CN114962066B - A counter-current rotating gas wave ignition detonation combustion device - Google Patents
A counter-current rotating gas wave ignition detonation combustion device Download PDFInfo
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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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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Abstract
Description
技术领域Technical Field
本发明属于爆震发动机技术领域，更具体地，涉及一种逆流式旋转气波点火爆震燃烧装置。The present invention belongs to the technical field of detonation engines, and more specifically, relates to a counter-flow rotating gas wave ignition detonation combustion device.
背景技术Background technique
因爆震燃烧具有自增压的优点，采用爆震燃烧室替换等压燃烧室后可显著提高发动机的综合热效率。不仅如此，爆震燃烧与等压燃烧相比，不存在燃烧不稳定和容易熄火等问题，而且爆震燃烧的燃烧速度很快，燃烧产物在高温区的停留时间很短，可减小NOx等污染物的排放。基于爆震燃烧上述优势，国内外多家研究机构、高校开展了大量将脉冲爆震燃烧室用于航空燃气涡轮发动机相关研究，以大幅提高现有发动机的性能。如发明专利CN201911094367.3公开了一种脉冲爆震发动机依靠独立控制的脉冲点火单元来实现脉冲点火，发明专利CN201410472741.X公开了一种脉冲爆震发动机首先将液体燃料汽化并利用起爆管来起爆主爆管达到脉冲爆震燃烧的目的，等等。Because detonation combustion has the advantage of self-pressurization, the comprehensive thermal efficiency of the engine can be significantly improved by replacing the isobaric combustion chamber with a detonation combustion chamber. Not only that, compared with isobaric combustion, detonation combustion does not have problems such as unstable combustion and easy flameout, and the combustion speed of detonation combustion is very fast, and the residence time of the combustion products in the high temperature zone is very short, which can reduce the emission of pollutants such as NOx. Based on the above advantages of detonation combustion, many research institutions and universities at home and abroad have carried out a large number of studies on the use of pulse detonation combustion chambers in aviation gas turbine engines to greatly improve the performance of existing engines. For example, invention patent CN201911094367.3 discloses a pulse detonation engine that relies on an independently controlled pulse ignition unit to achieve pulse ignition, and invention patent CN201410472741.X discloses a pulse detonation engine that first vaporizes liquid fuel and uses a detonator to detonate the main detonator to achieve the purpose of pulse detonation combustion, and so on.
为了将爆震燃烧的优势推向工程化，人们在脉冲爆震发动机的点火起爆和短距离快速达到爆震燃烧方面做了很多工作。前者可分为连续点火起爆和脉冲点火起爆。连续点火起爆方式具有便于控制、点火能量可控等优势，但额外消耗的点火能量高，且必须提高一套独立的燃料供应系统，导致发动机结构复杂。脉冲点火起爆方式在起爆频率和爆震发动机工作频率匹配的情况下可大幅降低点火能量的消耗，但为达到稳定起爆的目的需在瞬间产生一个很高的点火能量峰值，这在工程化方面存在一定难度。气动点火方式是一种新颖的点火方式，如激波聚焦点火、超声速射流撞击点火等，在流场局部可以达到很高的点火能量，有望解决这一工程难题。In order to promote the advantages of detonation combustion to engineering, people have done a lot of work on the ignition and detonation of pulse detonation engines and the rapid achievement of detonation combustion in a short distance. The former can be divided into continuous ignition and detonation and pulse ignition. The continuous ignition and detonation method has the advantages of easy control and controllable ignition energy, but the additional ignition energy consumed is high, and an independent fuel supply system must be added, resulting in a complex engine structure. The pulse ignition and detonation method can greatly reduce the consumption of ignition energy when the detonation frequency matches the operating frequency of the detonation engine, but in order to achieve the purpose of stable detonation, a very high ignition energy peak must be generated in an instant, which is difficult in engineering. The pneumatic ignition method is a novel ignition method, such as shock wave focusing ignition, supersonic jet impact ignition, etc., which can achieve very high ignition energy in the local flow field and is expected to solve this engineering problem.
发明内容Summary of the invention
针对现有技术的缺陷，本发明提供了一种逆流式旋转气波点火爆震燃烧装置，采用旋转射流装置与一端带有封闭凹腔一端开口的起爆震荡波周期性的接通与闭合，在起爆震荡管内产生脉冲激波并向封闭端凹腔方向运动，当脉冲激波达到封闭端凹腔式会产生激波聚焦现象，在激波聚焦点达到很高的瞬态温度，从而实现起爆爆震管内可燃混气的脉冲点火起爆，起爆后的爆震波向起爆爆震管开口端传播，随后从爆震燃烧室尾端喷出，完成一个爆震燃烧循环，可有效避免常规脉冲爆震发动机复杂的起爆装置结构，同时点火起爆频率连续可调，便于发动机输出功率的控制。In view of the defects of the prior art, the present invention provides a countercurrent rotating gas wave ignition detonation combustion device, which adopts a rotating jet device and a detonation shock wave with a closed cavity at one end and an open end to periodically connect and close, so as to generate a pulse shock wave in the detonation shock tube and move toward the closed end cavity. When the pulse shock wave reaches the closed end cavity, a shock wave focusing phenomenon will occur, and a very high transient temperature will be reached at the shock wave focusing point, thereby realizing pulse ignition and detonation of the combustible mixture in the detonation tube. The detonation wave after detonation propagates toward the open end of the detonation tube, and then ejects from the tail end of the detonation combustion chamber to complete a detonation combustion cycle, which can effectively avoid the complex detonation device structure of conventional pulse detonation engines. At the same time, the ignition and detonation frequency can be continuously adjusted, which is convenient for controlling the engine output power.
为实现上述目的，本发明提供了一种逆流式旋转气波点火爆震燃烧装置，包括同轴布置的进气喷管、环形旋转的爆震燃烧室、旋转射流盘和电动机，电动机设置在爆震燃烧室内，旋转射流盘的旋转轴与电动机相连，旋转射流盘在电动机的带动下进行旋转；旋转射流盘外围周向依次布置有多个射流腔、排气通道和过流腔；旋转射流盘面向进气喷管的进气来流一侧开有一个或多个进气孔，进气孔通过旋转射流盘内部通道与射流腔联通；To achieve the above-mentioned object, the present invention provides a counter-flow rotating gas wave ignition detonation combustion device, comprising a coaxially arranged intake nozzle, a circular rotating detonation combustion chamber, a rotating jet disk and a motor, wherein the motor is arranged in the detonation combustion chamber, the rotating shaft of the rotating jet disk is connected to the motor, and the rotating jet disk rotates under the drive of the motor; a plurality of jet cavities, exhaust channels and flow passages are sequentially arranged in the circumferential direction of the outer periphery of the rotating jet disk; one or more intake holes are opened on the side of the rotating jet disk facing the intake flow of the intake nozzle, and the intake holes are connected to the jet cavity through the internal channel of the rotating jet disk;
爆震燃烧室包括多个周向同轴布置的起爆爆震管，起爆爆震管的一端采用凹腔结构进行封闭，另一端为开口布置；起爆爆震管与旋转射流盘上的排气通道及爆震加力震荡管彼此接通后构成一个联通的爆震通道；起爆爆震管和爆震加力震荡管保持静止。The detonation combustion chamber includes a plurality of circumferentially coaxially arranged detonation tubes, one end of which is closed by a concave cavity structure and the other end is open; the detonation tubes are connected with the exhaust channel on the rotating jet disk and the detonation afterburner shock tube to form a connected detonation channel; the detonation tubes and the detonation afterburner shock tubes remain stationary.
进一步地，射流腔出口与起爆爆震管开口端相对布置，射流向起爆爆震管的凹腔封闭端运动。Furthermore, the jet cavity outlet is arranged opposite to the opening end of the detonation tube, and the jet moves toward the concave cavity closed end of the detonation tube.
进一步地，射流腔的周向长度d满足如下关系：Furthermore, the circumferential length d of the jet cavity satisfies the following relationship:
其中，n为旋转射流盘转速，单位是rpm；r为射流腔高度中位线半径；us为脉冲激波在起爆爆震管内的传播速度。Among them, n is the rotation speed of the rotating jet disk, the unit is rpm; r is the radius of the median line of the jet cavity height; us is the propagation speed of the pulse shock wave in the detonation tube.
进一步地，起爆爆震管的凹腔可以有多种形式，如尖锥凹腔，椭圆凹腔等，满足激波聚焦的截面形式即可。Furthermore, the cavity of the detonation tube may have various forms, such as a pointed cone cavity, an elliptical cavity, etc., as long as the cross-sectional form satisfies the shock wave focusing.
进一步地，旋转射流盘上还包括爆震加力震荡管，爆震加力震荡管为可选部件。起爆爆震管与旋转射流盘上的排气通道及爆震加力震荡管彼此接通后构成一个联通的爆震通道Furthermore, the rotating jet disk also includes a detonation boosting shock tube, which is an optional component. The detonation tube, the exhaust channel on the rotating jet disk and the detonation boosting shock tube are connected to each other to form a connected detonation channel.
进一步地，射流腔的高度和排气通道的高度与起爆爆震管和爆震加力震荡管的高度相同。Furthermore, the height of the jet cavity and the height of the exhaust passage are the same as the height of the detonation tube and the detonation afterburner shock tube.
进一步地，爆震加力震荡管与起爆爆震管采用相同方式布置，其根数相同。Furthermore, the detonation boost shock tubes and the detonation initiation detonation tubes are arranged in the same manner and have the same number.
进一步地，起爆爆震管和爆震加力震荡管均布置有连续燃料喷口，喷射方向均朝向起爆爆震管凹腔封闭端。Furthermore, both the detonation tube and the detonation booster shock tube are provided with continuous fuel nozzles, and the injection directions are all toward the closed end of the detonation tube cavity.
进一步地，旋转射流盘上过流腔高度要大于起爆爆震管通道高度，便于引射来流空气进入起爆爆震管，为下一个周期的爆震燃烧创造条件。Furthermore, the height of the flow cavity on the rotating jet disk should be greater than the height of the detonation tube channel, so as to facilitate the introduction of incoming air into the detonation tube and create conditions for the next cycle of detonation combustion.
进一步地，起爆爆震管长度与其上所布置燃料喷射雾化时的雾化距离相当，便于在起爆爆震管封闭凹腔处形成良好的雾化液体燃料液滴和空气的可燃混气，保证爆震点火成功。Furthermore, the length of the detonation tube is equivalent to the atomization distance of the fuel spray atomization arranged thereon, which facilitates the formation of a good combustible mixture of atomized liquid fuel droplets and air in the closed cavity of the detonation tube, thereby ensuring successful detonation ignition.
通过本发明所构思的以上技术方案，与现有技术相比，本发明提供的一种逆流式旋转气波点火爆震燃烧装置，依靠射流腔与起爆爆震管开口端周期性接通或闭合产生脉冲激波，利用凹腔激波反射聚焦点火原理，克服了连续超声速聚心射流碰撞产生的激波聚焦衰减问题和高频不稳定激波聚焦点火问题，具有如下优点：Through the above technical scheme conceived by the present invention, compared with the prior art, the present invention provides a counter-current rotating gas wave ignition detonation combustion device, which relies on the periodic connection or closing of the jet cavity and the opening end of the detonation tube to generate a pulse shock wave, and utilizes the concave cavity shock wave reflection focusing ignition principle to overcome the shock wave focusing attenuation problem and high-frequency unstable shock wave focusing ignition problem caused by continuous supersonic converging jet collision, and has the following advantages:
第一，改变旋转射流盘的旋转速度主动控制激波聚焦频率，即爆震燃烧装置的工作频率，突破使用传统点火器提高脉冲爆震发动机工作频率的技术界限；First, the rotation speed of the rotating jet disk is changed to actively control the shock wave focusing frequency, that is, the operating frequency of the detonation combustion device, breaking through the technical limit of using traditional igniters to increase the operating frequency of pulse detonation engines;
第二，利用运动激波的增压特性，合理回收进气来流压力能，改善燃油的雾化蒸发和掺混特性，易于形成可燃混气，可以有效降低爆震起爆的点火能量；Second, by utilizing the boost characteristics of the moving shock wave, the pressure energy of the incoming air flow can be reasonably recovered, the atomization, evaporation and mixing characteristics of the fuel can be improved, and a combustible mixture can be easily formed, which can effectively reduce the ignition energy of the knock initiation;
第三，采用凹腔激波聚焦点火原理，避免传统的火花塞或连续点火方式的固有缺点，大幅降低了爆震燃烧装置结构的复杂性；Third, the concave cavity shock wave focusing ignition principle is adopted to avoid the inherent shortcomings of traditional spark plugs or continuous ignition methods, greatly reducing the complexity of the detonation combustion device structure;
第四，采用轴流进气道进气方式，与传统发动机进气方式保持一致，可方便向传统航空发动机燃烧室移植。Fourth, the axial flow inlet duct air intake method is adopted, which is consistent with the traditional engine air intake method and can be easily transplanted to the combustion chamber of the traditional aircraft engine.
综上所述，本发明具有脉冲爆震燃烧稳定工作频率的主动控制、燃烧装置功率可调、减小燃烧室结构质量和便于向传统航空发动机燃烧室移植的特点，适应了脉冲爆震发动机发展的迫切需要。In summary, the present invention has the characteristics of active control of stable operating frequency of pulse detonation combustion, adjustable power of combustion device, reduced structural mass of combustion chamber and easy transplantation to traditional aircraft engine combustion chamber, which meets the urgent needs of the development of pulse detonation engines.
附图说明BRIEF DESCRIPTION OF THE DRAWINGS
图1是本发明提供的一种逆流式旋转气波点火爆震燃烧装置的结构示意图；FIG1 is a schematic structural diagram of a counter-flow rotating gas wave ignition detonation combustion device provided by the present invention;
图2是旋转射流盘结构示意图；Fig. 2 is a schematic diagram of the structure of a rotating jet disk;
图3是起爆爆震管结构效果图；FIG3 is a structural effect diagram of the detonation tube;
图4是爆震加力震荡管结构效果图；FIG4 is a structural effect diagram of a detonation afterburner shock tube;
附图标记：Reference numerals:
1-进气喷管，2-第一固定环，3-起爆燃料雾化喷头，4-爆震燃烧装置圆桶外壳，5-发动机定位盘，6-加力燃料雾化喷头，7-电动机，8-旋转轴，9-射流腔，10-第三固定环，11-爆震加力震荡管，12-旋转射流盘，13-第二固定环，14-起爆爆震管，15-激波聚焦凹腔，16-过流腔，17-轴孔，18-排气通道，19-连通孔，20-进气孔。1-intake nozzle, 2-first fixed ring, 3-initiation fuel atomizing nozzle, 4-drum shell of detonation combustion device, 5-engine positioning plate, 6-afterburner fuel atomizing nozzle, 7-motor, 8-rotating shaft, 9-jet cavity, 10-third fixed ring, 11-detonation afterburner shock tube, 12-rotating jet disk, 13-second fixed ring, 14-initiation detonation tube, 15-shock wave focusing cavity, 16-flow cavity, 17-axial hole, 18-exhaust channel, 19-connecting hole, 20-intake hole.
具体实施方式Detailed ways
为了使本发明的目的、技术方案及优点更加清楚明白，以下结合附图及实施例，对本发明进行进一步详细说明。应当理解，此处所描述的具体实施例仅仅用以解释本发明，并不用于限定本发明。此外，下面所描述的本发明各个实施方式中所涉及到的技术特征只要彼此之间不构成冲突就可以相互组合。In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.
激波在凹腔壁面的聚焦反射可以产生局部的高温高压区域，对可燃预混气而言，在适当的条件下可诱导着火甚至爆轰。这一过程是一个典型的非定常过程，稳定点火成功的基本前提是爆震燃烧的每个周期内都能产生激波聚焦过程。这决定了爆震管内必须周期性的产生脉冲激波。本发明的核心技术是采用旋转射流盘通过旋转运动使射流腔周期性的与起爆爆震管开口端接通和闭合，在爆震管接通的瞬间产生脉冲激波，保证起爆爆震管的封闭端凹腔发生激波聚焦现象的非定常激波稳定可靠的发生，最终实现激波聚焦点火的可控与稳定点火。The focused reflection of the shock wave on the wall of the cavity can produce a local high temperature and high pressure area. For the combustible premixed gas, it can induce ignition or even detonation under appropriate conditions. This process is a typical unsteady process. The basic premise for successful stable ignition is that the shock wave focusing process can be generated in each cycle of the detonation combustion. This determines that pulse shock waves must be generated periodically in the detonation tube. The core technology of the present invention is to use a rotating jet disk to periodically connect and close the jet cavity with the open end of the detonation tube through rotational motion, and generate a pulse shock wave at the moment the detonation tube is connected, so as to ensure the stable and reliable occurrence of the unsteady shock wave of the shock wave focusing phenomenon in the closed end cavity of the detonation tube, and finally realize the controllable and stable ignition of shock wave focusing ignition.
结合图1和图2，本发明提供的一种逆流式旋转气波点火爆震燃烧装置包括进气喷管1、起爆爆震管14、旋转射流盘12、爆震加力震荡管11和电动机7，并依次同轴布置组成。1 and 2 , a counter-flow rotating gas wave ignition detonation combustion device provided by the present invention includes an air intake nozzle 1, an initiation detonation tube 14, a rotating jet disk 12, a detonation afterburner oscillation tube 11 and a motor 7, which are coaxially arranged in sequence.
所述的进气喷管1和爆震燃烧装置圆桶外壳4一起构成爆震燃烧装置的外壳整体，在其内部起爆爆震管14和爆震加力震荡管11同轴布置，并分别依靠第一固定环2、第二固定环13和第三固定环10静止布置在爆震燃烧装置外壳整体内部；所述起爆爆震管14结构示意图如图3所示，其一端采用一凹腔结构进行封闭，另一端为开口布置，将起爆爆震管14周期性的绕轴布置构成环形起爆爆震室；所述爆震加力震荡室11结构示意图如图4所示，其震荡管两端均为开口布置，同样周期性的绕轴布置构成环形爆震加力燃烧室；所述起爆爆震管14和爆震加力震荡管11的截面高度相同，通过排气通道18可以构成光滑连通的爆震管；所述旋转射流盘12布置在静止的起爆爆震管14和爆震加力震荡管11之间，其上布置有射流腔9、排气通道18和过流腔16，可以周期性的布置多个；所述射流腔9为一朝向起爆爆震管14开口的半封闭腔室，其截面高度与起爆爆震管14截面高度相等；所述排气通道18为一通孔结构，其通孔高度也与起爆爆震管14截面高度相等；所述过流腔16为一台阶状结构，台阶高度要大于起爆爆震管14的截面高度，以此形成一个过流区域；所述旋转射流盘12朝向燃烧装置进气口侧布置有进气孔20，进气孔20经旋转射流盘12内部的连通通道与连通孔19相连，连通孔19与射流腔9相连；所述旋转射流盘12经旋转轴8与电动机7，由电动机7驱动旋转；所述旋转轴8由发动机定位盘5进行固定安装。The air intake nozzle 1 and the cylindrical shell 4 of the detonation combustion device together constitute the shell of the detonation combustion device as a whole, and the detonation tube 14 and the detonation afterburner shock tube 11 are coaxially arranged inside the detonation combustion device, and are respectively statically arranged inside the shell of the detonation combustion device as a whole by relying on the first fixing ring 2, the second fixing ring 13 and the third fixing ring 10; the structural schematic diagram of the detonation tube 14 is shown in Figure 3, one end of which is closed by a concave cavity structure, and the other end is open, and the detonation tube 14 is periodically arranged around the axis to form an annular detonation chamber; the structural schematic diagram of the detonation afterburner shock chamber 11 is shown in Figure 4, and both ends of the shock tube are open, and the same periodic arrangement around the axis forms an annular detonation afterburner combustion chamber; the cross-sectional heights of the detonation tube 14 and the detonation afterburner shock tube 11 are the same, and a smoothly connected detonation tube can be formed through the exhaust channel 18; the rotating jet disk 12 is arranged on the stationary detonation tube Between the shock tube 14 and the detonation boost shock tube 11, a jet chamber 9, an exhaust channel 18 and a flow chamber 16 are arranged thereon, and multiple ones can be arranged periodically; the jet chamber 9 is a semi-enclosed chamber opening toward the detonation shock tube 14, and its cross-sectional height is equal to the cross-sectional height of the detonation shock tube 14; the exhaust channel 18 is a through-hole structure, and its through-hole height is also equal to the cross-sectional height of the detonation shock tube 14; the flow chamber 16 is a stepped structure, and the step height is greater than the cross-sectional height of the detonation shock tube 14, thereby forming a flow area; the rotating jet disk 12 is arranged with an air inlet 20 on the side facing the air inlet of the combustion device, and the air inlet 20 is connected to the connecting hole 19 through the connecting channel inside the rotating jet disk 12, and the connecting hole 19 is connected to the jet chamber 9; the rotating jet disk 12 is connected to the motor 7 through the rotating shaft 8, and is driven to rotate by the motor 7; the rotating shaft 8 is fixedly installed by the engine positioning disk 5.
当本发明提供的一种逆流式旋转气波点火爆震燃烧装置开始工作时，电动机7旋转驱动旋转射流盘12同轴转动。进气喷管1吸入飞行器飞行过程中冲压形成的高压空气，高压空气经减速扩压后经进气孔20流过连通孔19进入射流腔9。在旋转射流盘12的转动下，当射流腔9转动到与起爆爆震管14的开口端接同时，增压后的高压空气会逆向射流喷入起爆爆震管14，同时形成脉冲激波往起爆爆震管14的凹腔封闭端传播。当运行的脉冲激波传播到起爆爆震管14的凹腔封闭端，在凹腔壁面的反射聚焦下产生一激波聚焦点，瞬间产生一个高温高压区。起爆燃料雾化喷头3在起爆爆震管内逆向喷射雾化液体燃料，经过一定雾化距离后，在起爆爆震管14的凹腔封闭端与吸入的空气混合成可燃混气，在前述激波聚焦产生的高温高压区作用下点火起爆。点火起爆成功后，爆震波将在凹腔封闭端反射下向起爆爆震管14下游传播。当爆震波向下游传播到起爆爆震管14的开口端时，排气通道18在旋转射流盘12的旋转下与起爆爆震管14开口端接通，使爆震波得以继续向下游的爆震加力震荡管11传播。若需增加爆震燃烧装置的输出功率，加力燃料雾化喷头6在爆震加力震荡管11内逆流喷射雾化额外的燃料，在上游传播过来的爆震波作用下点火起爆提高燃烧装置的输出功率。起爆爆震管14内的高温高压燃气排空后，过流腔16在旋转射流盘12的旋转下与起爆爆震管14的开口端接通，通过过流腔16的开口结构使起爆爆震管14与进气喷管1后的气腔连通，在起爆爆震管14内膨胀波的作用下吸入新鲜空气，为下一周期的爆震燃烧提供氧化剂。以上过程周而复始，使爆震燃烧装置的每根起爆爆震管14点火起爆并产生爆震波经爆震加力震荡管11排出，从而产生正推力。When the countercurrent rotating gas wave ignition detonation combustion device provided by the present invention starts to work, the motor 7 rotates to drive the rotating jet disk 12 to rotate coaxially. The air intake nozzle 1 inhales the high-pressure air formed by the ramming during the flight of the aircraft. After deceleration and expansion, the high-pressure air flows through the connecting hole 19 through the air intake hole 20 and enters the jet cavity 9. Under the rotation of the rotating jet disk 12, when the jet cavity 9 rotates to connect with the opening end of the detonation detonation tube 14, the pressurized high-pressure air will be reversely jetted into the detonation detonation tube 14, and a pulse shock wave will be formed to propagate toward the closed end of the concave cavity of the detonation detonation tube 14. When the running pulse shock wave propagates to the closed end of the concave cavity of the detonation detonation tube 14, a shock wave focus point is generated under the reflection and focusing of the concave cavity wall, and a high temperature and high pressure area is instantly generated. The detonation fuel atomizing nozzle 3 sprays atomized liquid fuel in the detonation tube in reverse direction, and after a certain atomization distance, it is mixed with the inhaled air at the closed end of the concave cavity of the detonation tube 14 to form a combustible mixed gas, and ignites and detonates under the action of the high temperature and high pressure zone generated by the aforementioned shock wave focusing. After the ignition and detonation is successful, the detonation wave will propagate downstream of the detonation tube 14 under the reflection of the closed end of the concave cavity. When the detonation wave propagates downstream to the open end of the detonation tube 14, the exhaust channel 18 is connected to the open end of the detonation tube 14 under the rotation of the rotating jet disk 12, so that the detonation wave can continue to propagate to the downstream detonation booster shock tube 11. If it is necessary to increase the output power of the detonation combustion device, the booster fuel atomizing nozzle 6 sprays and atomizes additional fuel in the detonation booster shock tube 11 in reverse flow, and ignites and detonates under the action of the detonation wave propagating from the upstream to increase the output power of the combustion device. After the high-temperature and high-pressure gas in the detonation tube 14 is emptied, the flow cavity 16 is connected to the open end of the detonation tube 14 under the rotation of the rotating jet disk 12, and the detonation tube 14 is connected to the air cavity behind the intake nozzle 1 through the opening structure of the flow cavity 16, and fresh air is inhaled under the action of the expansion wave in the detonation tube 14 to provide oxidant for the next cycle of detonation combustion. The above process is repeated, so that each detonation tube 14 of the detonation combustion device is ignited and detonated, and a detonation wave is generated and discharged through the detonation afterburner oscillation tube 11, thereby generating positive thrust.
由上述工作过程可知，本发明提供的一种逆流式旋转气波点火爆震燃烧装置利用起爆爆震管开口端与射流腔的周期性接通与闭合稳定产生脉冲激波，脉冲激波产生的频率和强度可以灵活的由旋转射流盘的转速来调节，结构简单，也大幅提高了爆震燃烧室直接点火起爆的可靠性。本发明采用轴向气流入口，与传统发动机吸气方向一致，可以很好地移植到现有的发动机燃烧室设计中。It can be seen from the above working process that the counter-current rotating gas wave ignition detonation combustion device provided by the present invention utilizes the periodic connection and closure of the opening end of the detonation tube and the jet cavity to stably generate pulse shock waves. The frequency and intensity of the pulse shock waves can be flexibly adjusted by the rotation speed of the rotating jet disk. The structure is simple and the reliability of direct ignition and detonation of the detonation combustion chamber is greatly improved. The present invention adopts an axial airflow inlet, which is consistent with the air intake direction of the traditional engine and can be well transplanted into the existing engine combustion chamber design.
本领域的技术人员容易理解，以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本发明的保护范围之内。It will be easily understood by those skilled in the art that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
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