CN106968833B - A kind of supersonic speed detonation engine and its propulsion system - Google Patents
A kind of supersonic speed detonation engine and its propulsion system Download PDFInfo
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- CN106968833B CN106968833B CN201710197059.8A CN201710197059A CN106968833B CN 106968833 B CN106968833 B CN 106968833B CN 201710197059 A CN201710197059 A CN 201710197059A CN 106968833 B CN106968833 B CN 106968833B
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- inclined plate
- air intake
- intake duct
- propulsion system
- combustion chamber
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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
- 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
- F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Abstract
The invention discloses a kind of propulsion system, including air intake duct and combustion chamber, the ramp assemblies for guiding oblique detonation wave are installed in the combustion chamber, the ramp assemblies include for changing the inclined plate of incoming flow flow direction, and the tilt adjustable of the inclined plate.Propulsion system provided by the present invention, by the inclined plate for setting the inclined plate in the ramp assemblies to adjustable angle, it can be in the flow velocity difference of the incoming flow, by the tilt angle for adjusting the inclined plate, adapt to the incoming flow different in flow rate, guarantee that incoming flow pinking is gone on smoothly, prevents the oblique detonation wave of induction from forward pass occurs, improve the use reliability of the engine.The invention also discloses a kind of supersonic speed detonation engines including above-mentioned propulsion system.
Description
Technical field
The present invention relates to detonation engine apparatus fields, more particularly to a kind of propulsion system.Moreover, it relates to
A kind of supersonic speed detonation engine including above-mentioned propulsion system.
Background technique
With the development of hypersonic aircraft, the efficiency of propulsion system becomes restriction motor power and further increases
One of bottleneck, and detonating combustion efficiency of thermal cycle is high, heat release is fast, the supersonic speed propulsion system layout based on detonating combustion
Compact, structure is simple, and therefore, pinking base engine can be used as the potential scheme of hypersonic propulsion system.
In the prior art, under the conditions of hypersonic, detonation combustor tissue in such a way that slope induces pinking burns,
In integrated supersonic speed detonation engine, fuel is sprayed into precursor, and burning and incoming flow mix rapidly, and slope induces at precursor
Oblique detonation wave is generated, is promptly burnt in combustion chamber by the premixed gas of detonation wave, is expanded produce by expansion segment later
Raw thrust.
However, what is considered due to existing pinking base engine is slope induced synthesis detonation wave using fixed angle
Mode tissue detonating combustion, when incoming flow operating condition changes, ramp angles are fixed, and burning corrugated can generate congestion and make the oblique quick-fried of induction
Forward pass occurs for seismic wave.
Meanwhile propulsion system in the prior art, combustion chamber and expanding nozzle are separately provided, since combustion chamber needs to mix
Fuel, therefore, the length of combustion chamber are generally all longer, cause the volume of entire propulsion system larger, and structure is complicated for engine.
Therefore, the reliability for how improving propulsion system, is a technical problem that technical personnel in the field need to solve at present.
Summary of the invention
The object of the present invention is to provide a kind of propulsion system, which can effectively prevent by adjusting the angle on slope
Forward pass occurs for the oblique detonation wave only induced.It is a further object of the present invention to provide a kind of supersonic speed including above-mentioned propulsion system is quick-fried
Shake engine.
To achieve the above object, the invention provides the following technical scheme:
A kind of propulsion system, including air intake duct and combustion chamber are equipped with for guiding oblique detonation wave in the combustion chamber
Ramp assemblies, the ramp assemblies include for changing the inclined plate of incoming flow flow direction, and the tilt adjustable of the inclined plate.
Preferably, the ramp assemblies further include the extensible member for adjusting the swash plate angle, the extensible member installation
In a side lower part of the inclined plate far from the air intake duct, and the one end and the burning of the inclined plate close to the air intake duct
Room is hinged.
Preferably, the ramp assemblies further include the pedestal for installing the inclined plate, and one end of the extensible member
It is connect with the pedestal, the other end is connect with the inclined plate.
Preferably, the inclined plate is tilted upwards to one end far from the air intake duct from one end close to the air intake duct and is set
It sets.
Preferably, the extensible member is to hang the chain being located in the combustion chamber, one end of the chain and the burning
The inner wall of room connects, and the other end is connect with the inclined plate.
Preferably, further include the controller being connect with the extensible member, the controller is used for:
The flow velocity of the incoming flow obtained；
According to the optimum tilt angle on slope described in the flow relocity calculation of the incoming flow, so that the incoming flow was formed after lighting
Oblique detonation wave acts on the wall surface of expanding nozzle；
The length of the extensible member is adjusted, so that the slope is in optimum tilt angle.
Preferably, the combustion chamber is equipped with expanding nozzle, and the combustion chamber and institute far from one end of the air intake duct
It states expanding nozzle and forms Integrated Combustion room expanding nozzle.
Preferably, it is connected between the air intake duct and the combustion chamber by distance piece.
Preferably, the front end of the air intake duct is equipped with precursor fuel spray mouth, and the precursor fuel spray mouth is used for institute
It states and sprays into fuel in air intake duct to premix fuel.
The present invention also provides a kind of supersonic speed detonation engines, including propulsion system described in above-mentioned any one.
Propulsion system provided by the present invention, including air intake duct and combustion chamber are equipped with for guiding in the combustion chamber
The ramp assemblies of oblique detonation wave, the ramp assemblies include for changing the inclined plate of incoming flow flow direction, and the inclination of the inclined plate
Adjustable angle.The propulsion system can be described by setting the inclined plate in the ramp assemblies to the inclined plate of adjustable angle
When the flow velocity difference of incoming flow, by adjusting the tilt angle of the inclined plate, the incoming flow different in flow rate is adapted to, guarantees that incoming flow is quick-fried
Shake is gone on smoothly, and is prevented the oblique detonation wave of induction from forward pass occurs, is improved the use reliability of the engine.
Supersonic speed detonation engine provided by the present invention is equipped with above-mentioned propulsion system, since the propulsion system is with upper
Technical effect is stated, therefore, the supersonic speed detonation engine equipped with the propulsion system should also be as having corresponding technical effect.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
It obtains other drawings based on these drawings.
Fig. 1 is a kind of structural schematic diagram of specific embodiment of propulsion system provided by the present invention；
Fig. 2 is the enlarged structure schematic diagram of ramp assemblies shown in Fig. 1；
Wherein: 1- precursor fuel spray mouth, 2- premix fuel, 3- inlet mouth, 4- ramp assemblies, 41- inclined plate, 42-
Extensible member, 43- pedestal, the oblique detonation wave of 5-, A- air intake duct, B- distance piece, C- Integrated Combustion room expanding nozzle.
Specific embodiment
Core of the invention is to provide a kind of propulsion system, which can effectively prevent by adjusting the angle on slope
Forward pass occurs for the oblique detonation wave only induced, significantly improves the use reliability of detonation engine.Another core of the invention is to mention
For a kind of supersonic speed detonation engine including above-mentioned propulsion system.
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Fig. 1 and Fig. 2 are please referred to, Fig. 1 is a kind of structural representation of specific embodiment of propulsion system provided by the present invention
Figure；Fig. 2 is the enlarged structure schematic diagram of ramp assemblies shown in Fig. 1.
In this embodiment, propulsion system includes air intake duct A and combustion chamber, and the air intake duct A in the propulsion system is main
It is responsible for capture incoming flow, more incoming flows is made to enter combustion chamber after the compression of air intake duct A precursor；It is equipped in combustion chamber for drawing
The ramp assemblies 4 of oblique detonation wave 5 are led, ramp assemblies 4 include for changing the inclined plate 41 of incoming flow flow direction, and the inclination of inclined plate 41
Adjustable angle, the propulsion system design point are hypersonic state, and the speed of incoming flow in combustion chamber is greater than oblique detonating combustion wave
Flame forward pass speed, enable slope induce oblique detonation wave 5 stablize in combustion chamber position.
The ramp angles of the propulsion system are adjustable, and design point is hypersonic state, carrys out flow velocity in combustion chamber
Degree is greater than the flame forward pass speed of oblique detonating combustion wave.
Further, inclined plate 41 is obliquely installed upwards from one end close to air intake duct A to one end far from air intake duct A, i.e., tiltedly
Plate 41 can provide thrust obliquely in the direction of advance of incoming flow, so that incoming flow is formed under the induction of the slope of inclined plate 41
Oblique detonation wave 5.
Specifically, 41 ramp assemblies 4 of inclined plate further include the extensible member 42 for adjusting 41 angle of inclined plate, extensible member 42 is installed
In a side lower part of the inclined plate 41 far from air intake duct A, and inclined plate 41 is hinged close to one end of air intake duct A and combustion chamber, i.e. inclined plate
41 one end and combustion chamber are hinged, and the other end can be swung up and down under the action of extensible member 42, and then realize that inclined plate 41 tilts
The change of angle.In above-mentioned setting, extensible member 42 is mounted on a side lower part of the inclined plate 41 far from air intake duct A, it can be effective
Reduce influence of the high temperature incoming flow to extensible member 42, guarantee the normal use of extensible member 42, reduce damage, stability is good.
The propulsion system can be in incoming flow by setting the inclined plate 41 in ramp assemblies 4 to the inclined plate 41 of adjustable angle
Flow velocity difference when, by adjusting the tilt angle of inclined plate 41, adapt to incoming flow different in flow rate, guarantee incoming flow pinking smoothly into
Row prevents the oblique detonation wave 5 of induction from forward pass occurs, improves the use reliability of the engine.
On the basis of the respective embodiments described above, ramp assemblies 4 further include the pedestal 43 for installing inclined plate 41, and are stretched
One end of contracting part 42 is connect with pedestal 43, and the other end is connect with inclined plate 41.In above-mentioned setting, the first end and pedestal 43 of inclined plate 41
Hingedly, second end rises under the action of extensible member 42, and one end of extensible member is connect with the second end of inclined plate 41, the other end and bottom
Seat 43 connects.
Preferably, extensible member 42 is telescopic oil cylinder.
On the basis of the respective embodiments described above, extensible member 42 can also be to hang the chain set in a combustion chamber, chain
The connection of the inner wall of one end and combustion chamber, the other end connect with inclined plate 41, when needing to change the tilt angle of inclined plate 41, pass through
Change the length of chain.
On the basis of the respective embodiments described above, which further includes the controller connecting with extensible member 42, control
Device is used for:
The flow velocity of the incoming flow of acquisition；
According to the optimum tilt angle on the flow relocity calculation slope of incoming flow, specifically, the optimum tilt angle of above-mentioned inclined plate 41
Determination principle be that the oblique detonation wave 5 formed after lighting incoming flow acts on the wall surface of expanding nozzle, specifically can be by more
Secondary Test Summary goes out the relationship between incoming flow flow velocity and the optimum tilt angle on slope, and in this, as the data reference of controller
Foundation；
Then, controller passes through the length for adjusting extensible member 42, so that slope is in optimum tilt angle.
On the basis of the respective embodiments described above, combustion chamber is equipped with expanding nozzle far from one end of air intake duct A, and burns
Room is structure as a whole with expanding nozzle, and combustion chamber and expanding nozzle collectively form Integrated Combustion room expanding nozzle C, by oblique pinking
Combustion chamber and thrust expanding nozzle are combined to one piece, can effectively reduce the reflection between oblique detonation wave 5 and expanding nozzle wall surface
Angle.
It on the basis of the respective embodiments described above, is connected between air intake duct A and combustion chamber by distance piece B, distance piece B structure
At the distance piece of the propulsion system, distance piece is located between air intake duct A and Integrated Combustion room expanding nozzle C, and distance piece B is removed
Have outside the effect that interferes with each other between isolation air intake duct A and combustion chamber, fuel can distance piece it is relatively long away from
The uniform flammable premixed gas cmpletely mixed is formed in the outlet of distance piece, the i.e. entrance of combustion chamber from interior further mixing
Body.
On the basis of the respective embodiments described above, the front end of air intake duct A is equipped with precursor fuel spray mouth 1, precursor fuel spray
Geat 1 is used to spray into fuel into air intake duct A to premix fuel 2.Specifically, air intake duct A has the function of fuel blending, into
The preceding body position of air flue A is equipped with precursor fuel spray mouth 1, and spray is hydrogen fuel, and the fuel of penetrating, which has, centainly penetrates depth
Degree, the distance of air intake duct A precursor, arrive distance piece when fuel elementary mixing it is uniform, and fuel just can completely into
Air flue entrance 3 will not be overflowed from following lip, i.e. inlet mouth 3.
In the propulsion system, due to being equipped with precursor fuel spray mouth 1 in the front end of air intake duct A, and in air intake duct A and combustion
It burns and distance piece B is set between room, therefore, fuel can be mixed in the precursor portions and distance piece of air intake duct A, reach combustion
When burning room, by evenly mixing, the length of combustion chamber can shorten as far as possible, and then form integral structure with expanding nozzle,
Integrated Combustion room expanding nozzle C referred herein refers to be enough to form oblique detonation wave in one end of expanding nozzle setting length
Length so that the total length of Integrated Combustion room expanding nozzle C compared with the existing technology in combustion chamber and expanding nozzle
Length be substantially reduced so that the length of engine reduces, simplify structure, save cost of manufacture, weight is reduced, can also be dropped
The transportation cost of low engine.
Propulsion system provided by the present embodiment uses detonating combustion, improves efficiency of combustion, utilizes the oblique of angle adjustable
Slope induction detonation incoming flow premixed gas sufficiently expands after burning so that incoming flow premixes gas full combustion, and makes full use of tiltedly quick-fried
Expanding nozzle and combustion chamber compact design are integrated by the characteristic of gas expansion after seismic wave 5, are greatly shortened, are simplified engine
Structure.
Specifically, this propulsion system, under hypersonic inlet flow conditions, combustion chamber and export expansion type face are incorporated in one
It rises, passes through the oblique detonation wave 5 that forward pass does not occur that the slope induced synthesis of the adjustable angle of combustion chamber wall surface is stable, premixed gas
Fuel is burnt by oblique detonation wave 5, discharges rapidly heat, and expansion generates thrust.
Moreover, air intake duct A is in such a way that preceding body position fuel shifts to an earlier date spray premix, combustion chamber and expansion segment are combined,
The oblique detonation wave 5 of the slope induced synthesis of adjustable angle, the hypersonic Jet propulsion system of integration based on detonating combustion.Such as
Shown in Fig. 1, which detonates oblique pinking propulsion system mainly by air intake duct A, distance piece, the expansion of Integrated Combustion room
The slope apparatus of jet pipe C, precursor fuel spray mouth 1 and adjustable angle form.
The slope of angle adjustable and the cooperation of Integrated Combustion room expanding nozzle C are the features of propulsion system maximum.Tool
Body, it is assumed that ramp angles θ1, the propagation of the oblique detonation wave 5 Mach 2 ship M of premixed gasCJ, it is θ for ramp angles1, when next
Flow Mach number M0Between [MUnder, MOn] and have MUnder>MCJWhen, incoming flow, which premixes gas, to induce the oblique detonation wave 5 that detonates by slope.
Work as θ1When reduction, MUnderAnd MOnIt can increase simultaneously；Otherwise θ1When increase, MUnderAnd MOnIt can reduce simultaneously.At distance piece end
Tail, before combustion chamber, fuel is sufficiently mixed, and speed is greater than the forward pass speed M of oblique detonating combustion wave0>MCJ, can be lured by slope
The raw oblique detonation wave 5 of artificial delivery.The forward pass speed of oblique detonating combustion wave is still greater than when speed of incoming flow is lower, needs biggish ramp angle
Degree, which just can induce, generates oblique detonation wave 5, but ramp angles cannot be excessive, otherwise can make the oblique detonation wave 5 generated and expansion face
Angle it is too big, burning generate congestion, occur forward pass, cause detonation fail.When speed of incoming flow is slightly larger than oblique 5 forward pass of detonation wave speed
Spend MCJWhen, ramp angles can be reduced by being adjusted slightly in the range of pinking can detonate to avoid that congestion occurs.Cause
This, ramp angles can be with flexible modulation, when so that speed of incoming flow changing from small to big, and from becoming smaller greatly, guarantee can induce ramp angles
Quick-fried oblique detonation wave 5, but not making detonation wave that congestion forward pass occur causes detonation to fail.The slope of appropriate angle passes through induced ultrasonic speed
Incoming flow forms bowshock, and bowshock lights rapidly incoming flow combustible gas and forms oblique detonation wave 5.At oblique 5 face of detonation wave, fuel is fast
Quick burning burning becomes combustion product and discharges a large amount of heat, and oblique detonation wave 5 just acts on expanding nozzle wall surface, and tiltedly quick-fried
Seismic wave 5 and wall surface angle are small, and the high-temperature combustion product after detonation wave is expanded in jet pipe, and speed increases, so that propulsion system
Generate thrust.Generally speaking, when speed of incoming flow is more than MCJAfterwards, slope at an angle, induces oblique detonation wave 5, and guarantees tiltedly quick-fried
Seismic wave 5 reflects expansion on Integrated Combustion room expansion wall surface, and guarantees that congestion forward pass does not occur for oblique detonation wave 5；Speed of incoming flow
After increase, control reduces ramp angles, and slope is still able to the oblique detonation wave 5 that detonates at this time, and ensure that oblique detonation wave 5 is not gathered around
Plug.
Other than above-mentioned propulsion system, the present invention also provides a kind of, and the supersonic speed pinking including above-mentioned propulsion system is sent out
Motivation, refer to the prior art for other Each parts of the supersonic speed detonation engine, and repeats no more herein.
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.
Propulsion system provided by the present invention is described in detail above.Specific case used herein is to this hair
Bright principle and embodiment is expounded, method of the invention that the above embodiments are only used to help understand and its
Core concept.It should be pointed out that for those skilled in the art, in the premise for not departing from the principle of the invention
Under, it can be with several improvements and modifications are made to the present invention, these improvement and modification also fall into the protection of the claims in the present invention
In range.
Claims (2)
1. a kind of propulsion system, which is characterized in that including air intake duct (A) and combustion chamber, the combustion chamber is far from the air intake duct
(A) one end is equipped with expanding nozzle, and the combustion chamber and the expanding nozzle form Integrated Combustion room expanding nozzle
(C), the ramp assemblies (4) for inducing oblique detonation wave (5) are installed, the ramp assemblies (4) include: in the combustion chamber
For changing the inclined plate (41) of incoming flow flow direction, and the tilt adjustable of the inclined plate (41), the inclined plate (41) from
It is obliquely installed upwards close to the one end of the air intake duct (A) to one end far from the air intake duct (A), the inclined plate (41) is close
One end and the combustion chamber of the air intake duct (A) are hinged；
For adjusting the extensible member (42) of the inclined plate (41) angle, it is separate that the extensible member (42) is installed on the inclined plate (41)
One side lower part of the air intake duct (A)；
For installing the pedestal (43) of the inclined plate (41), and one end of the extensible member (42) and the pedestal (43) are even
It connects, the other end is connect with the inclined plate (41)；
The controller connecting with the extensible member (42), the controller are used for: obtaining the flow velocity of the incoming flow；According to it is described come
The optimum tilt angle on slope described in the flow relocity calculation of stream, so that the oblique detonation wave (5) that the incoming flow is formed after lighting acts on
On the wall surface of expanding nozzle；The length of the extensible member (42) is adjusted, so that the slope is in optimum tilt angle；
It is connected between the air intake duct (A) and the combustion chamber by distance piece (B)；
The front end of the air intake duct (A) is equipped with precursor fuel spray mouth (1), and the precursor fuel spray mouth (1) is used for described
Fuel is sprayed into air intake duct (A) to premix fuel (2).
2. a kind of supersonic speed detonation engine, including propulsion system, which is characterized in that the propulsion system is claim 1 institute
The propulsion system stated.
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| CN108488004B (en) * | 2018-01-25 | 2021-02-26 | 南京航空航天大学 | Stationary detonation engine based on variable wedge angle |
| CN109114591A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | It is a kind of to change the combustion chamber for realizing detonation control by wall angle |
| CN109114590A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of combustion chamber of movable step control detonation |
| CN109140497A (en) * | 2018-07-25 | 2019-01-04 | 南京理工大学 | A kind of combustion chamber for controlling oblique detonation and starting interior detonation point initiation |
| CN109114593A (en) * | 2018-07-25 | 2019-01-01 | 南京理工大学 | A kind of multi-step cascade combustion chamber for controlling detonation |
| CN109110143B (en) * | 2018-09-07 | 2020-09-04 | 叶加军 | Unmanned aerial vehicle engine carries out a mouthful device |
| CN109322761B (en) * | 2018-10-12 | 2021-07-27 | 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 | high-Mach-number in-flight engine annular combustion chamber and spiral oblique detonation combustion method |
| CN111207009B (en) * | 2019-12-26 | 2023-01-13 | 中国空气动力研究与发展中心 | Method for initiating oblique detonation wave in supersonic velocity airflow by using external instantaneous energy source |
| CN111608820A (en) * | 2020-04-30 | 2020-09-01 | 南京理工大学 | Wedge surface structure for controlling oblique detonation waves by utilizing local large-angle wedge surface |
| CN112648638A (en) * | 2020-12-16 | 2021-04-13 | 南京航空航天大学 | Scramjet engine based on combined combustion law |
| CN112761817B (en) * | 2021-01-28 | 2022-06-24 | 北京理工大学 | Oblique detonation engine combustion chamber spray pipe integrated control method and device |
| CN113048516B (en) * | 2021-04-08 | 2022-04-19 | 中国人民解放军国防科技大学 | Detonation combustion chamber, scramjet engine and hypersonic aircraft |
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| CN106089489B (en) * | 2016-08-17 | 2018-03-09 | 中国人民解放军国防科学技术大学 | A kind of scramjet engine |
| CN106352372B (en) * | 2016-10-11 | 2017-05-31 | 中国人民解放军国防科学技术大学 | A kind of supersonic speed detonation combustor and its detonation and self-holding control method |
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