CN101806260A - Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof - Google Patents

Abstract

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 parallel parallel detonation combustor whose axes are on the same plane, and 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

A multi-tube parallel pulse detonation combustion chamber and its ignition and detonation method

technical field

The invention relates to the technical field of engines, in particular to a combustion chamber of a pulse detonation engine and an ignition and detonation method thereof.

Background technique

The discovery of detonation waves can be traced back to the end of the 18th century. Compared with deflagration waves, the propagation speed of detonation waves can reach several kilometers per second, and at the same time, extremely high gas pressure (greater than 15 to 55 atmospheres) and gas temperature (greater than 2800K), according to the traditional CJ theory, the CJ knock point is the minimum point of entropy increase, which means that the propulsion system based on detonation combustion will have an advantage in thermal cycle efficiency, so since the 1940s, Various institutions are competing to study detonation engines. In the exploration and research stage of more than 60 years, various types of detonation engines have appeared. The current research hotspots in this field mainly focus on pulse detonation engines based on pulse detonation cycles.

Since the pulse detonation engine uses intermittent detonation combustion to generate thrust, each detonation combustion chamber usually requires a periodic ignition source. Currently, the main ignition sources used are spark discharge, transient plasma ignition, and spark-triggered jet The disadvantage of ignition and pre-detonation tubes is that each detonation chamber needs an independent ignition system and control system, which brings complexity to the system.

In order to overcome the shortcomings of pulse detonation engines that rely heavily on high-power pulse ignition units, the U.S. Air Force Laboratory proposed that the detonation wave at the tail of one of the detonation combustors be introduced into the head of the other detonation combustors to be ignited through the cross-fire tube. The ignition and detonation method, through the series connection of multiple tubes, finally realizes the continuous ignition and detonation of multiple tubes. From the perspective of its test equipment, because the entrances of the multi-tube detonation chambers are on the same plane, longer cross-fire tubes are needed, and at the same time to achieve For the purpose of flame transfer, how to fill the explosive mixture into the cross-fire tube is also a technical difficulty. The Chinese patent with application number 200710018897.0 proposes a detonation combustion chamber structure in which multiple detonation chambers are connected in series through jet propagation pipes without using a long cross-fire tube, that is, the upstream of the outlet of one of the detonation chambers is based on this ignition and detonation method. The detonation jet outlet of the first detonation chamber is connected with the detonation jet inlet downstream of the entrance of the next detonation chamber, and finally forms a multi-tube annular combustion chamber, so the entrance of a single detonation chamber is along the tangential direction of the circumference and has a large deflection from the direction of the circumferential axis Angle, while the entrance points of each head of the detonation chamber are distributed along the circumference. When the air flow is in the direction of the axis (this is the direction of air flow at the entrance of the traditional aero-engine combustion chamber), these shortcomings lead to the engine having to use additional air guides and diverter devices to lead to the entrance of each detonation chamber, which is inconvenient. The transplantation of the detonation combustion chamber to the traditional aero-engine combustion chamber; at the same time, due to the large deflection of the air flow direction during this process, the total pressure loss will also increase.

Contents of the invention

In order to overcome the deficiencies of the prior art, such as long jet propagation tubes or dispersed entrance points of multi-tube detonation chambers, excessive deflection angles between the entrance direction of each detonation chamber and the axis of the engine, large total pressure loss, and inconvenient transplantation, the present invention proposes a A suitable multi-tube parallel pulse detonation combustion chamber and its ignition and detonation method can solve the above shortcomings, thereby making it easier to replace the main combustion chamber and afterburner of the existing gas turbine with the pulse detonation combustion chamber.

The technical solution adopted by the present invention to solve its technical problems is: comprising starting the detonation device 6 and a plurality of parallel detonation chambers 2, each detonation chamber 2 comprising a detonation chamber inlet 1, a detonation jet inlet 4, and a detonation jet outlet 5 and the detonation chamber outlet 3; the detonation chamber inlet 1 and the detonation chamber outlet 3 are located at both ends of the detonation chamber 2, the detonation chamber inlet 1 is at the most upstream of the intake air flow direction, and the detonation chamber outlet 3 is at the detonation chamber The most downstream of the air flow; the detonation jet inlet 4 and the detonation jet outlet 5 are located at both ends of the detonation chamber 2, and each detonation chamber 2 is different according to the relative positions of the detonation jet inlet 4 and the detonation jet outlet 5 in the detonation chamber. 2 can be divided into two types, that is, the head initiation jet ignition detonation chamber 2a and the tail initiation jet ignition detonation chamber 2b. For the head detonation jet ignition detonation chamber 2a, the detonation jet inlet 4 is located downstream of the detonation chamber inlet 1 at a distance 1 to 2 times the equivalent diameter of the detonation chamber 2a, and the detonation jet outlet 5 is located upstream of the detonation chamber outlet 3. The jet outlet 5 is connected to the detonation jet inlet 4 of the adjacent detonation chamber 2b ignited by the tail detonation jet; the detonation jet inlet 4 of the tail detonation jet ignition detonation chamber 2b is located 1 to 2 times upstream of the detonation chamber outlet 3 At the equivalent diameter distance of the detonation chamber 2b, the detonation jet outlet 5 is located downstream of the detonation chamber inlet 1, and is connected to the detonation jet inlet 4 of the adjacent detonation chamber 2a that adopts head detonation jet ignition; and so on, After multiple detonation chambers are connected, the detonation jet outlet 5 of the last detonation chamber is connected with the detonation jet inlet of the initial detonation chamber, connected end to end, and together constitute multiple detonation chamber inlets 1 and multiple detonation chamber outlets 3 detonation combustion chambers connected parallel to the axes of multiple tubes on the same plane, the detonation jet outlet 5 and the detonation jet inlet 4 are connected through a jet propagation pipe 8, and the jet propagation pipe 8 connected between every two adjacent detonation chambers equal in length. The starting detonation device 6 is installed at a distance 1-2 times the equivalent diameter of the detonation chamber downstream of the detonation chamber entrance 1 of any one of the detonation chambers 2a ignited by the head detonation jet in the multi-tube parallel detonation combustion chamber, and is connected with The detonation jet inlets 4 of the detonation chamber are staggered.

As the first preferred solution of the present invention, when the number of a group of parallel detonation chambers is N times of a certain integer M, the detonation chamber entrances of N detonation chambers separated by M-1 detonation chambers can be 1. The starting detonation device is installed downstream. When starting, N starting detonation devices 6 are detonated at the same time, so that there can always be N detonation waves chasing each other. Let the sum of the length between the detonation jet inlet 4 and the detonation jet outlet 5 of any detonation chamber plus the length of a jet propagation pipe 8 be L, and let V be the maximum detonation wave propagation under all working conditions of the detonation combustion chamber Speed, let T be a knock working cycle, then M should be greater than VT/L.

As the second preferred solution of the present invention, when a plurality of detonation chambers are evenly distributed in parallel along the circular surface along the incoming flow direction, assuming that the number of detonation chambers connected in parallel is N times of a certain integer M, then the center of the circular surface The circular surface is divided into N fans as the center, and each fan includes M parallel detonation chambers along the incoming flow direction, and finally multiple detonation chambers are divided into N with the same arrangement along the incoming flow direction of the detonation combustion chamber. Each group contains M detonation chambers, and the detonation device 6 is installed in each group of detonation chambers in any one of the outermost layers of the circular surface of the multi-tube parallel pulse detonation combustion chamber. Chamber 2a, and the installation position of the detonation device 6 in each group of detonation chambers should be the same.

As the third preferred solution of the present invention, the pulse detonation combustion chamber distributed in a multi-tube parallel circular ring is divided into inner and outer layers. The detonation chamber 2a is composed, the inner layer is composed of the detonation chamber 2b which is ignited by the tail detonation jet, and the starting detonation device 6 is only installed in the outer detonation chamber 2a. When there are multiple starting detonation devices 6, they should be evenly installed in the circumferential direction of the outer detonation chamber.

As the fourth preferred solution of the present invention, for the detonation chamber 2b ignited by the detonation jet at the tail, if the combustion chamber uses air as the oxidant, then when the detonation jet is injected into its tail, the blockage ratio of the detonation chamber outlet 3 should be greater than 0.2 .

The present invention also provides a method for ignition and detonation of the detonation combustion chamber, comprising the following steps: when all detonation chamber inlets 1 have detonable mixed gas to fill the entire detonation chamber 2 under the same conditions, start the detonation device 6 to work , forming a detonation wave that propagates downstream. After the detonation wave propagates to the detonation jet outlet 5, most of the detonation wave is discharged through the detonation chamber outlet 3, and a part of the detonation wave propagates through the detonation jet outlet 5 to the next detonator that is ignited by the tail detonation jet. The detonation jet inlet 4 of the detonation chamber 2b, thereby rapidly forming a detonation wave in the detonation chamber 2b, and the detonation wave quickly propagates upstream in the detonation chamber 2b to the detonation jet outlet 5, at this time, the detonation chamber inlet 1 is closed, and a part The detonation wave propagates through the detonation jet outlet 5 to the detonation jet inlet 4 of the next detonation chamber 2a ignited by the head detonation jet, so that it is continuously transmitted downstream. For a single detonation chamber, regardless of whether the initial detonation wave propagates upstream or downstream, the compression wave will eventually be discharged from the detonation chamber outlet 3 and propagate to the low-pressure components connected to the downstream of the detonation chamber or the external environment, thereby forming an expansion wave Propagate from the detonation chamber outlet 3 to the detonation chamber inlet 1, so that the pressure in the detonation chamber drops, and when the pressure drops to the filling pressure, the detonable mixture rushes into the detonation chamber inlet 1 again, and the detonation starts A new round of filling process for the chamber. When the detonation wave reaches the detonation jet outlet 5 of the last detonation chamber, it returns to the detonation chamber 2a equipped with the detonation device 6. At this time, the detonation chamber 2a equipped with the detonation device 6 has completed exhaust gas discharge and detonation. During the gas mixture filling process, after the detonation jet enters the detonation chamber 2a, a detonation wave is rapidly formed, and the detonation device is no longer working.

Combustion wave can not propagate to the detonation chamber 2b connected to each other by the jet propagation pipe 8 on the upstream side of the detonation chamber 2a when preventing the initial start detonation device 6 from working. The jet inlet 4 is equipped with a starting valve 7. When the starting detonation device 6 is working, the starting valve 7 is closed. After the detonation chamber 2b upstream of the starting valve 7 forms a detonation wave, the starting valve 7 is opened and kept open when the combustion chamber is working normally. state.

The beneficial effects of the present invention are: firstly, the ignition and detonation method of the present invention alternately utilizes the detonation wave in the detonation chamber to ignite and detonate another detonation chamber, so that the detonation of the detonation wave is close to direct detonation without the need for additional high-energy high-frequency pulse ignition system, so that the pulse detonation combustion chamber accessory system is more simplified; on the other hand, in the organization of the detonation jet, each detonation chamber in the multi-tube pulse detonation combustion chamber is divided into the head jet detonation detonation chamber 2a and the tail There are two types of jet detonation detonation chambers 2b, through alternate jet detonation, the ignition detonation method can be directly used in the existing common multi-tube parallel pulse detonation combustion chamber without changing the overall structure of the engine, solving the problem of the existing multi-tube pulse detonation combustion chamber. The problem of ignition and detonation in the detonation combustion chamber.

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

Description of drawings

Fig. 1 is a schematic diagram of the start-up process of the present invention;

Fig. 2 is a schematic diagram of the working process of ignition and detonation of the present invention, wherein Fig. 2.1 is a schematic diagram of the working process when the detonation jet is ignited at the head of the detonation chamber, and Fig. 2.2 is a schematic diagram of the working process when the detonation jet is ignited at the tail of the detonation chamber.

Fig. 3 is a technical schematic diagram of Embodiment 1 of the present invention, wherein Fig. 3.1 is a schematic structural diagram of a multi-tube detonation combustor, and Fig. 3.2 is a technical schematic diagram when viewed from upstream to downstream of a multi-tube detonation combustor;

Fig. 4 is the technical schematic diagram when looking downstream from the upstream of the multi-pipe detonation combustion chamber of Embodiment 2 of the present invention;

Fig. 5 is a technical schematic diagram of Embodiment 3 of the present invention when viewed from upstream to downstream of the multi-tube detonation combustion chamber.

In the figure, 1-detonation chamber entrance, 2-detonation chamber, 2a-head detonation jet ignition detonation chamber, 2b-tail detonation jet ignition detonation chamber, 3-detonation chamber exit, 4-detonation jet inlet, 5-Detonation jet outlet, 6-Start detonation device, 7-Start valve, 8-Jet propagation pipe, 9-Left-travel expansion wave, 10-Left-travel detonation wave, 11-Incident detonation wave, 12-Right-travel detonation wave, 13-the jet direction of the detonation jet in the jet propagation pipe downstream of the detonation chamber entrance, 14-the jet direction of the detonation jet in the jet propagation pipe upstream of the detonation chamber outlet.

Detailed ways

Embodiment 1: Referring to FIG. 3 , it includes a start-up detonation device 6 and six parallel detonation chambers 2, and the parallel detonation chambers 2 are connected by jet propagation pipes 8 to form six parallel pulse detonation combustion chambers distributed around the circumference, each The detonation chamber 2 includes a detonation chamber inlet 1, a detonation chamber outlet 3 and a jet propagation pipe 8, and the jet propagation pipe includes the detonation jet outlet 5 of the upper detonation chamber connected together and the detonation jet outlet 5 of the lower detonation chamber. The jet inlet 4; the detonation chamber inlet 1 and the detonation chamber outlet 3 are located at both ends of the detonation chamber 2, and the detonation chamber inlet 1 is at the most upstream; the detonation jet inlet 4 and the detonation jet outlet 5 are located at both ends of the detonation chamber 2, according to The relative positions of the detonation jet inlet 4 and the detonation jet outlet 5 of each detonation chamber 2 are different in the detonation chamber. The detonation chamber 2 can be divided into two types, namely the head detonation jet ignition detonation chamber 2a and the tail detonation jet ignition detonation chamber 2a. The detonation chamber 2b; the starting detonation device 6 is installed in the detonation chamber inlet 1 downstream of one of the detonation chambers 2 in the six-tube parallel detonation combustion chamber at a distance 1 to 2 times the equivalent diameter of the detonation chamber, and the corresponding detonation chamber It is the detonation chamber 2a that adopts the head detonation jet to ignite. For the head detonation jet ignition detonation chamber 2a, the detonation chamber inlet 1 is on the upstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located downstream of the detonation chamber inlet 1 1 to 2 times the equivalent diameter of the detonation chamber 2a. , the detonation chamber outlet 3 is on the downstream side of the detonation chamber airflow, the detonation jet outlet 5 is located upstream of the detonation chamber outlet 3, and the detonation jet outlet 5 is connected to the detonation jet of the adjacent detonation chamber 2b ignited by the tail detonation jet The inlets 4 are connected; the detonation chamber outlet 3 of the detonation chamber 2b is on the downstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located upstream of the detonation chamber outlet 3, which is 1 to 2 times the equivalent of the detonation chamber 2b At the diameter distance, the detonation jet outlet 5 is located downstream of the detonation chamber inlet 1, and is connected with the detonation jet inlet 4 of the adjacent detonation chamber 2a ignited by the head detonation jet; and so on, after the six detonation chambers are connected , the detonation jet outlet 5 of the last detonation chamber is connected with the detonation jet inlet of the initial detonation chamber, connected end to end, and jointly constitute a plurality of detonation chamber inlets 1 and a plurality of detonation chamber outlets 3 respectively in the same plane, six Six detonation chambers connected in an S-shape with parallel parallel detonation combustion chambers. After starting the detonation device 6 in Figure 3 to work, a detonation wave propagating downstream is formed in the detonation chamber 2a where it is located. To the upstream of the outlet of the adjacent detonation chamber 2b, and then generate a detonation wave propagating upstream in the detonation chamber 2b, which is then transmitted to the upstream of the entrance of the next adjacent detonation chamber 2a through the upstream jet propagation pipe 8 , so that the detonation wave continues to propagate in the detonation combustion chamber under the action of the jet propagation tube. Viewed from the upstream to the downstream of the detonation combustion chamber, it forms a counterclockwise ignition sequence as shown in the direction of the arrow in Figure 3.1.

Embodiment 2: With reference to Fig. 4, it comprises six starting detonating devices 6 and thirty-six parallel detonation chambers 2 uniformly distributed along the direction of the incoming flow, and first divides it into equal parts as shown in the figure along the direction of the incoming flow. Six fans, each fan contains six parallel detonation chambers, and finally divides the thirty-six detonation chambers into six groups with the same arrangement along the incoming flow direction of the detonation combustion chamber. The groups are independent and have no connection relationship. Each set contains six detonation chambers. For each group, the parallel detonation chambers 2 are connected by a jet propagation pipe 8, each detonation chamber 2 includes a detonation chamber inlet 1, a detonation chamber outlet 3 and a jet propagation pipe 8, and the jet propagation pipes include upper The detonation jet outlet 5 of the first detonation chamber and the detonation jet inlet 4 of the next detonation chamber; the detonation chamber inlet 1 and the detonation chamber outlet 3 are located at both ends of the detonation chamber 2, and the detonation chamber inlet 1 is at the most upstream The detonation jet inlet 4 and the detonation jet outlet 5 are located at the two ends of the detonation chamber, and according to the relative positions of the detonation jet inlet 4 and the detonation jet outlet 5 of each detonation chamber 2 in the detonation chamber, the detonation chamber 2 can be divided into two Type, that is, the head detonation jet ignition detonation chamber 2a and the tail detonation jet ignition detonation chamber 2b; the starting detonation device 6 is installed in the group of parallel detonation chambers, one of which is located in the middle of the outermost layer of the entire detonation combustion chamber The distance downstream of the detonation chamber entrance 1 of the detonation chamber 2 is 1 to 2 times the equivalent diameter of the detonation chamber, and the corresponding detonation chamber is the detonation chamber 2a ignited by the head detonation jet. For the head detonation jet ignition detonation chamber 2a, the detonation chamber inlet 1 is on the upstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located downstream of the detonation chamber inlet 1 1 to 2 times the equivalent diameter of the detonation chamber 2a. , the detonation chamber outlet 3 is on the downstream side of the detonation chamber airflow, the detonation jet outlet 5 is located upstream of the detonation chamber outlet 3, and the detonation jet outlet 5 is connected to the detonation jet of the adjacent detonation chamber 2b ignited by the tail detonation jet The inlets 4 are connected; the detonation chamber outlet 3 of the detonation chamber 2b is on the downstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located upstream of the detonation chamber outlet 3, which is 1 to 2 times the equivalent of the detonation chamber 2b At the diameter distance, the detonation jet outlet 5 is located downstream of the detonation chamber inlet 1, and is connected with the detonation jet inlet 4 of the adjacent detonation chamber 2a ignited by the head detonation jet; after the six detonation chambers are connected, the last detonation chamber The detonation jet outlet 5 of the detonation chamber is connected with the detonation jet inlet of the initial detonation chamber, connected end to end, and together constitute a group of detonation chamber inlets 1 and multiple detonation chamber outlets 3 respectively on the same plane, six detonation chambers S-type connected six-pipe axis parallel detonation combustion chamber. Finally, each group of detonation chambers has a starting detonation device 6. In order to realize that the detonation wave passes through all the detonation chambers in each group within one cycle, the detonation chamber 2a and detonation chamber 2b shown in Figure 4 are finally obtained. Corresponding arrangement; when the detonation wave is transmitted from the detonation chamber 2a to the detonation chamber 2b, the two detonation chambers are connected through the jet propagation pipe upstream of the outlet, and when the detonation wave is transmitted from the detonation chamber 2b to the detonation chamber 2a, The two detonation chambers are connected downstream of the inlet by a jet propagation tube. When all the detonation chambers have the detonable mixture filling the entire detonation chamber 2 under the same conditions, the six starting detonation devices 6 work simultaneously, forming detonation waves propagating downstream in their respective detonation chambers 2a, and the detonation waves propagate After reaching the upstream of the outlet of the detonation chamber 2a, part of the detonation wave propagates to the next adjacent detonation chamber 2b through the jet propagation pipe, so that a detonation wave propagating upstream is rapidly formed downstream of the detonation chamber 2b, and then it passes through the upstream The jet propagating tube is transmitted to the upstream of the entrance of the next adjacent detonation chamber 2a, so that the detonation wave is continuously propagated in each group of detonation chambers under the action of the jet propagating tube. Looking from the upstream to the downstream of the detonation combustion chamber, six groups The detonation chambers all form a counterclockwise ignition sequence as shown in the direction of the arrow in Figure 4.

Embodiment 3: Referring to Fig. 5, it includes three starting detonating devices and twenty-four detonation chambers distributed in parallel along the direction of incoming flow, and each detonation chamber 2 includes a detonation chamber inlet 1 , the detonation chamber outlet 3 and the jet propagation pipe 8, the jet propagation pipe 8 includes the detonation jet outlet 5 of the upper detonation chamber connected together and the detonation jet inlet 4 of the next detonation chamber; the detonation chamber inlet 1 and the detonation chamber outlet 3 are located at both ends of the detonation chamber 2, and the detonation chamber inlet 1 is at the most upstream; the detonation jet inlet 4 and the detonation jet outlet 5 are located at both ends of the detonation chamber 2, according to the detonation jet inlet 4 and the relative position of the detonation jet outlet 5 in the detonation chamber, the detonation chamber 2 can be divided into two types, namely the head detonation jet ignition detonation chamber 2a and the tail detonation jet ignition detonation chamber 2b. The twenty-four tube parallel pulse detonation combustors are divided into inner and outer layers, each containing the same number of detonation chambers, and the detonation chambers in the outer layer are ignited by head detonation jets, and the detonation chambers in the inner layer are ignited by tail detonation jets Ignition, that is, the outer layer contains 12 detonation chambers 2a, the inner layer contains 12 detonation chambers 2b, and the detonation chambers of the inner and outer layers are arranged in a staggered manner, so that any one detonation chamber 2a is located between two adjacent detonation chambers 2b and Any one of the detonation chambers 2b is located between two adjacent detonation chambers 2a; the three starting detonation devices 6 are evenly distributed along the circumference and installed on the outer layer of the pulse detonation combustion chamber, among which the downstream of the entrance 1 of the three detonation chambers 2a is 1 to 2 times On the outside of the equivalent diameter distance of the detonation chamber, viewed from upstream to downstream of the detonation combustion chamber, a corresponding arrangement of detonation chamber 2a and detonation chamber 2b is finally formed as shown in FIG. 5 . For the head detonation jet ignition detonation chamber 2a, the detonation chamber inlet 1 is on the upstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located downstream of the detonation chamber inlet 1 1 to 2 times the equivalent diameter of the detonation chamber 2a. The detonation chamber outlet 3 is on the downstream side of the detonation chamber air flow, the detonation jet outlet 5 is located upstream of the detonation chamber outlet 3, and the detonation jet outlet 5 is adjacent to the inner layer of the detonation chamber 2b that is ignited by the tail detonation jet The detonation jet inlet 4 is connected; the tail detonation jet ignites the detonation chamber outlet 3 of the detonation chamber 2b on the downstream side of the detonation chamber air flow, and the detonation jet inlet 4 is located upstream of the detonation chamber outlet 3 by 1 to 2 times the size of the detonation chamber At the equivalent diameter distance of 2b, the detonation jet outlet 5 is located downstream of the detonation chamber inlet 1, and is connected to the detonation jet inlet 4 of the detonation chamber 2a adjacent to the outer layer that adopts head detonation jet ignition; twenty-four detonation chambers After the connection, the detonation jet outlet 5 of the last detonation chamber is connected with the detonation jet inlet of the first detonation chamber, connected end to end, and jointly constitute a group of detonation chamber inlets 1 and multiple detonation chamber outlets 3 respectively on the same plane , the twenty-four detonation chambers are interlaced and connected with multi-pipe axis parallel parallel detonation combustion chambers. When all the detonation chambers have the detonable mixture filling the entire detonation chamber 2 under the same conditions, the three starting detonation devices 6 work at the same time, forming a detonation wave propagating downstream in the detonation chamber 2a where they are respectively located, and the detonation wave transmission After the upstream of the detonation chamber 2a outlet, a part of the detonation wave propagates to the next detonation chamber 2b at the adjacent inner layer through the jet propagation pipe, so that a detonation wave propagating upstream is rapidly formed downstream of the detonation chamber 2b, and then it again Through the upstream jet propagation pipe, it is transmitted to the upstream of the entrance of the next detonation chamber 2a in the adjacent outer layer, so that the detonation wave continues to propagate in the detonation chamber under the action of the jet propagation pipe, thus forming a situation where the three detonation waves chase each other , and finally the multi-tube detonation combustor forms a counterclockwise and inner-inner-layer cross-ignition sequence as shown in the direction of the arrow in Figure 5 . Afterwards, the detonation combustion chamber enters a stable cycle, no external ignition equipment is needed, and the propagation time of the detonation wave passing through the two adjacent detonation chambers 2a of the outer layer and the propagation time of the detonation wave passing through the two adjacent detonation chambers 2b of the inner layer are the same, This facilitates the control of the intake valve at the front end of the detonation combustion chamber.

Claims (7)

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; Detonation chamber inlet and detonation chamber outlet are positioned at the detonation chamber two ends, and the detonation chamber inlet comes the upstream of flow path direction, detonation chamber to export 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 that detonates 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 detonation chamber outlet upstream, 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 of detonation chamber outlet upstream 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 that detonates 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, join end to end, a plurality of detonation chamber inlets and the outlet of a plurality of detonation chamber have been constituted jointly respectively at conplane multitube parallel axes detonation combustor in parallel, 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 the multitube parallel detonation combustor wherein any one adopts head to detonate 1～2 times in the detonation chamber inlet downstream of detonation chamber of jet igniting to this detonation chamber equivalent diameter distance, and stagger with the jet inlet that detonates of this detonation chamber.

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 1, it is characterized in that: the N of described integer M doubly a detonation chamber along coming flow path direction along disc when in parallel uniform, 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 be installed in be positioned in every group of detonation chamber this disc outermost any one 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, it is characterized in that: the pulse detonation combustor that described multitube parallel ring distributes is divided into inside and outside two-layer, the detonation chamber number that internal and external layer comprised is identical, outer by adopting the detonate detonation chamber of jet igniting of head to form, internal layer is by adopting the detonate detonation chamber of jet igniting of afterbody to form, and the startup priming device only is installed in outer detonation chamber; When a plurality of startup priming device, it is circumferentially evenly installed at outer detonation chamber.

5. 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.

6. the ignition and detonation method of the described 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, most of detonation wave is discharged by the detonation chamber outlet, part detonation wave propagates into next the detonate jet inlet that detonates of detonation chamber of jet igniting of afterbody that adopts by the jet exit that detonates, thereby in detonation chamber, form detonation wave fast, detonation wave upstream propagates into the jet exit that detonates rapidly in this detonation chamber, this moment, the detonation chamber inlet was closed, part detonation wave propagates into next the detonate jet inlet that detonates of detonation chamber of jet igniting of head that adopts by the jet exit that detonates, and constantly like this transmits downstream; For single detonation chamber, no matter initial detonation wave is upstream or propagates down stream, final this compressional wave will export 3 discharges from detonation chamber and propagate into low pressure parts or the external environment that links to each other with the detonation chamber downstream, and then form one extensional wave and oppositely propagate to the detonation chamber inlet from the detonation chamber outlet, 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, the detonation chamber that starts priming device is housed this moment has finished toxic emission and 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.

7. the ignition and detonation method of a kind of multitube parallel pulse detonation combustor according to claim 6, it is characterized in that: the startup valve is installed at the jet inlet that detonates that the detonation chamber that starts priming device is housed, when starting priming device work, start valve closing, after starting valve downstream detonation chamber formation detonation wave, start valve opening, and when the proper functioning of firing chamber, keep normally open always.

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