CN107842442A - A kind of aero-engine - Google Patents
A kind of aero-engine Download PDFInfo
- Publication number
- CN107842442A CN107842442A CN201711102132.5A CN201711102132A CN107842442A CN 107842442 A CN107842442 A CN 107842442A CN 201711102132 A CN201711102132 A CN 201711102132A CN 107842442 A CN107842442 A CN 107842442A
- Authority
- CN
- China
- Prior art keywords
- compressor
- engine
- aero
- jet pipe
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K44/00—Machines in which the dynamo-electric interaction between a plasma or flow of conductive liquid or of fluid-borne conductive or magnetic particles and a coil system or magnetic field converts energy of mass flow into electrical energy or vice versa
- H02K44/08—Magnetohydrodynamic [MHD] generators
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Power Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of aero-engine, including air intake duct, compressor, combustion chamber and jet pipe, air-flow enters compressor by air intake duct, combustion chamber is entered back into after compression, discharged after burning by jet pipe, turbine is not provided with the engine, by motor driving compressor work；Maximum innovative point is that in the present invention eliminates turbine and corresponding cooling system within the engine, is generated electricity with plasma thermojet, drives compressor with motor, so as to solve the restricted problem of stagnation temperature before current turbine.
Description
Technical field
The invention belongs to engine art, the aero-engine being specifically related to is applied to aircraft of the Mach below 3.
Background technology
Aero-engine is a national Hi-Tech Strategy industry, influences the political and diplomatic of country.To increase aviation
The thrust and thrust-weight ratio of engine are, it is necessary to which stagnation temperature is as high as possible before turbine.But current aero-engine is by material and cooling skill
The limitation of art, stagnation temperature can not be too high (stagnation temperature is up to 2000K before the turbine of forth generation aero-engine) before turbine.
Due to the influence of high-temperature fuel gas, current aero-engine is needed to cool down turbo blade, and this will be designed
One cold gas system, blown out from bleed air and then from the aperture of turbo blade；What it is this not only adds aero-engine is
System complexity, also increase flow losses, reduce the thermal efficiency and thrust of aero-engine.The turbo blade of aero-engine simultaneously
In high temperature, hyperbaric environment, this causes, and the production cost of turbo blade is high, service life is short, constrains aeroplane engine for long-term work
The economy that machine uses.
Turbine is rotary part, it is necessary to have bearing and lubricating system.To avoid turbine Bearing Temperature, it is necessary to bleed pair
Part near turbine bearing is cooled down, and the high-temperature fuel gas for preventing to leak between stage of turbine pours in down a chimney.And in reality in use, often
It is commonly present turbo blade hole plug, high-temperature fuel gas pours in down a chimney at bearing to pouring in down a chimney.
Compressor is connected in same root axle with turbine, and rotating speed is identical with power, and this causes the compressor and turbine of aero-engine
Matching problem.Multiaxis, which designs, can improve the interstage matched of compressor, but high-pressure rotary part is between low pressure rotary part,
Only it could realize that multiple-rotor designs using spatial axes；Other compressor among turbine across combustion chamber, rotating shaft needs through
Among combustion chamber, this make it that textural anomaly is complicated, more difficult using multiple-rotor design.Therefore current aerospace engine is usual only
There are 1-2 rotating shaft, only the rotating shaft engine of Britain sieve sieve development of company 3.
To improve aeroengine thrust and thrust-weight ratio, the matching of improvement component capabilities, evading high-temperature material and cooling technology
Limitation, it is necessary to develop a kind of high-temperature fuel gas aero-engine simple in construction, without turbo blade.
The content of the invention
It is an object of the invention to provide a kind of aero-engine of no turbo blade, evade high-temperature material and cooling technology
Limitation, realize bigger thrust and Geng Gao thrust-weight ratio.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of aero-engine, including air intake duct, compressor, combustion chamber and jet pipe, air-flow enter compressor by air intake duct, pressure
Combustion chamber is entered back into after contracting, is discharged after burning by jet pipe, turbine is not provided with the engine, compressor is driven by motor
Work.
In the above-mentioned technical solutions, the compressor has higher pressure ratio, and the combustion chamber uses isobaric combustion, described
The oil spout of jet pipe leading portion carries out constant-temperature combustion.
In the above-mentioned technical solutions, the motor is arranged in the wheel hub of aerostatic press, the motor include coil windings and
Magnet, the coil windings are integrated with compressor disk.
In the above-mentioned technical solutions, the compressor has some levels, and several motors are provided with the wheel hub of compressor,
Each motor at least drives one-level compressor.
In the above-mentioned technical solutions, thermojet magnetic electrical device, the thermojet magnetic electrical device bag are provided with the jet pipe
Include positive and negative electrode and magnet.
In the above-mentioned technical solutions, the jet pipe turns square jet pipe to be circular, and square section includes receiving expanding wall and flat wall, institute
State receipts expanding wall internal face and be provided with electrode, the flat wall outside wall surface is provided with magnet.
In the above-mentioned technical solutions, several electrodes and magnet are provided with the jet pipe, the output end of electrode is connected to
Motor.
In the above-mentioned technical solutions, the combustion chamber is streamlined revolving structure, from compressor one end to jet pipe end burning
Its radius of gyration of room progressively reduces.
In the above-mentioned technical solutions, the jet pipe front end is provided with some circle atomizers, by being carried out in jet pipe front end etc.
Temperature burning substitutes traditional afterbunring, realizes the higher thermal efficiency.
In the above-mentioned technical solutions, the workflow of engine is：
Step 1：Drive compressor to work by external power source, and drive thermojet magnetic electrical device to work simultaneously, in compressor just
Often after work, fuel oil is sprayed into combustion chamber, and light a fire；
Step 2：The powered plasma air-flow of high speed is sprayed after successful ignition, after burning, air-flow is produced by thermojet magnetic electrical device
Raw electric current；
Step 3：After being worked Deng engine stabilizer, externally fed is cut off, is powered from thermojet magnetic electrical device to motor, by motor
Compressor work is driven, engine enters idling work state.
Step 4：In take-off process, increase fuel feeding, improve rotating speed, engine enters climb mode, into the height specified
Enter cruising condition with all parts system, engine is adjusted with fuel feeding is reduced after speed.
In the above-mentioned technical solutions, gas ionization is at high temperature plasma by the ionized catalyst in the fuel oil,
When plasma gas stream is among the magnet that high speed passes through thermojet magnetic electrical device, plasma cutting magnetic line in magnetic field produces
Raw induced electromotive force, so as to form electrical potential difference between two electrodes, produce galvanic current stream.
In the above-mentioned technical solutions, the effect of catalyst is the ionization temperature for reducing air-flow, passes through catalyst
The ionization temperature of gas is reduced to 3000K or so by 6000K or so.
In summary, by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
Maximum innovative point is that in the present invention eliminates turbine and corresponding cooling system within the engine, so as to solve
The restricted problem of stagnation temperature before turbine, the thrust loss that cooling system is brought is removed, motor power is significantly greatly increased；Use plasma
Thermojet generates electricity, drives compressor with motor, and electric energy can freely distribute in the motor of each compression member, it is easy to realize more turns
Axle, solves the matching problem of compressibility；The power transmission shaft between former turbine and compressor is removed, structure complexity substantially reduces,
The problem of rotor dynamics, complexity weakened, and influence of the critical speed to engine weakens；Using the constant-temperature combustion behind combustion chamber
Traditional afterbunring is substituted, the thermal efficiency increases considerably.
Brief description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of the present invention；
Fig. 3 is the receipts expanding wall structural representation of jet pipe of the present invention；
Fig. 4 is the flat wall structural representation of jet pipe of the present invention；
Wherein：1 is air intake duct, and 2 be compressor, and 3 be combustion chamber, and 4 be jet pipe, and 5 be motor, and 6 be thermojet magnetic electrical device, and 7 are
Electrode, 8 be magnet.
Embodiment
All features disclosed in this specification, or disclosed all methods or during the step of, except mutually exclusive
Feature and/or step beyond, can combine in any way.
As shown in Fig. 1, Fig. 2, engine of the present invention include air intake duct, compressor, combustion chamber, jet pipe, motor,
Thermojet magnetic electrical device totally six core components, change traditional engine structure, eliminate turbine, use electric energy offer instead
Work done during compression.
Remove maximum improvement after turbo blade in the present invention and be that and compressor is improved, compressor rotor with
Before be to have to move with turbine concentric zones turn, and the present invention driven using independent motor.In the wheel hub of compressor in the present invention
Interior several motors of setting, each motor at least drive one-level compressor rotor to rotate, and the motor in the present invention uses coil
Winding and magnet composition, the power supply of motor are powered by thermojet magnetic electrical device.
In order to coordinate above-mentioned motor to work in the present invention, thermojet magnetic electrical device is introduced in jet pipe, such as Fig. 3, Fig. 4
It is shown, it is provided with two electrodes on the receipts expanding wall internal face of jet pipe（Certainly, several electrodes, figure can be set on whole jet pipe
In only identify two and convenient understand）, magnet is provided with flat wall outside wall surface（Certainly, can be set on whole jet pipe some
Individual magnet, two are only identified in figure and convenient is understood）, when high speed plasma air-flow is through two electrodes, air-flow is cut
Magnetic field magnetic induction line is cut between electrode so as to produce electromotive force, forms steady dc voltage between electrodes, and by direct current
Pressure is input in above-mentioned motor, drives air pressure machine rotor to rotate.Here magnetic field by superconducting electromagnet or other magnetic compared with
Strong permanent magnet is provided so that the engine under working condition, plasma thermojet magnetic electrical device can be obtained ceaselessly
Electric energy be then output to motor.
The coil windings of motor in the present invention and the wheel disc of aerostatic press are structure as a whole, and combine electromagnet（Or
Permanent magnet）A direct current generator is formed, when inputting the DC voltage from thermojet magnetic electrical device in coil, motor is with regard to that can start
Work and drive aerostatic press blade to be rotated, realize the work of aerostatic press.
There is a key point in the present invention, be how to realize that the electric energy of plasma thermojet magnetic electrical device provides, because
Catalyst is with the addition of in this present invention in fuel oil, catalyst is ionized catalyst, in general contains alkali species（Such as potassium
Salt）.When fuel oil breaks into high temperature after combustion, catalyst is at high temperature just by air ionization into plasma.It is because substantial amounts of
Plasma flow accelerates in jet pipe, is then ejected from jet pipe, and substantial amounts of electric charge is carried in plasma, when wait from
Daughter through two electrodes magnetic field when, cutting magnetic induction line, the particle with positive positive and negative charge is known from experience under the influence of a magnetic field to not
Same electrode drift, so that forming electrical potential difference between two electrodes.
In the present invention it is above-mentioned it is all on the basis of, canceled traditional turbo blade and cooling gas circuit, this to fire
The outlet temperature of burning room is higher, and engine thermal efficiency is higher, and specific discharge thrust is bigger.By combustion chamber by traditional loop configuration
Make the arcuate structure of this programme into, the radian from compressor one end to jet pipe one end combustion chamber is stepped up, realize combustion chamber with
Jet pipe Combined design (as shown in Figure 2).The improvement of this structure causes the gas rapid expanding after burning and causes engine long
Degree shortens.
Entirely the specific work process of engine is：
In takeoff condition, compressor is driven by airport external power supply, and superconducting electromagnet is worked；In compressor normal work
Afterwards, fuel oil (added with sylvite or other ionization Cui agents in fuel oil) is sprayed into toward combustion chamber, and lighted a fire；
After successful ignition, external power supply maintains the several seconds, treats engine steady operation；After engine stabilizer work, disconnect external
Power supply, is powered from thermojet magnetic electrical device to compressor and electromagnet, and engine enters idling mode；
After being connected to takeoff order, increase engine oil, engine enters maximum climb mode, and thrust is maximum；
To after specified altitude assignment and speed, reduce fuel feeding and regulation component system, engine enters cruising condition.
Above-mentioned engines ground, which starts, can use plug-in starting, accumulator drive and miniature gas turbine to start three kinds of sides
Case.When using plug-in starting, the external ground power unit of motor, the oil jetting combustion after compressor work is driven, complete after starting
Disengage power supply；During using accumulator drive, aircraft is needed from charged pool, is powered for motor during starting, is started rear engine as electricity
Charge in pond；When being started using miniature gas turbine, starting process is consistent with existing aero-engine.
The invention is not limited in foregoing embodiment.The present invention, which expands to, any in this manual to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (9)
1. a kind of aero-engine, including air intake duct, compressor, combustion chamber and jet pipe, air-flow enters compressor by air intake duct,
Combustion chamber is entered back into after compression, is discharged after burning by jet pipe, it is characterised in that turbine is not provided with the engine, by electricity
Machine driving compressor work, the combustion chamber use isobaric combustion, and the jet pipe leading portion oil spout carries out constant-temperature combustion.
2. a kind of aero-engine according to claim 1, it is characterised in that the motor is arranged on the wheel hub of aerostatic press
Interior, the motor includes coil windings and magnet, and the coil windings are integrated with compressor disk.
3. a kind of aero-engine according to claim 2, it is characterised in that the compressor has some levels, compressor
Wheel hub in be provided with several motors, each motor at least drives one-level compressor.
4. a kind of aero-engine according to claim 1, it is characterised in that thermojet magnetoelectricity is provided with the jet pipe
Device, the thermojet magnetic electrical device include positive and negative electrode and magnet.
5. a kind of aero-engine according to claim 4, it is characterised in that the jet pipe turns square jet pipe, side to be circular
Shape section includes receiving expanding wall and flat wall, and the receipts expanding wall internal face is provided with electrode, and the flat wall outside wall surface is provided with magnet.
6. a kind of aero-engine according to claim 56, it is characterised in that several electrodes are provided with the jet pipe
And magnet, the output end of electrode are connected to motor.
A kind of 7. aero-engine according to claim 1, it is characterised in that the combustion chamber is streamlined revolving structure,
From compressor one end to nozzle end combustion chamber, its radius of gyration progressively reduces.
8. according to a kind of any described aero-engines of claim 1-7, it is characterised in that the workflow of engine is：
Step 1：Drive compressor to work by external power source, and drive thermojet magnetic electrical device to work simultaneously, in compressor just
Often after work, fuel oil is sprayed into combustion chamber, and light a fire；
Step 2：After successful ignition, the combustion chamber plasma air-flow powered by high speed is sprayed, air-flow passes through thermojet magnetic electrical device
Produce electric current；
Step 3：After being worked Deng engine stabilizer, externally fed is cut off, is powered from thermojet magnetic electrical device to motor, by motor
Compressor work is driven, engine enters idling work state；
Step 4：In take-off process, increase fuel feeding, improve rotating speed, engine enters climb mode, into the height and speed specified
Reduce fuel feeding and regulation all parts system after degree, engine enters cruising condition.
9. a kind of aero-engine according to claim 8, it is characterised in that the ionized catalyst in the fuel oil is in height
By gas ionization it is plasma under temperature, when plasma gas stream is among the magnet that high speed passes through thermojet magnetic electrical device, etc.
Gas ions cutting magnetic line in magnetic field produces induced electromotive force, so as to form electrical potential difference between two electrodes, produces stable
DC current.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711102132.5A CN107842442B (en) | 2017-11-10 | 2017-11-10 | Aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711102132.5A CN107842442B (en) | 2017-11-10 | 2017-11-10 | Aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107842442A true CN107842442A (en) | 2018-03-27 |
| CN107842442B CN107842442B (en) | 2020-09-18 |
Family
ID=61681535
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711102132.5A Active CN107842442B (en) | 2017-11-10 | 2017-11-10 | Aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107842442B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110608108A (en) * | 2018-06-14 | 2019-12-24 | 哈尔滨工业大学 | Non-turbine jet engine integrated with solid oxide fuel cell |
| CN113091090A (en) * | 2021-04-14 | 2021-07-09 | 中国航空发动机研究院 | Aero-engine for controlling combustion in combustion area by electric field |
| CN113847623A (en) * | 2021-09-16 | 2021-12-28 | 中国空气动力研究与发展中心计算空气动力研究所 | Microscale combustion chamber |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
| WO2023167751A2 (en) | 2021-12-03 | 2023-09-07 | Propelled Limited | High-power hybrid-electric propulsion systems and methods |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101208509A (en) * | 2003-04-28 | 2008-06-25 | 马里厄斯·A·保罗 | Turbo rocket with real Carnot cycle |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN103441641A (en) * | 2013-09-02 | 2013-12-11 | 董国光 | Detonation wave ejection loop type magnetic fluid power generation system |
-
2017
- 2017-11-10 CN CN201711102132.5A patent/CN107842442B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101208509A (en) * | 2003-04-28 | 2008-06-25 | 马里厄斯·A·保罗 | Turbo rocket with real Carnot cycle |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN103441641A (en) * | 2013-09-02 | 2013-12-11 | 董国光 | Detonation wave ejection loop type magnetic fluid power generation system |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110608108A (en) * | 2018-06-14 | 2019-12-24 | 哈尔滨工业大学 | Non-turbine jet engine integrated with solid oxide fuel cell |
| CN113091090A (en) * | 2021-04-14 | 2021-07-09 | 中国航空发动机研究院 | Aero-engine for controlling combustion in combustion area by electric field |
| CN113847623A (en) * | 2021-09-16 | 2021-12-28 | 中国空气动力研究与发展中心计算空气动力研究所 | Microscale combustion chamber |
| CN113847623B (en) * | 2021-09-16 | 2023-06-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Microscale combustion chamber |
| WO2023167751A2 (en) | 2021-12-03 | 2023-09-07 | Propelled Limited | High-power hybrid-electric propulsion systems and methods |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107842442B (en) | 2020-09-18 |
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Effective date of registration: 20210827 Address after: 621052 No.6, south section of 2nd Ring Road, Fucheng District, Mianyang City, Sichuan Province Patentee after: COMPUTATIONAL AERODYNAMICS INSTITUTE OF CHINA AERODYNAMICS RESEARCH AND DEVELOPMENT CENTER Address before: 621052 No.6, south section of 2nd Ring Road, Fucheng District, Mianyang City, Sichuan Province Patentee before: COMPUTATIONAL AERODYNAMICS INSTITUTE OF CHINA AERODYNAMICS RESEARCH AND DEVELOPMENT CENTER Patentee before: Qiu Ming |
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