CN108995817A - A kind of polycyclic heat exchanger and propulsion system and method based on polycyclic heat exchanger - Google Patents
A kind of polycyclic heat exchanger and propulsion system and method based on polycyclic heat exchanger Download PDFInfo
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- CN108995817A CN108995817A CN201810778759.0A CN201810778759A CN108995817A CN 108995817 A CN108995817 A CN 108995817A CN 201810778759 A CN201810778759 A CN 201810778759A CN 108995817 A CN108995817 A CN 108995817A
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- heat exchanger
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- cooling gas
- heat exchange
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- 125000003367 polycyclic group Chemical group 0.000 title claims abstract description 85
- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000000112 cooling gas Substances 0.000 claims abstract description 68
- 239000012530 fluid Substances 0.000 claims abstract description 48
- 238000010438 heat treatment Methods 0.000 claims abstract description 41
- 230000001141 propulsive effect Effects 0.000 claims description 21
- 239000007789 gas Substances 0.000 claims description 13
- 238000002485 combustion reaction Methods 0.000 claims description 11
- 238000001816 cooling Methods 0.000 claims description 9
- 239000003758 nuclear fuel Substances 0.000 claims description 8
- 238000003860 storage Methods 0.000 claims description 5
- 230000002411 adverse Effects 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 4
- 238000012546 transfer Methods 0.000 claims description 4
- 206010037660 Pyrexia Diseases 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims description 3
- 230000002085 persistent effect Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 238000010276 construction Methods 0.000 claims description 2
- 238000009413 insulation Methods 0.000 claims description 2
- 238000009830 intercalation Methods 0.000 claims description 2
- 230000003416 augmentation Effects 0.000 claims 1
- 230000001788 irregular Effects 0.000 claims 1
- 239000000446 fuel Substances 0.000 abstract description 5
- 238000004140 cleaning Methods 0.000 abstract description 4
- 230000002045 lasting effect Effects 0.000 abstract description 4
- 230000006872 improvement Effects 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 125000004122 cyclic group Chemical group 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 229910001338 liquidmetal Inorganic materials 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000002285 radioactive effect Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/22—Aircraft characterised by the type or position of power plant using atomic energy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/408—Nuclear spacecraft propulsion
Abstract
The invention discloses a kind of polycyclic heat exchanger and propulsion system and method based on polycyclic heat exchanger, by air intake duct, compressor, polycyclic heat exchanger, jet pipe constituted, and polycyclic heat exchanger includes: polycyclic heat exchange structure and turbine wheel shaft；Polycyclic heat exchange structure includes flow-disturbing fin, external insulated wall, cooling gas power chamber and heating fluid line, wherein heating fluid line is optional with fluid heating inlet flow tube and fluid heating exit flow tube.The present invention reaches optimal polycyclic chamber structure using cleaning, high efficient energy sources, using heat exchange and propulsion simultaneously, after continuous heat source is added, it is possible to provide meets the lasting thrust power stablized cruise with reinforce continuation of the journey double mode；The propulsion system safety of optional enclosed thermodynamic cycle is higher, and the influence to environment and the public is small；So that fuel carrying amount is reduced, it is the Optimal improvements to existing propulsion system that system load increases on year-on-year basis, which is suitable for the mission requirements of a variety of scales, has biggish application prospect for the utilization of polycyclic heat exchanger structure.
Description
Technical field
The present invention relates to nuclear propulsion field, specially a kind of polycyclic heat exchanger and propulsion system based on polycyclic heat exchanger and
Method.
Background technique
For propulsion system, presently, there are the problem of be: quick start with to stablize cruise be to judge that propulsion system is started
The important external index of machine performance superiority and inferiority, fuel feeding are too fast, in fact it could happen that compressor surge leads to combustion chamber richextinction, before whirlpool
Temperature, which is promoted rapidly, may cause system overheat, these limiting factors seriously constrain the fast lifting of temperature before whirlpool.To realize
The stable heat exchange of engine continuous is adjusted, and polycyclic needle recuperator is used to replace combustion chamber can be stable to provide for propulsion system
Energy source.Polycyclic needle recuperator can be asked unstable vigorous combustion by the fluid interchange in the small space of research, narrow passage
Topic be converted to stable heat transfer problem, avoid runner acutely exchange heat and caused by additional energy lose；And it is narrow logical using annular
The advantage in road optimizes the heat exchange structure of combustion chamber.
In terms of energy utilization, have data to show: medium-long range propulsion system reaches in full load fuel oil carrying amount is
50% or more of gross weight of uniting.Therefore, there are biggish performance boost spaces for large-scale propulsion system.Heat exchanger heat source may be from clearly
Clean energy combustion heat release can be from energy of fissioning or decay in nuclear energy, this reduces propulsion system fuel to a certain extent
Carrying amount；Using nuclear energy as the propulsion system of heat source, is supplied by stable heat, can be needed to automatically adjust power need according to flight
Ask, compared with traditional combustion, propulsion system loss of weight amplitude can reach 40% or more, nuclear energy support under cruise and afterburner flying,
It can be completely achieved long endurance autonomous flight, it is to propulsion system performance that this is of great significance to propulsion system performance is improved
It is whole to improve.
Compared with prior art, conventional nuclear propulsion system reactor can only individually be arranged outside propulsion system, by gas
The limitation of the cooling reactor core exchange capability of heat difference of body and reactor core marginal requirements, reactor is bulky, and weight is larger.The present invention is existing
On the basis of Conventional propulsion systems, reactor core no longer single use gas heat-transfer, reactor volume can be smaller, more steps up
It gathers, realizes the flexible arrangement of shut-down system；In addition, reactor can make full use of combustion chamber if being embedded in nuclear fuel at fin
Narrow space, and combine polycyclic heat exchanger large area heat exchange Inherent advantage, realize reactor miniaturized compact design；This
A little innovative designs will play an important role to the optimization of atomic propulsion system propulsive performance.
Summary of the invention
The technology of the present invention solves the problems, such as: overcoming the deficiencies of the prior art and provide a kind of polycyclic heat exchanger and is changed based on polycyclic
The propulsion system and method for hot device are the improvement carried out to traditional propulsion system, pass through heat exchange structure annular under optimal judgement
Spacing dimension adjustment and optimization, obtain the optimal heat exchanger structure under decision criteria；It is a large amount of to reduce vigorous combustion bring
Thermal loss is realized and stablizes lasting heat exchange；The heat exchange structure can satisfy all kinds of power demands, be suitble to a variety of propulsion air inlets；For
Ensure the security reliability of propulsion system, the independent thermal source of indirect cyclic process can be matched, to avoid radiating the dirt to air inlet is promoted
Dye, realize propulsion system cleaning, efficiently.
In order to reach above-mentioned target, the technical scheme adopted by the invention is as follows:
A kind of polycyclic heat exchanger and the propulsion system based on polycyclic heat exchanger, by air intake duct 11, compressor 12, polycyclic heat exchange
Device 13, jet pipe 14 are constituted, and polycyclic heat exchanger 13 is located at after compressor 12 and before jet pipe 14, comprising: polycyclic heat exchange
Structure 1 and turbine wheel shaft 2；Polycyclic heat exchange structure 1 passes through nested mode and turbine wheel shaft 2 between external insulated wall 4 and turbine wheel shaft 2
It is connected；External insulated wall 4 is fitted and connected with propulsion system outer casing inner wall；
Cooling gas is inhaled into inside propulsion system as propulsive working medium through air intake duct 11, and cooling gas subtracts in air intake duct
High pressure cooling gas is compressed to through compressor 12 after speed；It is quasi- using optimal judgement according to the Flowing characteristic parameters of high pressure gas
Then obtain the optimum structure of polycyclic heat exchanger 13；High pressure cooling gas sprays after entering new type heat exchanger heat exchange by jet pipe 14
Completion system promotes, and generates thrust power；
There is also following characteristics by the present invention:
Polycyclic heat exchange structure 1 includes flow-disturbing fin 3, external insulated wall 4, cooling gas power chamber 5 and heating fluid line
6；The flow-disturbing fin 3 is embedded in 5 inside and outside wall face of cooling gas power chamber and is symmetrically arranged as fin protrusion, changes for strengthening
Heat or as nuclear fuel storage embedded chip be used for intercalating dye element.
The cylinder-shaped heat exchange structure that cooling gas power chamber 5 is made of Multi-layer exchanging heat wall surface, each cylinder-shaped heat exchange
Structure is divided into two chambers, arranged stacked, and outer layer chamber circulates cooling gas, and internal layer chamber is connected with heating fluid line 6, guarantor
Card wall surface has lasting heat cooling gas；Wherein, internal layer cavity space spacing is constant, the space spacing of outer layer chamber according to
The result of optimal judgement obtains the optimal value of chamber spacing △ S.
For selecting optimum structure, specific implementation is the Optimal condition criterion；To obtain cooling gas power cavity
The optimal value of outer layer chamber spacing △ S, according to minimum, the maximum r for arranging radius in the arrangement space of polycyclic heat exchanger 13min,
rmaxThe threshold range of △ S variation is obtained, wherein optimal decision criteria includes: to be promoted in the threshold range about △ S
The heat exchanger structure of system propulsive performance paying close attention to variable T and h and being optimal simultaneously, T and h is that the function of △ S is to push away
The normalized value of power, heat exchange efficiency or thrust, heat exchange efficiency；Obtained after T and h value are fitted its co-variate function P (T,
H), the maximum of points P of matched curvemaxThe numerical value △ S of △ S under (T, h) coordinateoptimum, that is, it is determined as optimum structure.
The heating fluid line 6 heats flow tube without external inlet and outlet when containing embedded nuclear fuel storage piece,
It is optional with fluid heating inlet flow tube 7 and fluid heating exit flow tube 8 when being heated using external heat source fluid, respectively with cooling air
Body power chamber 5 be connected, flow into heating liquid cooling gas power cavity wall surface is heated, and with the arrangement of adverse current with
Cooling gas flow direction is opposite；The origin of heat of the heating fluid line 6 is suitable for disintegration energy, decay energy or the cleaning of other high energy
The energy.
The novel propulsion system uses polycyclic 13 structure of heat exchanger that traditional combustion room is replaced to provide power for propulsion system
It supports.The polycyclic heat exchanger 13 can be used as space propultion, aero propulsion or aircraft propulsion heat exchanger near the ground；It is polycyclic
The occupied cavity structure of heat exchange structure 1 is suitable for the customization chamber of original propulsion system chamber cavity or equivalent constructions.
The turbine wheel shaft 2 is using its outer envelope as the containment surfaces of annular heat exchange structure, to maximally utilise original
Fuel oil propulsion system structure.
The advantages of the present invention over the prior art are that:
(1) polycyclic heat exchanger provided by the invention has the double benefit for improving exchange capability of heat and improving propulsion effect；It can
It realizes fuel and system loss of weight purpose, improves propulsion system load carrying capability；Using the high-efficiency cleaning energy, can not change it is more
Under conditions of ring heat exchange structure, long endurance continuation of the journey and afterburner flying dual-mode functions are realized using optimum structure, and save reinforcing
Chamber structure, so that whole improve propulsion system performance.
(2) conventional nuclear propulsion system reactor need to be individually arranged in outside propulsion system, be exchanged heat by gas cooling reactor core
The limitation of ability difference and reactor core marginal requirements, reactor is bulky, and weight is larger.The present invention is in existing Conventional propulsion systems
On the basis of, reactor core no longer single use gas heat-transfer, reactor volume can be smaller, and it is more compact, realize shut-down system
Flexible arrangement；
(3) if being embedded in nuclear fuel at fin, reactor can make full use of the narrow space of original combustion chamber, and tie
The Inherent advantage for closing polycyclic heat exchanger large area heat exchange, realizes the design of reactor miniaturized compact；According to external heat source fluid
Heating the internal layer chamber of cooling gas power chamber, then radioactive fluid will not be leaked to the Outdoor Space of propulsion system,
With preferable environment friendly.
Above-mentioned innovative design will play an important role to the optimization of atomic propulsion system propulsive performance.
Detailed description of the invention
The accompanying drawings constituting a part of this application is used to provide further understanding of the present invention, and of the invention shows
Examples and descriptions thereof are used to explain the present invention for meaning property, does not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is a kind of propulsion system structure figure based on polycyclic heat exchanger of the invention；
Fig. 2 is the structural front view of polycyclic heat exchanger of the invention；
Fig. 3 is the structural side view of polycyclic heat exchanger of the invention；
Fig. 4 is propulsion system overall layout chart of the invention；
Fig. 5 is optimal polycyclic heat exchange structure decision criteria figure in the present invention, and (a) figure is that propulsive performance is bent with the variation of △ S
Line chart；(b) figure is the Optimal Fitting curve graph of propulsive performance；
Figure label:
The polycyclic heat exchange structure of 1-；2- turbine wheel shaft；3- flow-disturbing fin；4- external insulated wall；5- cooling gas power chamber；6- adds
Hot fluid pipeline；7- fluid heats inlet flow tube；8- fluid heating exit flow tube；11- air intake duct；12- compressor；13- is polycyclic
Heat exchanger；14- jet pipe.
Specific embodiment
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, with reference to the accompanying drawing and specific real
Applying mode, the present invention is described in further detail:
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.For system disclosed in embodiment
For, due to corresponding to the methods disclosed in the examples, so being described relatively simple, related place is referring to method part illustration
?.
Those skilled in the art can use different methods to achieve the described function each specific application, but
It is that such implementation should not be considered as beyond the scope of the present invention.
Obviously, those skilled in the art can carry out various modification and variations without departing from spirit of the invention to invention
And range.If in this way, these modifications and changes of the present invention belong to the claims in the present invention and its equivalent technologies range it
Interior, then the invention is also intended to include including these modification and variations.
As shown in figure 1, figure 2, figure 3, figure 4 and figure 5, to a kind of propulsion system based on polycyclic 13 structure of heat exchanger of the invention
System, by air intake duct 11, compressor 12, polycyclic heat exchanger 13 and jet pipe 14 are constituted, air intake duct 11 be located at propulsion system most before
End enters compressor 12 for sucking cooling gas, cooling gas after slowing down in air intake duct as propulsive working medium, boil down to is high
Press cooling gas；According to the Flowing characteristic parameters of high pressure gas, the optimal of polycyclic heat exchanger 13 is obtained using optimal decision criteria
Structure；Compressor outlet is connected with the outer layer chamber of polycyclic heat exchanger cooling gas power cavity, cooling gas and polycyclic heat exchanger
The wall surface that exchanges heat carries out heat exchange and obtains energy；After cooling gas leaves polycyclic heat exchanger 13, by being arranged in propulsion system end
The jet pipe 14 at end sprays completion system and promotes, and generates thrust power；Polycyclic heat exchanger 13 includes: polycyclic heat exchange structure 1 and whirlpool
Wheel shaft 2；Polycyclic heat exchange structure 1 is connected between external insulated wall 4 and turbine wheel shaft 2, through nested mode with turbine wheel shaft 2；Insulation
Outer wall 4 is fitted and connected with propulsion system outer casing inner wall；Polycyclic heat exchanger 13 is arranged in after air intake duct 11, compressor 12, simultaneously
Before jet pipe 14；
As shown in Figure 2,3, polycyclic heat exchange structure 1 includes flow-disturbing fin 3, external insulated wall 4,5 He of cooling gas power chamber
Heat fluid line 6；The cylinder-shaped heat exchange structure that cooling gas power chamber 5 is made of Multi-layer exchanging heat wall surface, each cylinder
Shape heat exchange structure is divided into two chambers, and arranged stacked, outer layer chamber circulation cooling gas, internal layer chamber and fluid heat flow tube phase
Even, continuous heat source guarantees the persistent fever of cylinder wall surface；Cooling gas flow after heat exchanges acquisition heat with hot wall face
Cooling gas power chamber 5 out flows to jet pipe 14 and generates motive force；The internal layer cavity space spacing of cooling gas power chamber
Constant, the space spacing of outer layer chamber obtains the optimal value of chamber spacing △ S according to the result of optimal judgement；Cooling gas power
Chamber 5 can be individually customization structure or utilize original propulsion system chamber cavity.
Flow-disturbing fin 3 can be enhanced heat exchange fin or nuclear fuel storage embedded chip；It is embedded in cooling gas power cavity
Indoor external wall surface is for enhanced heat exchange or as additional nuclear heat source；
The heating fluid line 6 heats flow tube without external inlet and outlet when containing embedded nuclear fuel storage piece,
It is optional with fluid heating inlet flow tube 7 and fluid heating exit flow tube 8 when being heated using external heat source fluid, respectively with cooling air
Body power chamber 5 be connected, flow into heating liquid cooling gas power cavity wall surface is heated, and with the arrangement of adverse current with
Cooling gas flow direction is opposite.
The origin of heat of heating fluid line 6 can be disintegration energy, decay energy or other high energy clean energy resourcies.
When energy is from nuclear energy, heat exchanger flow-disturbing fin 3 is embedded in the structure of nuclear fuel element, can effectively reduce propulsion
Larger heat-exchange temperature is brought in system fuel space, effectively improves system heat exchange efficiency；Meanwhile it can match cooling from reactor
The indirect cyclic process of agent heat exchange, cooling fluid can be inert gas, liquid metal or other heat-conducting mediums, and be added by fluid
Hot inlet flow tube 7 and 8 heat exchanging device of fluid heating exit flow tube are heated.
Polycyclic heat exchanger 13 can be used as the heat exchanger of space propultion, aero propulsion or aircraft propulsion near the ground.
Polycyclic heat exchange structure 1 is the multi-layer annular structure with optimal heat exchange and propulsive performance.
Optimal decision criteria includes: to obtain paying close attention to variable T and h reaches most simultaneously in the threshold range about △ S
Excellent heat exchanger structure, T and h are that the function of △ S can be the normalized value of thrust, heat exchange efficiency or thrust, heat exchange efficiency.
The maximum value obtained after its co-variate function P (h, T) fitting, can determine that as optimum structure.
Due to the cylinder-shaped heat exchange structure that cooling gas power chamber 5 is made of Multi-layer exchanging heat wall surface, each cylindrical shape
Heat exchange structure is divided into two chambers, and arranged stacked, outer layer chamber circulation cooling gas, internal layer chamber is for guaranteeing that it is lasting that wall surface has
Heat cooling gas；Wherein, internal layer cavity space spacing is constant, and the space spacing of outer layer chamber can be according to propulsive performance
Optimization is adjusted；Therefore, cooling gas need to be according to the flowing of working medium before by polycyclic heat exchange structure 1 as propulsive working medium
Characteristic simultaneously determines with reference to optimal as a result, obtaining the optimal value of outer layer chamber spacing △ S.
To obtain the optimal value of cooling gas power cavity outer layer chamber spacing △ S, emptied according to the cloth of polycyclic heat exchanger 13
Minimum, the maximum r of interior arrangement radiusmin,rmaxObtain △ S variation threshold range, wherein optimal decision criteria include:
In threshold range about △ S, the heat exchange of propulsion system propulsive performance paying close attention to variable T and h and being optimal simultaneously is obtained
Device structure, T and h are that the function of △ S can be the normalized value of thrust, heat exchange efficiency or thrust, heat exchange efficiency；T or h is closed
Carry out curve fitting to obtain propulsive performance with the change curve of △ S in the functional relation of △ S；Using normalized function by T or h into
Row curve is quasi-, obtains the functional relation between T and h, obtains the propulsive performance fitting function P (h, T) about T and h, promoted
The Optimal Fitting curve of performance；Under matched curve, the maximum of points P of existence function in the threshold range of △ Smax(T, h), should
The numerical value △ S of △ S under coordinateoptimumIt can determine that as polycyclic 13 optimum structure of heat exchanger.
The threshold range of the △ S can state are as follows:
R=r0+(2+△S)·n+△S
rmin≤r≤rmax
The optimal judgement can be stated are as follows:
P (h, T)=h (△ s) × T (△ s)
As P (h, T)=Pmax(h,T)
In formula:
r0For turbine shaft housing radius；
△ S is cooling gas power cavity outer layer chamber spacing；
N is cooling gas power chamber layer number；
R is each layer chamber outer radius；
H (△ S), T (△ S) is respectively propulsive performance evaluation function；
P (h, T) is propulsive performance fitting function；
PmaxThe maximum value of (h, T) fitting function；
The inverse function of fitting function；
△SoptimumFor optimal spacing.
Above embodiments are provided merely to describing the purpose of the present invention, and be not intended to limit the scope of the invention.This hair
Bright range is defined by the following claims.It does not depart from spirit and principles of the present invention and the various equivalent replacements made and repairs
Change, should all cover within the scope of the present invention.
Claims (10)
1. a kind of polycyclic heat exchanger, it is characterised in that: including polycyclic heat exchange structure (1) and turbine wheel shaft (2)；The polycyclic heat exchange knot
Structure (1) includes flow-disturbing fin (3), external insulated wall (4), cooling gas power chamber (5) and heating fluid line (6)；Cooling air
Body power chamber (5) is heat exchanger components, for the heat exchange of incoming flow cold air and polycyclic chamber hot wall face, is located at external insulated wall (4)
Between turbine wheel shaft (2), it is connected by nested mode with turbine wheel shaft (2)；External insulated wall (4) is bonded with propulsion system outer casing inner wall
Connection；Flow-disturbing fin (3) is embedded in cooling gas power cavity indoor external wall surface for enhanced heat exchange or additional nuclear heat source；It is described to add
Hot fluid pipeline (6) includes fluid heating inlet flow tube (7) and fluid heating exit flow tube (8), heating fluid conduit joint point
It is not connected with cooling gas power chamber (5), flows into heating liquid and cooling gas power cavity wall surface is heated, and with adverse current
Arrangement it is opposite with cooling gas flow direction.
2. polycyclic heat exchanger according to claim 1, it is characterised in that: the cooling gas power chamber structure is for pushing away
Into system chamber cavity or the customization chamber of equivalent constructions, cooling gas power chamber (5) is made of Multi-layer exchanging heat wall surface
Cylinder-shaped heat exchange structure, each cylindrical shape heat exchange structure is divided into two chambers, arranged stacked, and outer layer chamber circulates cooling air
Body, internal layer chamber are connected with fluid heating inlet flow tube (7) and fluid heating exit flow tube (8), there is heating fluid constant flow
So that cylindrical wall persistent fever.
3. polycyclic heat exchanger according to claim 1, it is characterised in that: cooling gas power chamber (5) is changed by three layers
The cylinder-shaped heat exchange structure of hot wall face composition, the number of plies are determined by optimal decision criteria.
4. polycyclic heat exchanger according to claim 1, it is characterised in that: the flow-disturbing fin (3) has in insulation wall surface
The fin protrusion being arranged symmetrically, fin protrusion are irregular flat hole configurations, are arranged symmetrically, are used for around Multi-layer exchanging heat wall surface
Enhanced heat exchange fin or as nuclear fuel storage embedded chip be used for intercalating dye element, fin by conduit card slot mode with
The wall surface of cooling gas power chamber connects.
5. polycyclic heat exchanger according to claim 1, it is characterised in that: the polycyclic heat exchanger is space propultion, aviation
Propulsion or aircraft propulsion heat exchanger near the ground.
6. polycyclic heat exchanger according to claim 1, it is characterised in that: the origin of heat of heating fluid line (6)
Suitable for disintegration energy, decay energy or other high energy clean energy resourcies.
7. polycyclic heat exchanger according to claim 1, it is characterised in that: the turbine wheel shaft (2) is using outside turbine wheel shaft axle sleeve
Containment surfaces of the involucrum as polycyclic heat exchange structure maximally utilise former fuel oil propulsion system structure.
8. a kind of propulsion system based on polycyclic heat exchanger, it is characterised in that: including air intake duct (11), compressor (12), polycyclic
Heat exchanger (13) and jet pipe (14)；In propulsion system shell, air intake duct (11) is located at the front end of propulsion system for inhaling
Enter cooling gas, compressor (12) is located at the end of air intake duct (11), and air intake port is connected with compressor inlet, for suction
Enter gas and carry out compressed action, compressor outlet is connected with the outer layer chamber of polycyclic heat exchanger cooling gas power cavity, for cold
But the heat exchange of gas and internal layer chamber high-temperature wall surface, jet pipe (14) are located at propulsion system least significant end, and cooling gas is more in outflow
Ring heat exchanger (13) enters jet pipe (14) afterwards and realizes thrust power；
The polycyclic heat exchanger includes polycyclic heat exchange structure (1) and turbine wheel shaft (2)；The polycyclic heat exchange structure includes flow-disturbing fin
(3), external insulated wall (4), cooling gas power chamber (5) and heating fluid line (6)；The heating fluid line (6) includes
Fluid heats inlet flow tube (7) and fluid heating exit flow tube (8)；
Cooling gas power chamber (5) is heat exchanger components, for the heat exchange of incoming flow cold air and polycyclic chamber hot wall face, is located at exhausted
Between hot outer wall (4) and turbine wheel shaft (2), it is connected by nested mode with turbine wheel shaft (2)；Outside external insulated wall (4) and propulsion system
Shell inner wall is fitted and connected；Flow-disturbing fin (3) is embedded in cooling gas power cavity indoor external wall surface for enhanced heat exchange or additional core
Heat source；The heating fluid line (6) includes fluid heating inlet flow tube (7) and fluid heating exit flow tube (8), heats fluid
Pipeline (6) connector is connected with cooling gas power chamber (5) respectively, flows into heating liquid and carries out to cooling gas power cavity wall surface
Heating, and it is opposite with cooling gas flow direction with the arrangement of adverse current；Cooling gas power chamber (5) is by Multi-layer exchanging heat wall surface
The cylinder-shaped heat exchange structure of composition, each cylindrical shape heat exchange structure are divided into two chambers, arranged stacked, the circulation cooling of outer layer chamber
Gas, internal layer chamber are connected with fluid heating inlet flow tube (7) and fluid heating exit flow tube (8), have heating fluid persistently to flow
It moves so that cylindrical wall persistent fever；Wherein, internal layer cavity space spacing is constant, and the space spacing of outer layer chamber is according to optimal judgement
Result obtain the optimal value of chamber spacing △ S；
A kind of propulsion system based on polycyclic heat exchanger is that the combustion chambers burn heat exchange of air intake duct rear end is generated to the process of thrust
It is converted into the device that polycyclic chamber heat exchange generates same thrust, augmentation of heat transfer is carried out using flow-disturbing fin (3), to make polycyclic heat exchange
Device propulsive performance is optimal, and is carried out using optimum number of strata of the Optimal condition to cooling gas power cavity inner cylindrical heat exchange chamber
Determine, the optimum structure of polycyclic heat exchanger (13) is obtained in threshold range, obtains the optimal value of the ring cavity number of plies, thus changes and push away
It promotes comprehensively performance into system.
9. a kind of propulsion system based on polycyclic heat exchanger according to claim 8, it is characterised in that: the Optimal condition
Selection optimum structure is embodied as；To obtain the optimal value of cooling gas power cavity outer layer chamber spacing △ S, according to polycyclic heat exchanger
(13) minimum, the maximum r of arrangement radius in arrangement spacemin,rmaxThe threshold range of △ S variation is obtained, wherein optimal sentence
It fixes, includes: in the threshold range about △ S, the variable T and h that pays close attention to for obtaining propulsion system propulsive performance reaches simultaneously
To optimal heat exchanger structure, it is the normalized value of thrust, heat exchange efficiency or thrust, heat exchange efficiency that T and h, which is the function of △ S,；
Its co-variate function P (T, h), the maximum of points P of matched curve are obtained after T and h value are fittedmax△ under (T, h) coordinate
The numerical value △ S of Soptimum, that is, it is determined as optimum structure.
10. a kind of propulsion system propulsion method based on polycyclic heat exchanger, which comprises the following steps:
(1) cooling gas is inhaled into inside propulsion system as propulsive working medium through air intake duct 11；Cooling gas subtracts in air intake duct
High pressure cooling gas is compressed to through compressor 12 after speed；
(2) high pressure cooling gas enters the outer layer chamber of cooling gas power chamber 5, and outer layer chamber is that the heat exchange of variable spacing is empty
Between；The variation of spacing is codetermined by the Flowing characteristic parameters of acquired high pressure gas and optimal decision criteria；
(3) wing of the flow behavior of acquired high pressure gas by the cooling flat hole configurations of 5 surface imperfection of aerodynamic force chamber
Piece protrusion influences；The heating fluid of the internal layer chamber of high pressure gas and cooling gas power chamber 5 carries out uniform heat exchange, heating amount
Variation and meanwhile influence the flow behavior of high pressure gas；
(4) to be optimal polycyclic heat exchanger propulsive performance, using Optimal condition criterion to the inside and outside layer of cooling gas power cavity
The optimum number of strata of chamber is determined, by adjusting the spacing of outer layer chamber, changes the number of plies of ectonexine chamber, and in threshold value model
The optimum structure of polycyclic heat exchanger 13 is obtained in enclosing, obtains the optimal value of the ring cavity number of plies；
(5) the optimal polycyclic heat exchanger after adjusting spacing has a distinct increment in propulsive performance and exchange capability of heat, passes through adjusting
Cooling gas power cavity internal layer chamber heats the heat exchange amount of fluid, high thrust, high heat exchange when realizing propulsion system afterburner flying
The performance requirement of amount, then high pressure cooling gas no longer needs to enter after-burner after entering the heat exchange of polycyclic heat exchanger, is directly over
The ejection of jet pipe 14 just can complete system propulsion, generate thrust power, thus promote the propulsive performance of propulsion system entirety.
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| CN109823573A (en) * | 2019-01-22 | 2019-05-31 | 南京航空航天大学 | A kind of propelling integrated solar thermal propulsion system of accumulation of heat-power generation- |
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