CN109899177A - Multicore scheming band after-burner turbofan aeropropulsion system and aircraft - Google Patents
Multicore scheming band after-burner turbofan aeropropulsion system and aircraft Download PDFInfo
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Abstract
The present invention changes the mentality of designing of existing jet-propelled turbofan aero-engine, using two to rotary fan to increase air-breathing and charging efficiency, using the whirlpool Duo Tai axis aero-engine as core engine；The power of engine is substantially improved in a short time using augmentor；It only allows a core engine to work by the control of clutch or more core engines is allowed to work at the same time；Big-flow high-pressure air-flow spirt pressure chamber, pressure chamber is allowed to become the buffer that each nozzle assembly sprays air-flow, become the muffler of abatement fan running, fuel oil explosive combustion noise, extends the benefit that fuel oil increases fuel oil in the burning time of aircraft interior；The throughput and jet direction that let us can be sprayed by each vector nozzle that open and close and adjusting are located at around aircraft, are connected to pressure chamber, increase the simplification that aircraft manipulates；Multicore scheming band after-burner turbofan aeropropulsion system and the aircraft of maximum bypass ratio, most fuel-efficient, minimum noise in the world are creatively invented.
Description
Technical field
The invention belongs to aircraft jet engine correlative technology field, in particular to a kind of multicore scheming band afterbunring
Room turbofan aeropropulsion system and aircraft.
Background technique
Currently, well known jet-propelled Convertiplane currently in use is Britain's " sparrow hawk formula " and the U.S. " F-35 ", Britain
Engine used in " sparrow hawk formula " jet-propelled Convertiplane is world-famous " flying horse " turbofan aero-engine；And the U.S.
" F-135 " aero-engine used in the jet-propelled Convertiplane of F-35 is stealthy by the state-of-the-art F-22 bird of prey of U.S. army
" F-119 " turbofan aero-engine of opportunity of combat converts, and such aircraft jet engine is clearly present the following
Shortcoming:
(1) F-35 jet-propelled Convertiplane in the U.S. uses the fanjet of small bypass ratio, " the F- that it is used
The bypass ratio of 135 " turbofan aero-engines only has 0.3, although the state of taking off vertically can also in the middle part of aircraft to turn rise
Power fan component sprays lift of the air-flow as front support aircraft, in a disguised form increases the bypass ratio of engine, but normally flying
Under row state, the phenomenon that but causing excessive oil consumption since bypass ratio is too low, substantially reduces the radius of aircraft and big
Width increases routine use cost.
(2) there are four nozzles for the jet-propelled Convertiplane installation of Britain " sparrow hawk formula ", send out respectively from " flying horse " turbofan aviation
It is drawn out to two rotatable nozzles of front fuselage after the drawing fan of motivation and is divided into the two of rear end by the jet pipe of engine
A rotatable nozzle.Low-temperature airflow after drawing fan is sprayed by two nozzles of front end, the high temperature that nozzle sprays
Air-flow is then divided into two strands of two nozzles by rear end and sprays, and is aircraft by the injection direction that four nozzles of rotation change air-flow
The thrust of lift and flight forward is provided.When aircraft engine change power, aerial flow perturbation, imitate interference etc. because
When element causes the posture of aircraft to change, the thrust of four nozzles in front and back will will appear fluctuation, to cause aircraft
Corresponding variation occurs for posture, and pilot is difficult to the phenomenon that effectively controlling.It will be by controlling, changing engine large flow-rate gas stream
Injection direction and injection flow are able to maintain aircraft and steadily suspend in the sky or from the state of taking off vertically smoothly mistake
Spend regular flight condition be it is extremely difficult, This Is England " sparrow hawk formula ", and jet-propelled Convertiplane is difficult to the original manipulated
Cause.Therefore, its steerable system is sufficiently complex, and the maneuvering capability and respond requirement to pilot are very high, and this opportunity of combat is simultaneously
It is not that common opportunity of combat pilot can drive, it is necessary to those pilots the most outstanding are selected, using long-term stringent
Training could drive this jet-propelled Convertiplane, although the requirement to pilot is so stringent, Britain's " sparrow hawk formula " flies
The crash ratio of machine is still far higher than common jet plane.It sprays the front and back of the jet-propelled Convertiplane of U.S. F-35
Although mouth design has very big difference with Britain " sparrow hawk formula " aircraft, in addition using modern advanced computer control technology to each nozzle
Component is controlled, good than Britain " sparrow hawk formula " opportunity of combat to the manipulation of attitude of flight vehicle in vertical lift and hovering stage
More but ununified due to the air-flow of each nozzle assembly ejection buffer units, still unavoidable front and back nozzle assembly
Thrust fluctuates, so that the posture of aircraft be caused to be difficult to the case where manipulating.Therefore, the reaction power system of this two kinds of aircrafts
System be not appropriate for using the ordinary people as automobile can drive it is jet-propelled can be among vertical translation aircraft.
(3) Britain " sparrow hawk formula " and the jet-propelled Convertiplane of the U.S. F-35 noise and hair that in flight, fan is generated
The huge noise that motivation fuel oil explosive combustion generates all is to be passed directly to outside, is not provided with effective sound arrester, therefore, this
Two kinds of reaction power systems are not appropriate for requiring low noise, the jet-propelled of shuttle flight can be vertically moved up or down among city
Aircraft uses.
Summary of the invention
The technical problem to be solved by the present invention is to how overcome above-mentioned every defect of existing aircraft jet engine, this
The first purpose of invention be to provide it is a kind of be easy to manufacture and cheap, low noise and energy conservation and environmental protection, allow installation this
The multicore scheming band after-burner turbofan aviation power system that the aircraft of kind engine is easy manipulation, ordinary people can drive
System.
In order to overcome existing technical deficiency, main technical schemes of the invention are as follows: a kind of multicore scheming band afterbunring
Room turbofan aeropropulsion system, which is characterized in that passed including drawing fan, drawing fan transmission shaft, force(d) (draft) fan, force(d) (draft) fan
Moving axis, uni-drive gear box, reinforcing fuel nozzle, after-burner, clutch, power transmission shaft, several whirlpool axis aero-engines,
Engine charge pipeline, engine exhaust conduit, pressure chamber and several vector nozzle assemblies；The vector nozzle assembly is (described
Vector nozzle assembly has applied for another patent of invention: " novel jet aero-engine vector nozzle and aero-engine ",
Application number: 201810762795.8), including the connection pressure chamber, be mounted on it is jet-propelled can vertical translation aircraft it is (described to fly
Row device has applied for another patent of invention: " jet-propelled to be vertically moved up or down airborne aircraft and new aeropropulsion system ") around
Rear middle nozzle assembly, rear left nozzle assembly, rear right nozzle component, front left nozzle assembly, front right nozzle assembly；The driving cog
Force(d) (draft) fan transmission gear shape in roller box is that cone, centre have a cylindrical space, the force(d) (draft) fan transmission
Axis is also that centre has a cylindrical space and is fixedly connected with the force(d) (draft) fan transmission gear, in the force(d) (draft) fan transmission shaft
Between cylindrical space diameter be equal to the force(d) (draft) fan transmission gear mediate cylindrical space diameter, be greater than the air-breathing wind
Fan the outer dia of transmission shaft；The drawing fan transmission shaft passes through the hollow force(d) (draft) fan transmission shaft, the pressurization wind
The cylindrical space for fanning transmission gear is also the air-breathing wind of cone shape in the drawing fan and the uni-drive gear box
Fan transmission gear is fixedly connected；Power transmission gear in the uni-drive gear box is also cone shape, the whirlpool axis
Aero-engine is connect by the clutch, the power transmission shaft with the power transmission gear；The whirlpool axis aviation hair
The shaft power of motivation rotation output is rotated by the power transmission gear drives the force(d) (draft) fan transmission gear and the suction
Air fan transmission gear is counter-rotation, drives the air-breathing by the drawing fan transmission shaft and the force(d) (draft) fan transmission shaft
Fan, the force(d) (draft) fan are counter-rotation simultaneously, suck simultaneously pressurized air；The engine charge pipeline is connected to the whirlpool axis boat
The air inlet of empty engine and the force(d) (draft) fan rear portion, provide for the whirlpool axis aero-engine and are pressurized through the force(d) (draft) fan
High pressure fresh air afterwards；The engine exhaust conduit be connected to the whirlpool axis aero-engine exhaust outlet and the pressure
Chamber discharges into the high-temp waste gas that the whirlpool axis aeroengine combustor buring is crossed in the pressure chamber；The reinforcing fuel nozzle is fixed
Be mounted on the uni-drive gear box rear portion, the after-burner be located at the reinforcing fuel nozzle rear portion and with the pressure chamber
Fixed connection；The pressure chamber is mounted on the bottom of the aircraft, as the load-bearing chassis of the aircraft, becomes aircraft
One load-bearing support member of fuselage；The vector nozzle assembly is mounted on aircraft bottom surrounding, the fixed connection pressure
Chamber.
The multicore scheming band after-burner turbofan aeropropulsion system as a preferred technical solution, passes through institute
It states drawing fan, force(d) (draft) fan sucking and pressurized air, pressure-air and the pressure is flowed by the after-burner
In chamber, then by being mounted on aircraft bottom surrounding, the fixed several vector nozzle assemblies for being connected to the pressure chamber
Outside ejection machine, thrust, lift are provided for the aircraft；The aircraft take off vertically, landing phases, the vector nozzle
Component sprays downwards air-flow, provides lift, thrust for the aircraft, haves a wide reach in the formation of aircraft bottom surrounding
Airflow supports face；In the cruising level flight stage, the vector nozzle assembly of the aircraft sprays air-flow backward, flies to be described
Row device provides thrust, forms the air-flow to have a wide reach at the rear portion of the aircraft and pushes face；Each vector nozzle assembly,
Have the function of adjusting and sprays throughput size or unlatching, closes ejection air-flow；The vector nozzle assembly, is fitted into
Air-flow rudder face can enable it that can swing 60 ° as needed, spray the injection direction of air-flow to the left, to the right to change；Installation
In the vector nozzle assembly of the aircraft, can be needed by specific, enable its can be rotated upwards from level orientation 15 ° and
105 ° are rotated down, so that changing these described nozzle assemblies sprays the upper and lower of air-flows, left and right directions；It can also be needed by specific,
Enable its can only downward jet-stream wind, can not change spray air-flow up and down direction, only can be changed spray air-flow left and right directions；Or
Person is needed as specific, enable its only can jet-stream wind backward, can not change spray air-flow up and down, left and right directions.
Core engine of several civilian whirlpool axis aero-engines as dynamical system is used as a preferred technical solution,
Power is provided for the aircraft.Due to the civilian whirlpool axis aero-engine for providing power for helicopter it is cheap, it is light-weight,
Performance is stable and power is abundant, it is often more important that civilian whirlpool axis aero-engine is readily available on the market, is little affected by
The limitation of appropriate authorities, the present invention have creatively used core of the more whirlpool axis aero-engines as dynamical system
Machine, the after-burner, the pressure chamber and vector nozzle assembly composition multicore scheming band after-burner turbofan navigate
Lost motion Force system, the inexpensive property of let us mass production it is excellent it is described it is jet-propelled can vertical translation aircraft be possibly realized.
As a preferred technical solution, by using two to rotary fan to increase air-breathing and charging efficiency, with the whirlpool
Axis aero-engine is as core engine to save fuel oil；The more whirlpool axis aero-engines pass through the clutch and the biography
Movable tooth roller box is connected, and every whirlpool axis aero-engine can be controlled by the open and close of the clutch in dynamical system
Disembark and run, entire dynamical system can be allowed only to run the whirlpool axis aero-engine or the more whirlpool axis
Aero-engine is run simultaneously, drives the drawing fan and the force(d) (draft) fan opposite direction rotating by the uni-drive gear box,
The large flow-rate gas stream of cryogenic high pressure, then each vector nozzle sets by being connected to the pressure chamber are provided to the pressure chamber
Part sprays air-flow to outside and generates thrust, forms a set of bypass ratio and is more than 20, sprays outside the aircraft when not opening augmentor
The jet-propelled turbofan aeropropulsion system of superelevation bypass ratio of the gas flow temperature in portion lower than 100 degrees Celsius, green energy conservation.
The whirlpool axis aero-engine is sucked fresh by the engine charge pipeline as a preferred technical solution,
Air is from two to the pressure-air introduced after rotary fan, pressure is 2.5atm-3atm after being pressurized, therefore the whirlpool axis aviation
The power that engine generates will be than being mounted on pure helicopter, the same engine directly from external suction pressure for 1atm air
20% is increased above, just as installing the automobile engine of turbo charging installation additional, the power of generation will be than same engine
Increase above 20%.
The bypass ratio due to multicore scheming with after-burner turbofan aeropropulsion system is super as a preferred technical solution,
The gas flow temperature of the aircraft exterior is sprayed when crossing 20, not opening augmentor lower than 100 degrees Celsius, when starting augmentor,
The high pressure draught spirt great amount of fuel oil of the reinforcing fuel nozzle into the after-burner, allows the height for spraying the aircraft
Pressure gas stream substantially heats up, and the thrust of dynamical system output is also significantly increased；Due to fanjet (such as the duct of low bypass ratio
Than the modern combat aircraft engine for 0.3) in the case where not starting augmentor, dynamical system sprays the air-flow of aircraft
Temperature is about 1000 degrees Celsius, and every 100 degrees Celsius of the promotion of the gas flow temperature that jet-propelled turbofan aero-engine sprays, and is moved
The thrust of Force system output also can correspondingly increase by 7%, and in the case where starting augmentor, dynamical system sprays aircraft
Gas flow temperature can be promoted to 1800 degrees Celsius, and (band after-burner turbofan aero-engine used in modern combat aircraft sprays
The gas flow temperature of aircraft is typically all 1800 degrees Celsius), the thrust F1 (adding) of dynamical system output also can be increased to correspondingly:
F (adding)=F+F*0.07* (1800-1000)/100=1.56F,
Wherein F is the thrust of dynamical system output in the case where not starting augmentor
Due to spraying the aircraft when multicore scheming band after-burner turbofan aeropropulsion system does not open augmentor
External gas flow temperature is lower than 100 degrees Celsius, and in the case where starting augmentor, dynamical system sprays the gas of the aircraft
Stream temperature can be promoted to 1800 degrees Celsius, and the thrust of dynamical system output also can be increased to correspondingly:
F2 (adding)=F+F*0.07* (1800-100)/100=2.19F
Wherein F is the thrust of dynamical system output in the case where not starting augmentor
If the turbofan aero-engine of a cuff after-burner, bypass ratio is the 0.3 (culvert of modern combat aircraft engine
0.3) road is than being typically all, its thrust is 8 tons under normal circumstances, and in the case where starting augmentor, its thrust will
It increases to:
1.56*8=12.48 ton
If also having a set of multicore scheming band after-burner turbofan aeropropulsion system, under normal circumstances its thrust
It is 8 tons, in the case where starting augmentor, its thrust will be increased to:
2.19*8=17.52 ton
That is, using multicore scheming with its maximum of the aircraft of after-burner turbofan aeropropulsion system
Take-off weight is higher by 5 than the aircraft for the small bypass ratio turbofan aero-engine that the modern combat aircraft using same thrust uses
Ton.Moreover, because multicore scheming band after-burner turbofan aeropropulsion system sprays the aircraft when not opening augmentor
External gas flow temperature is lower than 100 degrees Celsius, and the small bypass ratio turbofan aero-engine that modern combat aircraft uses is not starting
In the case where augmentor, the gas flow temperature that dynamical system sprays aircraft exterior is about 1000 degrees Celsius, multicore scheming band
After-burner turbofan aeropropulsion system generates the oil consumption rate of same thrust, only in the case where not starting augmentor
It is one of three parts of the small bypass ratio turbofan aero-engine that modern combat aircraft uses, it can be seen that multicore scheming band afterbunring
The huge advantage that room turbofan aeropropulsion system superelevation bypass ratio has.
As a preferred technical solution, the aircraft vertical go up and down the stage, need to be substantially improved aircraft power system
When the thrust exported of uniting, augmentor can be started, at this moment multicore scheming band after-burner turbofan aeropropulsion system can provide
The thrust of the aircraft maximum take-off weight 50%-110% allows the aircraft vertical to go up and down；In aircraft climb, accelerate
Stage, augmentor are then not required to enable, and whirlpool axis aero-engine described in multi-section is used only and provides power, by the air-breathing wind
Fan, force(d) (draft) fan sucking and pressurized air, then the pressure chamber is connected to by being mounted on the aircraft aft, fixing
Outside the rear left nozzle assembly, the rear right nozzle component and the rear middle nozzle assembly ejection machine, provided for the aircraft
The thrust of maximum take-off weight 30%-50%, to reach the effect of saving fuel oil；In the aircraft cruising flight phase,
It can also only use the whirlpool axis aero-engine by the closure of clutch described in control dynamical system and power is provided, then
It is described by being mounted on outside the rear middle nozzle assembly ejection machine of the aircraft aft, the fixed connection pressure chamber
The thrust of aircraft offer maximum take-off weight 10%-30%；Therefore, multicore scheming band after-burner turbofan aviation power system
System has wide power output range.
The pressure chamber multicore scheming with after-burner turbofan aeropropulsion system as a preferred technical solution,
The load-bearing chassis of the aircraft is made into mitigate the weight of the aircraft and fill part using multicore scheming band after-burner
The inner space of turbofan aviation aircraft allows engine sucking, the large flow-rate gas stream spirt multicore scheming band reinforcing combustion of pressurization
Burn the pressure chamber of room turbofan aviation aircraft, then each vector nozzle assembly by being connected on the pressure chamber
It ejects；It is cleverly arranged by this, can produce following every benefit:
(1) pressure chamber described in will become the buffer of big-flow high-pressure air-flow, when the engine of the aircraft changes
Power, aerial flow perturbation, imitate interference etc. factors cause sucking dynamical system big-flow high-pressure air-flow fluctuate, institute
These fluctuation effects of air-flow will be filtered out by stating the cryogenic high pressure air in pressure chamber, make air-flow described by being connected to
Each vector nozzle assembly on pressure chamber equably ejects, to avoid pushing away for each vector nozzle assembly
There is transient fluctuation in power, causes as Britain's " sparrow hawk formula " and the jet-propelled Convertiplane of U.S. F-35, due to the flight
The thrust that each nozzle of device generates in a short time is uneven and the posture of the aircraft is caused to be difficult to the case where manipulating, and allows
We can be connected to the throughput and jet that each vector nozzle assembly sprays on the pressure chamber by adjusting respectively
Direction, it is more convenient simply to manipulate the aircraft.
(2) when starting augmentor, fire in the reinforcing by the great amount of fuel oil in the reinforcing fuel nozzle spirt air-flow
It burning and flows into the pressure chamber after primary combustion in room, fuel oil burns away under the environment of high temperature, high pressure and fresh air abundance,
Time with air-flow in aircraft interior flow burning will extend, and further release those and have enough time reinforcing not yet
The fuel oil energy to burn in combustion chamber, increases the efficiency of fuel burning, to increase the thrust of dynamical system generation；Therefore,
The fuel oil work doing efficiency of the jet-propelled vertical translation aircraft with the pressure chamber, it will do not pressed higher than dynamical system
The common jet plane of power chamber increases the jet-propelled vertical translation aircraft economy used in everyday, reduces fuel oil pair
Adverse effect caused by environment.
(3) the huge noise that drawing fan described in, the force(d) (draft) fan and engine intermediate fuel oil explosive combustion generate will
It is absorbed by cryogenic high pressure air insulated a large amount of in the pressure chamber, energy entrained by these huge noises acts on the pressure
In pressure-air in power chamber, the temperature of pressure-air in the pressure chamber is allowed to increase and be converted to thrust, is greatly reduced and passes to
The noise of aircraft exterior；Let us is produced low noise, the jet-propelled of shuttle flight can be vertically moved up or down among city
Aircraft is possibly realized.
It is installed simultaneously on the pressure chamber due to us as a preferred technical solution, and several close, opens and can
It continuously adjusts and sprays throughput, the changeable vector nozzle assembly for spraying airflow direction, let us passes through to each arrow
The operation of flow nozzle component controls, and can not only allow the aircraft smoothly to take off vertically landing, flight forward, can also allow described
Aircraft hovers in the sky and slowly movement all around, greatly strengthens the functionality and use scope of the aircraft.
Each vector nozzle assembly being connected to as a preferred technical solution, with the pressure chamber is mounted on the flight
The surrounding of device, each vector nozzle assembly is in the shape of long trapezoid body and containing multiple nozzles, outer spout in expanding
It is horn-like；The air-flow that each vector nozzle assembly sprays forms both long and broad uniform and fluctuation very little ejection air-flows
Face, from the surrounding of the aircraft, support supports aircraft in large area, be significantly increased the aircraft take off landing or
The stability of hovering phase in the sky becomes easy the manipulation of the aircraft simply；Let us can be controlled more easily
The posture for making, changing the aircraft, so that the aircraft is manipulated simple, ordinary people as automobile can all drive.
The second object of the present invention be to provide it is a kind of it is novel it is jet-propelled can vertical translation aircraft, the novel jet
Formula can vertical translation aircraft include above-described multicore scheming band after-burner turbofan aeropropulsion system.
Compared to the prior art, the present invention has an advantage that
1, the present invention creatively uses core engine of the whirlpool the Duo Tai axis aero-engine as dynamical system, due to go straight up to
The civilian whirlpool axis aero-engine that machine provides power is cheap, light-weight, performance is stable and power is abundant, and in market
On be readily available, be little affected by the limitation of appropriate authorities, excellent jet-propelled of the inexpensive property of let us mass production is vertically moved up or down
Airborne aircraft is possibly realized.
2, by the present invention in that use two to rotary fan with increase air-breathing and charging efficiency, using whirlpool axis aero-engine as
Core engine is to save fuel oil；The whirlpool Duo Tai axis aero-engine is connected by clutch with uni-drive gear box, and clutch can be passed through
Open and close control every whirlpool axis aero-engine disembarking in dynamical system and run, entire dynamical system can be allowed only to transport
One whirlpool axis aero-engine of row or the whirlpool Duo Tai axis aero-engine run simultaneously, drive air-breathing wind by uni-drive gear box
Fan and force(d) (draft) fan opposite direction rotating provide the large flow-rate gas stream of cryogenic high pressure to pressure chamber, then pass through each of connection pressure chamber
Vector nozzle assembly sprays air-flow to outside and generates thrust, forms ejection when a set of bypass ratio is more than 20, does not open augmentor and flies
The multicore scheming band after-burner whirlpool of superelevation bypass ratio of the gas flow temperature lower than 100 degrees Celsius, green energy conservation outside row device
Fan aeropropulsion system.
3, the present invention is provided with pressure chamber, and pressure chamber is made into the load-bearing chassis of aircraft to mitigate the weight of aircraft
And fill part utilize aircraft inner space, allow engine sucking, pressurization large flow-rate gas stream spirt aircraft pressure chamber,
It is ejected again by each vector nozzle assembly being connected on pressure chamber；It is cleverly arranged by this, dynamical system
Pressure chamber will become big-flow high-pressure air-flow buffer, when aircraft engine change power, aerial flow perturbation,
The factors such as ground effect interference cause the big-flow high-pressure air-flow of sucking dynamical system to fluctuate, the cryogenic high pressure air in pressure chamber
These fluctuation effects that air-flow will be filtered out make air-flow equal by each vector nozzle assembly being connected on pressure chamber
It ejects evenly, so that the thrust of each vector nozzle assembly be avoided transient fluctuation occur；When starting augmentor, reinforcing
Great amount of fuel oil in fuel nozzle spirt air-flow enters pressure chamber in after-burner after primary combustion, high temperature, high pressure and
It burning away under the environment of fresh air abundance, time of the fuel oil with air-flow in aircraft interior flow burning will extend,
Those fuel oil energy for being in time for burning in after-burner not yet are further released, the efficiency of combustion of fuel oil is increased,
To increase the thrust of dynamical system generation；Drawing fan, force(d) (draft) fan and engine intermediate fuel oil explosive combustion generate huge
Big noise will be absorbed by cryogenic high pressure air insulated a large amount of in pressure chamber, and energy entrained by these huge noises acts on
In pressure-air in pressure chamber, the temperature of pressure-air in pressure chamber is allowed to increase and be converted to thrust, be greatly reduced pass to it is winged
Noise outside row device；The present invention on pressure chamber simultaneously install it is several close, open and continuously adjustable spray throughput,
The changeable vector nozzle assembly for spraying airflow direction, let us are controlled by the operation to each vector nozzle assembly, not only can
It allows aircraft smoothly to take off vertically landing, flight forward, aircraft can also be allowed to hover in the sky and slowly mobile all around,
Greatly strengthen the jet-propelled functionality for being vertically moved up or down airborne aircraft and use scope.
4, the present invention has wide power output range, can provide maximum take-off weight 10%-110%'s for aircraft
Thrust；Bypass ratio of the multicore scheming with after-burner turbofan aeropropulsion system is more than 20, in the feelings for not starting augmentor
Under condition, the gas flow temperature of aircraft exterior is sprayed lower than 100 degrees Celsius, generates the oil consumption rate of same thrust, only modern war
One of three parts of the small bypass ratio turbofan aero-engine that bucket machine uses；When starting augmentor, fuel nozzle is reinforced to reinforcing
High pressure draught spirt great amount of fuel oil in combustion chamber allows the high pressure draught for spraying aircraft substantially to heat up, dynamical system output
Thrust is also significantly increased, it can be seen that possessed by multicore scheming band after-burner turbofan aeropropulsion system superelevation bypass ratio
Huge advantage.
Detailed description of the invention
Fig. 1 be it is jet-propelled can vertical translation aircraft surface structure aerial view；
Fig. 2 be it is jet-propelled can vertical translation aircraft side view；
Fig. 3 is structure of transmission gear box schematic diagram；
Fig. 4 be it is jet-propelled can vertical translation aircraft bottom view；
Fig. 5 is multicore scheming band after-burner turbofan aeropropulsion system appearance three-dimensional figure；
Fig. 6 is multicore scheming band after-burner turbofan aeropropulsion system structural perspective；
Fig. 7 is multicore scheming band after-burner turbofan aeropropulsion system structure aerial view；
Fig. 8 is the structural schematic diagram of vector nozzle assembly；
Fig. 9 is the rearview of vector nozzle assembly；
Figure 10 is the side view of vector nozzle assembly；
Wherein, 1, jet-propelled can vertical translation aircraft；20, rear middle nozzle assembly；21, rear left nozzle assembly；22, rear left
Nozzle assembly air-flow rudder face；23, rear right nozzle component；24, rear right nozzle component air-flow rudder face；25, front left nozzle assembly；26,
Front left nozzle assembly air-flow rudder face；27, front right nozzle assembly；28, front right nozzle assembly air-flow rudder face；40, drawing fan；41,
Drawing fan transmission shaft；42, force(d) (draft) fan；43, force(d) (draft) fan transmission shaft；44, uni-drive gear box；45, fuel nozzle is reinforced；
46, clutch；47, power transmission shaft；48, whirlpool axis aero-engine；49, engine charge pipeline；50, the exhaust pipe of engine
Road；51, after-burner；52, pressure chamber air inlet；53, pressure chamber；54, vector nozzle assembly；55, vector nozzle assembly gas
Flow rudder face；56, force(d) (draft) fan transmission gear；57, drawing fan transmission gear；58, power transmission gear；
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with drawings and embodiments
Invention is further described in detail.It should be appreciated that described herein, specific examples are only used to explain the present invention, not
For limiting the present invention.
As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9, Figure 10:
A kind of multicore scheming band after-burner turbofan aeropropulsion system, including drawing fan 40, drawing fan are driven
Axis 41, force(d) (draft) fan 42, force(d) (draft) fan transmission shaft 43, uni-drive gear box 44, reinforcing fuel nozzle 45, after-burner 51, from
Clutch 46, power transmission shaft 47, several whirlpool axis aero-engines 48, engine charge pipeline 49, engine exhaust conduit 50,
Pressure chamber 53 and several vector nozzle assemblies 54；Vector nozzle assembly 54 (vector nozzle assembly has applied for another patent of invention:
" novel jet aero-engine vector nozzle and aero-engine ", application number: 201810762795.8), including connection pressure
Power chamber 53, be mounted on it is jet-propelled can vertical translation aircraft 1 (it is jet-propelled can vertical translation aircraft applied for that another invention is special
Benefit: " jet-propelled to be vertically moved up or down airborne aircraft and new aeropropulsion system ") around rear middle nozzle assembly 20, rear left spray
Nozzle assembly 21, rear right nozzle component 23, front left nozzle assembly 25, front right nozzle assembly 27；Pressurization wind in uni-drive gear box 44
Fan 56 shape of transmission gear is that cone, centre have a cylindrical space, and force(d) (draft) fan transmission shaft 43 is also intermediate to have one
Cylindrical space is simultaneously fixedly connected with force(d) (draft) fan transmission gear 56, the diameter in 43 mediate cylindrical space of force(d) (draft) fan transmission shaft
Equal to the diameter in 56 mediate cylindrical space of force(d) (draft) fan transmission gear, greater than the outer dia of drawing fan transmission shaft 41；It inhales
Air fan transmission shaft 41 passes through the cylindrical space of hollow force(d) (draft) fan transmission shaft 43, force(d) (draft) fan transmission gear 56, suction
Air fan 40 is fixedly connected with the drawing fan transmission gear 57 that shape in uni-drive gear box 44 is also cone；Driving cog
Power transmission gear 58 in roller box 44 is also cone shape, and whirlpool axis aero-engine 48 passes through clutch 46, power transmission
Axis 47 is connect with power transmission gear 58；The shaft power of the rotation output of whirlpool axis aero-engine 48 passes through power transmission gear 58
Rotation drives force(d) (draft) fan transmission gear 56 and drawing fan transmission gear 57 counter-rotation, by drawing fan transmission shaft 41 and
Force(d) (draft) fan transmission shaft 43 drives drawing fan 40, force(d) (draft) fan 42 counter-rotation simultaneously, sucks simultaneously pressurized air；Engine into
Feed channel 49 be connected to whirlpool axis aero-engine 48 42 rear portion of air inlet and force(d) (draft) fan, for whirlpool axis aero-engine 48 provide through
The pressurized high pressure fresh air of force(d) (draft) fan 42；Engine exhaust conduit 50 be connected to whirlpool axis aero-engine 48 exhaust outlet and
Pressure chamber 53 discharges into axis aero-engine 48 burned high-temp waste gas in whirlpool in pressure chamber 53；It is fixed to reinforce fuel nozzle 45
It is mounted on 44 rear portion of uni-drive gear box, after-burner 51 is located at reinforcing 45 rear portion of fuel nozzle and fixes with pressure chamber 53 and connects
It is logical；Pressure chamber 53 be mounted on it is jet-propelled can vertical translation aircraft 1 bottom, as it is jet-propelled can vertical translation aircraft 1
Load-bearing chassis becomes a load-bearing support member of aircraft fuselage；Vector nozzle assembly 54 is mounted on and jet-propelled can vertically rise
1 bottom surrounding of aircraft, fixed connection pressure chamber 53 drop.
Multicore scheming band after-burner turbofan aeropropulsion system is sucked and is increased by drawing fan 40, force(d) (draft) fan 42
Air is pressed, pressure-air passes through in 51 feed pressure chamber 53 of after-burner, then by being mounted on 1 bottom surrounding of aircraft, consolidating
Surely it is connected to outside the 54 ejection machine of several vector nozzle assemblies of pressure chamber 53, provides thrust, lift for aircraft 1；Aircraft 1 is hanging down
It directly takes off, landing phases, vector nozzle assembly 54 sprays downwards air-flow, lift, thrust is provided for aircraft 1, in aircraft 1
Bottom surrounding forms the airflow supports face to have a wide reach；Aircraft 1 sprays backward in cruising level flight stage vector nozzle assembly 54
Air-flow provides thrust for aircraft 1, forms the air-flow to have a wide reach at the rear portion of aircraft 1 and pushes face；Each vector nozzle sets
Part 54 has the function of adjusting ejection throughput size or unlatching, closes ejection air-flow；It is mounted in vector nozzle assembly 54
Air-flow rudder face 55, can enable it that can swing 60 ° as needed, spray air-flow injection direction to the left, to the right to change；
Be mounted on the vector nozzle assembly 54 of aircraft 1, can be needed by specific, enable its can be rotated upwards from level orientation 15 ° and to
Lower 105 ° of rotation, so that changing these nozzle assemblies 54 sprays the upper and lower of air-flow, left and right directions；It can also be needed by specific, enable it
Can only downward jet-stream wind, can not change spray air-flow up and down direction, only can be changed spray air-flow left and right directions；Or it presses
It is specific to need, enable its only can jet-stream wind backward, can not change spray air-flow up and down, left and right directions.
It is jet-propelled can vertical translation aircraft 1 pressure chamber 53 of dynamical system is made into the load-bearing chassis of aircraft to mitigate
The weight of aircraft and the inner space that part utilizes aircraft is filled, allows the multicore scheming band afterbunring with after-burner 51
Pressure chamber 53 of the room turbofan aeropropulsion system big-flow high-pressure air-flow spirt aircraft 1；It is installed simultaneously on pressure chamber 53
Several, which have to adjust, sprays throughput size, can open, close the arrow for spraying air-flow and can changing jet direction up and down
Flow nozzle component 54 allows the air-flow in pressure chamber 53 to spray generation thrust by each relevant vector nozzle assembly 54；Pressure chamber
53 become big-flow high-pressure air-flow buffer, when aircraft 1 engine change power, aerial flow perturbation, imitate it is dry
The factors such as disturbing causes the big-flow high-pressure air-flow in spirt pressure chamber 53 to fluctuate, the considerable low-temperature high pressure in pressure chamber 53
Air will filter out these fluctuation effects of air-flow, and air-flow can be sprayed uniformly across the vector being connected on pressure chamber 53
Nozzle assembly 54 ejects, so that the thrust of vector nozzle assembly 54 be avoided therefore to fluctuate, cause as Britain " sparrow hawk formula " and
The posture of the such aircraft of the jet-propelled Convertiplane of U.S. F-35 is difficult to the case where manipulating.Let us can pass through the company of adjusting
It connects each throughput sprayed in relation to vector nozzle assembly 54 and jet direction on aircraft pressure chamber 53 and increases aircraft 1
Controllability, to produce simple, cheap, the easy manipulation of structure, all dirigible jet of the ordinary people as automobile
Formula can be vertically moved up or down airborne aircraft.
Since the multicore scheming band after-burner turbofan aeropropulsion system with after-burner 51 is big flow height
The pressure chamber 53 of pressure gas stream spirt aircraft 1, then each vector nozzle assembly 54 by being connected on pressure chamber 53 eject
Come, the time that air-flow flows in aircraft 1 will extend.When starting augmentor, 45 spirt air-flow of fuel nozzle is reinforced
In great amount of fuel oil in after-burner 51 after primary combustion, into pressure chamber 53 after filled in high temperature, high pressure and fresh air
It continues to burn under the environment of foot, further releases those fuel oils for being in time for burning in after-burner 51 not yet
Energy increases the efficiency of combustion of fuel oil while increasing the thrust of engine.Therefore, jet-propelled with pressure chamber is vertically moved up or down
The fuel oil service efficiency of aircraft 1 does not have the jet-propelled Convertiplane of pressure chamber after will being far longer than engine, into one
Step increase it is jet-propelled can vertical translation aircraft 1 routine use economy and reduce fuel oil adverse effect caused by environment.
Since the multicore scheming band after-burner turbofan aeropropulsion system with after-burner 51 is big flow height
The pressure chamber 53 of pressure gas stream spirt aircraft 1, then each vector nozzle assembly 54 by being connected on pressure chamber 53 eject
Come, the huge noise that drawing fan 40, force(d) (draft) fan 42 and engine intermediate fuel oil explosive combustion generate will be by pressure chamber 53
A large amount of cryogenic high pressure air insulated absorbs, and energy entrained by these huge noises acts on the pressure-air in pressure chamber 53
In, allow the temperature of these pressure-airs to increase and be converted to thrust, only the noise of very little can pass to the outside of aircraft 1, allow
We produce low noise, the jet-propelled airborne aircraft that is vertically moved up or down of shuttle flight can be possibly realized among city.
Due to we on pressure chamber 53 simultaneously install it is several close, open and continuously adjustable spray throughput, can
Change the vector nozzle assembly 54 for spraying airflow direction, let us is controlled by the operation to each nozzle assembly, can not only be allowed winged
Row device 1 smoothly takes off vertically landing, flight forward, and aircraft 1 can also be allowed to hover in the sky and slowly mobile all around,
Greatly strengthen it is jet-propelled can vertical translation aircraft 1 functionality and use scope；The preceding left nozzle of 1 bottom front of aircraft
Component 25, front right nozzle assembly 27 can close, open and continuously adjustable sprays throughput, the Raphael of vector nozzle assembly 54
Two side of spout is fitted with air-flow rudder face 55, and air-flow rudder face 55 can swing 60 °, to change the left and right side for spraying air-flow
To；Rear left nozzle assembly 21, the rear right nozzle component 23 of 1 bottom rear end of aircraft can not only close, open and continuously adjustable
Throughput is sprayed, the air-flow rudder face 55 being fitted into can also swing 60 °, to change the left and right direction for spraying air-flow；Afterwards
Left nozzle component 21, rear right nozzle component 23 can also be swung up 15 degree and to 105 degree of lower swing, to change ejection gas
The upper and lower direction of stream.
Each vector nozzle assembly 54 being connected to the pressure chamber 53 is mounted on the surrounding of aircraft 1, each vector nozzle
Component 54 is in the shape of long trapezoid body and horn-like in expanding containing multiple nozzles, outer spout；Each vector nozzle assembly 54
The air-flow of ejection is uniform and fluctuates very little, forms both long and wide ejection air-flow faces, holds in large area from the surrounding of aircraft 1
Support support aircraft 1, is significantly increased aircraft 1 in landing or the stability of hovering phase in the sky of taking off, also makes aircraft 1
Manipulation become easy simply；Let us can control more easily, the posture of change of flight device 1, make jet-propelled can vertically rise
Dropping aircraft 1 easy manipulation, ordinary people as automobile can all drive.
By using two to rotary fan to increase air-breathing and charging efficiency, using whirlpool axis aero-engine 48 as core engine
To save fuel oil；The whirlpool Duo Tai axis aero-engine 48 is connected by clutch 46 with uni-drive gear box 44, and clutch 46 is passed through
Open and close control every whirlpool axis aero-engine 48 disembarking in dynamical system and run, can allow entire dynamical system only
It runs a whirlpool axis aero-engine 48 or the whirlpool Duo Tai axis aero-engine 48 while running, driven by uni-drive gear box 44
Dynamic 42 opposite direction rotating of drawing fan 40 and force(d) (draft) fan provides the large flow-rate gas stream of cryogenic high pressure to pressure chamber 53, then passes through company
Each vector nozzle assembly 54 of logical pressure chamber 53 sprays air-flow to outside and generates thrust, and forming a set of bypass ratio is more than 20, no
Superelevation bypass ratio of the gas flow temperature lower than 100 degrees Celsius of aircraft exterior, the multicore of green energy conservation are sprayed when opening augmentor
Scheming band after-burner turbofan aeropropulsion system system.
Multicore scheming band after-burner turbofan aeropropulsion system, to rotary fan air-breathing and pressurization, is removed by using two
Because the stator of removal fan can reduce the weight of dynamical system and simplify outside the structure of dynamical system, can also be substantially improved
The efficiency of dynamical system.The use experience of amp- 70 military transportation airplane of power is provided according to Russia using co-axial contra rotating propeller, is adopted
It uses second mate's co-axial contra rotating propeller as power, provides same thrust ratio using the engine of single propeller and want fuel-efficient 20%-30%.
Some use experiences using second mate's relative rotation propcopter also indicate that, using the engine driving of same power, adopt
It is 10%- higher than using the helicopter of single Design of Propeller with the helicopter lift of second mate's relative rotation Design of Propeller
12%.In multicore scheming band after-burner turbofan aeropropulsion system, due to sucking big flow to rotary fan using two
Air-flow and these air-flows are pressurized to 2.5atm-3atm by 1atm, by dynamic to 51 spirt of after-burner after rotary fan
In the pressure chamber 53 of Force system, then by being connected to pressure chamber 53 and being installed on the ejection of vector nozzle assembly 54 of 1 surrounding of aircraft,
It is converted into the thrust of aircraft 1, multicore scheming will can be made to increase with the thrust that after-burner turbofan aeropropulsion system generates
10%-12% or so.
Whirlpool axis aero-engine 48 by the fresh air that engine charge pipeline 49 sucks be from two to rotary fan after
The pressure-air that portion introduces, pressure is 2.5atm-3atm after being pressurized, therefore the power that whirlpool axis aero-engine 48 generates will be than peace
20% is increased above mounted in pure helicopter, directly from the same power engine that external suction pressure is 1atm air, just as
The automobile engine for installing turbo charging installation additional is such, and the power of generation will increase above 20% than same power engine.
It is mounted on power caused by the whirlpool axis aero-engine of pure helicopter, about 20% will distribute to helicopter
Tail rotor use, the centrifugal force that generates when for overcoming helicopter big propeller to rotate maintains the balance of helicopter, makes fuselage
It does not rotate, does not play a role during providing lift for helicopter, but navigate in multicore scheming band after-burner turbofan
Power caused by the whirlpool axis aero-engine 48 used in lost motion Force system is then all inhaled for driving two to rotary fan
Enter and be pressurized large flow-rate gas stream, then by connection pressure chamber 53, the vector nozzle assembly 54 for being installed on 1 surrounding of aircraft sprays downwards
Out, it is converted into the lift of aircraft.Therefore multicore scheming is mounted on the whirlpool axis boat in after-burner turbofan aeropropulsion system
Empty engine 48 is that the lift that aircraft can be provided theoretically will be more general than being mounted on due to our exquisite design arrangements
The whirlpool axis aero-engine of same power on logical helicopter increases 30%-50% or so.
In order to illustrate more clearly of every advanced function of the invention, we are explained in detail with an example: if adopted
Domestic 16 aero-engine of whirlpool axis (in the present example, the two whirlpool axis aero-engines for being 1500KW with two maximum powers
It is mounted on two side of left and right of uni-drive gear box 44, the up and down direction of tangible uni-drive gear box 44 can also install two whirlpool axis again
Aero-engine, whole system can install four whirlpool axis aero-engines simultaneously, can pass through every whirlpool axis aero-engine 48
The open and close of the clutch 46 of connection control every whirlpool axis aero-engine 48 disembarking in dynamical system and run, and control whole
A dynamical system only runs a whirlpool axis aero-engine 48 or the whirlpool Duo Tai axis aero-engine 48 while running output and moves
Rate), drawing fan 40 and 42 opposite direction rotating of force(d) (draft) fan are driven by uni-drive gear box 44, the air-breathing for the use of diameter being 1.3 meters
Fan, then each second about can be to 230 kilograms of the offer of pressure chamber 53, temperature lower than 100 degrees Celsius, 2.5atm -3atm low temperature height
Air is pressed, then the thrust (U.S. that air-flow generates about 8 tons is sprayed to outside by the vector nozzle assembly 54 of connection pressure chamber 53
Lift is in rotary fan component in the middle part of the jet-propelled Convertiplane of F-35, and the diameter of fan is 1.27 meters, and each second sprays downwards
230 kilograms of cold air out generates 9 tons of down thrust).
The U.S. " Apache " armed helicopter maximum take-off weight reaches 10 tons, is equipped with two GE company maximum work outputs
The whirlpool the T-700-GE-701C axis aero-engine that rate is 1800 kilowatts；China Wu Zhishi armed helicopter maximum take-off weight 6
Ton, domestic 9 aero-engine of whirlpool axis for being 1200 kilowatts equipped with two peak power outputs.
Although the big propeller of helicopter passes through me because diameter can provide biggish lift often greatly for helicopter
Exquisite design arrangement, be mounted on it is jet-propelled can two 1500KW above vertical translation aircraft 1 domestic whirlpool axis 16
Aero-engine, the lift that can be provided for aircraft 1 theoretically will be than being mounted on the whirlpool of same power on pure helicopter
Axis aero-engine increases 30%-50% or so.Still use two power for 1500KW domestic 16 aviation of whirlpool axis send out
Motivation drives drawing fan 40 and 42 opposite direction rotating of force(d) (draft) fan, provides the cryogenic high pressure air-flow of big flow to pressure chamber 53,
In the case where not opening augmentor, for it is jet-propelled can vertical translation aircraft 18 tons of down thrust, two whirlpool axis 16 are provided
The 3000KW power that aero-engine is exported is enough.
At this time, the air mass flow for flowing into two whirlpool axis, 16 aeroengine combustor buring room each second is only 10 kilogram (two
Axis 16 aero-engine in platform whirlpool generates inspiratory capacity when peak power), then the bypass ratio of entire dynamical system is up to 230/10
=23, it is the jet-propelled aeropropulsion system of current highest bypass ratio in the world.
Entire dynamical system is not in the case where starting augmentor, oil consumption rate about 900 kilograms of (two whirlpool axis ten per hour
Six aero-engines generate highest oil consumption rate hourly when maximum power), it is only using small bypass ratio turbofan aero-engine
One of about five parts of jet-propelled Convertiplane oil consumption rate (since small bypass ratio turbofan aero-engine is not opening reinforcing
It is about 1000 degrees Celsius that the temperature of air-flow is sprayed when device, and our this multicore scheming band after-burner turbofan aviation powers
System sprays the temperature of air-flow when not opening augmentor but will be lower than 100 degrees Celsius, therefore oil consumption under normal operating conditions
Rate is very low), it is added significantly to the radius of aircraft 1 and routine use cost is greatly reduced, use civilian whirlpool axis aviation
Engine fills part as the advantage of superelevation bypass ratio dynamical system core engine and presents out.
Due to the superelevation bypass ratio of entire dynamical system, 230 kg of air per kg of water evaporated per second by pressure chamber 53 major part absolutely is all
It is not to be up to the fresh air that 2.5atm-3atm, temperature are but lower than 100 degrees Celsius by burning, air pressure.If starting reinforcing
Device, clockwise after-burner 51 per second sprays about ten kilograms of fuel oils, and (by calculating, 230 kg of air per kg of water evaporated heat up from 100 degrees Celsius
To 1800 degrees Celsius, 8 kilograms of aviation kerosines are needed, some unknowable losses is reserved herein, therefore is set as 10 kilograms), then may be used
Air themperature by 53 per second 230 kilograms of pressure chamber is promoted to about 1800 degrees Celsius of (turbofan aviations with augmentor
It is about 1800 degrees Celsius that the temperature of air-flow is sprayed when engine starts augmentor), the thrust that entire dynamical system generates will
More than 17 tons, (by calculating, when the temperature for spraying air-flow is 1800 degrees Celsius, the thrust that entire dynamical system generates is
17.52 ton):
F2 (adding)=F+F*0.07* (1800-100)/100=2.19*F=2.19*8=17.52 tons
It is enough that taking off vertically for 16 tons of aircraft 1 of maximum take-off weight is supported (to pass through and calculate, institute in 230 kg of air per kg of water evaporated
Oxygenous completely burned, needs 15 kilograms of aviation kerosines, and the heat of generation can heat up 230 kg of air per kg of water evaporated from 100 degrees Celsius
To about 3500 degrees Celsius, the thrust that dynamical system generates will be more than 19 tons, reserve herein some unknowable losses and
Limitation in engineering manufacture to material, technique, therefore only dynamical system is designed as to be warming up to 1800 degree, generate 17 tons
Thrust.In fact, the power output of entire dynamical system there are also it is wide can room for promotion).
It is jet-propelled can vertical translation aircraft 1 entire voyage exhausted most time all in cruising level flight state, this
When multicore scheming with after-burner turbofan aeropropulsion system need to only provide the thrust of 1 total weight of aircraft about 10% just
It can maintain the cruising level flight state of aircraft 1；For aircraft 1 in acceleration mode, engine needs to provide aircraft gross weight amount
About 30% thrust can maintain the acceleration mode of aircraft 1, and aircarrier aircraft is in when airfield runway is slided and taken off
This state；And aircraft 1, when taking off vertically state, engine then needs to provide pushing away for 1 105% or more total weight of aircraft
Power just can allow aircraft 1 to take off vertically.Therefore, it is jet-propelled can vertical translation aircraft 1 to require engine to have wide dynamic
Power output area, and at present in the world all reaction power system can not be provided in the state of saving fuel oil it is so wide
Wide power output range, the reaction power system as used in Britain's " sparrow hawk formula ", U.S. F-35 jet-propelled Convertiplane
System, it is about 1000 degrees Celsius that it, which sprays the temperature of air-flow when maintaining the cruising level flight state of aircraft, in the state of taking off vertically
It is about 1800 degrees Celsius that the temperature of air-flow is sprayed when starting augmentor, and oil consumption rate is not very greatly that aircraft is entirely navigating respectively
Journey substantially reduces the radius of aircraft and routine use cost is significantly increased all in high oil consumption state.And multi-core
The temperature that machine sprays air-flow with after-burner turbofan aeropropulsion system when maintaining the cruising level flight state of aircraft 1 is lower than
100 degrees Celsius, when the state of taking off vertically starts augmentor, the temperature for spraying air-flow is about 1800 degrees Celsius, entire power
The power output of system haves a wide reach, and oil consumption rate differs greatly.Therefore, aircraft 1 is in the oil consumption of entire voyage compared with Britain " sparrow hawk
Formula ", the jet-propelled Convertiplane of U.S. F-35 want much lower.
Two whirlpool axis aero-engines 48 used by multicore scheming band after-burner turbofan aeropropulsion system are logical
It crosses clutch 46 to be connected with uni-drive gear box 44, then drives 42 opposite direction rotating of drawing fan 40 and force(d) (draft) fan.Pass through clutch
The open and close of device 46, we control the separation of whirlpool axis aero-engine 48 and uni-drive gear box 44, connection in which can be convenient.It is this
Design allows for just in case there is a whirlpool axis aero-engine 48 to break down, we can separate it and be passed by clutch 46
The connection of movable tooth roller box 44, and only drawing fan 40 and pressurization are driven using another normal whirlpool axis aero-engine 48
The opposite direction rotating of fan 42 continues to provide power for aircraft 1, increases the safety coefficient of aircraft 1.It is patrolled when aircraft 1 is in
When boat equals winged state, a small amount of thrust of 1 total weight of aircraft about 10% only need to be provided to maintain the cruising level flight shape of aircraft
State, we also can use this function and only start a whirlpool axis aero-engine 48, and another is in shutdown status, thus
Fuel oil is substantially saved, the radius of aircraft 1 is increased.
In the above-mentioned example, navigate if we only start the domestic whirlpool axis 16 that a maximum power is 1500KW
Empty engine, it can provide 2 tons to 4 tons of thrust for aircraft 1, fully meet 16 tons of maximum take-off weight of aircraft 1
Power demand in cruising level flight state, but the oil consumption of aircraft 1 can halve be down to per hour be about 200 kilogram -400
Kilogram.Due to aircraft 1 entire voyage exhausted most time all in cruising level flight state, therefore carrying same weight combustion
In the case where oil, the radius of aircraft 1 will only start wherein one because of with this open and close by clutch
Core engine provides the unique function of power and doubles, to generate huge economic benefit.16 tons of maximum take-off weight
If aircraft 1 carries 5 tons of fuel oils, 1 ton therein is kept for the use when taking off vertically, landing of aircraft 1, entrained 4
Ton fuel oil can allow aircraft 1 to fly more than ten hour in cruising level flight state, if the common civil aviaton of speed per hour picture of aircraft 1
Machine is 900 kilometers per hour like that, then the radius of aircraft 1 will be considerably beyond 10,000 kilometers, and close to 1.5 ten thousand kilometers.
The above content is combine specific optimal technical scheme further detailed description of the invention, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For the professional technician of the technical field of the invention,
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, should all be considered as belonging to of the invention
Protection scope.
Claims (10)
1. a kind of multicore scheming band after-burner turbofan aeropropulsion system, which is characterized in that including drawing fan, air-breathing wind
It fans transmission shaft, force(d) (draft) fan, force(d) (draft) fan transmission shaft, uni-drive gear box, reinforcing fuel nozzle, after-burner, clutch, move
Power transmission shafr, several whirlpool axis aero-engines, engine charge pipeline, engine exhaust conduit, pressure chamber and the spray of several vectors
Nozzle assembly；The vector nozzle assembly, including be connected to the pressure chamber, be mounted on it is jet-propelled can be around vertical translation aircraft
Middle nozzle assembly, rear left nozzle assembly, rear right nozzle component, front left nozzle assembly, front right nozzle assembly afterwards；The transmission gear
Force(d) (draft) fan transmission gear shape in case is that cone, centre have a cylindrical space, the force(d) (draft) fan transmission shaft
And there is a cylindrical space in centre and is fixedly connected with the force(d) (draft) fan transmission gear, among the force(d) (draft) fan transmission shaft
The diameter of cylindrical space is equal to the diameter in the force(d) (draft) fan transmission gear mediate cylindrical space, is greater than the drawing fan
The outer dia of transmission shaft；The drawing fan transmission shaft passes through the hollow force(d) (draft) fan transmission shaft, the force(d) (draft) fan
The cylindrical space of transmission gear is also the drawing fan of cone shape in the drawing fan and the uni-drive gear box
Transmission gear is fixedly connected；Power transmission gear in the uni-drive gear box is also cone shape, the whirlpool axis boat
Empty engine is connect by the clutch, the power transmission shaft with the power transmission gear；The whirlpool axis aeroplane engine
The shaft power of machine rotation output is rotated by the power transmission gear drives the force(d) (draft) fan transmission gear and the air-breathing
Fan transmission gear is counter-rotation, drives the air-breathing wind by the drawing fan transmission shaft and the force(d) (draft) fan transmission shaft
Fan, the force(d) (draft) fan are counter-rotation simultaneously, suck simultaneously pressurized air；The engine charge pipeline is connected to the whirlpool axis aviation
The air inlet of engine and the force(d) (draft) fan rear portion provide after force(d) (draft) fan pressurization for the whirlpool axis aero-engine
High pressure fresh air；The engine exhaust conduit is connected to the exhaust outlet and the pressure chamber of the whirlpool axis aero-engine,
The high-temp waste gas that the whirlpool axis aeroengine combustor buring is crossed is discharged into the pressure chamber；The reinforcing fuel nozzle is fixedly mounted
At the uni-drive gear box rear portion, the after-burner is located at the reinforcing fuel nozzle rear portion and fixes with the pressure chamber
Connection；The pressure chamber be mounted on it is described it is jet-propelled can vertical translation aircraft bottom, the load-bearing bottom as the aircraft
Disk becomes a load-bearing support member of the aircraft fuselage；The vector nozzle assembly is mounted on the aircraft bottom
Surrounding, the fixed connection pressure chamber.
2. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that pass through
The drawing fan, force(d) (draft) fan sucking and pressurized air, pressure-air flow into the pressure by the after-burner
In power chamber, then by being mounted on aircraft bottom surrounding, the fixed several vector nozzle sets for being connected to the pressure chamber
Outside part ejection machine, thrust, lift are provided for the aircraft；The aircraft take off vertically, landing phases, vector spray
Nozzle assembly sprays downwards air-flow, provides lift, thrust for the aircraft, and it is wide to form range in aircraft bottom surrounding
Wide airflow supports face；Aircraft vector nozzle assembly described in the cruising level flight stage sprays air-flow backward, flies to be described
Row device provides thrust, forms the air-flow to have a wide reach at the rear portion of the aircraft and pushes face；Each vector nozzle assembly,
Have the function of adjusting and sprays throughput size or unlatching, closes ejection air-flow.
3. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that described
Vector nozzle assembly, air-flow rudder face therein can enable it that can swing 60 ° as needed, thus change spray air-flow to the left,
Injection direction to the right；It is mounted on the vector nozzle assembly of aircraft, can be needed by specific, enable it can be from level orientation
Rotation and is rotated down 105 ° by 15 ° upwards, thus change these nozzle assemblies spray air-flow up and down, left and right directions；It can also press
It is specific to need, enable its can only downward jet-stream wind, can not change and spray the up and down direction of air-flow, the left side for spraying air-flow only can be changed
Right direction；Or needed by specific, enable its only can jet-stream wind backward, can not change spray air-flow up and down, left and right directions.
4. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that if with
Cheap, the fuel-efficient helicopter whirlpool axis aero-engine of dry platform is dynamic as the multicore scheming band after-burner turbofan aviation
The core engine of Force system provides power for the aircraft.
5. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that described
The shaft power of whirlpool axis aero-engine rotation output drives the drawing fan and the pressurization wind by the uni-drive gear box
Opposite direction rotating is fanned to increase air-breathing and charging efficiency, does not have stator part between two fans.
6. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that pass through
Use two to rotary fan to increase air-breathing and charging efficiency, using several whirlpool axis aero-engines as core engine to save
Fuel oil, the drawing fan and the force(d) (draft) fan opposite direction rotating, Xiang Suoshu pressure chamber provide the large flow-rate gas stream of cryogenic high pressure,
Air-flow generation thrust, lift are sprayed to outside by being connected to each nozzle assembly of the pressure chamber again, forms a set of culvert
Road than more than 20, do not open the multi-core of superelevation bypass ratio of the augmentor jet temperature lower than 100 degrees Celsius, green energy conservation
Machine band after-burner turbofan aeropropulsion system.
7. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that spray
Air-flow is the cryogenic high pressure air-flow of pressure 2.5atm-3atm, temperature lower than 100 degrees Celsius, when starting augmentor, the reinforcing
Fuel nozzle flows through great amount of fuel oil spirt the high pressure draught in the after-burner, the energy that fuel oil vigorous combustion releases
The temperature of ejection air-flow can be promoted to 1800 degrees Celsius, it is dynamic that the multicore scheming band after-burner turbofan aviation is substantially improved
The thrust of Force system output.
8. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that start
Machine sucking, pressurization large flow-rate gas stream spirt described in aircraft the pressure chamber, then by connection on the pressure chamber
Each vector nozzle assembly eject, the pressure chamber as each vector nozzle assembly spray air-flow buffer；
The huge noise that the drawing fan, the force(d) (draft) fan and engine intermediate fuel oil explosive combustion generate is by big in the pressure chamber
The cryogenic high pressure air insulated of amount absorbs, efficient sound arrester of the pressure chamber as dynamical system；When unlatching augmentor
When, the reinforcing fuel nozzle flows through great amount of fuel oil spirt the high pressure draught of the pressure chamber, and the pressure chamber can extend combustion
Oil increases the utilization benefit of fuel oil in the burning time of aircraft interior.
9. multicore scheming band after-burner turbofan aeropropulsion system according to claim 1, which is characterized in that in institute
When stating the aircraft vertical lifting stage, dynamical system being needed to provide the thrust more than the aircraft takeoff weight, it can start and add
Power device, the reinforcing fuel nozzle flow through great amount of fuel oil spirt the high pressure draught of the pressure chamber, and fuel burning is promoted high
The temperature of pressure gas stream, at this moment dynamical system can provide the thrust of the aircraft takeoff weight 50%-110%, be substantially improved winged
The thrust of row device dynamical system output；In the aircraft cruising flight phase, the whirlpool axis aero-engine is used only and provides
Power provides the thrust of take-off weight 30%-50% for the aircraft；Clutch described in control dynamical system can also be passed through
Closure only uses the whirlpool axis aero-engine and provides power, provides take-off weight 10%-30%'s for the aircraft
Thrust.
10. a kind of novel aircraft, which is characterized in that including any one of the claim 1-9 multicore scheming band reinforcing combustion
Burn room turbofan aeropropulsion system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810919096.XA CN109899177B (en) | 2018-08-08 | 2018-08-08 | Multi-core aircraft with afterburner turbofan aviation power system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN109899177B CN109899177B (en) | 2023-02-17 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110714853A (en) * | 2019-10-28 | 2020-01-21 | 唐荣虎 | Aircraft engine |
| CN113586282A (en) * | 2021-08-10 | 2021-11-02 | 中国电子科技集团公司第三十八研究所 | Multistage turbofan engine with series supercharging function |
| US11346249B2 (en) | 2019-03-05 | 2022-05-31 | Pratt & Whitney Canada Corp. | Gas turbine engine with feed pipe for bearing housing |
| US11391179B2 (en) | 2019-02-12 | 2022-07-19 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing support structure |
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| CN202670093U (en) * | 2012-03-30 | 2013-01-16 | 高正君 | Autogiro capable of taking off and landing vertically |
| CN105667782A (en) * | 2014-11-22 | 2016-06-15 | 吴建伟 | Combined type vertical take-off and landing aircraft |
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| GB2379483A (en) * | 2001-09-08 | 2003-03-12 | Rolls Royce Plc | Augmented gas turbine propulsion system |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN202670093U (en) * | 2012-03-30 | 2013-01-16 | 高正君 | Autogiro capable of taking off and landing vertically |
| CN105667782A (en) * | 2014-11-22 | 2016-06-15 | 吴建伟 | Combined type vertical take-off and landing aircraft |
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| US11391179B2 (en) | 2019-02-12 | 2022-07-19 | Pratt & Whitney Canada Corp. | Gas turbine engine with bearing support structure |
| US11346249B2 (en) | 2019-03-05 | 2022-05-31 | Pratt & Whitney Canada Corp. | Gas turbine engine with feed pipe for bearing housing |
| CN110714853A (en) * | 2019-10-28 | 2020-01-21 | 唐荣虎 | Aircraft engine |
| CN113586282A (en) * | 2021-08-10 | 2021-11-02 | 中国电子科技集团公司第三十八研究所 | Multistage turbofan engine with series supercharging function |
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| Publication number | Publication date |
|---|---|
| CN109899177B (en) | 2023-02-17 |
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