CN107701312A - A kind of hypersonic jets - Google Patents
A kind of hypersonic jets Download PDFInfo
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- CN107701312A CN107701312A CN201711102041.1A CN201711102041A CN107701312A CN 107701312 A CN107701312 A CN 107701312A CN 201711102041 A CN201711102041 A CN 201711102041A CN 107701312 A CN107701312 A CN 107701312A
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- Prior art keywords
- compressor
- engine
- combustion chamber
- motor
- jet pipe
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of hypersonic jets, 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, gas forecooler is provided between the air intake duct and compressor, the gas forecooler import BOR Bunker of Redelivery pump, outlet is connected to combustion chamber, and turbine is not provided with the engine, by motor driving compressor work.The present invention cancels the turbine of engine and corresponding cooling system, is generated electricity with plasma thermojet, drives compressor with motor, so as to solve the restricted problem of stagnation temperature before current turbine；Multiple-rotor scheme is realized with multiple motors, to substitute traditional hollow shaft scheme.
Description
Technical field
The invention belongs to empty day to promote field, and in particular to a kind of hypersonic across spatial domain engine.Such a aeroplane engine
Machine can be as 0 to 6 Mach of aircraft power, and 0-9 Mach flying power demands can be met by being combined with ultra-combustion ramjet.
Background technology
Hypersonic near space vehicle is the Hi-Tech Strategy weapon of our times big country, influence country politics and
Diplomacy.It is that each big country of our times falls over each other to study and hypersonic jets are the embodiments of highest technology in this strategic arms
Advanced subject.Current research shows, turbine base punching press combined engine (claim " TBCC ", it by aero-turbine with
High speed stamping cluster engine is closed and is used together) it is the more satisfactory power of hypersonic aircraft；But current aeroturbine hair
Motivation is limited by material and cooling technology, and stagnation temperature can not be too high before turbine, and maximum flight Mach number is too low (typically not greater than
3)；And the minimum work Mach number of scramjet engine is too high (generally more than 4, even more high)；Both are in flight Mach
There is a wide gap in number, can not realize that operation mode is changed.Therefore, TBCC not can apply to engineering reality always.
As flight Mach number increases, the static temperature and stagnation temperature of aero-engine compressor entrance all increase.Static temperature increases meeting
So that air viscosity increases, Reynolds number reduces, and this can cause engine cisco unity malfunction under High Mach number.Stagnation temperature, which increases, to be caused
Work done during compression increase required for compressor is, it is necessary to increase engine speed, to keep the work Mach number of compressor similar, but by
This may cause the breaking-up of engine；Simultaneously under High Mach number, blower outlet stagnation temperature amplification ratio entrance stagnation temperature amplification is big
Much, further refueling after burning, stagnation temperature transfinites before turbine, so as to burn out turbo blade.
Due to the influence of high-temperature fuel gas, turbogenerator needs to cool down turbo blade, this will design one it is cold
Gas system, blown out from bleed air and then from the aperture of turbine blade surface；This not only adds the system of aero-engine
Complexity, also increase flow losses, reduce the thermal efficiency and thrust of aero-engine.The turbo blade of engine works in simultaneously
High temperature, hyperbaric environment, this causes, and the production cost of turbo blade is high, service life is short, constrains the economy that engine uses.
Turbine is High Temperature Rotating part, it is necessary to have bearing and lubricating system.To avoid turbine Bearing Temperature, it is necessary to draw
Gas cools down to the part near turbine bearing, and the high-temperature fuel gas for preventing to leak between stage of turbine pours in down a chimney.And used in reality
In, it is usually present turbo blade hole plug, high-temperature fuel gas pours in down a chimney at bearing.
To improve aero-turbine thrust and thrust-weight ratio, and evade the limitation of high-temperature material and cooling technology, it is necessary to
Develop a kind of high-temperature fuel gas aero-engine simple in construction, without turbo blade.Simultaneously by such engine and pre- refrigeration technique knot
Close, the hypersonic near space engine of Mach more than 5 can be developed.
Compressor connects on a shaft with turbine portion, and rotating speed is identical with power；This causes the pressure of aero-turbine
There is matching problem in mechanism of qi and turbine, only could realize that multiple-rotor designs using spatial axes.Among other compressor and turbine
Across combustion chamber, rotating shaft is needed through among combustion chamber, and this make it that textural anomaly is complicated, more difficult using multiple-rotor design.
Therefore current turbine engine generally use 1-2 rotating shafts, only the rotating shaft engine of Britain sieve sieve development of company 3.
The content of the invention
It is an object of the invention to provide a kind of pre- cold engine of no turbo blade, evade high-temperature material and cooling technology
Limitation；In the case of the other engines of no combination, can ground self-starting, meet that Mach 5 arrives the flying power need of Mach 6
Ask；In the case of being combined with scramjet engine, solve current TBCC Mach number wide gap, can smoothly realize mode conversion.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of hypersonic jets, including air intake duct, compressor, combustion chamber and jet pipe, air-flow is entered by air intake duct calms the anger
Machine, combustion chamber is entered back into after compression, is discharged after burning by jet pipe, gas precooling is provided between the air intake duct and compressor
Device, the gas forecooler import BOR Bunker of Redelivery pump, outlet are connected to combustion chamber, turbine are not provided with the engine, by electricity
Machine driving compressor work.
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 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 is sprayed into combustion chamber, and is lighted a fire, gas forecooler is lowered into the gas temperature of aerostatic press；
Step 2：After successful ignition, high speed plasma air-flow is sprayed behind combustion chamber, air-flow produces electricity by thermojet magnetic electrical device
Stream；
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, the fuel is liquid hydrogen, and fuel is used as cooling agent simultaneously（Referred to herein as " combustion is cold
But agent "）, the liquid hydrogen gasifies in forecooler, absorbs heat from air intake duct end, reduce gas flow temperature, gasify as hydrogen, directly
Combustion chambers burn is sprayed into, without needing fuel atomization device.
In the above-mentioned technical solutions, ionized catalyst is included in the flammable cooling agent, at high temperature by gas ionization
For plasma, when plasma gas stream is among the magnet that high speed passes through thermojet magnetic electrical device, plasma is in magnetic field
Cutting magnetic line produces induced electromotive force, so as to form electrical potential difference between two electrodes, produces galvanic current stream.
In summary, by adopting the above-described technical solution, the beneficial effects of the invention are as follows：
Maximum innovative point, which is that, in the present invention proposes a kind of new concept engine, can ground start, meet Mach below 6
Flying power demand；Cancel the turbine of engine and corresponding cooling system, generated electricity with plasma thermojet, driven and pressed with motor
Mechanism of qi, so as to solve the restricted problem of stagnation temperature before current turbine；Fuel and cooling agent are used as by the use of liquid hydrogen simultaneously so that precooling
System design is simple, it is no longer necessary to extra thermodynamic cycle, different from the precooling scheme such as Britain's " sword worn at the waist ", " tulwar "；With multiple electricity
Machine realizes multiple-rotor scheme, to substitute traditional hollow shaft scheme；The power of traditional high and low pressure turbine can only be transmitted to corresponding height
Low-pressure compressor, this causes the matching of high-low pressure part to have difficulties, and height can artificially be carried out by using instead after electricity drives motor-driven compressor
The power distribution of splenium part, improve high-low pressure parts match.
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 receipts expanding wall structural representation of jet pipe of the present invention；
Fig. 3 is the flat wall structural representation of jet pipe of the present invention；
Wherein：1 is air intake duct, and 2 be forecooler, and 3 be compressor, and 4 be combustion chamber, and 5 be motor, and 6 be jet pipe, and 7 be thermojet magnetic
Electric installation, 8 be electrode, and 9 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 figure 1, engine of the present invention includes air intake duct, compressor, combustion chamber, jet pipe, motor, thermojet
Magnetic electrical device totally six core components, change traditional engine structure, eliminate turbo blade, no longer provided by turbine
Work done during compression, in order to reduce the static temperature of compressor inlet and stagnation temperature, a forecooler is set between compressor and air intake duct, and this is pre-
Flowing is flammable cooling agent, mainly liquid hydrogen or other flammable liquids in cooler, and the outlet of the forecooler is being burnt
Room, the air of air intake duct, which first passes through, to be entered back into compressor after forecooler cooling and is compressed, and the liquid hydrogen in forecooler is absorbing
Combustion chamber is spurted into after the air-flow heat of air intake duct afterbody to be burnt.
After removing turbine in the present invention, maximum improvement, which is that, to be improved compressor, and former compressor turns
Son is rotated coaxially by turbine drives, and with turbine, and the present invention is rotated using independent motor come driving blade.In the present invention
Several motors are set in the wheel hub of compressor, and each motor at least drives one-level compressor rotor to rotate, in the present invention
Motor formed using coil windings and magnet, the power supply of motor is by aerostatic press externally fed.
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. 2, Fig. 3
It is shown, it is provided with two electrodes on the receipts expanding wall internal face of jet pipe（Certainly, several electrodes are provided with whole jet pipe, are schemed
In only identify two and convenient understand）, magnet is provided with flat wall outside wall surface（Certainly, it is provided with 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 compressor rotor blade to rotate.Here magnetic field is by superconducting electromagnet or other magnetic
Property stronger permanent magnet provide so that the engine under working condition, plasma thermojet magnetic electrical device can be ceaselessly
The electric energy of acquisition is then output to motor.
The coil windings of motor in the present invention and the wheel disc of compressor are structure as a whole, and combine permanent magnet（Or
Electromagnet）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 compressor rotor to rotate, 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 flammable cooling agent, catalyst is ionized catalyst, the general salt for using alkali metal containing
Class (such as sylvite).When flammable cooling agent breaks into high temperature after combustion, catalyst is at high temperature just by air ionization into plasma
Body.Substantial amounts of plasma flow accelerates in jet pipe, is then ejected from jet pipe, and substantial amounts of electricity is carried in plasma
Son, when magnetic field of the plasma through two electrodes, cutting magnetic induction line, the particle with positive and negative charge knows from experience the effect in magnetic field
It is lower to different electrode drifts 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.
Embodiment 1
As shown in figure 1, the present invention proposes a kind of new hypersonic jets, including oil piping system, lubricating system, igniting dress
Put, not shown in figure.Engine of the present invention uses Brayton cycle, the coil windings and compressor disk of the motor
One, compressor is driven to rotate after powered up, the high-temperature gas of the combustion chamber is all or part of in the presence of Cui's agent
Be ionized into plasma, the plasma of motion flows through the high-intensity magnetic field between magnet, cutting magnetic induction line and produce electromotive force, so as to
Steady dc voltage is formed between two electrodes 7, the magnet uses superconducting electromagnet or the permanent magnet of other relatively high magnetisms,
The energy of the electric energy that the thermojet magnetic electrical device obtains as motor.
Specific work process is as follows：
In takeoff condition, compressor is driven by airport external power supply, and make work of electromagnet；After compressor normal work,
Fuel oil (added with sylvite or other ionization Cui agents in fuel oil) is sprayed into toward combustion chamber, and is 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, there is provided rotating speed, engine enter maximum climb mode, and thrust is most
Greatly.
To after specified altitude assignment and speed, reduce fuel feeding and regulation component system, engine enters cruising condition.
Embodiment 2
Punching engine is burnt based on hypersonic jets proposed by the present invention (as shown in Figure 1), and with super burn (in figure not
Show) combination, form a kind of novel compositions engine.The combined engine uses two kinds of fuel, liquid hydrogen and aviation kerosine；Its
Middle liquid hydrogen is used for engine of the present invention, and aviation kerosine is used for scramjet engine.
It is described as follows to the specific work process for closing engine：
In takeoff condition, scramjet engine is closed；Compressor is driven by airport external power supply, and makes work of electromagnet；
After compressor normal work, spraying into fuel oil toward combustion chamber, (fuel oil is liquid hydrogen, wherein added with sylvite or other ionization Cuiization
Agent), and light 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, increasing engine oil, improve rotating speed of gas compressor, engine enters maximum climb mode,
Thrust is maximum.
After specified altitude assignment and Mach number is reached (here by taking 11 kilometers and 4.5 Mach as an example), open ultra-combustion ramjet and start
Machine, now two engines work in the lump；After flight Mach number up to after 5.5, scramjet engine steady operation, stop spray
Enter hydrogen fuel, disconnect motor power, close the engine inlets.
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 (11)
1. a kind of hypersonic jets, including air intake duct, compressor, combustion chamber and jet pipe, air-flow is entered by air intake duct presses
Mechanism of qi, combustion chamber is entered back into after compression, is discharged after burning by jet pipe, it is characterised in that set between the air intake duct and compressor
Gas forecooler, the gas forecooler import BOR Bunker of Redelivery pump are equipped with, outlet is connected to combustion chamber, is not provided with the engine
There is turbine, by motor driving compressor work.
2. a kind of aviation hypersonic jets according to claim 1, it is characterised in that the motor is arranged on air pressure
In the wheel hub of machine, the motor includes coil windings and magnet, and the coil windings are integrated with compressor disk.
3. a kind of aviation hypersonic jets according to claim 2, it is characterised in that the compressor has some
Grade, several motors are provided with the wheel hub of compressor, each motor at least drives one-level compressor.
4. a kind of aviation hypersonic jets according to claim 1, it is characterised in that be provided with heat on the jet pipe
Jet magnetic electrical device, the thermojet magnetic electrical device include positive and negative electrode and magnet.
5. a kind of aviation hypersonic jets according to claim 4, it is characterised in that the jet pipe turns side to be circular
Shape jet pipe, square 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 set
It is equipped with magnet.
6. a kind of aviation hypersonic jets according to claim 5, it is characterised in that if being provided with the jet pipe
Dry electrode and magnet, the output end of electrode are connected to motor.
7. a kind of aviation hypersonic jets 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 aviation hypersonic jets of claim 1-7, it is characterised in that the work of engine
Flow 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 is sprayed into combustion chamber by gas forecooler, and lighted a fire, gas forecooler is lowered into the gas of aerostatic press
Temperature；
Step 2：After successful ignition, high velocity air is sprayed after burning, air-flow produces electric current by thermojet magnetic electrical device；
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.
9. step 4：In take-off process, increase fuel feeding, improve rotating speed, engine enters climb mode, into the height specified with
Reduce fuel feeding and regulation all parts system after speed, engine enters cruising condition.
10. a kind of aviation hypersonic jets according to claim 8, it is characterised in that the fuel is liquid hydrogen, combustion
Material is used as cooling agent simultaneously, and the liquid hydrogen gasifies in forecooler, absorbs heat from air intake duct end, reduces gas flow temperature, gasification
For hydrogen, combustion chambers burn is injected directly into, without needing fuel atomization device.
11. a kind of aviation hypersonic jets according to claim 8, it is characterised in that wrapped in the flammable cooling agent
Ionized catalyst has been included, has been at high temperature plasma by gas ionization, plasma gas stream passes through thermojet magnetoelectricity in high speed
When among the magnet of device, plasma cutting magnetic line in magnetic field produces induced electromotive force, so as between two electrodes
Electrical potential difference is formed, produces galvanic current stream.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711102041.1A CN107701312B (en) | 2017-11-10 | 2017-11-10 | Hypersonic engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711102041.1A CN107701312B (en) | 2017-11-10 | 2017-11-10 | Hypersonic engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107701312A true CN107701312A (en) | 2018-02-16 |
| CN107701312B CN107701312B (en) | 2020-11-03 |
Family
ID=61179079
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|---|---|---|---|
| CN201711102041.1A Active CN107701312B (en) | 2017-11-10 | 2017-11-10 | Hypersonic engine |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108612598A (en) * | 2018-04-24 | 2018-10-02 | 中国空气动力研究与发展中心吸气式高超声速技术研究中心 | Change the method and engine chamber of dual-mode scramjet burning mode |
| CN109296473A (en) * | 2018-08-10 | 2019-02-01 | 西安理工大学 | A kind of magnetic control pulsed discharge hypersonic inlet assistant starting flow control method |
| CN112197625A (en) * | 2020-09-30 | 2021-01-08 | 中国航空发动机研究院 | Central air intake heat exchanger for high-speed air-breathing engine |
| CN113482774A (en) * | 2021-08-16 | 2021-10-08 | 中国科学院工程热物理研究所 | Small-sized high-speed turbojet engine with kerosene jet precooling function |
| CN113513427A (en) * | 2020-11-02 | 2021-10-19 | 曹建峰 | Cooling energy conversion aerospace engine |
| CN114750965A (en) * | 2022-06-15 | 2022-07-15 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
| CN115219147A (en) * | 2022-09-15 | 2022-10-21 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
| CN117553321A (en) * | 2024-01-11 | 2024-02-13 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
| US11927136B1 (en) | 2021-06-04 | 2024-03-12 | Rtx Corporation | Turbofan engine with precooler |
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| 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 |
| CN105156227A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Pre-cooling air-breathing type variable cycle engine |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108612598A (en) * | 2018-04-24 | 2018-10-02 | 中国空气动力研究与发展中心吸气式高超声速技术研究中心 | Change the method and engine chamber of dual-mode scramjet burning mode |
| CN109296473A (en) * | 2018-08-10 | 2019-02-01 | 西安理工大学 | A kind of magnetic control pulsed discharge hypersonic inlet assistant starting flow control method |
| CN112197625B (en) * | 2020-09-30 | 2022-05-06 | 中国航空发动机研究院 | Central air intake heat exchanger for high-speed air-breathing engine |
| CN112197625A (en) * | 2020-09-30 | 2021-01-08 | 中国航空发动机研究院 | Central air intake heat exchanger for high-speed air-breathing engine |
| CN113513427A (en) * | 2020-11-02 | 2021-10-19 | 曹建峰 | Cooling energy conversion aerospace engine |
| US11927136B1 (en) | 2021-06-04 | 2024-03-12 | Rtx Corporation | Turbofan engine with precooler |
| CN113482774A (en) * | 2021-08-16 | 2021-10-08 | 中国科学院工程热物理研究所 | Small-sized high-speed turbojet engine with kerosene jet precooling function |
| CN113482774B (en) * | 2021-08-16 | 2022-01-14 | 中国科学院工程热物理研究所 | Small-sized high-speed turbojet engine with kerosene jet precooling function |
| CN114750965A (en) * | 2022-06-15 | 2022-07-15 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
| CN114750965B (en) * | 2022-06-15 | 2022-09-13 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Cooling device based on bionic veins |
| CN115219147A (en) * | 2022-09-15 | 2022-10-21 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
| CN115219147B (en) * | 2022-09-15 | 2022-11-18 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Adjustable fan blade type second throat and test section Mach number control method |
| CN117553321A (en) * | 2024-01-11 | 2024-02-13 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
| CN117553321B (en) * | 2024-01-11 | 2024-03-22 | 中国空气动力研究与发展中心计算空气动力研究所 | Multi-channel discharge plasma fuel cracking pneumatic nozzle |
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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 |