Distributed propulsion system
Technical field
The present invention relates to a kind of aeropropulsion system, specifically a kind of distributed propulsion system.
Background technology
Economy is the transporter key factor to be considered, meanwhile, with constantly highlighting for environmental problem, people are to reduction
Carbon emission it is also proposed increasingly harsher requirement.This requires the efficiency for improving existing transport mechanomotive force (fanjet).
It is to use higher bypass ratio to improve one of effective measures of fanjet efficiency, to obtain high propulsive efficiency.Current
Civilian fanjet bypass ratio is already close to 10, but because the limitation of structure and parts match is difficult further improves.Distribution
Formula propulsion system breaches structure and the parts match limitation of traditional fanjet, thus can obtain higher bypass ratio.
Distributed propulsion system is also more suitable for the power of following blended wing-body aircraft simultaneously.
Rolls-Royce company of Britain obtains the invention of multinomial " distributed propulsion system and its control method " in 2012-2013
Patent, the patent No.:EP2581308A2、US2013/0094963 A1、US9376213B2.The invention uses two installed under the wing
Platform turbogenerator drives engine power generation, then by power transmission to being distributed on wing, wing tip or fuselage afterbody both sides
Propeller on, by motor drive propeller produce thrust.Rolls-Royce company also applied for a similar China specially in 2014
Profit, the patent No.:CN 104670503 A.
United Technologies Corporation obtained the invention of entitled " to the distributed propulsion system of rotary type rotor " in 2015
Patent, the patent No.:EP2930114A1、US 2015/0284071 A1.The thinking of the invention is to utilize the combustion positioned at afterbody
Gas generator driving power turbine operating, by main reducing gear and time decelerator, driving is located at rear body both sides to power turbine indirectly
To rotary type rotor produce thrust.
United Technologies Corporation proposes a kind of fly in the A1 of Publication No. US 2008/0098719 innovation and creation
Machine propulsion system.In the system, single gas generator drives low-pressure turbine, and low-pressure turbine is driven indirectly by double reduction gear
Multiple fans of motivation body both sides.Air-flow after fan compression is then divided into two strands, and one is discharged by duct from airplane tail group, separately
One is sucked by compressor, participates in the thermodynamic cycle of gas generator.
Air Passenger company discloses a kind of invention of the aircraft with electric device in Publication No. CN 104229144A
Create.The invention is essentially a kind of distributed propulsion system based on electric energy.Electric energy is produced by generator of electric energy, then passed through
Electric energy is assigned in the propulsion plant of fuselage both sides to drive it to produce thrust by electric supply installation.In order to solve electric energy
Energy storage device and hybrid power system are further provided with device power output and the unmatched problem of propeller demand power, the system
System.
Proposed in Publication No. CN 104973234A innovation and creation a kind of using distributed electric ducted fan wing flap
The aircraft of high-lift system.Its intension be using power source drive be located at wing on multiple ducted fans and after fuselage
The ascending fan system in portion.Do not point out which kind of power source used in text.
There is presently no the academic dissertation and scientific paper on distributed propulsion system.
The essence of distributed propulsion system is, by the energy of the energy source generator generation of concentration, to distribute to multiple distributions
Propeller, this along with energy distribution and transmission.Transmission means is distributed according to energy, can be by existing distributed promote
System is divided into two classes:One class is to be based on driven by power (patent:EP2581308A2、US2013/0094963 A1、US9376213B2、
104,229,144 104973234 A of A, CN of A, CN of CN 104670503), another kind of is to be based on machine driving (patent:
EP2930114A1、US 2015/0284071 A1、US 2008/0098719 A1).In both systems, gas turbine hair
The high-temperature high-pressure fuel gas that motivation is produced be used to generate electricity or drive turbine to produce shaft work, and subsequent electric energy and shaft work drive propeller again
Operating produces thrust.Both systems still suffer from some technical difficulties in implementation process.Distribution based on electric power distribution
The technical barrier of formula propulsion system is the development of high density energy storage device and super high power motor.And based on mechanically operated point
The problem of cloth propulsion system, is its mechanical constraint for not being completely free of gas generator and propeller, is limited to mechanical biography
The factors such as the structure and weight of dynamic device, the distance of propeller distribution is limited, is unfavorable for layout on board the aircraft.
The content of the invention
Existing energy storage device and motor power (output) can not expire when electric power distribution is based on present in prior art to overcome
Sufficient demand;During based on machine driving, mechanical transmission mechanism is complicated, weight is big, is unfavorable for the deficiency of layout on board the aircraft, this
Invention proposes a kind of distributed propulsion system.
The present invention includes turbogenerator core engine, efficient working medium transmitting device, high energy working medium harvester and distribution
Propeller.The input of the gas collecting apparatus of the high energy working medium harvester and the core engine compressor of turbogenerator core engine
Output end connection;The output end of the high energy working medium harvester and the inlet communication of efficient working medium transmitting device.The height
The input of the output end that transmission in effect working medium transmitting device is in charge of respectively with the propeller turbine volute of each distributed propeller
End connection;The input that the transmission is in charge of is connected with the transmission house steward in the efficient working medium transmitting device.6 distributed propulsions
Device is distributed on the turbogenerator core engine both sides.
The turbogenerator core engine is single rotor gas turbine jet or birotary burbine jet engine;
Described distributed propeller is the turbo-driven ducted fan of propeller or the turbo-driven propeller of propeller.
Described gas collecting apparatus includes four airway tubes, collector ring and four airway tube regulating valves.Described gas collection toroidal shell
The same side surface of body is evenly equipped with four airway tube connecting holes, and the input of four airway tubes is separately mounted to each airway tube connection
Kong Shang.Four airway tube regulating valves are separately mounted to the output end of each airway tube.The surface of the collector ring housing is arc
Shape, and being open for the arc collector ring housing is located at the inner side of collector ring housing, makes its cross section " U "-shaped.By the pressure
The outer casing cutting of mechanism of qi is two sections;Two side at the collector ring opening is consolidated with cutting for casing outside two sections of compressor respectively
Even, the collector ring is made to together form blower outlet air-flow outer ring channel with the outer casing of compressor.Described gas turbine
Core engine compressor on engine core machine has two ring exits, respectively annular outlet and outer ring exit;It is described
Outer ring exit connected with the input of blower outlet air-flow outer ring channel;The annular outlet and core engine combustion chamber
Input connection.
During assembling, by the output end of four airway tubes on collector ring housing respectively be distributed in turbine rear casing four
The input connection of individual tail gas regenerative apparatus, by each airway tube by the air stream transportation of blower outlet air-flow outer ring channel to each
In tail gas regenerative apparatus.4 tail gas regenerative apparatuses are divided into two groups, and the output end of each group tail gas regenerative apparatus passes through hot sky
Airway is connected with the transmission house steward positioned at the turbogenerator core engine both sides respectively.
The tail gas regenerative apparatus is circumferentially uniformly mounted on the inside of turbine rear casing, the axis of the tail gas regenerative apparatus with
Angle α=0 °~90 ° between the axis of the turbogenerator core engine.
The transmission house steward has two, respectively positioned at the turbogenerator core engine both sides.One group of U-tube beam regenerator
Output end connect hot air duct, by three-way connection respectively with it is each transmission house steward input connect.In each transmission
Three air-flow outputs are distributed with house steward, being connected to transmission in each air-flow output is in charge of.It is described to transmit what is be in charge of
Input of the output end respectively with the propeller turbine volute of each distributed propeller is connected.
The input being in charge of that transmits is through the via on the distributed propeller support plate, with propeller turbine volute
Input be connected.Propeller turbine volute is ring-like, is wrapped in around propeller turbine, its output end is distributed in propeller
The inner side of turbine volute, and be connected with the input of centrifugal propeller turbine.
When distributed propeller ducted fan turbo-driven for propeller, described ducted fan includes fan, contained
Road fancase, gear reduction unit, propeller turbine wheel shaft, propeller turbine volute, propeller turbine, machine in distributed propeller
Casket and distributed propeller support plate.4 distributed propeller support plates are distributed on ducted fan casing and machine in distributed propeller
Between casket, one end of the distributed propeller support plate is set to be fixed on the inner surface of ducted fan casing, the other end is fixed on institute
State the outer surface of casing in distributed propeller.The propeller turbine wheel shaft is located in distributed propeller in casing, and two ends are equal
It is arranged on by bearing on distributed propeller inner support;The distributed propeller inner support of described support is fixed on the distribution
The inner surface of casing in formula propeller;The center of the center line of the propeller turbine wheel shaft and casing in the distributed propeller
Line is overlapped.
When the gas-turbine unit core engine uses birotary burbine jet engine, the turbogenerator core
The output end of the high-pressure compressor of machine is connected with the input of the gas collecting apparatus of high energy working medium harvester;The high energy working medium is adopted
The output end of acquisition means and the inlet communication of efficient working medium transmitting device.
When described distributed propeller propeller turbo-driven for propeller, propeller promotes air-flow to transport backward
It is dynamic, produce pulling force.
Essential distinction of the invention with existing distributed propulsion system is to realize distribution by the way of working medium is transmitted
The distribution and transmission of energy in propulsion system, i.e., the high energy working medium directly produced energy source are transferred in distributed propeller
To drive propeller to operate.On the one hand distribution based on electric power distribution can be overcome based on the distributed propulsion system that working medium is transmitted
Dependence of the propulsion system to high-energy-density energy storage device and super high power motor, lifts can be achieved for distributed propulsion system
Property;On the other hand it can break away from based on the machinery in mechanically operated distributed propulsion system between gas generator and propeller about
Beam, breaks through the bypass ratio limit of traditional fanjet and conventional distributed power, and realizes that back-heating type is designed, and improves and promotes effect
Rate.
Present invention uses existing spiral case technology and U-tube beam regenerator technology.Spiral case is centripetal turbine outer wrapping
One ghost, inside there is guide vane, for outside air-flow to be collected, and imports in centripetal turbine, promotes centripetal turbine to do
Work(.Spiral case is a kind of conventional structure of aero-turbine, is also widely used in turbocharger.
Regenerator is a core component in intercooled regeneration turbogenerator, and compressor output end air-flow is exported with turbine
Hold combustion gas to carry out heat exchange by regenerator, be effectively utilized turbine output end waste heat gas, improve compressor output end gas
The acting ability of stream.U-tube beam regenerator is exactly the one kind for the regenerator that intercooled regeneration turbogenerator is used, its primary structure
It is the array U-tube of discharge and discharge both sides, heat exchange air-flow enters from inlet manifold, passes through opposed double u-tube stream
Enter outlet discharge, hotter turbine output end combustion gas to flow the angle of attack necessarily to skim over heat exchanger, so as to reach the purpose of heat exchange.
In the present invention, gas-turbine unit core engine, high energy work are included based on the distributed propulsion system that working medium is transmitted
Matter harvester, efficient working medium transmitting device and distributed propeller.Its working method is gas-turbine unit core engine
The working medium of high energy is produced by its internal thermodynamic cycle.High energy working medium harvester is installed on gas-turbine unit core engine
On, and the unnecessary high energy working medium produced collects.The output end of high energy working medium harvester is transmitted with efficient working medium and filled
Put connected, high energy working medium is transferred to distributed propeller by efficient working medium transmitting device.With height in distributed propeller
The energy driving propeller of energy working medium produces thrust.
Gas-turbine unit core engine is single rotor or twin spool gas turbine jet engine;Pass through its internal cloth
Leiden circulation produces high energy working medium.High energy working medium is the compressed air drawn after core engine compressor, can be in turbine output end
Backheat is carried out, further the interior energy of lifting working medium.
High energy working medium harvester is returned comprising at least one gas collecting apparatus, at least a set of transfer conduit and at least one tail gas
Thermal.A set of gas collecting apparatus is at least installed in each gas-turbine unit core engine.The input of gas collecting apparatus and combustion gas
The compression member output end connection of turbogenerator core engine, the unnecessary high energy working medium that gas-turbine unit core engine is produced
Collect.Gas collecting apparatus output end is connected with transfer conduit input, and working medium is transferred at least one by transfer conduit
In tail gas regenerative apparatus.Transfer conduit output end is connected with the input of tail gas regenerative apparatus, and compressed air is filled in tail gas backheat
Exchanged heat in putting with tail gas.The output end of tail gas regenerative apparatus is connected with the input of efficient working medium conveying arrangement.
Efficient working medium transmitting device is high thermal resistance, lower resistance working medium conveyance conduit, and it is act as the working medium transmission of high energy
To among distributed propeller.Efficient working medium transmitting device is comprising at least transmission house steward and multiplexing are in charge of all the way.Transmission is total
The input (that is, input of efficient working medium transmitting device) of pipe is connected with the output end of working medium harvester, transmission house steward's
Output end is then in charge of for multiplexing in parallel.The input being in charge of is transmitted with transmission house steward to be connected;Transmit the output end being in charge of
Then connect distributed propeller.Each distribution propeller correspondence at least be in charge of all the way by transmission.Transmission house steward and transmission be in charge of by
The high temperature high voltage resistant and higher material of thermal resistance is made, is provided with guiding device, to reduce flow losses at pipeline interior corners.
The effect of distributed propeller is the propulsion work(that the energy of high energy working medium is converted into aircraft, its implementation bag
Contain but be not limited to by turbo-driven gear drive fan system, such as turbo-driven geared airscrew system.For
Using the turbo-driven gear drive fan system of propeller, the transmission that high energy working medium passes sequentially through efficient working medium transmitting device is total
Pipe is in charge of into propeller turbine with transmission, and drives it to operate.Propeller turbine drives fan running by gear reduction unit,
Produce thrust.
Compared with prior art, the present invention can further lift the efficiency of existing transporter dynamical system, reduce carbon row
Put, energy-conserving and environment-protective, meanwhile, the realizability of the distributed propulsion system of lifting.Concrete analysis is as follows:
The transmission of alternative electric energy and mechanical energy by the way of working medium is transmitted, reduces the number of times of energy conversion, reachable
To higher system effectiveness and lower oil consumption rate.
The limit of the technologies such as mechanical structure, electric energy storage and super high power that existing distributed propulsion system is present is broken away from
System, can be achieved bigger bypass ratio, so as to obtain higher efficiency and lower oil consumption rate.
Working medium generating means, working medium harvester and the working medium transmitting device being related in the present invention have practical at present
Technology is alternative, and the technology maturity of basic technology is high, only need to carry out adaptive improvement remodeling for the system, so that
Improve the realizability of whole system.
At present, the bypass ratio of civilian big Bypass Ratio Turbofan Engine is close to 10, and the limit that future is likely to be breached is 10~15.
Aerothermodynamic computation model is established for examples detailed above, main design parameter is analyzed to propulsion system bypass ratio and oil consumption
The influence of rate.Distributed propulsion system aerothermodynamic result of calculation based on working medium is shown, in the state of the art, this hair
Bright bypass ratio is expected to reach more than 20~25, and oil consumption rate than most common CFM56 engines at present (bypass ratio is about 6.0,
Take off oil consumption rate about 0.37kg/kgf/h) oil consumption rate decline 40%~50%.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention;
Fig. 2 is the structural representation of embodiment 1;
Fig. 3 is the structural representation of gas-turbine unit core engine in embodiment 1;
Fig. 4 is the structural representation of gas-turbine unit core engine in embodiment 2;
Fig. 5 is the structural representation of gas-turbine unit core engine collector ring;Wherein 5a is the axonometric drawing of collector ring, 5b
It is front view, 5c is 5b partial enlarged drawing;
Fig. 6 is the structural representation of U-tube beam regenerator;Wherein 6a is front view, and 6b is side view, and 6c is top view;
Fig. 7 is the structural representation of distributed propeller in embodiment 1;Wherein 7a is front view, and 7b is side view, and 7c is
Top view;
Fig. 8 is the structural representation of distributed propeller in embodiment 3;Wherein 8a is front view, and 8b is side view, and 8c is
Top view;
Fig. 9 is the layout of distributed propulsion system on board the aircraft;Wherein 9a is front view, and 9b is top view.In figure:
1. distributed propeller inner support;2. high energy working medium harvester;3. gas collecting apparatus;4. transfer conduit;5. tail gas
Regenerative apparatus;6. high-pressure compressor;7. efficient working medium transmitting device;8. transmit house steward;9. high-pressure turbine;10. transmission is in charge of;
11. high-pressure turbine shaft;12. distributed propeller;13. guiding device;14. gas-turbine unit core engine;15. core engine pressure
Mechanism of qi;16. core engine combustion chamber;17. core engine turbine;18. core engine jet pipe;19. propeller turbine;20. gear reduction unit;
21. fan;22. propeller;23. contain jet pipe outside propeller;24. distributed propulsion system;25. blended wing-body aircraft;26. push away
Enter cabin;27. distributed propeller support plate;28. propeller intension jet pipe;29. casing in distributed propeller;30. airway tube;
31. the outer casing of compressor;32. turbine rear casing;33. collector ring;34.U types restrain regenerator;35. regenerator input;36.
Regenerator output end;37.U type heat exchanger tubes;38.U type heat exchanger tube output ends;39. hot combustion gas input;40. hot combustion gas output end;
41. house steward is flowed cold;42. hot return header;43. hot air duct;44.U type heat exchanger tube inputs;45. propeller turbine snail
Shell;46. propeller turbine wheel shaft;47. ducted fan casing;48. airway tube regulating valve;49 bearings;50. low-pressure compressor;51. it is low
Press turbine;52. low-pressure turbine shaft
Embodiment
Embodiment 1
The present embodiment is a kind of distributed propulsion system transmitted based on working medium.
The present embodiment includes turbogenerator core engine 14, efficient working medium transmitting device 7, the and of high energy working medium harvester 2
Distributed propeller 12.The input of the gas collecting apparatus 3 of the high energy working medium harvester 2 and the core of turbogenerator core engine
The output end connection of scheming compressor 15;The output end of the high energy working medium harvester 2 is entered with efficient working medium transmitting device 7
Mouth connection.Transmission in the efficient working medium transmitting device 7 is in charge of 10 output end and pushed away respectively with each distributed propeller 12
Enter the input connection of device turbine volute 45;10 input and the biography in the efficient working medium transmitting device 7 are in charge of in the transmission
Defeated house steward 8 connects.In the present embodiment, the distributed propeller 12 has six;Six distributed propellers 12 are distributed on described
The both sides of turbogenerator core engine 14.In the present embodiment, the turbogenerator core engine 14 is a single rotor gas turbine
Jet engine.
Described gas collecting apparatus 3 includes four airway tubes 30, collector ring 33 and four airway tube regulating valves 48.Shown collection
Compression ring 33 is toroidal shell, and four airway tube connecting holes, four air guides are evenly equipped with the same side surface of the housing of collector ring 33
The input of pipe 30 is separately mounted on each airway tube connecting hole.Four airway tube regulating valves 48 are separately mounted to each air guide
The output end of pipe 30.The surface of the housing of collector ring 33 is arc, and the opening of the housing of arc collector ring 33 is located at collection
The inner side of the housing of compression ring 33, makes its cross section " U "-shaped.It it is two sections by the cutting of casing 31 outside the compressor;By the gas collection
Two side is connected with cutting for casing 31 outside two sections of compressor respectively at the opening of ring 33, makes outside the collector ring 33 and compressor
Casing 31 together form blower outlet air-flow outer ring channel.Core engine in described gas-turbine unit core engine 14
Compressor 15 has two ring exits, respectively annular outlet and outer ring exit;Described outer ring exit and compressor
The input connection of exit flow outer ring channel;The annular outlet is connected with the input of core engine combustion chamber 16.
During assembling, by the output end of four airway tubes 30 on the housing of collector ring 33 respectively with being distributed in turbine rear casing 32
The input connection of four interior tail gas regenerative apparatuses 5, by each airway tube 30 by the gas of blower outlet air-flow outer ring channel
It is streamed in each tail gas regenerative apparatus 5.4 tail gas regenerative apparatuses are divided into two groups, each group tail gas regenerative apparatus it is defeated
Go out end to connect with the transmission house steward 8 positioned at the both sides of turbogenerator core engine 14 respectively by hot air duct 43.
The tail gas regenerative apparatus 5 is circumferential to be uniformly mounted to the inner side of turbine rear casing 32, the axle of the tail gas regenerative apparatus
Angle α=0 °~90 ° between line and the axis of the turbogenerator core engine 14.
In the present embodiment, the tail gas regenerative apparatus 5 is U-tube beam regenerator 34.The regenerator import 35 with it is cold come
Stream house steward 41 connects.Multichannel U heat exchange 37 is connected in parallel on cold flow on the side wall of house steward 41.Air-flow flows the wall of house steward 41 by cold
On U heat exchange input 44 enter U heat exchange 37.Gap of the hot combustion gas of U heat exchange 37 from the outside of U heat exchange 37
Between flow through, pass through the compressed air heat exchange inside tube wall and U heat exchange 37.Hot-air after heat exchange is exported from U heat exchange
End 38 is collected into hot return header 42, and reaches regenerator output end 36 via hot return header 42.Each regenerator output
End 36 is connected with hot air duct 43 all the way respectively.The output end of hot air duct 43 and the transmission of efficient working medium transmitting device 7
House steward 8 is connected.HTHP air after heat exchange enters transmission house steward 8 by hot air duct 43.
The transmission house steward 8 has two, respectively positioned at the both sides of turbogenerator core engine 14.One group of U-tube beam is returned
The output end of hot device 34 connects hot air duct 43, and the input by three-way connection respectively with each transmission house steward is connected.
Three air-flow outputs are distributed with each transmission house steward 8, biography is connected in each air-flow output
It is defeated to be in charge of 10.The input of 10 output end respectively with the propeller turbine volute 45 of each distributed propeller 12 is in charge of in the transmission
End connection.
The distributed propeller 12 drives fan 21 using propeller turbine 19.
When distributed propeller is the turbo-driven ducted fan of propeller, described ducted fan include fan 21,
Ducted fan casing 47, gear reduction unit 20, propeller turbine wheel shaft 46, propeller turbine volute 45, propeller turbine 19, distribution
Casing 29 and distributed propeller support plate 27 in formula propeller.The distributed propeller support plate 27 has 4, and is distributed on duct
In fancase 47 and distributed propeller between casing 29, one end of the distributed propeller support plate 27 is set to be fixed on duct
The inner surface of fancase 47, the other end is fixed on the outer surface of casing 29 in the distributed propeller.The propeller whirlpool
Wheel shaft 46 is located in distributed propeller in casing 29, and two ends are arranged on distributed propeller inner support 1 by bearing 49;
The distributed propeller inner support 1 of described support is fixed on the inner surface of casing 29 in the distributed propeller;It is described to promote
The center line of device turbine wheel shaft 46 is overlapped with the center line of casing 29 in the distributed propeller.
The gear reduction unit 20 is sleeved on the front end of the propeller turbine wheel shaft 46;The propeller turbine 19 is sleeved on
The rear end of the propeller turbine wheel shaft 46.
Described gear reduction unit 20 is planetary reducer;The sun gear of planetary reducer is sleeved on described push away
Enter the front end of device turbine wheel shaft 46;Fan 21 is sleeved on the external toothing of planetary reducer.
The transmission is in charge of 10 input through the via on the distributed propeller support plate 27, with propeller turbine
The input of spiral case 45 is connected.Propeller turbine volute 45 is ring-like, is wrapped in around propeller turbine 19, its output end is equal
The inner side of propeller turbine volute 45 is distributed in, and is connected with the input of centrifugal propeller turbine 19.
The interior energy of HTHP air is converted into shaft work by propeller turbine 19, and passes through propeller turbine wheel shaft 46 and gear
The driving fan 21 of decelerator 20 is operated.Optimal of fan 21 and the rotating speed of propeller turbine 19 can be realized by gear reduction unit 20
Match somebody with somebody.Incoming air is sucked ducted fan casing 47 and is compressed by fan 21.Then, compressed air contains jet pipe outside propeller
Accelerating Removal is expanded in 23 and produces main thrust.
The working method of the present embodiment:
Gas-turbine unit core engine 14 produces high energy working medium using the Brighton circulation occurred in it.Core engine is calmed the anger
Incoming air is sucked and is compressed by machine 15.Compressed air is divided into two strands, one in the output of core engine compressor 15
Stock air-flow enters collector ring 33 by the input of collector ring 33, and another strand of air-flow enters in core engine combustion chamber 16 to be carried out with fuel
Blending burning, forms the combustion gas of HTHP.Combustion gas expansion work in core engine turbine 17, and promote core engine compressor 15
Operating.High-temperature high-pressure fuel gas after core engine turbine 17 continue through tail gas regenerative apparatus 5 and exchanged heat with compressed air.Combustion gas
Discharged by core engine jet pipe 18, produce a small amount of thrust.
The air that collector ring 33 is collected is transmitted to the import of U-tube beam regenerator 34 by airway tube 30, and enters cold next
Flow house steward 41.The U heat exchange input 44 that air-flow is flowed by cold on the wall of house steward 41 enters U heat exchange 37.Hot combustion gas
Flow through, exchanged heat by the compressed air inside tube wall and U heat exchange 37 between the gap in the outside of U heat exchange 37.After heat exchange
Hot-air be collected into hot return header 42 from U heat exchange output end 38, and reach regenerator via hot return header 42
Output end 36.Each regenerator output end 36 is connected with hot air duct 43 all the way respectively.Hot air duct 43 is by after heat exchange
HTHP air enters transmission house steward 8 by hot air duct 43.
The compressed air of HTHP is adjusted from transmission house steward 8 by airway tube regulating valve 48 to be in charge of into transmission step by step
In 10, and eventually arrive in multiple distributed propellers 12.
The air of HTHP is in charge of 10 by transmission and enters propeller turbine volute 45.Propeller turbine volute 45 is by height
Warm pressure-air imports propeller turbine 19.The expansion work of HTHP air is converted into shaft work by propeller turbine 19, and is led to
Cross propeller turbine wheel shaft 46 and the driving fan 21 of gear reduction unit 20 is operated.By gear reduction unit 20 fan 21 can be realized with pushing away
Enter the best match of the rotating speed of device turbine 19.Incoming air is sucked ducted fan casing 47 and is compressed by fan 21.Then, press
Contracting air is contained outside propeller expands Accelerating Removal generation main thrust in jet pipe 23.
Fig. 9 illustrates layout of the above-mentioned example of distributed propulsion system 24 on blended wing-body aircraft 25.Distribution is pushed away
Enter system 24 in the propelling module 26 on the upside of the afterbody of blended wing-body aircraft 25.Single gas-turbine unit core engine 14
In on the fuselage center line of blended wing-body aircraft 25,6 gear drive fan systems 22 are arranged symmetrically in gas-turbine unit core
The left and right sides of scheming 14.Such mounting means allows engine to utilize the low speed for flowing through the surface of blended wing-body aircraft 25 attached
Surface layer, improves propulsive efficiency.
Embodiment 2
The present embodiment is a kind of distributed propulsion system transmitted based on working medium.
The difference of embodiment 2 and embodiment 1 is that the gas-turbine unit core engine 14 in embodiment 2 is double
Rotor scroll jet engine.Remaining each part is same as Example 1.
The present embodiment includes turbogenerator core engine 14, efficient working medium transmitting device 7, the and of high energy working medium harvester 2
Distributed propeller 12.The input of the gas collecting apparatus 3 of the high energy working medium harvester 2 and the height of turbogenerator core engine
Press the output end connection of compressor 6;The output end of the high energy working medium harvester 2 connects with the import of efficient working medium transmitting device
It is logical.The propeller of 10 output end respectively with each distributed propeller 12 is in charge of in transmission in the efficient working medium transmitting device 7
The input connection of turbine volute 45;It is total with transmission in the efficient working medium transmitting device 7 that 10 input is in charge of in the transmission
Pipe 8 is connected.In the present embodiment, the distributed propeller 12 has six;Six distributed propellers 12 are distributed on the turbine
The both sides of engine core machine 14.In the present embodiment, the turbogenerator core engine 14 is a twin spool gas turbine jet
Engine.
Two side at the opening of the collector ring 33 is connected with cutting for casing 31 outside two sections of compressor respectively, makes institute
State collector ring 33 and together form high-pressure compressor exit flow outer ring channel with the outer casing 31 of compressor.Described gas turbine
High-pressure compressor 6 on engine core machine 14 has two ring exits, respectively annular outlet and outer ring exit;It is described
Outer ring exit connected with the input of high-pressure compressor exit flow outer ring channel;Fired with core engine the annular outlet
Burn the input connection of room 16.
During assembling, by the output end of four airway tubes 30 on the housing of collector ring 33 respectively with being distributed in turbine rear casing 32
The input connection of four interior tail gas regenerative apparatuses 5, by each airway tube 30 by high-pressure compressor exit flow outer ring channel
Air stream transportation to each tail gas regenerative apparatus 5 in.4 tail gas regenerative apparatuses are divided into two groups, each group tail gas regenerative apparatus
Output end connected respectively with the transmission house steward 8 positioned at the both sides of turbogenerator core engine 14 by hot air duct 43.
Embodiment 3
The present embodiment is a kind of distributed propulsion system transmitted based on working medium.
The difference of embodiment 3 and embodiment 1 is that the use propeller 22 in embodiment 3 substituted for the wind in embodiment 1
Fan 21.Remaining each part is same as Example 1.
The present embodiment includes turbogenerator core engine 14, efficient working medium transmitting device 7, the and of high energy working medium harvester 2
Distributed propeller 12.The input of the gas collecting apparatus 3 of the high energy working medium harvester 2 and the height of turbogenerator core engine
Press the output end connection of compressor 6;The output end of the high energy working medium harvester 2 connects with the import of efficient working medium transmitting device
It is logical.The propeller of 10 output end respectively with each distributed propeller 12 is in charge of in transmission in the efficient working medium transmitting device 7
The input connection of turbine volute 45;It is total with transmission in the efficient working medium transmitting device 7 that 10 input is in charge of in the transmission
Pipe 8 is connected.In the present embodiment, the distributed propeller 12 has six;Six distributed propellers 12 are distributed on the turbine
The both sides of engine core machine 14.
Three air-flow outputs are distributed with each transmission house steward 8, biography is connected in each air-flow output
It is defeated to be in charge of 10.The input of 10 output end respectively with the propeller turbine volute 45 of each distributed propeller 12 is in charge of in the transmission
End connection.
The distributed propeller 12 drives propeller 22 using propeller turbine 19.
The distributed propeller includes propeller 22, gear reduction unit 20, propeller turbine wheel shaft 46, propeller turbine snail
Casing 29 in shell 45, propeller turbine 19 and distributed propeller.The propeller turbine wheel shaft 46 is located in distributed propeller
In casing 29, two ends are arranged on distributed propeller inner support 1 by bearing 49;In the distributed propeller of described support
Support 1 is fixed on the inner surface of casing 29 in the distributed propeller;The center line of the propeller turbine wheel shaft 46 with it is described
The center line of casing 29 is overlapped in distributed propeller.
The gear reduction unit 20 is sleeved on the front end of the propeller turbine wheel shaft 46;The propeller turbine 19 is sleeved on
The rear end of the propeller turbine wheel shaft 46.
Described gear reduction unit 20 is planetary reducer;The sun gear of planetary reducer is sleeved on described push away
Enter the front end of device turbine wheel shaft 46;Propeller 22 is sleeved on the external toothing of planetary reducer.
The output end that the transmission is in charge of 10 is connected with the input of propeller turbine volute 45.Propeller turbine volute 45
To be ring-like, be wrapped in around propeller turbine 19, its output end is distributed in the inner side of propeller turbine volute 45, and with centrifugation
The input of formula propeller turbine 19 is connected.
The interior energy of HTHP air is converted into shaft work by propeller turbine 19, and passes through propeller turbine wheel shaft 46 and gear
The driving propeller 22 of decelerator 20 is operated.By gear reduction unit 20 propeller 22 can be realized with the rotating speed of propeller turbine 19 most
Good matching.Propeller 22 promotes air-flow to move backward, produces pulling force.