CN103195612A - Multifunctional turbofan jet engine - Google Patents
Multifunctional turbofan jet engine Download PDFInfo
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- CN103195612A CN103195612A CN2013101184313A CN201310118431A CN103195612A CN 103195612 A CN103195612 A CN 103195612A CN 2013101184313 A CN2013101184313 A CN 2013101184313A CN 201310118431 A CN201310118431 A CN 201310118431A CN 103195612 A CN103195612 A CN 103195612A
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Abstract
The invention discloses a multifunctional turbofan jet engine which includes a fan, a gas compressor, a second combustor, a turbine and an exhaust nozzle, wherein the fan is used for sucking air, the gas compressor is used for doing work on the sucked air, the second combustor is used for igniting gas on which the gas compressor does work, and the exhaust nozzle is used for exhausting the combusted gas. The multifunctional turbofan jet engine further comprises a first combustor, a first splitter plate and a second splitter plate, wherein the first combustor is arranged in front of the second combustor, the first splitter plate and the second splitter plate are used for splitting gas, the first splitter plate and the first combustor are correspondingly arranged, the second splitter plate and the second combustor are correspondingly arranged, and the first splitter plate and the second splitter plate are respectively provided with a travel switch I and a travel switch II which are used for rotating the corresponding splitter plate. The invention aims to provide the multifunctional turbofan jet engine which has the advantages of inlet air cooling, accurate gas splitting, balanced ignition, uniform-velocity starting, level-changing acceleration, high-efficiency, safety, thrust vectoring, easy operation and versatility.
Description
Technical field
The present invention relates to the Aero-Space technical field of engines, relate in particular to a kind of turbofan that adopts the multi-cylinder technology.
Background technique
Present aircarrier aircraft can only fly to 10 kilometers high zones; Fighter generally flies to about 20 kilometers high, and the higher position is very difficult again.It is considerably less to break through 20 kilometers high aircrafts.Satellite can not fly to below 100 kilometers, because satellite is not having power around earth operation below 100 kilometers, highly drops to apart from ground 100 kilometers, and satellite will soon fall down.At present, the proximity space in 20-100 kilometer high-altitude is a clear area basically.How each state all in research, develops the proximity space aircraft now.Who can break through and capture this commanding height ， Who and just grasp control of the air except space.Develop the proximity space aircraft, must grasp the characteristics of proximity space.The characteristics of proximity space are: air is arranged, but thin; Centrifugal force is littler than the low latitude, but bigger than space.The characteristics of aeroengine are High Temperature High Pressure.Do you overcome centrifugal force, by high temperature? obviously be not.Can only be by overcoming gravitational reaction force, this reaction force is exactly thrust concerning motor.From mode of operation: the thrust of turbofan is little, and speed is slow, but fuel-efficient; The thrust of whirlpool spray is big, and speed is fast, but not fuel-efficient; Punching press is counted in working as of thrust maximum.Thrust is mainly from high pressure, rather than high temperature.High temperature has not only diluted the density of inlet air, has reduced the quality of inlet air flow, has increased oil consumption, and temperature is too high also can destroy cylinder body and blade, influences the life-span of motor.Exactly because the thermal management capabilities of China's motor is not high, cooling is done well inadequately, and the life-span that causes China's motor makes the country prosperous not as external motor.Therefore, must control temperature, increase thrust, acquisition speed.I think will develop the proximity space aircraft, is not all right only according to the turbofan mode of operation of motor.Must be that turbofan, whirlpool spray add punching press, and based on the press work pattern, because the press work pattern, with high thrust aircraft is obtained at a high speed, to make the air of proximity space become no longer thin at a high speed, with cooling the density of air is increased, obtain high-quality air-flow.Therefore, the proximity space aircraft has only main employing press work pattern, just most possibly breaks through height and free flight more than 20 kilometers.
The great advantage of press work pattern is supersonic speed, and disadvantage is can not be automatic.Rocket carries the similar press work pattern of liquid hydrogen liquid oxygen.Different with general pressed engine is before the engine charge with air inlet after its air-flow all maintain more than 5 Mach the hypersonic speed.General pressed engine then needs air-flow deceleration supercharging.But in a single day airspeed has reached 5 Mach hypersonic speed when above, and the high pressure-temperature intensity that air-flow deceleration supercharging brings can surpass engine material bear the limit.So best solution is exactly air-breathing and process burning back hypersonic speed ejection at once with hypersonic speed.The static pressure static temperature that is detained in the scramjet engine just can not threaten the motor normal operation like this.And one of scramjet engine key technology difficult point is firing technique, adds fuel and light a fire to be tantamount to light a match in hypersonic speed in tornado! The scramjet engine key technology comprises injection, blending, the igniting of fuel.The airspeed that flows through scramjet engine is always ultrasound velocity, air flows through and has only several milliseconds holdup time in the aircraft body usually, want in the short like this time, to finish compression, supercharging, and to finish low loss, high efficiency blending, the some burning of fighting with fuel rapidly, uniformly and stably at the ultrasound velocity state that flows be very difficult, fine or not igniting length and the heat load that directly influences motor of the blending of fuel and air.Because incoming flow is inhomogeneous, the work of the firing chamber of scramjet engine is very complicated.Therefore, the design of firing chamber and test that particularly the ultrasound velocity Study on Combustion Process is extremely important.
According to external research, the Russian scramjet engine that begins one's study from the sixties, target is civilian transport airplane, Single Stage To Orbit space shuttle and the hypersonic cruise missile of M several 5 ~ 7.The eighties in 20th century, this research institute and center air fluid dynamic research cooperation such as the unit of grade carried out the Technical Development Program of " cold " hypersonic speed, main development test is with rectangle and axisymmetric bimodal scramjet engine.1991 ~ 1998 years, carried out the checking flight test of 5 scramjet engines altogether, flight M number is the highest by 6.5, and what motor used is hydrogen fuel.Wherein the 2nd, 3 time with France cooperation, cooperate with the U.S. for the 4th, 5 time.It is the most successful it is said for the second time, and the data of acquisition are the most complete.At present, this research institute is carrying out the technical research that speed is the hypersonic aircraft usefulness scramjet engine of 6 ~ 7 times of velocities of sound, and application target is military-civil hypersonic aircraft.
The U.S. carries out scramjet engine technical research country early.The sixties begin one's study, to the eighties, one of them important achievement in research is exactly so-called bimodal motor (Dual-mode scramjet), it is a kind of medium flight Mach number (4 ~ 8) that is applicable to, the pressed engine that not only can carry out subsonic combustion but also can carry out supersonic combustion has been widened the application lower limit of scramjet engine.It is a kind of annular inlet structure, comprises two intake ducts of subsonic speed and supersonic speed, and under different flight Mach numbers and fuel equivalence ratio situation, motor realizes that automatically the mode of inferior combustion and super combustion transforms.NASA, air and naval force have the development plan of oneself at present.On March 27th, 2004, unmanned research aircraft X-43A successfully reaches the speed of M several 7 in the 2nd flight test, become flying speed in the world the fastest be the aircraft of power plant with the air breathing jet engine.Expecting 2025, is that power is main hypersonic sky and space plane with the scramjet engine, might come into operation.
Why is air speed fast not as rocket speed? because the heart of rocket (firing chamber) is bigger than the heart (firing chamber) of aircraft.Take a broad view of the development history of air breathing engine, all be that the heart (firing chamber) is little, health (fan, gas compressor, turbine, nozzle) is big, eight, after the nineties, progressed into the epoch of having only a big annular combustion chamber to rule all the land, having only the first generation turbofan engine JT3D of the use multitube can annular type combustor that Pu Hui company produces the sixties is an exception.
Pu Hui company utilizes own technological reserve on turbojet engine, has adopted very ripe J57 as the intension core-engine of new turbofan engine.JT3D has used the connular combustor of 8 burner inner liners, pushes away motor in 8 tonnes of thrusts.Boeing 707 original dress JT3C turbojet engines, compare with JT3C, the JT3D takeoff thrust increases 50%, the thrust of cruising increases 27%, the oil consumption rate that cruises reduces by 13%, and the improvement that brings to aircraft is thus: ultimate run increases by 27.6%, and rate of climb improves 110%, maximum cruise improves 8.2%, and takeoff distance reduces 29.4%.The use of JT3D is very wide, not only is contained on civilian Boeing 707, the DC-8 aircraft, and military aircrafts such as the B-52H bomber in later stage and C-141A military transportation airplane, E-3A early warning plane are also adorned the military version TF-33 motor of JT3D.
It is said the of great reputation fortune 10 big aircrafts of China's the eighties, be subjected to inspiring from the research of JT3D getting out, flew more than 100 hour, flown over several big cities.It's a great pity fortune 10 because lack leadership structure when doing two bombs and one satellite and policy input etc. multiple former thereby get down from horse, become before China does not produce big aircraft, Chinese are eternal pain in the heart.The good news is that we have had fortune 20 now.But, there has been the foreign heart (firing chamber) just not have the Chinese heart (firing chamber), key is to reproduce and the strong Chinese heart (firing chamber).
Recently, the development of various countries' aeroengine has had many new developments: CE to announce its adaptive universal engine technology, has announced that its thermal management capabilities can be managed performance with the conversion motor by the flow through air quantity of engine core part of control.Think more many by the flow of core engine, the thrust of motor is just more big, and speed is just more high; Reduce the flow of core engine, with regard to fuel saving.
According to Britain's The Daily Telegraph newspaper November 28, utilize this new technology of the scientists invention of air breathing engine company of Britain engineering company, enter the air of motor and can be in the time of centisecond be reduced to subzero 150 degrees centigrade from 1000 degrees centigrade, but also can not produce any frost.This disruptive technology is to utilize a row to make the very thin pipe of " whirlpool " shape, loads onto concentrated nitrogen and draws airborne heat, and make air be cooled to subzero 150 degree before sending into motor.New refrigeration technology will allow air breathing engine with more high power safe handling, and it is overheated can not occur, and this means that its speed can surpass per hour 2000 miles.These researchers claim, have one reusable and also more efficiently motor will reduce the cost of space flight greatly.They wish that this motor just can come into operation in 10 years.
Russia chemical industry The Automation Design office (KBKhA) claims: successfully carried out thrust in September, 2012 and be 7.5 tons new engine test, this motor provides power by liquid oxygen and LNG Liquefied natural gas.Russia and Italy are with cooperation research and development liquid oxygen LNG Liquefied natural gas motor.
Recently, China's thrust maximum Launch Vehicle Engine of new generation---120 tonnes of oxygen kerosene high pressure afterburning cycle engines are succeeded in developing, this h type engine h will be as the power system of China New Generation carrier rocket, for the great special task of countries such as manned space flight, moon exploration provides safeguard.The expert claims that this h type engine h of succeeding in developing is the high pressure afterburning cycle engine that Chinese first type has independent intellectual property right.
No matter be the high pressure afterburning, still concentrate the nitrogen cooling, improve thermal management capabilities no matter be, also be to use fresh fuel, all improving the further good condition that provides of innovating on the thermal management capabilities for us, but the constraint that we are being subjected to long-term traditional thinking and Xi to be used to fixed pattern again simultaneously, we only make an accurate selection of the break-through point, just can capture the commanding height.
Now, we are necessary the firing chamber of JT3D is done further to analyze.Achievement to JT3D should affirm that the front was done to introduce the sixth of the twelve Earthly Branches.But JT3D also has problems, and mainly is that the connular combustor of JT3D is made up of 8 burner inner liners institute that forms a circle, and has flame-transferring tube to link to each other to guarantee that the outlet gaseous-pressure of each burner inner liner is greatly extremely equal between burner inner liner and burner inner liner.Even so the gaseous-pressure within each burner inner liner also still can not be equal fully, but the small gaseous-pressure in each burner inner liner also deficiency think trouble.But in the outlet port of each burner inner liner since the combustion gas meeting that two adjacent burner inner liners spray overlap, so at the temperature of the outlet adjacent of each burner inner liner temperature height than other places.The temperature contrast of the outlet temperature field of burner inner liner brings certain infringement can for the combustion gas guider of turbine front portion, and the part that temperature is high can be accelerated ablated.Such as on the JT3D of the connular combustor that has used 8 burner inner liners, has only 1/3rd of normal blade in the life-span of its gas diversion blade of burner inner liner wake flame overlapping.So JT3D has got down from horse like this.Really can't several problems have been proposed: 1, at burner inner liner wake flame overlapping temperature height blade is accelerated ablated this problem and solve Do here? is 2, air inlet how Fen Do enters the connular combustor of 8 burner inner liners? do 3, how needs different according to thrust allow air inlet Fen Do enter the connular combustor of dozens or even hundreds of burner inner liner?
Existing aeroengine, no matter be whirlpool spray or turbofan, no matter be domestic or external, all are vat (firing chambers), not only exist the temperature height, oil consumption is big, thrust is little, part is many, speed is slow, can not raise speed significantly and the problem of speed change, more dangerous is to have potential safety hazard, in case the only large-scale combustion chamber of motor (vat) break down, often will the fatal crass.
Summary of the invention
At above deficiency of the prior art, the object of the present invention is to provide a kind of air inlet cooling, accurately divide gas, balancedly light a fire, at the uniform velocity start, become a grade acceleration, highly effective and safe, thrust vectoring, easy to operate, multi-functional turbine fan jet engine that purposes is various.
For achieving the above object, technological scheme of the present invention is:
A kind of multi-functional turbine fan jet engine, comprise: be used for to suck the fan of air, to the gas compressor of inhaled air acting, be used for lighting through second firing chamber, the turbine of the gas after the gas compressor acting and the jet pipe of the gas discharge after will burn, also comprise first firing chamber that is arranged at the described second firing chamber inlet end, be provided with the tubular shape deflagrating jar in wherein said first firing chamber and second firing chamber; The cylindrical jacket Shang Fen Do of described first firing chamber and second firing chamber is provided with the outlet of the cooling pipe of the import of cooling pipe of charged control switch and charged control switch;
Be used for to divide first flow distribution plate and second flow distribution plate of gas, the circumference of described first flow distribution plate and second flow distribution plate is provided with the hole for minute gas, and described hole is equal with the corresponding setting in tubular shape deflagrating jar position and quantity on the tubular shape deflagrating jar; The equal diameters of the diameter in described hole and tubular shape deflagrating jar;
Described first flow distribution plate and first firing chamber are combined to form the first firing chamber modules A, and described second flow distribution plate and second firing chamber are combined to form the second firing chamber module B;
The described first flow distribution plate correspondence is arranged at the inlet end of first firing chamber, the described second flow distribution plate correspondence is arranged at the second firing chamber inlet end, on described first flow distribution plate and second flow distribution plate, also be respectively arranged with position limit switch I and position limit switch II for described first flow distribution plate of rotation and second flow distribution plate, also be provided with the double-action mechanism that first flow distribution plate and second flow distribution plate are not relatively rotated between described position limit switch I and the position limit switch II;
Described second firing chamber and first firing chamber are made up of at least three layers of equally distributed several tubular shape deflagrating jar on the circumference;
Described gas compressor is connected with turbine by central shaft, and the wherein said first firing chamber modules A and the second firing chamber module B arrange with central shaft is concentric.
Described gas compressor comprises low pressure compressor and high-pressure compressor, be provided with behind the wherein said high-pressure compressor charged control switch the cooling pipe import and be connected with gas-entered passageway;
Described low pressure compressor is provided with provided with internal duct and external duct air balance switch, also is provided with provided with internal duct and external duct air balance switch on the high-pressure compressor.
The exhaust pipe of described jet pipe is provided with the movable bypassing exhaust plate of charged control rotating distance switch and fixing bypassing exhaust plate.
Further, when first layer tubular shape deflagrating jar n1 was 4 on the circumference, second layer tubular shape deflagrating jar n2 was 8, and the 3rd layer of tubular shape deflagrating jar n3 is 16.
A nearlyer step ground, when the 3rd layer of tubular shape deflagrating jar n3 was 16 on the described circumference, the move angle of the position limit switch on the described flow distribution plate was 45 degree.
The quantity of n1 is more big, and the total quantity of tubular shape deflagrating jar is just more many, and the move angle of the position limit switch on the flow distribution plate of place is just more little.
Advantage of the present invention and beneficial effect are as follows:
1, owing to adopt concentric discs flow distribution plate technology and position limit switch cooperating, realizes the air inlet cooling of motor, accurate control and the uniform distribution of air inflow, reduced the oil consumption of aircraft, produced high Zhi amount steady air flow, improved thermal management capabilities.
2, owing to adopted the n cylinder n layer of concentric pipe to divide cylinder technology, adopt the multi-cylinder to arrange, be convenient to obtain the actual parameter data, eliminated the drawback that vat of motor is difficult to obtain actual parameter data and potential safety hazard, improved the safety coefficient of aircraft.
3, owing to adopted the module polyphone technology of concentric circle pipe-type chamber, the fractional combustion circulation, the high pressure afterburning, dash than increase, can make motor by different mode of operation work, reinforcing, acceleration and the variable speed capability of motor have been increased substantially, add the adding of Thrust Vectoring Technology, on the exhaust pipe of jet pipe, be provided with the movable bypassing exhaust plate of charged control rotating distance switch and fixing bypassing exhaust plate, the direction of dividing retaining effectively to control exhaust, can make aircraft fly De Genggao, faster, more economize, farther, more skilful, better.
4, the variable cycle engine of the present invention invention at the deficiency of domestic and international available engine, has successfully solved five big problems of air inlet cooling, precisely air inlet, safe navigation, afterburning speed change, thrust vectoring, the cost performance height, thrust weight ratio is big, dash than high, oil consumption is low, voyage is far away, long service life, the safety coefficient height has dual-use wide use prospect, is rich in high market development and is worth, might finish the situation that a vat is monopolized the world, the real arrival in declaration multi-cylinder epoch.
Description of drawings
Fig. 1 is the structural representation of a kind of multi-functional turbine fan jet engine of one embodiment of the present invention;
Fig. 2 is the sectional view of first flow distribution plate among the present invention along the A-A line;
Fig. 3 is the sectional view of second flow distribution plate among the present invention along the B-B line;
Fig. 4 is the structural representation of first firing chamber among the present invention and tubular shape deflagrating jar;
Fig. 5 is the structural representation of second firing chamber among the present invention and tubular shape deflagrating jar;
Fig. 6 is movable bypassing exhaust plate among the present invention and fixing bypassing exhaust plate structure schematic representation.
Wherein, 1-fan; The 2-1 low pressure compressor; The 2-2 high-pressure compressor; 3-1 first flow distribution plate; 3-2 second flow distribution plate; The 4-central shaft; The 5-turbine; The 6-jet pipe; 7-1 first firing chamber; 7-2 second firing chamber; 8-tubular shape deflagrating jar; 9-1 position limit switch I, 9-2 position limit switch II.The 10-serial verb construction; 11-1 hangs down press provided with internal duct and external duct air balance switch; 11-2 high-pressure unit provided with internal duct and external duct air balance switch; The import of 12-1 cooling pipe, the outlet of 12-2 cooling pipe; The movable bypassing exhaust plate of 13-1; 13-2 is the bypassing exhaust plate fixedly; The automatically controlled rotating distance switch of 13-3.
Embodiment
It is prototype that aeroengines such as the present existing Taihang of China and the Kunlun all adopt turbofan engine.
The invention will be further elaborated to provide the embodiment of an indefiniteness below in conjunction with accompanying drawing.
With reference to Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 and shown in Figure 6, a kind of multi-functional turbine fan jet engine, comprise: be used for to suck the fan 1 of air, to the gas compressor 2 of inhaled air acting, be used for lighting through the second firing chamber 7-2, the turbine 5 of the gas after the gas compressor acting and the jet pipe 6 of the gas discharge after will burn, also comprise the first firing chamber 7-1 that is arranged at the described second firing chamber 7-2 inlet end, be provided with tubular shape deflagrating jar 8 in the wherein said first firing chamber 7-1 and the second firing chamber 7-2; The cylindrical jacket Shang Fen Do of described first firing chamber and second firing chamber is provided with the outlet 12-2 of the cooling pipe of the import 12-1 of cooling pipe of charged control switch and charged control switch;
Be used for dividing the first flow distribution plate 3-1 and the second flow distribution plate 3-2 of gas, the circumference of the described first flow distribution plate 3-1 and the second flow distribution plate 3-2 is provided with the hole for minute gas, and the corresponding setting with the position of tubular shape deflagrating jar 8 in described hole and quantity equate; The diameter in described hole and tubular shape deflagrating jar 8 equal diameters;
The described first flow distribution plate 3-1 and the first firing chamber 7-1 are combined to form the first firing chamber modules A, and the described second flow distribution plate 3-2 and the second firing chamber 7-2 are combined to form the second firing chamber module B;
The described first flow distribution plate 3-1 correspondence is arranged at the inlet end of the first firing chamber 7-1, the described second flow distribution plate 3-2 correspondence is arranged at the second firing chamber 7-2 inlet end, on the described first flow distribution plate 3-1 and the second flow distribution plate 3-2, also be respectively arranged with position limit switch I 9-1 and position limit switch II 9-2 for the described first flow distribution plate 3-1 of rotation and the second flow distribution plate 3-2, also be provided with the double-action mechanism that the first flow distribution plate 3-1 and the second flow distribution plate 3-2 are not relatively rotated between described position limit switch I 9-1 and the position limit switch II 9-2;
The described second firing chamber 7-2 and the first firing chamber 7-1 are made up of at least three layers of equally distributed several tubular shape deflagrating jar 8;
Described gas compressor 2 is connected with turbine 5 by central shaft 4, the wherein said first firing chamber modules A and the second firing chamber module B and central shaft 4 concentric settings;
Described gas compressor 2 comprises low pressure compressor 2-1 and high-pressure compressor 2-2, wherein be provided with behind the wherein said high-pressure compressor 2-2 charged control switch the cooling pipe import and be connected (not indicating on the figure) with gas-entered passageway;
Described low pressure compressor 2-1 is provided with provided with internal duct and external duct air balance switch 11-1, also is provided with provided with internal duct and external duct air balance switch 11-2 on the high-pressure compressor 2-2;
Described firing chamber 7 is made up of at least three layers of equally distributed some tubular shape deflagrating jar 8;
Wherein second firing chamber is identical with the first firing chamber size, and tubular shape deflagrating jar quantity is identical with the position;
The exhaust pipe of described jet pipe is provided with the movable bypassing exhaust plate 13-1 of automatically controlled rotating distance switch 13-3 and fixing bypassing exhaust plate 13-2.
Preferably, when first layer tubular shape deflagrating jar n1 was 4, second layer tubular shape deflagrating jar n2 was 8, and the 3rd layer of tubular shape deflagrating jar n3 is 16; In like manner, first layer tubular shape deflagrating jar n1 also can be 3 tubular shape deflagrating jars, and then second layer n2 just is 6 tubular shape deflagrating jars, and the 3rd layer of n3 just is 12 tubular shape deflagrating jars, can also continue to add combustible zone n4, n5
Preferably, when described the 3rd layer of deflagrating jar n3 was 16 tubular shape deflagrating jars, the move angle of the position limit switch 9 on the described flow distribution plate 3 was 45 degree.The deflagrating jar that during original state is outermost one deck combustible zone n3 is connected and burning, when position limit switch is spent to right rotation 45//2=22.5, the cylinder that is n2 layer and n3 layer is connected and burning, be the turbofan form this moment, when position limit switch to anticlockwise 45//2=22.5 degree, when continuing to spend to anticlockwise 45//2=22.5, namely the cylinder of n1, n2 layer and n3 layer is connected also burning again, all connect this moment, and it is maximum that speed reaches;
Each tubular shape deflagrating jar all contains hydraulic pressure oil nozzle and spark plug, when air passes intake duct, make air be pressed into gas compressor by fan, the flabellum blade rotation of gas compressor is done work to air-flow, the pressure and temperature of air-flow is raise, the back of high pressure draught cooling subsequently enters the tubular shape deflagrating jar by flow distribution plate, the hydraulic pressure oil nozzle ejection fuel oil of tubular shape deflagrating jar, spark ignitor produces high temperature and high pressure gas simultaneously, discharge backward, high-temperature high-pressure fuel gas flows through turbine backward, and can expand in turbine in the part is converted into mechanical energy, drives the turbine rotation, because turbine and gas compressor are contained on same the central shaft, the energy that aircraft requires the maximum thrust of raising motor to extract from turbine is converted into shaft work, drives the gas compressor rotation, thereby compress the air that enters repeatedly, and very big MAF is provided; The part high-temperature high-pressure fuel gas is discharged from jet nozzle with high speed through jet pipe backward from turbine.Thereby produce the reaction thrust to motor, order about aircraft and fly forward by certain orientation through the bypassing exhaust plate.
For reaching technological scheme above-mentioned purpose of the present invention, must design from eight aspects such as cooling, branch gas, branch cylinder, speed change, igniting, reinforcing, module polyphone, thrust vectorings.
Cooling.The one, as previously mentioned, high temperature has not only diluted the density of inlet air, has reduced the quality of inlet air flow, has increased oil consumption, but also can destroy cylinder body and blade, influences engine life, therefore must suitably lower the temperature to motor.The 2nd, according to ram effect, when speed increased, momentum drag can make net thrust reduce.When the inlet pressure increase, current density and flow quality are all increased to some extent on the one hand, make the increase of jet pipe pressure ratio, and then gross thrust is increased.The in addition rising of aspect press temperature will improve the gas flow temperature of import gas compressor.When the engine intake temperature improved, the density of inlet air reduced, and flow quality reduces, and the energy that can add in the gas flow is also reducing, and thrust also can reduce, and the rising of ambient temperature sharply descends thrust.Notice specific thrust and unit fuel consumption rate have opposite characteristic with the increase of ambient temperature.Therefore, realize reinforcing, must suitably lower the temperature.The 3rd, concentrate the nitrogen cooling successful story is provided.The new refrigeration technology of Britain will allow air breathing engine with more high power safe handling, and it is overheated can not occur, and its speed can surpass per hour 2000 miles, can have one reusable and also more efficiently motor will reduce the cost of space flight greatly.Say the necessity of the cooling that is over, retell the possibility of cooling.How to carry out cooling? the one, the conveying that the admission line before module flow distribution plate and firing chamber installs charged control switch additional concentrates nitrogen cooling pipe and is connected leads to (not indicating on the figure).The 2nd, can C, D can also be arranged at each modules A, B(, C, D are after A, B, do not indicate on the figure) the cylindrical jacket of firing chamber on open two aperture 12-1,12-2, the conveying of installing charged control switch additional concentrates pipe and the connection of nitrogen cooling, in case of necessity as carrying the pore that concentrates the nitrogen cooling to use, wherein, 12-1 is the import of cooling pipe, and 12-2 is the outlet of cooling pipe.These two kinds of ways mode of operation during for turbofan can, when mode of operation is whirlpool spray and punching press, can use.Come with preparation, available also can, the need during with preemergency.The 3rd, C, D module also can be used as to carry and concentrate the use of nitrogen cooling pipeline.The 4th, because best pressure ratio is with the by-pass air duct air-flow stagnation pressure that equates to be arranged in the low-pressure turbine outlet, at this moment need to open the provided with internal duct and external duct balance cock 11-2 of low pressure compressor 11-1 and high-pressure compressor, both increased bypass ratio, be conducive to realize that the low-pressure turbine outlet has the stagnation pressure that equates with the by-pass air duct air-flow, suitably reduced the engine intake temperature again.
Divide gas.Because flow distribution plate and firing chamber are the concentric disjunctor of disk (hollow) structures of uniqueness with central shaft, can control by the automatically controlled rotating distance switch of flow distribution plate, precisely control the air inlet area, make the high quality air-flow enter the tubular shape deflagrating jar (firing chamber) of appointment.Divide pneumoelectric control rotating distance switch to realize that (absolute value is 0, and this time-division pneumoelectric control rotating distance switch is in closed condition from all layering tubular shape deflagrating jar area of contact minimums.), to the accurate control that moves in circles between all layering tubular shape deflagrating jar area of contact maximums, the air inlet area is more big, and high pressure ratio is just more little, and the air inlet area is more little, and high pressure ratio is just more big.Different with the west thinking is that this case is started with from reducing the suction port area, realizes accurately control air inlet, has just improved high pressure ratio, and economical.Increasing the effective method of thrust is exactly by increasing the mass flow rate of motor.It is emphasized that, effect by the flow distribution plate of automatically controlled rotating distance switch control is outstanding: the one, under the effect of flow distribution plate, inlet total pressure distortion can not take place, inlet swirl flow dis tortion can not take place, the even situation of air inlet stagnation temperature Bu Zhuo can not take place, will produce high Zhi amount steady air flow, improve thermal management capabilities.The 2nd, the time-division stream plate air inlet area that begins to light a fire is more little, and the tubular shape deflagrating jar is lighted a fire just more high into the shop rate.Owing to go into the shop rate and improved, solved the ignition problem of tubular shape deflagrating jar.The 3rd, solved the problem that JT3D exists; owing to take with the function division at interval of layer tubular shape deflagrating jar; implementation with interlayer every semi-circle tubular deflagrating jar burning; with interlayer every the burning that misfires of second half tubular shape deflagrating jar; outlet port at each burner inner liner; the combustion gas of having avoided two adjacent burner inner liners to spray effectively overlaps, and has protected turbine blade effectively, has prolonged the working life of turbine blade.The 4th, air inlet has had accurate control to main duct owing to the module flow distribution plate, provided with internal duct and external duct air balance switch handle control on low compressor and the high pressure mechanism of qi is arranged again, can precisely control the provided with internal duct and external duct air balance, can make motor under different environmental conditionss, according to the difference of executing the task, by different mode of operation (turbofan, whirlpool spray and the punching press) proper functioning of starting, add controlling of the multifactor cloud computing of computer and digital control panel, thereby make aircraft possess the adaptivity function, become a variable cycle engine.
Divide cylinder.Reforming key point is placed on outside the firing chamber different with the west thinking, I am placed on reforming key point on the firing chamber.Divide what tubular shape deflagrating jars suitable actually? how many be diameters of tubular shape deflagrating jar? how much be length of tubular shape deflagrating jar? that same tubular shape deflagrating jar or big or small tubular shape deflagrating jar mix arrangement? polyphone or and company? the how oiling of tubular shape deflagrating jar? how to light a fire? the present invention proposes the Design Conception of the concentric disjunctor variable cycle engine of disk: on hollow concentric disjunctor disk, equally distributed several tubular shape deflagrating jars (small-sized firing chamber) of being controlled by minute n cylinder n layer 4 retaining become radial arrangement to combine.Because the circular hole of described first, second flow distribution plate and diameter, structure and the position identical (except the position limit switch) of first, second firing chamber tubular shape deflagrating jar; Described first flow distribution plate and first firing chamber form a modules A; Described second flow distribution plate and second firing chamber form a module B.When we having solved in the branch gas problem, simultaneously, also just solved branch cylinder problem.The principle of dividing cylinder, layering and branch retaining: must be with one heart+equidistant+and connect+outer tubular shape deflagrating jar quantity multiplication (or quantity equates)+4 retaining.The endless tube of tubular shape deflagrating jar is wanted high temperature high voltage resistant in the technological process, the endless tube inwall adopts the THE BARCHAN DUNE VORTEX technology to increase surperficial area of contact, reserve the position of oil nozzle and spark plug earlier, after it is burn-on, the installation of tubular shape deflagrating jar is carried out one by one successively by the order of n1, n2, n3, n4, surface and the cylindrical jacket of the tubular shape deflagrating jar of burn-oning again at last.Because first, second flow distribution plate has the branch gas position limit switch of carrying out interlock, can realize that (absolute value is 0, and this time-division gas position limit switch is in closed condition from tubular shape deflagrating jar area of contact minimum.) to the accurate control that moves in circles between the tubular shape deflagrating jar area of contact maximum, like this, divide cylinder just to solve the oil consumption problem, this is one.When n1 is 8, n2 is 16, n3 is 32, n4 just is 64 ... in numerous tubular shape deflagrating jar (little cylinder), just in case the tubular shape deflagrating jar of Ge Do (little cylinder) breaks down, can not occur fatal crass's tragedy yet and take place, this is two.Simultaneously, because numerous tubular shape deflagrating jar (little cylinder) has been arranged, just established good basis for we solve the speed change problem, this is three.
Speed change.How does problem at former aeroengine can not raise speed significantly raise speed significantly or exponentially? mentality of designing of the present invention is by position limit switch as required, divides air inlet, igniting and the discharge of all tubular shape deflagrating jars in the 4 retaining management and control retainings.Can only open the position limit switch of 1 level at every turn.For example: open the 1st retaining, the tubular shape deflagrating jar of outermost one deck is started working; Open the 2nd retaining, the tubular shape deflagrating jar that outermost is two layers is started working; Open the 3rd retaining, the tubular shape deflagrating jar that comes back to outermost one deck is started working; Open the 4th retaining, the tubular shape deflagrating jar of structure at all levels is all started working; Oppositely return then.Like this, just successfully realized speed change.
Igniting.For anti-turbulent flow takes place, igniting must be carried out by symmetrical equilibrium.Because the tubular shape deflagrating jar is too much, can adopt igniting-throttle interlock technology to each tubular shape deflagrating jar, to contact with a wire between the igniting-throttle of each tubular shape deflagrating jar, when occurring to light a fire, will close tubular shape deflagrating jar throttle because circuit is obstructed automatically.All increase by 1 standby spark plug separately again at all tubular shape deflagrating jar afterbodys on the disk, carry out dual ignition (punching press pattern).The igniting of tubular shape deflagrating jar afterbody according to flight environment and task needs, can be lighted a fire, and also can misfire.The benefit of doing like this is: even Ge Do tubular shape deflagrating jar breaks down, influence the aircraft operation, the tragedy that the fatal crass more can not occur takes place also not too largely.
Afterburning.At first, because the One's name is legion of tubular shape deflagrating jar, the quantity of using position limit switch to increase the tubular shape deflagrating jar has just realized reinforcing.Open whole tubular shape deflagrating jar switches and just give power more.Secondly, use to become cylinder technology, increase and increase length and the capacity of tubular shape deflagrating jar cylinder body, also can realize reinforcing.Again, the mode of operation of more reengining (turbofan, whirlpool spray and punching press) can realize reinforcing better.
The module polyphone.When similar tubular shape deflagrating jar modules A, B, C, when D contacts, the concept of first and second firing chambers is relative, can transform.Just often the A module is that first flow distribution plate adds the first firing chamber 3-1+7-1, and the B module is that second flow distribution plate adds the second firing chamber 3-2+7-2, and the C module can be used as tail pipe burner, and the D module can become breather line.If the A module is injured in fight, B, C module can be used as first and second firing chambers, and the D module becomes breather line.When A, B module were first flow distribution plate and the first firing chamber 3-1+7-1 and second flow distribution plate and the second firing chamber 3-2+7-2, C, D module also can be made air-flow path and use, or standby as carrying the pipeline that concentrates the nitrogen cooling.My theory is that each tubular shape deflagrating jar of each module will be accomplished: complete (fuel conducting tube, cooling conducting tube, oil nozzle and igniter etc.), come with preparation, available also can, the need during with preemergency.The benefit of module polyphone is a lot: the one, and the function conversion.Each tubular shape deflagrating jar can be worked as firing chamber usefulness, also can only work as air-flow path usefulness, and each module and each tubular shape deflagrating jar can be realized taking turns to operate, and increases working life.Do seeming waste like this, but from protect expensive aircraft, from the more expensive pilot of protection, be necessary fully.Simultaneously, the function that has increased motor owing to C, D module is changed, and is necessary especially.The 2nd, oil consumption is successively decreased, and thrust increases progressively.If being the oil consumption of 1, B module, the oil consumption of A module just might just might just might be 0.1 for the oil consumption of 0.2, D module for the oil consumption of 0.5, C module; And thrust promotes successively significantly as tail pipe burner between A, B, C, D module.The 3rd, because might be by pilot and computer to the flight environment of outside (highly, brightness, wind-force, wind direction), enemy's situation (type, distance, speed, angle), task (is destroyed, forced landing) and the situation (performance of self motor, means) etc. multifactorly carry out the cloud computing automatic control, several similar tubular shape deflagrating jar modules owing to might contact, can carry out the fractional combustion circulation as rocket, the high pressure afterburning, increase to dash than, thrust (in theory) can be realized from 0 to infinitely-great acceleration, can realize the deceleration from infinity to 0 again, (in theory) realized from 0 to infinitely freely circulating the infinity, this is even more important concerning space shuttle.
Thrust vectoring.Thrust vectoring is a comprehensive very strong technology, and it comprises thrust steering nozzle technology and airframe/propelling/control system integrated technique.Do not adopt the aircraft of Thrust Vectoring Technology, the jet flow of motor all is with the dead in line of aircraft, the thrust of generation also along axis forward, the thrust of motor just is used for overcoming the suffered resistance of aircraft and providing aircraft required power in this case.And the aircraft of employing Thrust Vectoring Technology then is by nozzle deflection, and the thrust of utilizing motor to produce obtains unnecessary control moment, realizes the attitude control of aircraft.Its outstanding feature is that control moment and motor are closely related, and be not subjected to the influence of the attitude of aircraft own, can guarantee aircraft at low speed, the additional manipulation moment of utilizing thrust vectoring to provide during a few near failure of big angle of attack maneuvering flight and primary control surface is controlled air maneuver.The vectored thrust technological merit is a lot, it can provide the post stall maneuver ability is maneuverability under the big angle of attack, F/A-22, outstanding opportunity of combat such as Su-37 is exactly to use the masterpiece of thrust vectoring, the emulation air battle was once done with X-31 validator and F/A-18 by the U.S., military success is 32:1 as a result, its advantage has some idea of, and use the fighter of thrust vectoring all to have good STOL ability, Thrust Vectoring Technology has improved the control efficiency of aircraft in addition, can make the pneumatic control of aircraft look like vertical fin and vertical tail dwindles greatly, can alleviate aircraft weight, improve the stealthy ability of aircraft.How to accomplish thrust vectoring? the bypassing exhaust plate of charged control rotating distance switch is installed in this case design additional in the jet pipe exhaust pipe, the regulation and control exhaust airstream flows to, with jet pipe moving vane close fit, and conversion and control discharge directions (see figure 6).The bypassing exhaust plate is made of with one heart fixedly bypassing exhaust plate 13-2 and movable bypassing exhaust plate 13-1, and 13-2 is identical with the 13-1 diameter, and the distance of concentric equates.Wherein, fixedly bypassing exhaust plate 13-2 equidistantly is arranged on the bypassing exhaust plate by several tap hole equilibriums, and is fixed on the jet pipe exhaust pipe; Movable bypassing exhaust plate 13-1 by be less than on the fixing bypassing exhaust plate 13-2 tap hole also with it equilibrium equidistantly be arranged on the bypassing exhaust plate, the same fixedly some tap hole equal diameters of bypassing exhaust plate 13-2 (except the automatically controlled rotating distance switch) of the tap hole of movable bypassing exhaust plate 13-1, running orbit is identical, with automatically controlled rotating distance switch 13-3 control rotating distance, can carry out 360 degree rotations.The invention will be further elaborated to provide the embodiment of an indefiniteness below in conjunction with accompanying drawing.When fixing bypassing exhaust plate 13-2 equidistantly is arranged on the bypassing exhaust plate by 8 tap hole equilibriums, and be fixed on the jet pipe exhaust pipe; Movable bypassing exhaust plate 13-1 is by 3 adjacent equal diameters, the identical tap hole of running orbit is formed, 360 degree rotating distances by automatically controlled rotating distance switch 13-3 control activity bypassing exhaust plate 13-1, an every mistake fixedly tap hole on the bypassing exhaust plate 13-2 can be used as a retaining, first grade is that three holes shown in Figure 6 are original state downwards, if rotation counterclockwise to the right, this moment is if must get back to first grade of initial position left, and then be rotated clockwise to predetermined gear, be divided into 8 retaining conversion and control discharge directions, along with the angle of 3 tap holes of movable bypassing exhaust plate 13-1 clockwise or the inhour rotation change, just formed certain clockwise or counterclockwise vectored thrust, the aircraft gearshift conversion different flight path of just following one's bent up and down, this is conducive to improve flexibility and the stealthy performance of aircraft.
Any advanced person's invention design all will be satisfied real needs, is foundation with a series of test data, guarantees with advanced person's technology, advanced material, part, outstanding assembling reliably, just might achieve success at last.I believe, by national efforts, China's 5 multikilowatt all solid state lasers of Chinese titanium alloy 3D printing technique+advanced person of firepower change system+advanced person of the multifactor cloud computing control system of computer+advanced person of Big Dipper navigational satellite system+advanced person of radar equipment+advanced person of digital automatically controlled flight control system+advanced person of advanced motor+advanced person ... we are possibility " bend is overtaken other vehicles " fully, can Chinese aircraft surmounts the date of taking the lead in race also be far away?
The multi-cylinder design concept of motor is equally applicable to turbojet engine and pressed engine among the present invention, and the prototype that can be used as motor carries out corresponding change, comprises in the present invention equally.
These embodiments are interpreted as only being used for explanation the present invention and are not used in restriction protection scope of the present invention.After the content of having read record of the present invention, the technician can make various changes or modifications the present invention, and these equivalences change and modify and fall into claim of the present invention institute restricted portion equally.
Claims (5)
1. multi-functional turbine fan jet engine, comprise: be used for to suck the fan (1) of air, to the gas compressor (2) of inhaled air acting, be used for lighting through second firing chamber (7-2), the turbine (5) of the gas after the gas compressor acting and the jet pipe (6) of the gas discharge after will burn, it is characterized in that: also comprise first firing chamber (7-1) that is arranged at described second firing chamber (7-2) inlet end, be provided with tubular shape deflagrating jar (8) in wherein said first firing chamber (7-1) and second firing chamber (7-2); The cylindrical jacket Shang Fen Do of described first firing chamber and second firing chamber is provided with the outlet (12-2) of the cooling pipe of the import (12-1) of cooling pipe of charged control switch and charged control switch; The exhaust pipe of described jet pipe (6) is provided with the movable bypassing exhaust plate (13-1) of charged control rotating distance switch (13-3) and fixing bypassing exhaust plate (13-2);
Be used for dividing first flow distribution plate (3-1) and second flow distribution plate (3-2) of gas, described first flow distribution plate (3-1) and second flow distribution plate (3-2) are provided with the hole for minute gas, and described hole equates with the corresponding setting in the position of tubular shape deflagrating jar (8) and quantity; The diameter in described hole and tubular shape deflagrating jar (8) equal diameters;
Described first flow distribution plate (3-1) correspondence is arranged at the inlet end of first firing chamber (7-1), described second flow distribution plate (3-2) correspondence is arranged at second firing chamber (7-2) inlet end, on described first flow distribution plate (3-1) and second flow distribution plate (3-2), also be respectively arranged with position limit switch I (9-1) and position limit switch II (9-2) for rotation described first flow distribution plate (3-1) and second flow distribution plate (3-2), also be provided with the double-action mechanism (10) that first flow distribution plate (3-1) and second flow distribution plate (3-2) are not relatively rotated between described position limit switch I (9-1) and the position limit switch II (9-2);
Described second firing chamber (7-2) and first firing chamber (7-1) are made up of at least three layers of equally distributed several tubular shape deflagrating jar (8) on the circumference;
Described first flow distribution plate and first firing chamber are combined to form the first firing chamber modules A, and described second flow distribution plate and second firing chamber are combined to form the second firing chamber module B;
The cylindrical jacket Shang Fen Do of the described first firing chamber modules A and the second firing chamber module B is provided with the outlet (12-2) of the cooling pipe of the import (12-1) of cooling pipe of charged control switch and charged control switch;
Described gas compressor (2) is connected with turbine (5) by central shaft (4), the wherein said first firing chamber modules A and the second firing chamber module B and the concentric setting of central shaft (4).
2. multi-functional turbine fan jet engine according to claim 1, it is characterized in that: described gas compressor (2) comprises low pressure compressor (2-1) and high-pressure compressor (2-2), be provided with behind the wherein said high-pressure compressor (2-2) charged control switch the cooling pipe import and be connected with gas-entered passageway.
3. multi-functional turbine fan jet engine according to claim 2, it is characterized in that: described low pressure compressor (2-1) is provided with provided with internal duct and external duct air balance switch (11-1), also is provided with provided with internal duct and external duct air balance switch (11-2) on the high-pressure compressor (2-2).
4. multi-functional turbine fan jet engine according to claim 1, it is characterized in that: when first layer tubular shape deflagrating jar n1 was 4 on the circumference, second layer tubular shape deflagrating jar n2 was 8, and the 3rd layer of tubular shape deflagrating jar n3 is 16.
5. multi-functional turbine fan jet engine according to claim 4 is characterized in that: when the 3rd layer of tubular shape deflagrating jar n3 was 16 on the described circumference, the move angle of the position limit switch (9) on the described flow distribution plate (3) was 45 degree.
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| CN104373205A (en) * | 2013-08-16 | 2015-02-25 | 袁丽君 | Novel engine |
| CN105484898A (en) * | 2015-12-25 | 2016-04-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Mode switching device of variable cycle engine |
| CN106368851A (en) * | 2016-09-13 | 2017-02-01 | 中国民用航空飞行学院 | Multi-fan propelling device |
| CN107269395A (en) * | 2016-03-30 | 2017-10-20 | 通用电气公司 | Auxiliary flow path for adjusting flow distortion in gas-turbine unit |
| CN108518673A (en) * | 2018-04-25 | 2018-09-11 | 大连恒通和科技有限公司 | Vortex-spraying type combustor |
| CN109460628A (en) * | 2018-12-14 | 2019-03-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of air intake duct and the cooperative flow matches appraisal procedure of engine |
| CN113028449A (en) * | 2021-02-26 | 2021-06-25 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Streamline fuel flow distribution disc of fuel gas generator |
| CN113677880A (en) * | 2019-04-17 | 2021-11-19 | 赛峰飞机发动机公司 | Method for using an air intake duct of a turbojet engine nacelle during a thrust phase and a thrust reversal phase |
| CN114878175A (en) * | 2022-04-15 | 2022-08-09 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous adjusting mechanism of inner and outer culvert diversion exhaust system |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
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| CN113028449B (en) * | 2021-02-26 | 2023-03-17 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Streamline fuel flow distribution disc of fuel gas generator |
| CN114878175B (en) * | 2022-04-15 | 2024-02-23 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous regulating mechanism of inner culvert and outer culvert split-flow exhaust system |
| CN114878175A (en) * | 2022-04-15 | 2022-08-09 | 中国航发沈阳发动机研究所 | Outer culvert area synchronous adjusting mechanism of inner and outer culvert diversion exhaust system |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
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