CN101806260B - Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof - Google Patents
Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof Download PDFInfo
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Abstract
本发明公开了一种多管并联脉冲爆震燃烧室及其点火起爆方法，包括点火起爆装置及爆震室入口和出口分别在同一平面的多管轴线平行并联爆震燃烧室，每个爆震室包括爆震室入口、起爆射流入口、起爆射流出口和爆震室出口，每相邻的两个爆震室起爆射流入口分别在爆震室上游或下游，通过长度相等的射流传播管连接，点火起爆装置安装在任一头部起爆射流点火爆震室。工作时，点火起爆装置工作，点燃该爆震室中的可燃混气并逐级传递给下一个爆震室，形成循环。本发明使脉冲爆震燃烧室附件系统更加简化，可以在不改动发动机整体结构情况下直接用于现有常见多管并联脉冲爆震燃烧室，解决现有多管脉冲爆震燃烧室点火起爆问题。
The invention discloses a multi-tube parallel pulse detonation combustor and an ignition and detonation method thereof, comprising an ignition and detonation device and a multi-tube axis-parallel parallel detonation combustor in which the inlet and outlet of the detonation chamber are respectively on the same plane, each detonation The chamber includes the detonation chamber inlet, the detonation jet inlet, the detonation jet outlet and the detonation chamber outlet. The detonation jet inlets of two adjacent detonation chambers are respectively upstream or downstream of the detonation chamber, and are connected by jet propagation pipes of equal length. The ignition and detonation device is installed in any head detonation jet ignition detonation chamber. When working, the ignition and detonation device works, igniting the combustible gas mixture in the detonation chamber and passing it to the next detonation chamber step by step, forming a cycle. The invention simplifies the accessory system of the pulse detonation combustion chamber, can be directly used in the existing common multi-tube parallel pulse detonation combustion chamber without changing the overall structure of the engine, and solves the problem of ignition and detonation of the existing multi-tube pulse detonation combustion chamber .
Description
Technical field
The present invention relates to technical field of engines, especially a kind of firing chamber of pulse-knocking engine and ignition and detonation method thereof.
Background technique
The discovery of detonation wave can trace back to for 18 end of the centurys the earliest; Than deflagration wave, the pinking velocity of wave propagation can reach a few km per seconds, produces high gaseous-pressure (greater than 15 to 55 barometric pressure) and fuel gas temperature (greater than 2800K) simultaneously; Theoretical according to traditional C J; The CJ point of detonation is the smallest point that entropy increases, and this means with the knocking combustion to be that the propulsion system on basis will have advantage very much on the efficiency of cycle, therefore from last century the forties begin; Detonation engine is competitively studied by each mechanism; Various types of detonation engines have appearred in the exploratory development stage in six more than ten years, and the focus of current this area research mainly concentrates on based on pulse-knocking circuit pulse-knocking engine.
Because pulse-knocking engine utilization intermittently knocking combustion produces thrust; Therefore the incendiary source that needs one-period for each detonation combustor usually; The incendiary source of current main employing has jet igniting that sparkover, transient state plasma ignition, electrical spark trigger and pre-explosion pipe or the like; Its shortcoming is exactly that each detonation chamber needs independently ignition system and control system, thereby brings the complexity of system.
For overcoming the shortcoming that pulse-knocking engine seriously relies on the highpowerpulse igniting unit; The USAF laboratory has proposed one of them detonation combustor afterbody detonation wave, through the ignition and detonation method of other detonation combustor heads to be lighted a fire of flame tube interconnector introducing, connects through multitube; The final continuous ignition and detonation of realizing multitube; See from its testing installation, because its multitube detonation chamber ingress on same plane, therefore just needs long flame tube interconnector; Simultaneously for reaching the purpose that passes flame, how filling can quick-fried mixture also be technological difficulties in flame tube interconnector.The Chinese patent of application number 200710018897.0 has proposed a kind ofly to avoid adopting a plurality of detonation chambers of longer flame tube interconnector to propagate the knocking combustion cell structure of pipe series connection from beginning to end through jet based on this ignition and detonation method; The jet exit that detonates that is one of them detonation chamber outlet upper reaches links to each other with the jet inlet that detonates in next detonation chamber inlet downstream; The final multitube annular-shaped combustor that forms; So its single detonation chamber inlet is along the tangent to periphery direction; With the circumferential axis direction very big angle of yaw is arranged, each head entrance of detonation chamber is along circle distribution simultaneously.When the air incoming flow is axial direction (this is that present traditional aeroengine combustor buring chamber inlet air comes flow path direction); These shortcomings cause motor must adopt extra air conducting and part flow arrangement to guide to each detonation chamber inlet, thereby are not easy to the transplanting of detonation combustor to traditional aeroengine combustor buring chamber; Owing at this process air flow direction bigger deflection is arranged, pitot loss also will increase simultaneously.
Summary of the invention
To propagate pipe long or multitube detonation chamber entrance disperses, each detonation chamber Way in is with engine axis direction angle of yaw is excessive, pitot loss reaches deficiencies such as inconvenient transplanting greatly in order to overcome the existing technology jet; The present invention proposes a kind of suitable multitube parallel pulse detonation combustor and ignition and detonation method thereof; Can solve above shortcoming based on this, thus main combustion chamber, the tail pipe burner of the existing gas turbine of being more convenient for pulse detonation combustor is substituted.
The technical solution adopted for the present invention to solve the technical problems is: comprise the detonation chamber 2 that starts priming device 6 and a plurality of parallel connections, each detonation chamber 2 comprises detonation chamber inlet 1, the jet inlet 4 that detonates, detonate jet exit 5 and detonation chamber outlet 3; Detonation chamber inlet 1 is positioned at detonation chamber 2 two ends with detonation chamber outlet 3, and detonation chamber inlet 1 comes the upper reaches of flow path direction in air inlet, and detonation chamber outlet 3 is in the downstream of detonation chamber air-flow; The jet inlet 4 that detonates is positioned at detonation chamber 2 two ends with the jet exit 5 that detonates; With each detonation chamber 2 by different at the detonation chamber relative position of detonate jet inlet 4 and the jet exit 5 that detonates; Detonation chamber 2 can be divided into two kinds, i.e. head jet spark knock chamber 2a and the afterbody jet spark knock chamber 2b that detonates that detonates.For the head jet spark knock chamber 2a that detonates; The jet inlet 4 that detonates is positioned at detonation chamber and enters the mouth 1～2 times in 1 downstream to this detonation chamber 2a equivalent diameter distance; The jet exit 5 that detonates is positioned at detonation chamber and exports 3 upper reaches, and the jet exit 5 that detonates links to each other with the jet inlet 4 that detonates of the detonation chamber 2b of adjacent employing afterbody pinking jet igniting; The jet inlet 4 that detonates of afterbody pinking jet spark knock chamber 2b is positioned at detonation chamber and exports 1～2 times at 3 upper reaches to this detonation chamber 2b equivalent diameter distance; The jet exit 5 that detonates is positioned at detonation chamber 1 downstream that enter the mouth, and links to each other with the detonate jet inlet 4 that detonates of detonation chamber 2a of jet igniting of adjacent employing head; By that analogy; After a plurality of detonation chambers connect; The jet inlet that detonates of the detonate jet exit 5 and the initial detonation chamber of last detonation chamber is connected, and joins end to end, and has constituted a plurality of detonation chamber inlets 1 jointly and has exported 3 respectively at conplane multitube parallel axes parallel connection detonation combustor with a plurality of detonation chambers; Detonate jet exit 5 and detonate between the jet inlet 4 and to propagate pipe 8 through jet and connect, the jet that connects between per two adjacent detonation chambers is propagated the equal in length of pipe 8.Start priming device 6 and be installed in wherein any one of multitube parallel detonation combustor and adopt the detonate detonation chamber of detonation chamber 2a of jet igniting of head to enter the mouth 1～2 times in 1 downstream, and stagger with the jet inlet 4 that detonates of this detonation chamber to this detonation chamber equivalent diameter distance.
As first kind of preferred version of the present invention; When the detonation chamber number of one group of parallel connection when being N times of certain integer M; 1 downstream that can enter the mouth at the detonation chamber of N detonation chamber of M-1 the detonation chamber of being separated by are installed and are started priming device; During startup, N the startup priming device 6 that detonate simultaneously can have N detonation wave catching up with each other all the time.Jet inlet 4 and the length between the jet exit 5 of detonating add that a jet propagates the length of pipe 8 and be L if arbitrary detonation chamber detonates; And make that V is the maximum detonation wave propagation speed under all operating modes of detonation combustor; Make that T is a pinking operation cycle, then M should be greater than VT/L.
As second kind of preferred version of the present invention; When a plurality of detonation chambers along coming flow path direction when the disc parallel connection is uniformly distributed with; The detonation chamber number of supposing parallel connection is N a times of certain integer M; Be that the center is divided into N covering of the fan with its disc then with this disc center of circle; Along coming to comprise in each covering of the fan of flow path direction M parallelly connected detonation chamber, finally come flow path direction that a plurality of detonation chambers are divided into the N group of arranging identical along detonation combustor simultaneously, every group comprises M detonation chamber; Start priming device 6 and be installed in outermost any one of the disc that is positioned at the multitube parallel pulse detonation combustor in every group of detonation chamber and adopt the detonate detonation chamber 2a of jet igniting of head, starting the mounting point of priming device 6 in every group of detonation chamber simultaneously should be identical.
As the third preferred version of the present invention; It is two-layer inside and outside the pulse detonation combustor that the multitube parallel ring is distributed is divided into; The detonation chamber number that internal and external layer comprised is identical; Outer by adopting the detonate detonation chamber 2a of jet igniting of head to form, internal layer is by adopting the detonate detonation chamber 2b of jet igniting of afterbody to form, and startup priming device 6 only is installed in outer detonation chamber 2a.When a plurality of startup priming device 6, it should circumferentially evenly be installed at outer detonation chamber.
As the 4th kind of preferred version of the present invention, for the detonate detonation chamber 2b of jet igniting of afterbody, if the firing chamber is oxygenant with the air, the obstruction that then when the jet that detonates is injected its afterbody, should guarantee detonation chamber outlet 3 is than greater than 0.2.
The present invention also provides a kind of ignition and detonation method of said detonation combustor; May further comprise the steps: when all detonation chambers inlet 1 all has when can quick-fried mixed gas being full of whole detonation chamber 2 with the same terms; Start priming device 6 work; Form the detonation wave of propagates down stream, detonation wave propagation is behind the jet exit 5 that detonates, and most of detonation wave is discharged through detonation chamber outlet 3; Part detonation wave propagates into next the detonate jet inlet 4 that detonates of detonation chamber 2b of jet igniting of afterbody that adopts through the jet exit 5 that detonates; Thereby in detonation chamber 2b, form detonation wave fast, propagate is to the jet exit 5 that detonates rapidly in this detonation chamber 2b for detonation wave, and detonation chamber inlet 1 is closed at this moment; Part detonation wave propagates into next the detonate jet inlet 4 that detonates of detonation chamber 2a of jet igniting of head, the so continuous downstream delivery of adopting through the jet exit 5 that detonates.For single detonation chamber; No matter initial detonation wave is upstream or propagates down stream, finally this compressional wave will export 3 from detonation chamber and discharge and propagate into low pressure parts or the external environment that links to each other with the detonation chamber downstream, so form one extensional wave from detonation chamber outlet 3 oppositely to 1 propagation of detonation chamber inlet; Thereby the pressure in the detonation chamber is descended; When equal pressure drops to stuffing pressure, can pour detonation chamber inlet 1 again by quick-fried mixed gas, begin the filling process of this detonation chamber new round.Pass to when detonation wave to have got back to again behind the jet exit 5 that detonates of last detonation chamber the detonation chamber 2a that starts priming device 6 is housed; Be equipped with this moment the detonation chamber 2a that starts priming device 6 accomplished toxic emission with can quick-fried mixed gas filling process; The pinking jet forms detonation wave rapidly after importing detonation chamber 2a into, starts priming device and no longer works.
Combustion wave can not propagated to propagate the detonation chamber 2b that pipe 8 links to each other through the jet of this detonation chamber 2a upper reaches one side when preventing initial start priming device 6 work; The jet inlet 4 that detonates in that the detonation chamber 2a that starts priming device 6 is housed is installed startup valve 7; When starting priming device 6 work; Start valve 7 and close, wait to start valve 7 upper reaches detonation chamber 2b and form and start valve 7 behind the detonation wave and open, and keep normally open during proper functioning always in the firing chamber.
The invention has the beneficial effects as follows: ignition and detonation method at first of the present invention is alternately utilized another detonation chamber that detonates of the detonation wave ignition in the detonation chamber; Make detonating of detonation wave approach direct initiation; And do not need extra high energy high-frequency impulse ignition system, thereby the pulse detonation combustor accessory system is simplified more; On the other hand; At the tissue of jet that detonates; Each detonation chamber in the multi-pipe impulse detonation combustor is divided into head jet detonate two types of the detonation chamber 2b of detonation chamber 2a and afterbody jet that detonate; Through therebetween alternately jet detonate, make this ignition and detonation method directly to be used for existing common multitube parallel pulse detonation combustor under the motor overall structure situation not changing, solve existing multi-pipe impulse detonation combustor ignition and detonation problem.
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Description of drawings
Fig. 1 is a start-up course schematic representation of the present invention;
Fig. 2 is an ignition and detonation working procedure schematic representation of the present invention, working procedure schematic representation when wherein Fig. 2 .1 detonates the jet igniting for the detonation chamber head, working procedure schematic representation when Fig. 2 .2 detonates the jet igniting for the detonation chamber afterbody.
Fig. 3 is the technological schematic representation of the embodiment of the invention 1, and wherein Fig. 3 .1 is a multitube detonation combustor structural representation, the technological schematic representation of Fig. 3 .2 when being observed downstream by the multitube detonation combustor upper reaches;
Technological schematic representation when Fig. 4 is being seen downstream by the multitube detonation combustor upper reaches of the embodiment of the invention 2;
Technological schematic representation when Fig. 5 is being seen downstream by the multitube detonation combustor upper reaches of the embodiment of the invention 3.
Among the figure, 1-detonation chamber inlet, 2-detonation chamber, the 2a-head jet spark knock chamber of detonating; The 2b-afterbody jet spark knock chamber of detonating, the outlet of 3-detonation chamber, the 4-jet inlet that detonates, the 5-jet exit that detonates; 6-starts priming device, and 7-starts valve, and the 8-jet is propagated pipe; 9-left lateral extensional wave, 10-left lateral detonation wave, 11-incident detonation wave; 12-right lateral detonation wave, the 13-jet that detonates is propagated the jet direction in the pipe at detonation chamber inlet downstream part jet, and the 14-jet that detonates is propagated the jet direction in managing at detonation chamber outlet upstream end jet.
Embodiment
Embodiment 1: with reference to Fig. 3; Comprise 1 startup priming device 6 and six parallelly connected detonation chambers 2; Parallel connection detonation chamber 2 is propagated the six pipe parallel pulse detonation combustors that pipe 8 connects to form circle distribution through jet; Each detonation chamber 2 comprises detonation chamber inlet 1, detonation chamber outlet 3 and jet propagation pipe 8, and jet is propagated the jet inlet 4 that detonates that pipe comprises the detonate jet exit 5 and the next stage detonation chamber of the upper level detonation chamber that links together; Detonation chamber inlet 1 is positioned at detonation chamber 2 two ends with detonation chamber outlet 3, and detonation chamber inlet 1 is at the upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber 2 two ends with the jet exit 5 that detonates; The detonate jet inlet 4 and jet exit 5 relative position different in detonation chamber of detonating according to each detonation chamber 2; Detonation chamber 2 can be divided into two kinds, i.e. detonate jet spark knock chamber 2a and afterbody pinking jet spark knock chamber 2b of head; Start detonation chamber that priming device 6 is installed in one of them detonation chamber 2 of the parallelly connected detonation combustor of six pipes and enter the mouth 1～2 times in 1 downstream to this detonation chamber equivalent diameter distance, this detonation chamber is exactly to adopt the detonate detonation chamber 2a of jet igniting of head accordingly.For the head jet spark knock chamber 2a that detonates; Its detonation chamber inlet 1 is one side at the detonation chamber air-flow upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber and enters the mouth 1～2 times in 1 downstream to this detonation chamber 2a equivalent diameter distance; Detonation chamber outlet 3 is in detonation chamber airflow downstream one side, and the jet exit 5 that detonates is positioned at detonation chamber and exports 3 upper reaches, and the jet exit 5 that detonates links to each other with the jet inlet 4 that detonates of the detonation chamber 2b of adjacent employing afterbody pinking jet igniting; The detonation chamber outlet 3 of afterbody pinking jet spark knock chamber 2b is in detonation chamber airflow downstream one side; The jet inlet 4 that detonates is positioned at detonation chamber and exports 1～2 times at 3 upper reaches to this detonation chamber 2b equivalent diameter distance; The jet exit 5 that detonates is positioned at detonation chamber 1 downstream that enter the mouth, and links to each other with the detonate jet inlet 4 that detonates of detonation chamber 2a of jet igniting of adjacent employing head; By that analogy; After six detonation chambers connect; The jet inlet that detonates of the detonate jet exit 5 and the initial detonation chamber of last detonation chamber is connected; Join end to end, constituted a plurality of detonation chamber inlets 1 jointly and exported 3 respectively on same plane with a plurality of detonation chambers, six six tube's axis parallel connection detonation combustors that detonation chamber S type links to each other.After starting priming device 6 work among Fig. 3; In the detonation chamber 2a of its place, form the detonation wave of propagates down stream; Detonation wave propagation is during to this detonation chamber outlet upper reaches, and a part of detonation wave is propagated pipe 8 through the jet of afterbody and passed to the adjacent detonation chamber 2b outlet upper reaches, and and then in detonation chamber 2b, produce the detonation wave of propagate; It is propagated pipe 8 through the jet at the upper reaches again and passes to the adjacent next detonation chamber 2a inlet upper reaches subsequently; Like this detonation wave jet propagate that the effect of pipe continues down in the indoor propagation of knocking combustion, see the counterclockwise igniting sequential of its formation shown in Fig. 3 .1 direction of arrow downstream from the detonation combustor upper reaches.
Embodiment 2: with reference to Fig. 4; Comprise six startup priming devices 6 and 36 parallelly connected detonation chambers 2 that are uniformly distributed with along incoming flow direction disc; At first along coming flow path direction to depend on shown in the figure it is divided into six covering of the fans, each covering of the fan comprises six parallelly connected detonation chambers, finally comes flow path direction 36 detonation chambers to be divided into six groups that arrange identical along detonation combustor; Separate no annexation between group and group, every group comprises six detonation chambers.For each group; Parallel connection detonation chamber 2 is propagated pipe 8 through jet and is connected; Each detonation chamber 2 comprises detonation chamber inlet 1, detonation chamber outlet 3 and jet propagation pipe 8, and jet is propagated the jet inlet 4 that detonates that pipe comprises the detonate jet exit 5 and the next stage detonation chamber of the upper level detonation chamber that links together; Detonation chamber inlet 1 is positioned at detonation chamber 2 two ends with detonation chamber outlet 3, and detonation chamber inlet 1 is at the upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber 2 two ends with the jet exit 5 that detonates; The detonate jet inlet 4 and jet exit 5 relative position different in detonation chamber of detonating according to each detonation chamber 2; Detonation chamber 2 can be divided into two kinds, i.e. detonate jet spark knock chamber 2a and afterbody pinking jet spark knock chamber 2b of head; Start priming device 6 and be installed in this and organize in the parallelly connected detonation chamber one of them detonation chamber that is positioned at the detonation chamber 2 in the middle of the whole detonation combustor outermost surface and enter the mouth 1～2 times in 1 downstream to this detonation chamber equivalent diameter distance, this detonation chamber is exactly to adopt the detonate detonation chamber 2a of jet igniting of head accordingly.For the head jet spark knock chamber 2a that detonates; Its detonation chamber inlet 1 is one side at the detonation chamber air-flow upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber and enters the mouth 1～2 times in 1 downstream to this detonation chamber 2a equivalent diameter distance; Detonation chamber outlet 3 is in detonation chamber airflow downstream one side, and the jet exit 5 that detonates is positioned at detonation chamber and exports 3 upper reaches, and the jet exit 5 that detonates links to each other with the jet inlet 4 that detonates of the detonation chamber 2b of adjacent employing afterbody pinking jet igniting; The detonation chamber outlet 3 of afterbody pinking jet spark knock chamber 2b is in detonation chamber airflow downstream one side; The jet inlet 4 that detonates is positioned at detonation chamber and exports 1～2 times at 3 upper reaches to this detonation chamber 2b equivalent diameter distance; The jet exit 5 that detonates is positioned at detonation chamber 1 downstream that enter the mouth, and links to each other with the detonate jet inlet 4 that detonates of detonation chamber 2a of jet igniting of adjacent employing head; After six detonation chambers connect; The jet inlet that detonates of the detonate jet exit 5 and the initial detonation chamber of last detonation chamber is connected; Join end to end; Constitute one group of detonation chamber inlet 1 jointly and exported 3 respectively on same plane with a plurality of detonation chambers, six six tube's axis parallel connection detonation combustors that detonation chamber S type links to each other.Final every group of detonation chamber all has a startup priming device 6, for being implemented in the cycle period detonation wave through all detonation chambers in every group, finally obtains detonation chamber 2a as shown in Figure 4 and detonation chamber 2b and arranges accordingly; When detonation wave passed to detonation chamber 2b by detonation chamber 2a, two detonation chambers were propagated pipe at the outlet upper reaches through jet and are linked to each other, and when detonation wave passed to detonation chamber 2a by detonation chamber 2b, two detonation chambers were propagated pipe in the inlet downstream through jet and linked to each other.When all detonation chambers all have when can quick-fried mixed gas being full of whole detonation chamber 2 with the same terms; Six startup priming devices 6 are worked simultaneously; Form the detonation wave of propagates down stream at the detonation chamber 2a that belongs to separately; Detonation wave propagation is behind the detonation chamber 2a outlet upper reaches, and a part of detonation wave is propagated pipe through jet and propagated in the adjacent next detonation chamber 2b, thereby forms the detonation wave of propagate fast in detonation chamber 2b downstream; It is propagated pipe through the jet at the upper reaches again and passes to the adjacent next detonation chamber 2a inlet upper reaches subsequently; Like this detonation wave jet propagate the effect of pipe lasting down every group of pinking indoor propagation, see downstream that from the detonation combustor upper reaches six groups of detonation chambers all form the counterclockwise igniting sequential shown in Fig. 4 direction of arrow.
Embodiment 3: with reference to Fig. 5; Comprise three startup priming devices and 24 detonation chambers along the parallel connection of incoming flow bearing circle annular spread; Each detonation chamber 2 of each detonation chamber comprises detonation chamber inlet 1, detonation chamber outlet 3 and jet propagation pipe 8, and jet is propagated the jet inlet 4 that detonates that pipe 8 comprises the detonate jet exit 5 and the next stage detonation chamber of the upper level detonation chamber that links together; Detonation chamber inlet 1 is positioned at detonation chamber 2 two ends with detonation chamber outlet 3, and detonation chamber inlet 1 is at the upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber 2 two ends with the jet exit 5 that detonates; The detonate jet inlet 4 and jet exit 5 relative position different in detonation chamber of detonating according to each detonation chamber 2; Detonation chamber 2 can be divided into two kinds, i.e. detonate jet spark knock chamber 2a and afterbody pinking jet spark knock chamber 2b of head.With 24 pipe parallel pulse detonation combustors be divided into respectively comprise the similar number detonation chamber inside and outside two-layer; Simultaneously the detonation chamber in the skin adopts the head jet igniting of detonating; Detonation chamber in the internal layer adopts the afterbody jet igniting of detonating, and promptly skin comprises 12 detonation chamber 2a, and internal layer comprises 12 detonation chamber 2b; The detonation chamber interlaced arrangement of internal and external layer, make any detonation chamber 2a between the two adjacent detonation chamber 2b and any detonation chamber 2b between two adjacent detonation chamber 2a; With three startup priming devices 6 along circumference evenly distribute be installed in the pulse detonation combustor skin wherein three detonation chamber 2a enter the mouth 1～2 times in 1 downstream to this detonation chamber equivalent diameter distance outside; See downstream from the detonation combustor upper reaches, finally form detonation chamber 2a as shown in Figure 5 and detonation chamber 2b and arrange accordingly.For the head jet spark knock chamber 2a that detonates; Its detonation chamber inlet 1 is one side at the detonation chamber air-flow upper reaches; The jet inlet 4 that detonates is positioned at detonation chamber and enters the mouth 1～2 times in 1 downstream to this detonation chamber 2a equivalent diameter distance; Detonation chamber outlet 3 is in detonation chamber airflow downstream one side, and the jet exit 5 that detonates is positioned at detonation chamber and exports 3 upper reaches, and the jet inlet 4 that detonates of the detonation chamber 2b of the employing afterbody pinking jet igniting that the jet exit 5 that detonates is adjacent with internal layer links to each other; The detonation chamber outlet 3 of afterbody pinking jet spark knock chamber 2b is in detonation chamber airflow downstream one side; The jet inlet 4 that detonates is positioned at detonation chamber and exports 1～2 times at 3 upper reaches to this detonation chamber 2b equivalent diameter distance; The jet exit 5 that detonates is positioned at detonation chamber 1 downstream that enter the mouth, and the detonate jet inlet 4 that detonates of detonation chamber 2a of jet igniting of the employing head adjacent with skin links to each other; After 24 detonation chambers connect; The jet inlet that detonates of the detonate jet exit 5 and the initial detonation chamber of last detonation chamber is connected; Join end to end; Constituted one group of detonation chamber inlet 1 jointly and exported 3 respectively on same plane, 24 staggered multitube parallel axes parallel connection detonation combustors that link to each other of detonation chamber internal and external layer with a plurality of detonation chambers.When all detonation chambers all have when can quick-fried mixed gas being full of whole detonation chamber 2 with the same terms; Three startup priming devices 6 are worked simultaneously; Form the detonation wave of propagates down stream at the detonation chamber 2a that belongs to separately; Behind the detonation wave transmission detonation chamber 2a outlet upper reaches, a part of detonation wave is propagated pipe through jet and is propagated in the next detonation chamber 2b in internal layer adjacent place, thereby forms the detonation wave of propagate fast in detonation chamber 2b downstream; It is propagated pipe through the jet at the upper reaches again and passes to the adjacent outer next detonation chamber 2a inlet upper reaches subsequently; Like this detonation wave jet propagate that the effect of pipe continues down in the pinking indoor propagation, thereby form the situation that three detonation waves catch up with each other, final multitube detonation combustor forms and shown in Fig. 5 direction of arrow, reaches internal and external layer cross-ignition sequential counterclockwise.After this detonation combustor gets into stable circulation; No longer need outside ignition installation; Detonation wave is identical through the propagation time of internal layer two adjacent detonation chamber 2b through propagation time and the detonation wave of outer two adjacent detonation chamber 2a simultaneously, and then is convenient to the control of detonation combustor front end air intake valve.
Claims (6)
1. a multitube parallel pulse detonation combustor comprises the detonation chamber that starts priming device and a plurality of parallel connections, it is characterized in that: each detonation chamber comprises detonation chamber inlet, the jet inlet that detonates, detonate jet exit and detonation chamber outlet; Outlet is positioned at the detonation chamber two ends with detonation chamber for detonation chamber inlet, and the detonation chamber inlet comes the upper reaches of flow path direction, detonation chamber to export the downstream at the detonation chamber air-flow in air inlet; Detonation chamber is divided into head jet spark knock chamber and the afterbody jet spark knock chamber of detonating of detonating; The detonate jet inlet of jet spark knock chamber of head is positioned at 1～2 times in detonation chamber inlet downstream to this detonation chamber equivalent diameter distance; The jet exit that detonates is positioned at the detonation chamber outlet upper reaches, and the jet exit that detonates links to each other with the jet inlet that detonates of the detonation chamber of adjacent employing afterbody pinking jet igniting; The jet inlet that detonates of afterbody pinking jet spark knock chamber is positioned at 1～2 times at the detonation chamber outlet upper reaches to this detonation chamber equivalent diameter distance; The jet exit that detonates is positioned at detonation chamber inlet downstream, and links to each other with the detonate jet inlet of detonation chamber of jet igniting of adjacent employing head; By that analogy; After a plurality of detonation chambers connect; The jet inlet that detonates of the detonate jet exit and the initial detonation chamber of last detonation chamber is connected, and joins end to end, and has constituted a plurality of detonation chamber inlets and the outlet of a plurality of detonation chamber jointly respectively at conplane multitube parallel axes parallel connection detonation combustor; The jet exit that detonates is propagated pipe with the jet inlet that detonates by jet and is connected, and the jet that connects between per two adjacent detonation chambers is propagated length of tube and equated; Start priming device and be installed in wherein any one of multitube parallel detonation combustor and adopt head to detonate 1～2 times in the detonation chamber inlet downstream of detonation chamber of jet igniting, and stagger with the jet inlet that detonates of this detonation chamber to this detonation chamber equivalent diameter distance.
2. a kind of multitube parallel pulse detonation combustor according to claim 1 is characterized in that: described detonation chamber number is during for N times of certain integer M, at the detonation chamber inlet downstream installation startup priming device of N detonation chamber of M-1 the detonation chamber of being separated by; M is greater than VT/L, and wherein, detonate jet inlet and the length between the jet exit of detonating of arbitrary detonation chamber adds that a jet propagates the length of pipe and be L, and V is the maximum detonation wave propagation speed under all operating modes of detonation combustor, and T is a pinking operation cycle.
3. a kind of multitube parallel pulse detonation combustor according to claim 2; It is characterized in that: the N of described integer M doubly a detonation chamber along coming flow path direction when the disc parallel connection is uniformly distributed with; With this disc center of circle is that the center is divided into the N group of arranging identical with detonation chamber; Every group comprises M detonation chamber; Start priming device and be installed in and be positioned at outermost any one of this disc in every group of detonation chamber and adopt the detonate detonation chamber of jet igniting of head, it is identical to start the mounting point of priming device in every group of detonation chamber simultaneously.
4. a kind of multitube parallel pulse detonation combustor according to claim 1 is characterized in that: the detonate detonation chamber of jet igniting of described afterbody is oxygenant with the air, and the obstruction of detonation chamber outlet is than greater than 0.2 when the jet that detonates is injected its afterbody.
5. the ignition and detonation method of the said multitube parallel pulse detonation combustor of claim 1; It is characterized in that comprising the steps: all having when can quick-fried mixed gas being full of whole detonation chamber with the same terms when all detonation chambers inlet; Start priming device work; Form the detonation wave of propagates down stream, detonation wave propagation is behind the jet exit that detonates, and most of detonation wave is discharged through the detonation chamber outlet; Part detonation wave propagates into next the detonate jet inlet of detonation chamber of jet igniting of afterbody that adopts through the jet exit that detonates; Thereby in detonation chamber, form detonation wave fast, propagate is to the jet exit that detonates rapidly in this detonation chamber for detonation wave, and this moment, the detonation chamber inlet was closed; Part detonation wave propagates into next the detonate jet inlet of detonation chamber of jet igniting of head, the so continuous downstream delivery of adopting through the jet exit that detonates; For single detonation chamber; No matter initial detonation wave is upstream or propagates down stream, finally this compressional wave will be discharged from the detonation chamber outlet and propagated into low pressure parts or the external environment that links to each other with the detonation chamber downstream, so form one extensional wave from the detonation chamber outlet oppositely to the propagation of detonation chamber inlet; Thereby the pressure in the detonation chamber is descended; When equal pressure drops to stuffing pressure, can pour the detonation chamber inlet again by quick-fried mixed gas, begin the filling process of this detonation chamber new round; Pass to when detonation wave to have got back to again behind the jet exit that detonates of last detonation chamber the detonation chamber that starts priming device is housed; Be equipped with this moment the detonation chamber that starts priming device accomplished toxic emission with can quick-fried mixed gas filling process; The pinking jet forms detonation wave rapidly after importing detonation chamber into, starts priming device and no longer works.
6. the ignition and detonation method of a kind of multitube parallel pulse detonation combustor according to claim 5; It is characterized in that: the jet inlet that detonates in that the detonation chamber that starts priming device is housed is installed the startup valve; When starting priming device work; Start valve closing, wait to start to start valve opening after the valve downstream detonation chamber forms detonation wave, and keep normally open during proper functioning always in the firing chamber.
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| CN102042121A (en) * | 2010-12-23 | 2011-05-04 | 西北工业大学 | Detonation tube structure of multi-tube pulse detonation engine |
| CN103899435B (en) * | 2014-03-28 | 2015-11-18 | 西北工业大学 | A kind of combined type pulse detonation engine detonation chamber |
| CN103899436B (en) * | 2014-04-01 | 2016-01-13 | 西北工业大学 | A spiral multi-channel pulse detonation engine |
| CN104100411B (en) * | 2014-07-08 | 2016-01-20 | 北京理工大学 | A kind of double pulsing gasifier section of parallel chamber structure |
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| US11674476B2 (en) * | 2017-06-09 | 2023-06-13 | General Electric Company | Multiple chamber rotating detonation combustor |
| CN108361125B (en) * | 2018-03-15 | 2023-05-23 | 张俊良 | Rotary pipe type multitube pulse detonation engine |
| DE102018109305A1 (en) * | 2018-04-19 | 2019-10-24 | Fogtec Brandschutz Gmbh & Co. Kg | Fire-Fighting Equipment |
| CN111305972A (en) * | 2020-03-28 | 2020-06-19 | 西北工业大学 | A pulse detonation combustion chamber and an air turbo rocket engine based on pulse detonation |
| CN111664026B (en) * | 2020-06-08 | 2021-03-30 | 西安航天动力研究所 | Disc-shaped annular cavity type high-energy detonator of rotary detonation engine |
| CN113803189A (en) * | 2021-09-08 | 2021-12-17 | 陈道如 | Self-excited detonation engine |
| CN113864085B (en) * | 2021-09-28 | 2023-10-10 | 江苏大学 | A multi-tube continuous working detonation engine |
| CN117028076B (en) * | 2023-10-09 | 2024-01-09 | 北京星河动力装备科技有限公司 | Rocket engine starting method and rocket |
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