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CN109209679B - Supersonic mixing reinforced structure with frequency characteristic and rocket-based combined engine - Google Patents

Supersonic mixing reinforced structure with frequency characteristic and rocket-based combined engine Download PDF

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Publication number
CN109209679B
CN109209679B CN201811206493.9A CN201811206493A CN109209679B CN 109209679 B CN109209679 B CN 109209679B CN 201811206493 A CN201811206493 A CN 201811206493A CN 109209679 B CN109209679 B CN 109209679B
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Prior art keywords
incoming flow
supersonic
drainage tube
supersonic incoming
partition
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CN109209679A (en
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杨瑞
王振国
赵玉新
王前程
周永易
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National University of Defense Technology
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National University of Defense Technology
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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
    • F02K7/12—Injection-induction jet engines
    • 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
    • F02K7/18—Composite ram-jet/rocket 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Accessories For Mixers (AREA)

Abstract

The invention provides an ultrasonic mixing enhancement structure with frequency characteristics and a rocket-based combined engine, which comprise an ultrasonic incoming flow partition plate, wherein two sides of the ultrasonic incoming flow partition plate are respectively provided with an ultrasonic incoming flow channel, the two ultrasonic incoming flow channels are communicated at the tail end of the ultrasonic incoming flow partition plate to form an ultrasonic incoming flow mixing area, the ultrasonic incoming flow mixing area is communicated with at least one ultrasonic incoming flow channel through at least one drainage tube, the drainage tube is arranged in the ultrasonic incoming flow partition plate, and at least one expansion cavity is arranged in the drainage tube. Because there is the pressure differential at the both ends of drainage tube, need not provide extra air supply just can form the efflux in supersonic velocity incoming flow blending area, realize the mixing enhancement control in supersonic velocity incoming flow blending area, arrange the expansion chamber simultaneously in the drainage tube for the efflux of drainage tube spun has certain frequency characteristic, arranges the expansion chamber of different quantity, realizes the stack of different frequencies. The invention is applied to the field of supersonic incoming flow mixing control.

Description

Supersonic speed blending enhancing structure and rocket base combined engine with frequency characteristic
Technical field
The present invention relates to Supersonic Stream blending control field more particularly to a kind of supersonic speed blending with frequency characteristic Enhancing structure and rocket base combined engine.
Background technique
Critical process of the injection as rocket base combined engine (Rocket Based Combined Cycle, RBCC), Play the role of mixing rocket combustion gas with incoming air.For RBCC, free incoming flow passes through air intake duct, in jet pipe Trailing edge is contacted with spray tube gas, can be chemically reacted when the mixing of the two reaches molecular level, is realized and is utilized oxygen in air The purpose of the high engine/motor specific impulse of air lift.However since speed of incoming flow is very high, the resident time is extremely short (less than 1- in the combustion chamber 3ms), how to realize combustion gas and the mixing of air rapidly and efficiently is the critical issue of injection, is i.e. enhancing mixing effect, determine whole The performance of a propulsion system.
Mixed supersonic layer is received significant attention as the typical liquid form of injection process, wherein generated with way-board again Mixed layer be main study subject.However in the actual process, the extreme temperatures of rocket combustion gas (are greater than 3500K, nozzle throat Heat flow density reaches 107~108W/m2), the temperature of nozzle exit is also above 2500K.In order to protect Rocket ejector geometry, It needs rear thickness certainly will be caused to increase in this way using certain type of cooling, forms supersonic speed blunt trailing edge mixed layer, flow field Structure is as shown in Figure 1.
It include in the prior art two major classes to the control mode of Supersonic Stream blending enhancing, i.e., actively and passively.Passively Control program is to change based on trailing edge structures, including tab, sawtooth, lobe etc., mostly based on trailing edge structures are changed, to generate stream To whirlpool or unstable pulsation.Active Control Method be then mainly by active Implantation Energy and momentum into controlled flow field, thus The feature structure for changing flow field has the function that control blending enhancing.
Based on the passive control program for changing trailing edge structures, structure is simple, control effect is obvious, but primarily directed to from now The thin rear mixed layer abstracted in real problem, for actual blunt trailing edge mixed layer, partition is thicker, not malleable rear Structure, while solar heat protection is unfavorable for using fine stern edge configuration.Based on the active control scheme of vibration piece, vibrating reed is arranged in flow field In, for the combined engine combustion chamber under truth, high-temperature fuel gas is easy for that vibrating reed can be melted.
Summary of the invention
Active control scheme is either used also for the control mode enhanced in the prior art Supersonic Stream blending It is that effectively application this technical problem in practice is all difficult to, the object of the present invention is to provide one kind using passive control program Supersonic speed blending enhancing structure and rocket base combined engine with frequency characteristic, draw in the setting of Supersonic Stream diaphragm internal Supersonic Stream dilution zone is connected to by flow tube with drainage tube with Supersonic Stream channel, since the both ends of drainage tube are there are pressure difference, It does not need to provide additional gas source, jet stream can be formed in Supersonic Stream dilution zone using the flow feature in flow field itself, To realize that the blending to Supersonic Stream dilution zone enhances control, while expansion cavity is arranged in drainage tube, so that drainage tube Interior air-flow reorganizes in expansion cavity, so that the jet stream that drainage tube sprays has certain frequency characteristic.
In order to achieve the above-mentioned object of the invention, the present invention provides a kind of supersonic speed blending enhancing structure with frequency characteristic, Itself the technical solution adopted is that:
Supersonic speed with frequency characteristic blends enhancing structure, including Supersonic Stream partition, the Supersonic Stream every The two sides of plate are respectively equipped with Supersonic Stream channel, and two Supersonic Stream channels are connected to simultaneously in the tail end of Supersonic Stream partition Supersonic Stream dilution zone, Supersonic Stream dilution zone and at least one ultrasound are formed at the rear of Supersonic Stream partition tail end Speed is carried out circulation road and is connected to by least one drainage tube, and the drainage tube is located at the inside of Supersonic Stream partition, the drainage At least one expansion cavity is equipped in pipe.
As a further improvement of the above technical scheme, the Supersonic Stream dilution zone and at least one Supersonic Stream Channel is connected to by least one drainage tube specifically:
Supersonic Stream dilution zone passes through at least one drainage tube with two Supersonic Stream channels respectively and is connected to.
As a further improvement of the above technical scheme, the Supersonic Stream dilution zone and two Supersonic Stream channels It is connected to respectively by least one drainage tube specifically:
Supersonic Stream dilution zone passes through a drainage tube with two Supersonic Stream channels respectively and is connected to.
As a further improvement of the above technical scheme, the expansion cavity is cylindrical structure or polyhedral structure or abnormity Body structure.
As a further improvement of the above technical scheme, the drainage tube is linear structure, curved configuration, broken line type The combination of one of structure or various structures.
In order to achieve the above-mentioned object of the invention, the present invention also provides a kind of rocket base combined engine, the technical side used Case is:
A kind of rocket base combined engine of the supersonic speed blending enhancing structure with above-mentioned with frequency characteristic, including hair Motivation ontology and the jet pipe trailing edge being located on engine body, the head end of the Supersonic Stream partition are fixedly connected on jet pipe On trailing edge, the Supersonic Stream in two Supersonic Stream channels is respectively rocket combustion gas and air.
Advantageous effects of the invention:
The present invention is by being arranged drainage tube for Supersonic Stream dilution zone and supersonic speed in the inside of Supersonic Stream partition Carry out circulation road connection, since flowing has Supersonic Stream in Supersonic Stream channel, two strands of high pressure Supersonic Streams flow through ultrasound Behind two sides of fast incoming flow partition, the recirculating zone of a low pressure is formed at Supersonic Stream partition tail end, and then makes to drain The both ends of pipe do not need to provide additional gas source there are pressure difference, using flow field itself flow feature can supersonic speed come It flows dilution zone and forms jet stream, to realize that the blending to Supersonic Stream dilution zone enhances control, while being arranged in drainage tube Expansion cavity, so that the air-flow in drainage tube reorganizes in expansion cavity, so that the jet stream that drainage tube sprays has certain frequency Rate characteristic, and can according to need the expansion cavity that different number is arranged in same drainage tube, to realize different frequency Superposition.
Detailed description of the invention
Fig. 1 is the schematic diagram of supersonic speed blunt trailing edge flow field of mixed layers；
Fig. 2 is the signal of supersonic speed blending the first embodiment of enhancing structure in the present embodiment with frequency characteristic Figure；
Fig. 3 is the signal of supersonic speed blending second of embodiment of enhancing structure in the present embodiment with frequency characteristic Figure；
Fig. 4 is the signal of supersonic speed blending the third embodiment of enhancing structure in the present embodiment with frequency characteristic Figure；
Fig. 5 is the schematic diagram of rocket base combined engine.
Specific embodiment
For the ease of implementation of the invention, it is further described below with reference to specific example.
Supersonic speed with frequency characteristic as shown in Figure 2 blends enhancing structure, including Supersonic Stream partition 1, ultrasound The two sides of fast incoming flow partition 1 are respectively equipped with Supersonic Stream channel 2, and two Supersonic Stream channels 2 are in Supersonic Stream partition 1 Tail end connection and the rear of Supersonic Stream partition tail end formed Supersonic Stream dilution zone 3, wherein Supersonic Stream every The tail end of plate 1 refers on Supersonic Stream partition 1 towards the end of Supersonic Stream flow direction, Supersonic Stream dilution zone 3 It is connected to at least one Supersonic Stream channel by least one drainage tube, drainage tube 4 is located at the interior of Supersonic Stream partition 1 Portion, i.e. drainage tube are to be used to be connected to Supersonic Stream dilution zone 3 and supersonic speed what 1 inside of Supersonic Stream partition was cut Carry out an interface channel of circulation road 2, at least one expansion cavity 41 is equipped in drainage tube 4, everywhere is transversal on expansion cavity 41 Area is all larger than the cross-sectional area of drainage tube 4, i.e., at one on the pipeline section of drainage tube 4 or has more expansion expansion, form expansion cavity 41, air-flow reorganizes after flowing into expansion cavity 41, so that the jet stream that drainage tube 4 sprays has certain frequency characteristic.Wherein, horizontal Section is the plane perpendicular to 4 axis of drainage tube.
The present embodiment is by being arranged drainage tube 4 for Supersonic Stream dilution zone 3 in the inside of Supersonic Stream partition 1 and surpassing The velocity of sound carrys out the connection of circulation road 2, since flowing has Supersonic Stream, two strands of high pressure Supersonic Stream streams in Supersonic Stream channel 2 After crossing two sides of Supersonic Stream partition 1, the recirculating zone of a low pressure is formed at 1 tail end of Supersonic Stream partition, into And make the both ends of drainage tube 4 there are pressure difference, and it does not need to provide additional gas source, it can be using the flow feature in flow field itself Supersonic Stream dilution zone 3 forms jet stream, to realize that the blending to Supersonic Stream dilution zone 3 enhances control, while drawing Expansion cavity 41 is arranged in flow tube 4, so that the air-flow in drainage tube 4 reorganizes in expansion cavity 41, so that drainage tube 4 sprayed Jet stream has certain frequency characteristic, blends enhancing periodically control to Supersonic Stream dilution zone 3 to realize, and can be with The expansion cavity 41 for arranging different number in same drainage tube as needed, to realize the superposition of different frequency.
It is further preferred that above-mentioned Supersonic Stream dilution zone 3 passes through at least one at least one Supersonic Stream channel A drainage tube connection specifically: Supersonic Stream dilution zone 3 and two Supersonic Stream channels pass through at least one drainage respectively Pipe connection.
It is further preferred that above-mentioned Supersonic Stream dilution zone 3 and two Supersonic Stream channels pass through at least one respectively A drainage tube connection specifically: Supersonic Stream dilution zone 3 and two Supersonic Stream channels pass through a drainage tube respectively and connect It is logical.It is set in Supersonic Stream partition 1 there are two drainage tube, one of drainage tube is connected to the tail end of Supersonic Stream partition 1 With a side of Supersonic Stream partition 1, another drainage tube is connected to the tail end and Supersonic Stream of Supersonic Stream partition 1 Another side of partition 1.
It is further preferred that expansion cavity 41 is cylindrical structure or polyhedral structure or obform body structure.
It is further preferred that drainage tube 4 is one of rectilinear structure, curved configuration, fold-line-shaped structure or a variety of The combination of structure.The structure of drainage tube 4 can be adjusted situation according to actual needs, the drainage tube 4 of different linear structures The flow-path-length of middle air-flow is different, and then different to the weakening degree of air-flow velocity, so that final jet intensity is not yet Together, therefore 4 pairs of drainage tube blending of different linear structures have different reinforcing effects.
As shown in Fig. 2 the drainage tube 4 of curved configuration, the arcuate structure being specially recessed inwardly, expansion cavity 41 are Cylindrical structure, the quantity of expansion cavity 41 are one, and by drainage tube 4, two sections of front and back, two sections of front and back drain expansion cavity 41 respectively Pipe is connected to the center at expansion cavity both ends, and Supersonic Stream enters the drainage tube of leading portion from Supersonic Stream channel 2, Expansion cavity 41 is subsequently entered, air-flow enters the drainage tube of back segment after reorganizing in expansion cavity 41, finally in back segment drainage tube End formed jet stream.In the drainage tube 4 of curved configuration, air-flow flow-path-length is relatively mild, and the jet stream of formation is strong It spends also relatively mild therefore also relatively mild to final blending reinforcing effect.
As shown in Fig. 3 the drainage tube 4 of rectilinear structure, expansion cavity 41 are cylindrical structure, the quantity of expansion cavity 41 It is one, for expansion cavity 41 by two sections of the difference of drainage tube 4 front and back, two sections of drainage tubes of front and back are connected to expansion cavity both ends, surpass Velocity of sound incoming flow enters the drainage tube of leading portion from Supersonic Stream channel 2, subsequently enters expansion cavity 41, air-flow weight in expansion cavity 41 Enter the drainage tube of back segment after new tissue, finally forms jet stream in the end of back segment drainage tube.In the drainage tube 4 of rectilinear structure In, air-flow flow-path-length is shorter, and the jet intensity of formation is also larger therewith, therefore also more to final blending reinforcing effect It is high.
As shown in Fig. 4 the drainage tube 4 of fold-line-shaped structure, expansion cavity 41 are cylindrical structure, the quantity of expansion cavity 41 It is one, for expansion cavity 41 by two sections of the difference of drainage tube 4 front and back, two sections of drainage tubes of front and back are connected to expansion cavity both ends, surpass Velocity of sound incoming flow enters the drainage tube of leading portion from Supersonic Stream channel 2, subsequently enters expansion cavity 41, air-flow weight in expansion cavity 41 Enter the drainage tube of back segment after new tissue, finally forms jet stream in the end of back segment drainage tube.In the drainage tube 4 of fold-line-shaped structure In, air-flow flow-path-length is longer, and institute is interrupted more, and the jet intensity of formation also dies down therewith, therefore mixes final Mixed reinforcing effect is relatively low.
The present embodiment also provides a kind of rocket base combined engine, the technical solution adopted is that:
Rocket base combination with the above-mentioned supersonic speed blending enhancing structure with frequency characteristic as shown in Figure 5 is started Machine is fixed including engine body 5 and the jet pipe trailing edge 6 being located on engine body 5, the head end of Supersonic Stream partition 1 It is connected on jet pipe trailing edge 6, the Supersonic Stream in two Supersonic Stream channels 2 is respectively rocket combustion gas and air.
Contain the explanation of the preferred embodiment of the present invention above, this be for the technical characteristic that the present invention will be described in detail, and Be not intended to for summary of the invention being limited in concrete form described in embodiment, according to the present invention content purport carry out other Modifications and variations are also protected by this patent.The purport of the content of present invention is to be defined by the claims, rather than by embodiment Specific descriptions are defined.

Claims (5)

1.具有频率特性的超声速掺混增强结构，其特征在于，包括超声速来流隔板，所述超声速来流隔板的两侧分别设有超声速来流通道，两个超声速来流通道在超声速来流隔板的尾端连通并在超声速来流隔板尾端的后方形成超声速来流掺混区，超声速来流掺混区与两个超声速来流通道分别通过至少一个引流管连通，所述引流管设在超声速来流隔板的内部，所述引流管内设有至少一个扩张腔，引流管是在超声速来流隔板内部所开凿出的用于连通超声速来流掺混区与超声速来流通道的一个连接通道；1. The supersonic mixing enhanced structure with frequency characteristics is characterized in that it comprises a supersonic incoming flow partition, and the two sides of the supersonic incoming flow partition are respectively provided with a supersonic incoming flow channel, and two supersonic incoming flow channels are separated by a supersonic incoming flow channel. The tail end of the flow partition is connected and forms a supersonic incoming flow mixing zone behind the tail end of the supersonic incoming flow partition, and the supersonic incoming flow mixing zone communicates with the two supersonic incoming flow channels respectively through at least one drainage tube, and the drainage tube Located inside the supersonic incoming flow partition, the drainage tube is provided with at least one expansion chamber, and the drainage tube is excavated inside the supersonic incoming flow partition for connecting the supersonic incoming flow mixing area and the supersonic incoming flow channel a connection channel; 在超声速来流隔板的内部设置引流管将超声速来流掺混区与超声速来流通道连通，由于超声速来流通道内流动有超声速来流，两股高压的超声速来流流过超声速来流隔板的上下表面后，在超声速来流隔板尾端处形成一个低压的回流区，此时导致引流管的两端形成压差，从而在超声速来流掺混区形成射流，同时引流管内的气流在扩张腔内重新组织，使得引流管喷出的射流具有一定的频率特性，从而实现对超声速来流掺混区掺混增强周期性控制。A drainage tube is set inside the supersonic incoming flow partition to connect the supersonic incoming flow mixing area with the supersonic incoming flow channel. Since there is a supersonic incoming flow flowing in the supersonic incoming flow channel, two high-pressure supersonic incoming flows flow through the supersonic incoming flow partition After the upper and lower surfaces of the supersonic incoming flow partition, a low-pressure recirculation zone is formed at the end of the supersonic incoming flow partition. At this time, a pressure difference is formed between the two ends of the drainage tube, thereby forming a jet in the supersonic incoming flow mixing area. At the same time, the air flow in the drainage tube is The expansion cavity is reorganized, so that the jet ejected from the drainage tube has a certain frequency characteristic, so as to realize the enhanced periodic control of the supersonic incoming flow mixing zone. 2.根据权利要求1所述具有频率特性的超声速掺混增强结构，其特征在于，所述超声速来流掺混区与两个超声速来流通道分别通过至少一个引流管连通具体为：2. The supersonic speed mixing enhanced structure with frequency characteristics according to claim 1, characterized in that, the supersonic incoming flow mixing zone communicates with the two supersonic incoming flow channels through at least one drainage tube, specifically: 超声速来流掺混区与两个超声速来流通道分别通过一个引流管连通。The supersonic incoming flow mixing area communicates with the two supersonic incoming flow channels respectively through a drainage tube. 3.根据权利要求1或2所述具有频率特性的超声速掺混增强结构，其特征在于，所述扩张腔为圆柱体结构或多面体结构或异形体结构。3. The supersonic mixing enhanced structure with frequency characteristics according to claim 1 or 2, characterized in that, the expansion cavity is a cylindrical structure, a polyhedral structure or a special-shaped structure. 4.根据权利要求1或2所述具有频率特性的超声速掺混增强结构，其特征在于，所述引流管为直线型结构、曲线形结构、折线型结构中的一种或多种结构的组合。4. According to claim 1 or 2, the supersonic mixing enhanced structure with frequency characteristics is characterized in that, the drainage tube is a combination of one or more structures in a linear structure, a curved structure, and a zigzag structure . 5.一种具有权利要求1至4任一项所述具有频率特性的超声速掺混增强结构的火箭基组合发动机，其特征在于，包括发动机本体以及设在发动机本体上的喷管尾缘，所述超声速来流隔板的首端固定连接在喷管尾缘上，两个超声速来流通道中的超声速来流分别为火箭燃气与空气。5. a rocket-based combined engine with the supersonic mixing enhanced structure with frequency characteristic described in any one of claims 1 to 4, is characterized in that, comprises engine body and the nozzle trailing edge that is arranged on engine body, so The head end of the supersonic incoming flow partition is fixedly connected to the trailing edge of the nozzle, and the supersonic incoming flows in the two supersonic incoming flow channels are respectively rocket gas and air.
CN201811206493.9A 2018-10-17 2018-10-17 Supersonic mixing reinforced structure with frequency characteristic and rocket-based combined engine Active CN109209679B (en)

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US3643676A (en) * 1970-06-15 1972-02-22 Us Federal Aviation Admin Supersonic air inlet control system
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JP2998405B2 (en) * 1992-03-24 2000-01-11 日産自動車株式会社 Scrumjet engine
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CN107013370B (en) * 2017-05-16 2018-05-25 中国人民解放军国防科学技术大学 The active control device of supersonic speed blunt trailing edge mixed layer

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