CN105221295B - Stamping-turbine air injection composite aero-engine - Google Patents
Stamping-turbine air injection composite aero-engine Download PDFInfo
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- CN105221295B CN105221295B CN201510747821.6A CN201510747821A CN105221295B CN 105221295 B CN105221295 B CN 105221295B CN 201510747821 A CN201510747821 A CN 201510747821A CN 105221295 B CN105221295 B CN 105221295B
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Abstract
The invention discloses a stamping-turbine air injection composite aero-engine and aims to solve the problems that the existing gas turbine engine is complicated in structure and limited in running speed range, and a ramjet engine cannot voluntarily start, cannot run at a low speed, is difficult in cooling, and has higher requirements for the high temperature resistance of a complete machine. The stamping-turbine air injection composite aero-engine comprises a stamping air inflow cone, an outer duct engine case, an inlet guide blade, a liquid oxygen regulating valve, a liquid nitrogen regulating valve, an inner duct engine case, a rectifying blade, a fuel oil regulating valve, a centrifugal compressor, a diffuser, a combustor, a concentric shaft, a worm wheel, an inner duct rectifying nozzle, a starting dynamo and the like. The stamping-turbine air injection composite aero-engine effectively utilizes the stamping effect and advantages of a turbojet engine, participates in precooling treatment, effectively solves the problems that the ramjet engine takes air in the starting and high-speed states, and the engine power is limited, is simple in structure, low in cost, high in efficiency, wide in running speed range and low in running speed of the complete machine, and has a better application prospect.
Description
Technical field
The present invention relates to aviation field, especially aero-engine field, specially a kind of punching press turbojet is combined
Aero-engine.The present invention is combined aero-engine as a kind of punching press turbojet of low cost, has preferable application
Prospect.
Background technology
Aero-engine provides the electromotor of flight required drive as airborne vehicle, and it is a kind of high complexity and precision
Thermal machine.Aero-engine, as the heart of aircraft, is described as " flower of industry ", and it directly affects the performance of aircraft, reliability
Property and economy, be a national science and technology, industry and military capability of the country important embodiment.Due to aero-engine technical threshold very
Height, only has a few countries such as the U.S., Russia, Britain, France can independently develop high performance turbine at present in the world and sends out
Motivation.
According to the difference of operation mechanism, aero-engine is divided into piston aviation engine, gas-turbine unit, punching
Hydraulic motor three class.
Wherein, piston aviation engine is the aero-engine of early stage application on aircraft or helicopter, is mainly used in
Drive propeller or rotor.At present, piston aviation engine is widely used for light aerocraft, helicopter and ultra light aircraft
On.
Gas-turbine unit is the aero-engine being most widely used, and it has compressor, combustor and combustion gas whirlpool
Wheel, main Types include turbojet, turbofan, turboprop and turboaxle motor.
Wherein, turboprop is mainly used in the aircraft that speed per hour is less than 800 kms；Turboaxle motor is mainly used in as going straight up to
Machine provides power；Turbofan is mainly used in the higher aircraft of speed；Turbojet is mainly used in supersonic speed
Aircraft.
Punching engine has the characteristics that no compressor and gas turbine, and the air entering combustor is using during high-speed flight
Punching press effect supercharging.Thus, it has the advantages that simple structure, thrust are big, is particularly well-suited to high speed high-altitude flight.
However, existing aero-engine there is also certain deficiency.Gas-turbine unit is applied at most as current
Aero-engine, its part is various, and blade construction is complicated, thus its processing cost is high, and processing technique is extremely complex.Separately
Outward, with the raising of the speed of service, being uprised by air velocity is affected, and the temperature rise of gas-turbine unit is also gradually obvious, makes
Become it to be difficult to work, lead to the operational speed range of gas-turbine unit limited.Punching engine is due to based on high-speed air
Punching press effect and act on, therefore can not voluntarily start it is necessary to be promoted by other propulsion plants, to obtain toggle speed, also cannot
Run under the low speed.Simultaneously as the rising of the lower intake air temperature of punching press effect, whole machine high temperature resistant property is required also further
Improve, it is very harsh for the requirement of combustor.In addition, the cooling of punching engine to be also always itself insoluble
Problem.
For this reason, in the urgent need to a kind of new aero-engine, to solve the above problems.
Content of the invention
The goal of the invention of the present invention is: has for existing gas-turbine unit complex structure, operational speed range
Limit, and punching engine can not voluntarily start it is impossible to run under the low speed, cooling is more difficult, and to whole machine high temperature resistant property
Require higher problem, provide a kind of punching press turbojet to be combined aero-engine.Effectively utilizes punching press effect of the present invention and
The advantage of turbojet, and add precooling to process, efficiently solve punching engine and start and fast state air inlet,
And the problem that engine power limits.Present configuration is simple, with low cost, efficiency high, and operational speed range is wide, whole machine fortune
Trip temperature is low, has preferable application prospect.
To achieve these goals, the present invention adopts the following technical scheme that
A kind of punching press turbojet is combined aero-engine, including punching press suction cone, by-pass air duct casing, inlet guide
Blade, for be connected with liquid oxygen apparatus liquid oxygen regulating valve, for be connected with liquid nitrogen plan liquid nitrogen regulating valve, arrange contain outside
Main duct casing inside road casing, straightener(stator) blade, the fuel regulator valve for being connected with oil burning installation, centrifugal compressor, expansion
Depressor, combustor, concentric shafts, turbine, main duct rectification spout, the startup motor being connected with main duct casing and startup motor
Connected electric power supply apparatus, control system, it is arranged on projection inside by-pass air duct casing；
The venthole that the rear portion of described punching press suction cone is provided with cavity, is connected with cavity, described air-intake guide vane
For hollow structure, described punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, described liquid oxygen regulating valve, liquid
Nitrogen regulating valve is connected with the hollow structure in air-intake guide vane respectively, and described punching press suction cone forms punching with by-pass air duct casing
Pressure runner；
Described straightener(stator) blade is hollow structure, and described main duct casing is connected with by-pass air duct casing by straightener(stator) blade, institute
State fuel regulator valve to be connected with combustor by straightener(stator) blade, described diffuser, combustor are successively set in main duct casing,
Described centrifugal compressor is connected with combustor through diffuser, and described concentric shafts pass through combustor, the outlet setting of described combustor
Have stator blade, described stator blade be located between combustor and turbine, described main duct rectification notch setting in turbine rear end,
Described centrifugal compressor, turbine are connected with concentric shafts respectively, and described startup motor is connected with concentric shafts and starts motor and can drive
Concentric shafts rotate；
Described raised be located between venthole and centrifugal compressor, described control system respectively with liquid oxygen regulating valve, liquid nitrogen
Regulating valve, fuel regulator valve are connected.
The nitrogen that the gas of stamped runner can be flowed out with venthole, oxygen collide, and realize heat exchange.
Described projection is triangular in shape along the sectional view of by-pass air duct casing radial direction.
Described set-up of control system is in main duct casing near one end of punching press suction cone.
Also include the liquid oxygen apparatus being connected with liquid oxygen regulating valve, the liquid nitrogen plan being connected with liquid nitrogen regulating valve.
Also include the oil burning installation being connected with fuel regulator valve.
Described electric power supply apparatus are power line.
For foregoing problems, the present invention provides a kind of punching press turbojet to be combined aero-engine, specially a kind of low
The punching press turbojet of cost is combined aero-engine.It includes punching press suction cone, by-pass air duct casing, inlet guide leaf
Piece, for be connected with liquid oxygen apparatus liquid oxygen regulating valve, be used for be connected with liquid nitrogen plan liquid nitrogen regulating valve, be arranged on by-pass air duct
Main duct casing inside casing, straightener(stator) blade, the fuel regulator valve for being connected with oil burning installation, centrifugal compressor, diffusion
Device, combustor, concentric shafts, turbine, main duct rectification spout, the startup motor being connected with main duct casing and startup motor phase
Electric power supply apparatus even, control system, it is arranged on projection inside by-pass air duct casing.
One end of punching press suction cone is arranged as front end with by-pass air duct casing, setting main duct casing in by-pass air duct casing
One end is rear end.The rear portion of punching press suction cone is provided with cavity, the venthole being connected with cavity, and air-intake guide vane is hollow
Structure, punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, liquid oxygen regulating valve, liquid nitrogen regulating valve respectively with
Hollow structure in air-intake guide vane is connected, and punching press suction cone forms the first inlet channel with by-pass air duct casing.
Straightener(stator) blade is hollow structure, and main duct casing is connected with by-pass air duct casing by straightener(stator) blade, fuel regulator valve
It is connected with combustor by straightener(stator) blade, diffuser, combustor are successively set in main duct casing, and centrifugal compressor is through diffusion
Device is connected with combustor, and concentric shafts pass through combustor, and the outlet of combustor is provided with stator blade, and stator blade is located at combustor
And turbine between, main duct rectification notch setting is connected with concentric shafts respectively in turbine rear end, centrifugal compressor, turbine, starts
Motor is connected with concentric shafts and starts motor and concentric shafts can be driven to rotate.
Raised be located between venthole and centrifugal compressor, control system respectively with liquid oxygen regulating valve, liquid nitrogen regulating valve, combustion
Oily regulating valve is connected.In the present invention, heat exchange effect is realized by projection, that is, the gas of stamped runner can be flowed out with venthole
Nitrogen, oxygen collision, realize heat exchange.Further, raised triangular in shape along the sectional view of by-pass air duct casing radial direction.
Further, set-up of control system, in main duct casing near one end of punching press suction cone, also includes adjusting with liquid oxygen
The section valve liquid oxygen apparatus (i.e. liquid oxygen storage tank) being connected, the liquid nitrogen plan (i.e. nitrogen storage tank) being connected with liquid nitrogen regulating valve, also
Including the oil burning installation being connected with fuel regulator valve, electric power supply apparatus are power line.
During present invention work, by-pass air duct casing front end airflow, punching press suction cone and by-pass air duct casing are collectively forming punching press
Runner.The front end of punching press suction cone forms vertebral body shock wave, forms normal shock wave between its rear end and by-pass air duct casing.Liquid oxygen, liquid
Nitrogen passes through liquid oxygen regulating valve respectively, liquid nitrogen regulating valve is entered in cavity, and flowed out by venthole.The cryogenic nitrogen flowing out through pore
Gas, cryogenic oxygen, in projection, (raised role is mainly heat exchange, and that is, projection is with the gas entering through by-pass air duct casing front end
Heat exchanger) in the presence of mix, realize heat exchange.In the middle part of by-pass air duct casing, main duct casing is arranged by straightener(stator) blade, thus with
By-pass air duct casing cooperatively forms little bypass ratio structure.The present invention arranges in the front end of main duct casing and starts motor, starts motor
Connect concentric shafts, the front end setting centrifugal compressor of concentric shafts, the rear end setting turbine of concentric shafts, diffuser is arranged on main duct
In casing, arrangement combuster and stator blade between diffuser and turbine, combustion gas is sprayed by rectification spout after turbine.
In the present invention, air inlet compression process completes with punching press air inlet vertebral body and centrifugal compressor, and control system is passed through to adjust each
The supply of regulating valve, realizes whole machine stable operation.Meanwhile, using cooperatively by air-intake guide vane and straightener(stator) blade, completes
Entry spin and by-pass air duct air-flow rectification.
In the present invention, punching press form combines formation boost section with centrifugal compressed form, and compression efficiency is higher；Possesses startup electricity
Machine, can achieve that no initial velocity starts；Whole machine operational speed range is wide, can adapt to low speed to supersonic range of operation；Regulation and control
, using injection gas and fuel oil combine regulation, mode is more flexible, and the effect reaching is more stable for mode；Add precooling to process,
So that internal efficiency is improved, so that whole machine antagonism high-temperature material requirement is reduced；Using modular construction simple, processing and manufacturing cost
Low.
In sum, due to employing technique scheme, the invention has the beneficial effects as follows:
1), in the present invention, using ram-compressed cooperation first-stage centrifugal compression, in hgher efficiency, wherein, ram-compressed is foundation
Air velocity produce it is not necessary to additional driving force, centrifugal compressed single-stage pressure ratio is higher, thus whole compression process only need to right
Centrifugal compressed applies to drive, the little energy being consumed；
2) in the present invention, precool the addition processing, so that whole machine running temperature is reduced, inlet end compression efficiency is higher,
Whole machine is reduced, high temperature resistance material requirements similarly reduces for the requirement of cooling system；
3) present invention is in low speed, air inlet and work by combustion work combustor and turbine with the centrifugal compressor of one-level
Realize, when through the transonic speed stage, punching press effect is progressively notable, solves the unit centrifugal compressor pressure ratio in high-speed cruising
Not enough situation, and speed-adaptive scope is wider；
4) present invention passes through cavity and pore, the injection of external liquid nitrogen liquid oxygen of front end punching press suction cone, can be at any time
Adjust aeration ratio, when external feed stream condition changes greatly or be unstable, can according to circumstances adjust the injection of liquid oxygen liquid nitrogen, and
During the injection of liquid oxygen liquid nitrogen, most of heat can be absorbed by heat exchanger, make compression effectiveness more preferably, simultaneously the spirit of combine regulation mode
Live, good stability；
5) rotor-support-foundation system of the present invention is single stage rotor, and compression process coordinates centrifugal compressor for punching press, and structure is relatively many
Level compressor is more simple, and the combustion gas after combustor, through one-level stator blade and turbine, coordinates common generation of outer flow passage to push away
, so that rotor-support-foundation system is more simple, manufacturability is good, thus the present invention has the advantages that structure is simple, with low cost for power.
Brief description
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is combined the cross-sectional view of aero-engine for the present invention.
In figure: 1 is punching press suction cone, 2 is by-pass air duct casing, and 3 is air-intake guide vane, and 4 is liquid oxygen regulating valve, and 5 are
Liquid nitrogen regulating valve, 6 is main duct casing, and 7 is straightener(stator) blade, and 8 is fuel regulator valve, and 9 is centrifugal compressor, and 10 is diffuser,
11 is combustor, and 12 is concentric shafts, and 13 is turbine, and 14 is main duct rectification spout, and 15 is to start motor, and 16 is supply of electric power dress
Put, 17 is projection, 18 is cavity, 19 is venthole, 20 is stator blade.
Specific embodiment
All features disclosed in this specification, or disclosed all methods or during step, except mutually exclusive
Feature and/or step beyond, all can combine by any way.
Any feature disclosed in this specification, unless specifically stated otherwise, all can be equivalent or there is similar purpose by other
Alternative features are replaced.I.e., unless specifically stated otherwise, each feature is a series of equivalent or one of similar characteristics example
?.
Embodiment 1
The punching press turbojet of the present embodiment is combined aero-engine and includes punching press suction cone, by-pass air duct casing, enters
Mouth guide vane, the liquid oxygen regulating valve for being connected with liquid oxygen apparatus, the liquid nitrogen regulating valve for being connected with liquid nitrogen plan, setting
Main duct casing inside by-pass air duct casing, straightener(stator) blade, for be connected with oil burning installation fuel regulator valve, be centrifuged calm the anger
Machine, diffuser, combustor, concentric shafts, turbine, main duct rectification spout, the startup motor being connected with main duct casing and startup
Electric power supply apparatus that motor is connected, control system, it is arranged on projection inside by-pass air duct casing.
In the front end of by-pass air duct casing, the rear portion of punching press suction cone is provided with cavity, the venthole being connected with cavity, enters
Mouth guide vane is hollow structure, and punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, liquid oxygen regulating valve,
Liquid nitrogen regulating valve is connected with the hollow structure in air-intake guide vane respectively, and punching press suction cone forms punching press with by-pass air duct casing
Runner.
Straightener(stator) blade is hollow structure, and main duct casing is connected with by-pass air duct casing by straightener(stator) blade, fuel regulator valve
It is connected with combustor by straightener(stator) blade, diffuser, combustor are successively set in main duct casing, and centrifugal compressor is through diffusion
Device is connected with combustor, and concentric shafts pass through combustor, and the outlet of combustor is provided with stator blade, and stator blade is located at combustor
And turbine between, main duct rectification notch setting is connected with concentric shafts respectively in turbine rear end, centrifugal compressor, turbine, starts
Motor is connected with concentric shafts and starts motor and concentric shafts can be driven to rotate.
Raised be located between venthole and centrifugal compressor, control system respectively with liquid oxygen regulating valve, liquid nitrogen regulating valve, combustion
Oily regulating valve is connected.
In the present embodiment, in main duct casing near one end of punching press suction cone, supply of electric power fills set-up of control system
Put and adopt power line.Liquid oxygen regulating valve is connected with liquid oxygen storage tank, and liquid nitrogen regulating valve is connected with liquid nitrogen storage tank, fuel regulator valve and combustion
Oil tank is connected.
The work process of aero-engine of the present invention is broadly divided into subsonic speed and across, supersonic speed stage.
In subsonic speed, air velocity is relatively low, and punching press suction cone can not form punching press effect with the cooperation of by-pass air duct casing,
Now air inlet relies primarily on centrifugal compressor and is pressurized and air inlet, passes through liquid oxygen regulating valve simultaneously and liquid nitrogen regulating valve is noted simultaneously
Enter two kinds of gases, after heat exchanger (i.e. raised), as pre-cooling before air inlet, and adjust Charge-Air Oxygen ratio.The pre- cold energy of air inlet
Effectively improve pressure ratio and the efficiency of centrifugal compressor, oxygen proportion is adjusted to adapt to combustion chambers burn, and control system is according to whole machine
Ruuning situation combines the input ratio reconciling each regulating valve.Subsonic speed air, after the inflow of by-pass air duct casing, is led through import
To blade, obtain certain inlet velocity angle after guiding such that it is able to fully with the low temperature nitrogen flowing out from venthole, oxygen
Gas mixes in heat exchanger, completes the gas after combination cooling and enters centrifugal compressor, completes compression process through diffuser.
Runner between main duct casing and by-pass air duct casing for another part gas, as whole machine cooling and rectification from
Afterbody sprays.After compression, gas is burnt with fuel oil through combustor, and high-speed fuel gas promote turbine acting through stator blade, finally
Spray through main duct rectification spout, with outer layer cooling stream cooperation, obtain thrust.
In, the work process in supersonic speed stage, maximum difference is with the subsonic speed stage: compress mode is not
With.Across, supersonic speed stage, with the raising of speed, punching press suction cone and by-pass air duct casing cooperatively form punching press and calm the anger effect
Really, after air-intake guide vane, obtained air has the characteristic of High Temperature High Pressure to the high pressure-temperature air after punching press, obtains final product
To high temperature and high pressure gas.Now, tune up the ratio being passed through liquid nitrogen, reduce the temperature of high temperature and high pressure gas, retain its high pressure characteristics,
So that the gas entering centrifugal compressor still is able to keep efficient compression effectiveness.Under this state, compression process is by punching press
Suction cone and by-pass air duct casing cooperatively form first order compression, and centrifugal compressor compresses for the second level, jointly completes compressed
Journey.Liquid oxygen regulating valve and liquid nitrogen regulating valve according to generator operating conditions come real-time regulation oxygen proportion, and pre-cooling of suitably lowering the temperature
But, after completing mixing, enter centrifugal compressor, complete compression process through diffuser.Another part gas is via main duct machine
Runner between casket and by-pass air duct casing, sprays from afterbody after straightener(stator) blade rectification.After compression gas through combustor with
Fuel oil burns, and high-speed fuel gas promote turbine acting through stator blade, eventually passes main duct rectification spout and sprays, with outer laminar flow
Road coordinates, and obtains thrust.
Above in conjunction with accompanying drawing, the present invention is exemplarily described, but the present invention is not limited to aforesaid way, only
The improvement of various unsubstantialities that carry out with technical scheme is conceived using the method for the present invention or directly applies to other occasions
, all fall within protection scope of the present invention.The invention is not limited in aforesaid specific embodiment.Present invention extension is taken office
What new feature of disclosing in this manual or any new combination, and the arbitrary new method that discloses or process step or
Any new combination.
Claims (10)
1. a kind of punching press turbojet is combined aero-engine it is characterised in that including punching press suction cone, by-pass air duct machine
Casket, air-intake guide vane, the liquid oxygen regulating valve for being connected with liquid oxygen apparatus, the liquid nitrogen regulation for being connected with liquid nitrogen plan
Valve, be arranged on main duct casing inside by-pass air duct casing, straightener(stator) blade, for be connected with oil burning installation fuel regulator valve,
Centrifugal compressor, diffuser, combustor, concentric shafts, turbine, main duct rectification spout, the startup electricity being connected with main duct casing
Machine, with start the electric power supply apparatus that motor is connected, control system, be arranged on projection inside by-pass air duct casing；
The venthole that the rear portion of described punching press suction cone is provided with cavity, is connected with cavity, during described air-intake guide vane is
Hollow structure, described punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, and described liquid oxygen regulating valve, liquid nitrogen are adjusted
Section valve is connected with the hollow structure in air-intake guide vane respectively, and described punching press suction cone forms ducted fluid flow with by-pass air duct casing
Road；
Described straightener(stator) blade is hollow structure, and described main duct casing is connected with by-pass air duct casing by straightener(stator) blade, described combustion
Oily regulating valve is connected with combustor by straightener(stator) blade, and described diffuser, combustor are successively set in main duct casing, described
Centrifugal compressor is connected with combustor through diffuser, and described concentric shafts pass through combustor, and the outlet of described combustor is provided with quiet
Blades, described stator blade is located between combustor and turbine, and described main duct rectification notch setting is in turbine rear end, described
Centrifugal compressor, turbine are connected with concentric shafts respectively, described startup motor be connected with concentric shafts and start motor can drive concentric
Axle rotates；
Described projection is located between venthole and centrifugal compressor, and described control system is adjusted with liquid oxygen regulating valve, liquid nitrogen respectively
Valve, fuel regulator valve are connected.
2. punching press turbojet is combined aero-engine it is characterised in that the gas of stamped runner according to claim 1
The nitrogen that body can be flowed out with venthole, oxygen collide, and realize heat exchange.
3. punching press turbojet according to claim 1 or claim 2 be combined aero-engine it is characterised in that described projection edge
The sectional view of by-pass air duct casing radial direction is triangular in shape.
4. punching press turbojet according to claim 1 or claim 2 is combined aero-engine it is characterised in that described control system
System is arranged on main duct casing one end near punching press suction cone.
5. punching press turbojet according to any one of claim 1 ~ 2 is combined aero-engine it is characterised in that also including
The liquid oxygen apparatus being connected with liquid oxygen regulating valve, the liquid nitrogen plan being connected with liquid nitrogen regulating valve.
6. punching press turbojet is combined aero-engine it is characterised in that also including adjusting with liquid oxygen according to claim 3
The section valve liquid oxygen apparatus being connected, the liquid nitrogen plan being connected with liquid nitrogen regulating valve.
7. punching press turbojet according to any one of claim 1,2,6 is combined aero-engine it is characterised in that also wrapping
Include the oil burning installation being connected with fuel regulator valve.
8. punching press turbojet is combined aero-engine it is characterised in that also including adjusting with fuel oil according to claim 3
The oil burning installation that section valve is connected.
9. punching press turbojet is combined aero-engine it is characterised in that also including adjusting with fuel oil according to claim 5
The oil burning installation that section valve is connected.
10. punching press turbojet is combined aero-engine it is characterised in that described supply of electric power according to claim 1
Device is power line.
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| CN105736178B (en) * | 2016-04-11 | 2018-05-29 | 清华大学 | Combined cycle engine |
| CN106224126A (en) * | 2016-08-29 | 2016-12-14 | 曾令霞 | Intermediate layer and the jet engine of following height |
| CN106438104B (en) * | 2016-09-18 | 2018-05-22 | 中国科学院工程热物理研究所 | A kind of fuel-rich pre-burning fanjet |
| CN106762221B (en) * | 2017-01-13 | 2018-10-26 | 厦门大学 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
| CN110273784A (en) * | 2018-03-13 | 2019-09-24 | 姚永新 | Screw eruption type engine |
| CN109281763B (en) * | 2018-07-30 | 2021-01-19 | 南京航空航天大学 | Combined power air inlet channel based on internal flow double-culvert adjusting control |
| CN109324528B (en) * | 2018-09-19 | 2020-04-21 | 中国航发湖南动力机械研究所 | Ducted turboshaft engine, and ducted control system and control method for turboshaft engine |
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| CN112096538A (en) * | 2020-08-26 | 2020-12-18 | 哈尔滨工业大学 | Hybrid multi-mode turbine stamping combined engine |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
| CN114776474B (en) * | 2022-04-13 | 2024-04-12 | 清华大学 | Power system, aircraft and control method thereof |
| CN116291953B (en) * | 2023-05-22 | 2023-07-25 | 北京大学 | Full-continuous detonation mode turbine rocket ram combined cycle engine and operation method |
| CN116902210B (en) * | 2023-09-13 | 2023-12-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Energy supply method and device for aircraft onboard system |
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