1.7-3) in a wide speed range (Mach 0-3). In addition, the real 'reverse thrust' of the engine can be realized very easily by changing the rotating direction of the fan or changing the angle of the fan blades, which cannot be imagined and realized by the traditional fuel jet engine.
Specifically, after the inner duct jet core machine 3 and the outer duct fan 5 are added, three high-efficiency working modes are realized: the mode can realize the real reverse thrust of the engine by changing the rotation direction of the fan or changing the angle of the fan blades; the jet-type and fan mixed mode mainly works in the middle-high subsonic speed and transonic speed regions and is suitable for the high-economical cruise stage under the high subsonic speed; and thirdly, a pure jet mode mainly works in a high supersonic speed region and is suitable for the high-altitude supersonic cruise stage.
In addition, the outer shell or the air inlet system of the outer duct in the embodiment further comprises an auxiliary air inlet or an auxiliary air inlet device, and the auxiliary air inlet or the auxiliary air inlet device is used in a low-speed stage and a reverse thrust stage such as take-off and landing, so that the air inlet amount is increased, and the thrust magnitude and the efficiency at the low speed are further improved.
The housing base of the inner duct in the embodiment further comprises an auxiliary air leakage device, and the auxiliary air leakage device is used for reducing air inflow when the air inflow is excessive and the high-speed flight is carried out at supersonic speed and the like, so that the thrust generated by the engine is maintained in a required range.
The exhaust mode of the inner duct and the outer duct in the embodiment is usually that the two are mixed and then exhausted into the atmosphere, but the unusual condition that the two are separately exhausted into the atmosphere is also included.
In this embodiment, the combination of the inner duct jet core machine and the outer duct fan forms a multi-mode, so that the principle of achieving high efficiency in a wide speed range is as follows:
according to the basic physical principle and the aviation propulsion and power principle, the thrust, the propulsion efficiency and the total efficiency of the aviation jet engine are respectively as follows:
(1)F＝Cp*(Vout-Vin)
wherein F is the thrust generated by the jet engine, CpIs the air flow rate of the engine, VinIs the intake speed, V, of the engineoutIs the exhaust speed of the engine. Whereas the inlet air velocity is approximately equal to the aircraft's airspeed, meaning that thrust is only generated when the engine's exhaust velocity exceeds the aircraft's airspeed.
(2)ηp＝2/(1+Vout/Vin)
Wherein, ηpFor the propulsion efficiency of the engine, VinIs the intake speed, V, of the engineoutIs the exhaust speed of the engine. Similarly, since the intake velocity is approximately equal to the aircraft's flight velocity (airspeed), the above equation illustrates that the closer the exhaust velocity of the engine is to the aircraft's flight velocity, the higher the propulsion efficiency.
(3)η＝ηe*ηp
Wherein η is the total efficiency, ηeFor energy conversion efficiency, the thermal efficiency of the conventional fuel oil jet engine is about 40-46%, and the electrical efficiency of the electric energy driven jet engine is about 80-90% or more, ηpIs the propulsion efficiency of the engine. This first demonstrates that the energy conversion efficiency of an electrically powered jet aircraft engine is more than twice that of a conventional fuel-fired jet aircraft engine, the former being far more efficient than the latter. At the same time, it is also shown that a decrease in propulsion efficiency also leads to a decrease in overall efficiency, which in turn leads to a decrease in more energy consumption, shorter range, higher cost, and fuel economy.
Wherein, at first glance, the formula (1) and the formula (2) seem contradictory, whereas otherwise, they are obtained according to the momentum theorem
F*t＝m*(Vout-Vin)
Theorem on the kinetic energy
Figure BDA0002385177900000121
The fundamental reasons for this are the mass m and the exhaust velocity V of the exhaust gas flowoutThe contribution to the thrust is one-dimensional, while the mass of the exhaust gas flow is still one-dimensional to the energy consumption, but the velocity of the exhaust gas flow is quadratic to the energy consumption, it can be seen that the mass and velocity of the exhaust gas flow contribute equally to the thrust, but the velocity of the exhaust gas flow is much greater than the mass to the power consumption, and the energy consumption is wasted in transferring to the excess kinetic energy of the engine exhaust. Therefore, in order to improve the efficiency and reduce the energy consumption as much as possible, the exhaust speed is higher than the intake speed VinThe exhaust speed V of the engine is based on the minimum basic requirement for generating thrust (approximate flying speed)outCloser to intake air flow velocity Vin(which approximates airspeed), the lower the better, the higher the efficiency, the better the economy; meanwhile, in order to ensure the thrust, the air flow rate of the engine is increased according to the momentum theorem.
According to the principle, the combination of the inner duct jet core engine and the outer duct fan in the embodiment, the mutually independent parallel design of the inner duct and the outer duct, and the independent free adjustment of the respective air inlet and exhaust flow rate and the exhaust flow rate of the inner duct and the outer duct in the embodiment can ensure that the high-speed airflow of the inner duct and the low-speed airflow of the outer duct can be mixed in any proportion, and the final exhaust flow rate of the mixed inner duct and the outer duct, which meets the thrust requirement, is closest to the flight speed and is less than or equal to any speed of the jet core engine at the highest exhaust speed, can be configured, so the propulsion efficiency can be greatly improved, and the high propulsion efficiency in a full speed range is realized, while the non-traditional fuel jet engine can only realize higher propulsion efficiency at a certain speed section; meanwhile, the energy conversion efficiency of the jet aircraft engine driven by electric energy is two times or more higher than that of the traditional fuel jet aircraft engine; according to the above formula (3), the present example can achieve a high overall efficiency far exceeding that of the conventional fuel jet engine, so that energy economy is greatly improved, flight cost is greatly reduced, a range is greatly increased, and simultaneously, a plurality of advantages of multi-mode, wide speed range and high efficiency which cannot be achieved or are extremely difficult to achieve by the conventional fuel jet engine are achieved.
According to another embodiment of the present invention, the jet aircraft engine is driven by electric energy, and the difference between the present embodiment and the first embodiment is the specific structure of the jet core engine 3, which is shown in fig. 3 to 5.
On the basis of the first embodiment, in this embodiment, a mode in which only a compressor is provided corresponding to a jet core engine is as follows: the compressor 31 comprises a single-stage or multi-stage element stage, and the element stages 30 in the compressor 31 are sequentially arranged in the front-back direction along the air inlet axial flow direction; any element level comprises a rotor single level and a stator single level which are alternately arranged front and back; and any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism.
A mode of integrally arranging the compressor 31 and the accelerator 32 in front and at the back corresponding to the jet core machine: the compressor 31 and the accelerator 32 both comprise a single-stage or multi-stage element stage 30, and all the element stages in the compressor 31 and the accelerator 32 are sequentially arranged in the front-back direction along the axial flow direction of the air inlet; any element stage 30 comprises a rotor single stage and a stator single stage which are alternately arranged front and back; any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism 4;
the rotor single stage comprises a plurality of blades 300 extending outwards along the radial direction of the central shaft 2, and the edges of the blade heights of the plurality of blades 300 in the rotor single stage are connected with an outer wheel disc 301 with a hollow inner part;
the electric energy driving mechanism is directly or in transmission connection with the outer wheel disc 301 of the rotor single stage and is used for driving the outer wheel disc 301 to move along the surrounding direction;
the stator single stage comprises a plurality of blades 300 extending radially outwards along the central axis 2, the blade height edges of the plurality of blades 300 in the stator single stage are all connected with the housing base, and/or the roots of the plurality of blades 300 in the stator single stage are connected with the intermediate base. The housing base and the middle base are connected and fixed through a supporting mechanism or other similar mechanisms in the prior art.
In a preferred embodiment, the roots of the plurality of blades 300 in the rotor single stage are connected to an inner wheel disc 302 which is hollow inside. The inner wheel disc 302 of the mover single stage is rotatably nested or connected on the middle base.
In this embodiment, the electric energy driving mechanism drives the rotor single-stage blades 300 to rotate; the two ends of the rotor single-stage blade 300, the outer wheel disc 301 and the inner wheel disc 302 are hermetically connected, the edge of the blade height of the stator single-stage blade 300 is connected with the shell base, the root of the blade height of the stator single-stage blade 300 is connected with the middle base, and the two ends of the stator single-stage blade 300 are also hermetically connected, so that no gap exists between the two ends of the rotor single-stage blade and the stator single-stage blade and the airflow channel, and no blade tip loss exists. The blade root of comparing traditional fuel jet engine fixes on central transmission shaft, and there is certain clearance between apex and the casing base or the casing base, brings the apex loss difference, consequently can realize than traditional fuel jet engine higher pressure boost ratio and higher efficiency. It should be noted that, in the exploded views of fig. 7 and 8, for the convenience of observation, the stator single-stage vane 300 is peeled off from the casing base, and substantially the blade height edge of the stator single-stage vane 300 is connected to the casing base, that is, the stator single-stage is connected to the outer casing.
As another preferred embodiment, the electric energy driving mechanism 4 includes a plurality of rotors 40a disposed on the outer disk 301 of each stage of mover, the plurality of rotors 40a can be uniformly distributed on the outer side of the outer disk 301, and further includes a plurality of stators 41a disposed on the outer periphery of the outer disk 301 and on the housing base on the side far away from the outer disk 301, and the stators 41a are disposed in one-to-one correspondence with the positions of the rotors 40 a;
the rotors 40a are induction coils or permanent magnets, and when the rotors 40a are permanent magnets, the magnetic property of adjacent rotors 40a is opposite, specifically, two or more adjacent rotors 40a can also be used as one group, and the magnetic property of the rotors 40a of each adjacent group is opposite.
An electric coil (not shown in the figure) is wound on the stator 41a, and the electric coil can be electrified with alternating current to drive the rotor 40a and further drive an outer wheel disc 301 connected with the rotor 40a to move in a surrounding manner; when the rotor 40a is a permanent magnet, the electric energy driving mechanism 4 can drive the outer wheel disc 301 to move along the surrounding direction thereof in a driving manner of a dc motor, and the principle of the dc motor is not described herein again; when the rotor 40a is an induction coil, the electric energy driving mechanism 4 can drive the outer wheel disc 301 to move along the surrounding direction thereof in a driving manner of an asynchronous ac motor, and the principle of the asynchronous ac motor is not described herein again.
In this embodiment, by specifically setting the electric energy driving mechanism 4, the outer wheel disc 301 at the edge of the rotor single-stage blade is driven, the outer wheel disc 301 rotates along the circumferential direction of the outer wheel disc after being driven by the electric energy driving mechanism 4, and simultaneously drives the moving blade 300 to rotate when rotating, thereby forming an edge driving mode, changing the traditional axis driving mode, enabling the driving mechanism to be changed from being concentrated on the axis area to be dispersed to the edge area, greatly reducing the overall thickness of each stage of rotor single-stage driving mechanism, and enabling the electric energy driving mechanism 4 of each stage of rotor single-stage to be seamlessly installed in the casing base (i.e. the casing base) without obviously increasing the casing thickness High reliability, long service life, low noise, etc. In addition, the rotor single-stage and the stator single-stage are alternately fixed on the central shaft and the casing step by step, specifically, two ends of the stator single-stage are respectively fixed on the shell base and the middle base, and the rotor single-stage is rotatably nested or connected on the middle base of the jet core machine, so that the rotor single-stage and the stator single-stage are alternately arranged front and back at a certain interval.
Preferably, the electric energy driving mechanism 4 further includes a plurality of rotors 42a disposed on the inner disk 302 of each stage of the mover, the rotors being far away from the blades, and a plurality of stators 43a disposed on the inner periphery of the inner disk 302 and the middle base near the inner disk 302, and the stators 43a are disposed in one-to-one correspondence with the rotors 42 a;
the rotors 42a are induction coils or permanent magnets, and when the rotors 42a are permanent magnets, the magnetic properties of adjacent rotors 42a are opposite, specifically, two or more adjacent rotors 42a can also be used as one group, and the magnetic properties of the rotors 42a of each adjacent group are opposite;
an electrified coil (not shown in the figure) is wound on the stator 43a, and the electrified coil is used for supplying alternating current to drive the rotor 42a and further drive the inner wheel disc 302 connected with the rotor 42a to move circularly; when the rotor 42a is a permanent magnet, the electric energy driving mechanism 4 can drive the inner wheel disc 302 to move along the surrounding direction thereof in a driving manner of a dc motor, and the principle of the dc motor is not described herein again; when the rotor 42a is an induction coil, the electric energy driving mechanism 4 can drive the inner wheel disc 302 to move along the surrounding direction thereof in a driving manner of an asynchronous alternating current motor, and the principle of the asynchronous alternating current motor is not described in detail herein.
Thus, the electric power driving mechanism 4 is connected with the inner wheel disc 302 of the mover single stage for driving the inner wheel disc 302 to move along the surrounding direction.
In this embodiment, in addition to the aforementioned outer ring driving (or outer wheel disc driving) for the mover single stage, an inner ring driving (or inner wheel disc driving) for the mover single stage may be performed at the same time, that is, the inner wheel disc 302 is driven to move along the surrounding direction. The inner disk 302 rotates in the circumferential direction thereof after being driven by the electric power driving mechanism 4, and drives the blade 300 to rotate when rotating. Of course, a single inner ring drive may be used to effect rotation of the blades 300 to generate the airflow, as desired.
In addition, it should be noted that the electric energy driving mechanism 4 corresponding to each stage of the mover single stage may be configured independently, so as to independently drive each stage of the mover single stage; alternatively, there are also cases where: the corresponding multi-stage rotor single-stage is combined and configured by the same electric energy driving mechanism 4, so that the electric energy driving mechanism 4 is synchronously connected with the multi-stage rotor single-stage in a driving way, and the multi-stage rotor single-stage is combined and driven.
As another preferred embodiment, the stator single-stage and the stator single-stage in the compressor 31 are alternately arranged in sequence along the air intake direction. Preferably, the flow cross section of each elementary stage 30 in the compressor 31 converges step by step. Wherein, the air current cross-section means: a cross section of the air flow channel perpendicular to the axial flow direction.
In this embodiment, the single-stage blades of each stage of the mover perform the function of applying work to the passing air, so that the air is accelerated, the dynamic pressure of the air is increased, and the total temperature and the total pressure of the air flow are increased. Each stage of stator blades in the gas compressor play roles of a rectifier and expanding pressurization, so that dynamic pressure of gas increased by the single-stage blades of the rotor is converted into static pressure, and the gas flow speed is reduced; specifically, the airflow cross section in the compressor 31 converges step by step in the following three forms and any combination thereof: a. the outer diameter of the bypass airflow section is gradually unchanged, and the inner diameter is gradually increased; b. the outer diameter of the bypass airflow section is gradually reduced, and the inner diameter is gradually unchanged; c. the outer diameter of the bypass airflow section is gradually reduced, and the inner diameter is gradually increased. It should be noted that, in some special cases, an arrangement mode in which a stator single stage is in front of a rotor single stage and the rotor single stage is behind the rotor single stage may also be adopted.
In another preferred embodiment, the accelerator 32 has stator single-stage in front and rotor single-stage in back alternately arranged along the air intake direction. Preferably, the accelerator 32 has a progressive expansion of the flow cross-section of each elementary stage 30.
In this embodiment, the blades of each stator single stage in the accelerator 32 play roles of a rectifier and expanding pressurization, so that on one hand, the direction of the outflow gas is directly opposite to the inlet direction of the rotor single stage blade of the next stage, and on the other hand, the shape expanding pressurization of the preceding stage gas flow is decelerated, thereby creating better conditions for the rotor single stage blade of the next stage to accelerate the gas flow more efficiently. Specifically, after the gas flows through the stator single stage of the accelerator 32, the speed is reduced, the dynamic pressure is reduced, the static pressure is increased, the dynamic pressure is converted into the static pressure, and the total temperature and the total pressure are basically unchanged; each stage of rotor single-stage blades in the accelerator 32 plays a role in applying work to the air flowing through, so that the air is accelerated, the dynamic pressure of the air is increased, and the total temperature and the total pressure of the air flow are continuously increased step by step. The stator single-stage is arranged in front, the rotor single-stage is arranged alternately in back, the expansion type pressurization and deceleration are firstly carried out, the dynamic pressure is increased through the acceleration, and the efficiency of the rotor single-stage for applying work to low-speed airflow is better. Specifically, the airflow cross section in the accelerator 32 is gradually expanded in the following three forms and any combination thereof: a. the inner diameter of the bypass airflow section is gradually unchanged, and the outer diameter is gradually increased; b. the inner diameter of the bypass airflow section is gradually reduced, and the outer diameter is gradually unchanged; c. the inner diameter of the bypass airflow section is gradually reduced, and the outer diameter of the bypass airflow section is gradually increased. It should be noted that, in some special cases, an arrangement mode that the mover single stage is in front of the stator single stage may also be adopted; the airflow cross section of each elementary stage in the accelerator can also take a step-by-step invariant form.
As another more preferred embodiment, the inclination angle of the mover single-stage and/or stator single-stage blades 300 of any one of the elementary stages 30 of the compressor 31 and the accelerator 32 is adjustable.
According to another embodiment of the present invention, based on the first embodiment of adding the bypass fan, as shown in fig. 13 to 17, the fan 5 includes a plurality of blades 500 extending radially outward along the central axis 2, and the edges of the blade heights of the plurality of blades 500 are connected to an inner hollow outer wheel disc 501;
the electric energy driving mechanism 4 is connected with an outer wheel disc 501 of the fan and used for driving the outer wheel disc 501 to move along the surrounding direction of the outer wheel disc 501, and an inner wheel disc 502 of the fan is rotatably nested on the periphery of the jet core machine 3.
Preferably, the electric energy driving mechanism 4 includes a plurality of rotors 40b disposed on the outer wheel disc 501 of each stage of fan 5, the plurality of rotors 40b can be uniformly distributed on the outer side of the outer wheel disc 501, and further includes a plurality of stators 41b disposed on the outer periphery of the outer wheel disc 501 and on the housing base on the side far away from the outer wheel disc 501, and the stators 41b and the rotors 40b are disposed in one-to-one correspondence;
the rotors 40b are induction coils or permanent magnets, and when the rotors 40b are permanent magnets, the magnetic property of adjacent rotors 40b is opposite, specifically, two or more adjacent rotors 40b can also be used as one group, and the magnetic property of the rotors 40b of each adjacent group is opposite.
An electric coil (not shown in the figure) is wound on the stator 41b, and the electric coil can be electrified with alternating current to drive the rotor 40b and further drive the outer wheel disc 501 connected with the rotor 40b to move in a surrounding manner; when the rotor 40b is a permanent magnet, the electric energy driving mechanism 4 can drive the outer wheel disc 501 to move along the surrounding direction thereof in a driving manner of a dc motor, and the principle of the dc motor is not described herein again; when the rotor 40b is an induction coil, the electric energy driving mechanism 4 can drive the outer wheel disc 501 to move along the surrounding direction thereof in a driving manner of an asynchronous ac motor, and the principle of the asynchronous ac motor is not described herein again.
Therefore, in the embodiment, the outer wheel disc 501 at the high edge of the fan blade is driven by the specific arrangement of the electric energy driving mechanism 4, the outer wheel disc 501 rotates in the circumferential direction after being driven by the electric energy driving mechanism 4, and simultaneously drives the blade 500 to rotate when rotating, so that an edge driving mode is formed, that is, the outer ring driving of the fan 5 is realized.
As another more preferred embodiment, the roots of the plurality of blades are connected to an inner disk 502 that is hollow inside; the inner disk 502 of the fan is rotatably nested around the outer circumference of the jet core machine.
Further preferably, the electric driving mechanism 4 further includes a plurality of rotors 42b disposed on the inner disc 502 of each stage of the fan 5, and further includes a plurality of stators 43b disposed on the middle base of the inner circumference of the inner disc 502 and near one side of the inner disc 502, and the stators 43b are disposed in one-to-one correspondence with the positions of the rotors 42 b;
the rotors 42b are induction coils or permanent magnets, and when the rotors 42b are permanent magnets, the magnetic properties of adjacent rotors 42b are opposite, specifically, two or more adjacent rotors 42b can also be used as one group, and the magnetic properties of the rotors 42b of each adjacent group are opposite;
an electrified coil (not shown in the figure) is wound on the stator 43b and is used for introducing alternating current to drive the rotor 42b and further drive the inner wheel disc 502 connected with the rotor 42b to move circularly; when the rotor 42b is a permanent magnet, the electric energy driving mechanism 4 can drive 502 to move along the surrounding direction thereof in a driving manner of a dc motor, and the principle of the dc motor is not described herein again; when the rotor 42b is an induction coil, the electric energy driving mechanism 4 can drive the inner wheel 502 to move along the surrounding direction thereof in a driving manner of an asynchronous ac motor, and the principle of the asynchronous ac motor is not described herein again.
Thus, the electric power driving mechanism is connected with the inner wheel disc 502 of the mover single stage for driving the inner wheel disc 502 to move along the surrounding direction.
In this embodiment, in addition to the aforementioned way of driving the fan by using the outer ring, that is, driving the outer wheel 501, the fan may be driven by using the inner ring, that is, the inner wheel 502 is driven to move along the surrounding direction. The inner disk 502 rotates in the circumferential direction thereof after being driven by the electric power driving mechanism 4, and simultaneously rotates to drive the blade 500 to rotate. Of course, in certain situations, a single inner ring drive may be used to effect rotation of the blades 500 to generate the airflow.
As another more preferred embodiment, the inclination angle of the plurality of blades 500 in the fan 5 is adjustable.
In the above embodiment, the specific structure of the fan 5 for adjusting the inclination angle of the blades is as follows:
the blades 500 are hinged to the outer disc 501 at one end close to the outer disc 501; specifically, the inner side of the outer wheel disc 501 is connected with a plurality of rotating rods 50, the rotating rods 50 are arranged on the inner side of the outer wheel disc 501 along the radial direction of the outer wheel disc 501, the inner ends of the plurality of rotating rods 50 are connected to the inner wheel disc 502, the blades are sleeved on the rotating rods 50, and the blades 500 are rotatably connected to the rotating rods 50 along the axial direction of the rotating rods 50, so that the blades 500 are hinged to the outer wheel disc 501;
the blade 500 is hinged with an angle connecting rod 51 on the outer edge end part connected with the closed outer wheel 501, the other end of the angle connecting rod 50 far away from the blade 500 is hinged with a synchronous rotating ring 52, the synchronous rotating ring 52 is arranged on one side of the outer wheel disc 501 in parallel along the axial direction of the outer wheel disc, and the synchronous rotating ring 52 is connected with the outer wheel disc 501 through a rotation synchronous mechanism;
the rotation synchronization mechanism comprises a fixed block 53 arranged on the outer wheel disc 501 and an adjusting block 54 arranged on the synchronization rotating ring 52, and the fixed block 53 and the adjusting block 54 are connected into a whole in a distance-adjustable manner through a bolt assembly.
In this embodiment, adjust the interval between fixed block 53 and the regulating block 54 through bolt assembly, make the distance between outer rim plate and the synchronous swivel change to can drive articulated blade 500 through angle connecting rod 51 and rotate along dwang 50, and then make the inclination or the rotation direction of blade 500 outer fringe tip change. It should be noted that, specific structures for adjusting the inclination angle of the blade 500 include, but are not limited to, the above-mentioned solutions.
When the blade angle of the fan 5 is fixed, the flow velocity of the outer duct can be adjusted by adjusting the rotating speed of the fan, so that the thrust is changed; the reversal of the direction of the thrust, i.e. "thrust reversal", can be achieved by changing the direction of rotation of the fan 5. When the blade angle of the fan 5 is adjustable, the flow velocity of the bypass can be adjusted by adjusting the rotating speed of the fan 5 and the blade angle of the fan 5, so that the thrust is changed; the reversal of the direction of the thrust, i.e. "thrust reversal", can be achieved by either changing the direction of rotation of the fan 5 or by changing the angle of the blades of the fan 5. The mode of changing the angle of the blade is free from inertia influence on the change of the flow velocity and the thrust, and the response is quicker.
The central shaft 2 in the above embodiments is used for fixing structural members such as a mover single stage, a stator single stage, an electric driving mechanism, etc., and in practical modification applications, the central shaft 2 may be fixed or may be in a rotatable manner.
According to another embodiment of the invention, as shown in fig. 1, an electric-driven jet aircraft engine is provided, and on the basis of the first embodiment, an intake air flow adjusting mechanism is arranged in the intake system and/or in the intake of the inner duct and/or in the outer duct, and is used for adjusting the intake and exhaust gas flow ratio of the inner duct and the outer duct.
In the embodiment, the air inlet flow regulating mechanism can adopt an air inlet guide vane or a baffle plate which can be adjusted in angle and opened and closed; or a multi-fish scale type adjusting mechanism similar to the adjustable tail nozzle is adopted. For example, the inlet guide vanes are arranged at the front ends of the inner duct inlet and the outer duct inlet, and the inclination angles of the guide vanes can be adjusted and opened and closed, so that the flow of inlet and outlet air flowing into the inner duct and the outer duct can be changed. It should be noted that the airflow adjusting mechanism is a commonly used structure in the prior art, and other flow adjusting structures capable of realizing the flow ratio of the inner duct and the outer duct may be adopted.
The intake flow adjusting mechanism in this embodiment may be disposed at a plurality of positions in the casing, for example, the openable guide vanes may be reused at the outer duct, the multi-fish-scale structure similar to the adjustable tail nozzle may also be used at the inlet lip of the inner duct, the adjustment of the air flow of the inner duct and the outer duct may also be implemented in the supersonic inlet by the adjustable baffle, and so on, which are not limited to these examples.
In addition, the inlet system in the present embodiment is divided into two categories, namely a subsonic inlet and a supersonic inlet. The subsonic or supersonic inlet of a conventional jet aircraft is used, depending on the designed maximum speed of flight. For the tail pipe (exhaust duct system), if the designed highest flying speed is subsonic or low supersonic (< 1.5-1.7 Mach), the tail pipe adopts a convergent tail pipe which comprises a fixed convergent tail pipe and an adjustable convergent tail pipe. If the designed highest flying speed is higher supersonic speed (> Mach 1.5-1.7), the tail nozzle adopts a fixed type first-convergence and then-expansion tail nozzle and an adjustable type first-convergence and then-expansion tail nozzle. If the jet nozzle is a vector jet nozzle, the jet nozzle becomes a vector jet engine.
The invention also discloses an aircraft which comprises the electric energy driven jet aircraft engine of any one of the embodiments.
It should be noted that the above embodiments can be freely combined as necessary. The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims (15)

1. An electric energy driven jet aircraft engine, characterized in that:
comprises a jet core machine; the jet core machine comprises a gas compressor, and the gas compressor is used for decelerating and pressurizing inlet air flow;
the electric energy driving mechanism is used for providing power for the gas compressor;
the front side of the jet core machine along the air inlet direction is provided with an air inlet channel system, and the rear side is provided with an exhaust channel system.
2. The electrically driven jet aircraft engine of claim 1, wherein:
the jet core machine also comprises an accelerator arranged behind the gas compressor along the gas inlet direction, and the accelerator is used for accelerating and pressurizing or accelerating and maintaining pressure or accelerating and decompressing the gas inlet flow; the compressor and the accelerator are integrally connected front and back;
the jet core machine further comprises an electric energy driving mechanism for providing power for the accelerator.
3. An electrically driven jet aircraft engine as claimed in claim 1 or 2, characterized in that:
an outer duct is formed between the periphery of the jet core machine and the outer shell, and a single-stage or multi-stage fan is arranged in the outer duct at the periphery of the jet core machine and/or at the front end of the jet core machine; the jet core machine also comprises an electric energy driving mechanism for providing power for the fans, and any stage of fan is directly or in transmission connection with the electric energy driving mechanism.
4. The electrically driven jet aircraft engine of claim 1, wherein:
the compressor comprises a single-stage or multi-stage element stage, and all the element stages in the compressor are sequentially arranged in the front-back direction along the axial flow direction of the air inlet; any element level comprises a rotor single level and a stator single level which are alternately arranged front and back; and any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism.
5. The electrically driven jet aircraft engine of claim 2, wherein:
the compressor and the accelerator both comprise single-stage or multi-stage element stages, and all the element stages in the compressor and the accelerator are sequentially arranged in the front-back direction along the axial flow direction of the air inlet; any element level comprises a rotor single level and a stator single level which are alternately arranged front and back; and any one stage of rotor single stage is directly or in transmission connection with the electric energy driving mechanism.
6. An electrically powered jet aircraft engine as claimed in claim 4 or 5, wherein:
the rotor single stage comprises a plurality of blades extending outwards along the radial direction of a central shaft, and the blade height edges of the blades are connected with an outer wheel disc;
the electric energy driving mechanism is directly or in transmission connection with the rotor single-stage outer wheel disc and is used for driving the outer wheel disc to move along the surrounding direction of the outer wheel disc;
the stator single stage includes a plurality of vanes extending radially outward along a central axis; the blade height edges of a plurality of blades in the stator single stage are connected with the shell base, and/or the roots of the blades in the stator single stage are connected with the middle base.
7. The electrically driven jet aircraft engine of claim 6, wherein:
the roots of a plurality of blades in the rotor single stage are connected with the inner wheel disc; the rotor single-stage inner wheel disc is rotatably nested or connected to the middle base.
8. The electrically driven jet aircraft engine of claim 5, wherein:
the gas flow sections of all element stages in the gas compressor converge step by step; and/or the presence of a gas in the gas,
the airflow cross section of each element stage in the accelerator is gradually expanded or unchanged.
9. The electrically driven jet aircraft engine of claim 3, wherein:
the fan comprises a plurality of blades extending outwards along the radial direction of a central shaft, and the high edges of the blades in the fan are connected with an outer wheel disc;
the electric energy driving mechanism is directly or in transmission connection with an outer wheel disc of the fan and is used for driving the outer wheel disc to move along the surrounding direction of the outer wheel disc.
10. The electrically driven jet aircraft engine of claim 9, wherein:
the roots of a plurality of blades in the fan are connected with the inner wheel disc; the inner wheel disc of the fan can be rotatably nested on the periphery of the jet core machine.
11. An electrically powered jet aircraft engine as claimed in claim 7 or 10 wherein:
the electric energy driving mechanism comprises a plurality of rotors arranged on an outer wheel disc or an inner wheel disc of each stage of rotor single stage or fan, and a plurality of stators arranged on a shell base on the outer wheel disc periphery and one side far away from the outer wheel disc or on a middle base on the inner wheel disc periphery and one side close to the inner wheel disc, wherein the stators and the rotors are arranged in a one-to-one correspondence manner;
the rotor is an induction coil or a permanent magnet;
and the stator is surrounded with an electrified coil, and the electrified coil is used for introducing alternating current to drive the rotor and then drive an outer wheel disc or an inner wheel disc connected with the rotor to move in a surrounding manner.
12. The electrically driven jet aircraft engine of claim 9, wherein:
the inclination angle of a plurality of blades in the fan is adjustable.
13. The electrically driven jet aircraft engine of claim 12, wherein:
one end of each blade close to the outer wheel disc is hinged to the outer wheel disc;
the blade is hinged with an angle connecting rod on the end part of the outer edge connected with the outer wheel disc, the other end of the angle connecting rod, which is far away from the blade, is hinged with a synchronous rotating ring, the synchronous rotating ring is arranged on one side of the outer wheel disc in parallel along the axial direction of the outer wheel disc, and the synchronous rotating ring is connected with the outer wheel disc through a rotating synchronous mechanism;
the rotating synchronous mechanism comprises a fixed block arranged on the outer wheel disc and an adjusting block arranged on the synchronous rotating ring, and the fixed block and the adjusting block are connected into a whole in a distance-adjustable mode through a bolt assembly.
14. The electrically driven jet aircraft engine of claim 3, wherein:
and an air inlet flow adjusting mechanism is arranged at the air inlet position of the inner culvert and/or the air inlet position of the outer culvert in the air inlet channel system and is used for adjusting the air inlet and exhaust flow ratio of the inner culvert and the outer culvert.
15. An aircraft comprising an electrically powered jet aircraft engine according to any of claims 1 to 14.
CN202010095452.8A 2020-02-17 2020-02-17 Electric-driven jet aircraft engine and aircraft Pending CN111237084A (en)

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