CN212027941U - Pulse detonation engine - Google Patents

Abstract

The utility model discloses a pulse detonation engine, which comprises a machine body and a machine head, wherein the machine body comprises six layers of cylinder bodies which are arranged from inside to outside in sequence; the machine head comprises a driving motor arranged at the left end of the central axis of the first cylinder and a hemispherical rotating protective shell connected with a first driving disc arranged on an output shaft of the driving motor, and the outer wall of the rotating protective shell is provided with a plurality of centrifugal air compression blades; an output shaft of the driving motor penetrates through the first cylinder along a central axis and is fixedly connected with the rotary impeller, a plurality of impeller blades are arranged on the circumference of the rotary impeller, and the tail end of the rotary impeller is connected with the conical air injection tail; the left end and the right end of the first cylinder are connected through the inner ring of the fixed bearing, and the outer ring of the first cylinder is connected with the inner wall of the first cylinder; the pulse electronic igniter is inserted into the second annular gap from the outside of the machine body; the method has the advantages that the dependence of the detonation engine on a complex fuel atomization device is eliminated, and the atomized fuel gas and air are fully mixed, so that the detonation is fully carried out.

Description

Pulse detonation engine

Technical Field

The utility model relates to an engine field especially relates to a pulse detonation engine.

Background

The pulse detonation engine is a new concept engine which generates thrust by using high-temperature and high-pressure gas generated by pulse detonation waves, has the advantages of high thermal cycle efficiency, simple structure and the like, can be used as a power device for combat aircrafts, unmanned planes and missiles, can also be used as a power device for orbit transfer engines, planetary landing engines, spacecraft attitude control, satellite maneuvering and the like, has wide application prospect in the future aerospace propulsion field, and is competitive with a plurality of research institutions at home and abroad in recent years for research work on pulse detonation engines.

The principle of pulse detonation engines is different from that of common rocket engines or jet aero engines. The engine directly utilizes the detonation wave generated by detonation combustion to compress gas in a combustion chamber so as to generate power. The pressure and temperature of the explosive fuel can be quickly raised by the detonation wave generated by detonation combustion, the pressure can be as high as 100 atmospheric pressures, and the temperature can be up to 2000 ℃. Therefore, the engine with detonation combustion can achieve the purpose of compressing gas without using a traditional gas compressor and a turbine part, greatly simplifies the structure and greatly reduces the cost. In addition, because the propagation speed of the detonation wave is extremely fast and reaches several kilometers per second, the whole combustion process is close to constant-pressure combustion, and because the heat cycle efficiency of the constant-pressure combustion is greatly higher than that of constant-volume combustion and reaches 49 percent, and the constant-volume combustion efficiency is only 27 percent, the performance of the propulsion system adopting the detonation combustion can be greatly improved. When the knocking frequency is high and reaches 80-100 Hz, continuous thrust can be generated.

At present, the research on pulse detonation engines in China is limited in a small range, and a few special research institutions mainly concentrate on universities and colleges of aerospace and the like, mainly mechanism research is carried out, and practical research is relatively few; however, even in this way, a relatively rich research result is obtained, and the theoretical research foundation is enriched. For example, the research work of the pulse detonation engine is firstly developed by western workers in China under the lead of strict professors junior in 1994 of northwest industrial university, the working principle of the detonation engine is scientifically clarified by using thermodynamics and detonation wave theories, and a method for working cycle and performance analysis of the detonation engine is established. A single-tube air-breathing pulse detonation engine model machine, a multi-tube air-breathing pulse detonation engine model machine and a mixed pulse detonation engine model machine are developed in 2006-2007 successively.

The existing pulse detonation engine is divided into an air suction type and a rocket type, and generally is a two-component propulsion system. A common liquid fuel/air pulse detonation engine utilizes an atomizing nozzle to directly inject fuel into a detonation chamber for detonation. The fuel atomization process has a great influence on the generation of the knock wave, and sometimes the ignition system engine using a large amount of energy is frequently misfired. For example, the diameter of the atomized oil drops is not more than 10 μm, and the detonation wave is not easily generated if the diameter exceeds 40-70 μm. Sometimes even though atomization is good, the size of the detonation chamber is large in order to complete the DDT process to create detonation combustion because the ignition energy is not high.

At present, most common liquid fuel pulse detonation engines perform fuel atomization, direct ignition detonation and detonation combustion in the same detonation chamber after finishing DDT process, and the detonation chamber is large in size and complex in structure. Atomization effect, ignition detonation energy, DDT distance, time and the like have great influence on the generation of detonation waves, and are mutually associated and coupled with the problems of detonation combustion and the like, so that once the problems occur, the reason is difficult to figure out, and further development and application of the pulse detonation engine are greatly limited.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a pulse detonation engine which can stabilize the propagated detonation wave and simultaneously the formation of the detonation wave does not depend on a complex atomization device; in order to achieve the technical purpose, the utility model provides a pulse detonation engine, including fuselage and aircraft nose, the fuselage includes six layers of barrels that set gradually from inside to outside, and the first barrel right-hand member of inlayer is equipped with first sealing ring, leaves annular breach between second barrel and the first sealing ring, the annular breach is sealed through the blade fixed ring in the fixed impeller, the fixed impeller still includes a plurality of vertical hollow fixed guide vanes that run through the blade fixed ring, the first annular clearance between first barrel and the second barrel passes through the third annular clearance intercommunication between fixed guide vane and third barrel and the fourth barrel, the right-hand member in third annular clearance is airtight, and the left end communicates with the second annular clearance between second barrel and the third barrel; the gas mixing device further comprises a fourth annular gap between the fourth barrel and the fifth barrel and a fifth annular gap between the fifth barrel and the sixth barrel, wherein the left end of the fourth annular gap is communicated with the second annular gap through a gas mixing chamber, and the right end of the fourth annular gap is communicated with the right end of the fifth annular gap; the fuel inlet pipe is communicated to the first annular gap from the outside of the machine body, and the fuel enters the second annular gap from the left side of the third annular gap after sequentially passing through the first annular gap, the fixed guide vane and the third annular gap from the fuel inlet pipe; the left end between the second cylinder and the fifth cylinder is sealed by a second sealing ring; the machine head comprises a driving motor arranged at the left end of the central axis of the first cylinder and a hemispherical rotary protective shell connected with a first driving disc arranged on an output shaft of the driving motor, the outer wall of the rotary protective shell is provided with a plurality of centrifugal air compression blades, a diffusion opening is reserved between the rotary protective shell and the sixth cylinder, and the diffusion opening is communicated with the fifth annular gap; an output shaft of the driving motor penetrates through the first cylinder along the central axis of the first cylinder and then is fixedly connected with a rotating impeller, a plurality of impeller blades are arranged on the circumference of the rotating impeller, and the tail end of the rotating impeller is connected with a conical air injection tail; the output shaft of the driving motor is connected with the left end and the right end of the first cylinder through the inner ring of the fixed bearing, and the outer ring of the fixed bearing is connected with the inner wall of the first cylinder; the first cylinder body is provided with a first annular gap, the first annular gap is arranged between the first cylinder body and the first cylinder body, the first cylinder body is provided with a first cylinder inlet pipe and a first cylinder outlet pipe, the first cylinder inlet pipe; and the pulse electronic igniter is inserted into the second annular gap from the outside of the machine body.

In particular, a plurality of elongated ribs are provided in the fifth annular gap and the fourth annular gap, the elongated ribs being radially disposed to separate the fifth annular gap and the fourth annular gap into a plurality of gas passages.

In particular, the rotating protective shell is provided with a shunting hole.

Particularly, a pure oxygen inlet pipeline is arranged at the joint of the rotary protective shell and the fifth annular gap.

Particularly, the device also comprises a temperature sensor arranged in the fifth annular gap and an air pressure sensor arranged on the sixth cylinder body and positioned at the corresponding position of the rotary protective shell.

Particularly, the cross sections of the fixed guide blades and the impeller blades are both hollow crescent-shaped, and the rotating impeller is connected with the output shaft of the driving motor through a second driving disk.

Particularly, the second driving disk is a solid disk, and a plurality of through holes are formed in the disk surface.

In particular, the centrifugal compressor blade is reverse S-shaped and the length direction of the centrifugal compressor blade is parallel to the central axis.

Particularly, the circumferential central axis of the tail end of the right side of the fourth cylinder body is folded.

The utility model has the advantages that: the detonation engine has the advantages that dependence of the detonation engine on a complex fuel atomization device is eliminated, the atomization process of fuel is converted into an independent process, and then the atomized fuel gas and air are fully mixed through mixing at the inlet of the combustion chamber, so that detonation is fully performed, and the problems that the size of the detonation chamber of the conventional detonation engine is large, and the reaction process is interwoven by a plurality of processes together, and faults are inconvenient to troubleshoot are solved.

Drawings

Fig. 1 is a schematic view of the axial section structure of the device of the present invention.

Fig. 2 is a schematic view of a rotary impeller structure.

Fig. 3 is a schematic view of a fixed impeller structure.

Fig. 4 is a schematic view of a rotary casing structure.

Wherein, the first cylinder-1; a first annular gap-1 a; a first sealing ring-11; a blade fixing ring-12; a fixed guide vane-13; a fuel inlet pipe-14; a fixed bearing-15; a third seal ring-16; air vent-17; a second cylinder-2; a second annular gap-2 a; a second sealing ring-21; a pulse electronic sparker-22; a third cylinder-3; a third annular gap-3 a; a fourth cylinder-4; a fourth annular gap-4 a; a fifth cylinder-5; a fifth annular gap-5 a; a sixth cylinder-6; a mixing chamber-7; a drive motor-8; a first drive disc-81; a second drive disk-82; rotating the protective shell-9; centrifugal compressed air blade-91; a diffuser-92; a rotating impeller-93; jet tail-94; a shunt hole-95; a pure oxygen inlet line-96.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

A pulse detonation engine comprises an engine body and an engine head, wherein the engine body comprises six layers of cylinders which are sequentially arranged from inside to outside, the right end of a first cylinder 1 on the innermost layer is provided with a first sealing ring 11, an annular gap is reserved between a second cylinder 2 and the first sealing ring 11, the annular gap is sealed through a blade fixing ring 12 in a fixed impeller, the fixed impeller further comprises a plurality of hollow fixed guide blades 13 which vertically penetrate through the blade fixing ring 12, a first annular gap 1a between the first cylinder 1 and the second cylinder 2 is communicated with a third annular gap 3a between a third cylinder 3 and a fourth cylinder 4 through the fixed guide blades 13, the right end of the third annular gap 3a is sealed, and the left end of the third annular gap is communicated with a second annular gap 2a between the second cylinder 2 and the third cylinder 3; the device also comprises a fourth annular gap 4a between the fourth barrel 4 and the fifth barrel 5 and a fifth annular gap 5a between the fifth barrel 5 and the sixth barrel 6, wherein the left end of the fourth annular gap 4a is communicated with the second annular gap 2a through a mixing air chamber 7, and the right end of the fourth annular gap 4a is communicated with the right end of the fifth annular gap 5 a; the fuel inlet pipe 14 is communicated with the first annular gap 1a from the outside of the machine body, and the fuel enters the second annular gap 2a from the left side of the third annular gap 3a after passing through the first annular gap 1a, the fixed guide vanes 13 and the third annular gap 3a from the fuel inlet pipe 14 in sequence; the left end between the second cylinder 2 and the fifth cylinder 5 is sealed by a second sealing ring 21; the machine head comprises a driving motor 8 arranged at the left end of the central axis of the first cylinder body 1 and a hemispherical rotary protective shell 9 connected with a first driving disc 81 arranged on the output shaft of the driving motor 8, the outer wall of the rotary protective shell 9 is provided with a plurality of centrifugal air compression blades 91, a diffusion opening 92 is reserved between the rotary protective shell 9 and the sixth cylinder body 6, and the diffusion opening 92 is communicated with the fifth annular gap 5 a; an output shaft of the driving motor 8 penetrates through the first cylinder 1 along a central axis of the first cylinder 1 and then is fixedly connected with a rotating impeller 93, a plurality of impeller blades are arranged on the circumference of the rotating impeller 93, and the tail end of the rotating impeller 93 is connected with a conical air injection tail 94; the output shaft of the driving motor 8 is connected with the left end and the right end of the first cylinder 1 through the inner ring of the fixed bearing 15, and the outer ring of the fixed bearing 15 is connected with the inner wall of the first cylinder 1; the first cylinder body 1 is provided with a first annular gap 1a, and the first cylinder body 1 is provided with a diffusion opening 92 and a first cylinder body 1 inner space, wherein the first cylinder body 1 is provided with a first sealing ring 16, the first sealing ring 16 is arranged at the tail part of a left end fixed bearing 15, the left end of the first annular gap 1a is sealed by the third sealing ring 16 at the left side of the fuel inlet pipe 14, and an air hole 17 is also arranged on the cylinder wall of the first cylinder body 1 at the left side of the third; and a pulse electronic igniter 22 inserted into the second annular gap 2a from the outside of the body.

The working principle of the device of the utility model is that, at the initial stage, the driving motor 8 is started by an external power supply, the first driving disk 81 on the output shaft of the driving motor 8 drives the rotary protective shell 9 to rotate, and because the centrifugal air compressing blades 91 are arranged outside the rotary protective shell 9, the driving motor 8 rotates to drive the centrifugal air compressing blades 91 to rotate, low air pressure is formed to suck the air outside the engine into the engine; after entering the engine, a part of the air enters the fifth annular gap 5a at the outermost layer through the diffuser 92, enters the fourth annular gap 4a at the right end of the fifth annular gap 5a, and enters the second annular gap 2a at the left end of the fourth annular gap 4a as an oxidant for fuel combustion; another portion of the air enters the interior of the handpiece through diffuser 92; because the first cylinder 1 is close to the end as far as possible and sealed by the fixed bearing 15 and the third sealing ring 16, the left end between the second cylinder 2 and the fifth cylinder 5 is sealed by the second sealing ring 21, and the first cylinder 1 is close to the cylinder wall on the left side of the third sealing ring 16 and is also provided with the air hole 17 for connecting the inner space of the first cylinder 1 and the diffusion port 92, therefore, air enters the first cylinder 1 from the air hole 17 and is discharged along the right end opening of the first cylinder 1.

And the fuel enters the first annular gap 1a via the fuel inlet pipe 14, since the left end of the first annular gap 1a is sealed by the third seal ring 16, so that the fuel enters the first annular gap 1a and then enters the third annular gap 3a through the crescent passage of the fixed guide vane 13 at the right end of the first annular gap 1a, because the right end of the third annular gap is closed, the fuel is gathered into the second annular gap 2a from the outlet at the left end of the third annular gap 3a, after being sufficiently mixed with the air in the second annular gap 2a, is ignited by the pulse electronic igniter 22, the detonation wave is generated in the second annular gap 2a, one part of the detonation wave is reflected by the fixed guide vanes 13 at the right end of the second annular gap 2a, and the other part of the detonation wave is rushed out from the right end of the second annular gap 2a through the gaps among the fixed guide vanes 13, so that the rotating impeller 93 is driven to rotate and then is discharged from the tail part of the fourth cylinder 4 after being gathered. Meanwhile, the rotating impeller 93 can also drive the first driving disk 81 to rotate through the output shaft of the driving motor 8, so that the started driving motor 8 can automatically run in a power-off mode.

Because the knocking process is generated in the second annular gap 2a, and the pressure in the second annular gap 2a is increased in the knocking process, a part of the burnt gas mixture is pressed back into the third annular gap 3a and the fourth annular gap 4a, so that the function of isolating fuel and air is realized, and continuous ignition is prevented; after the detonation process in the initial stage is finished, the temperature in the machine body is increased due to a large amount of generated heat, so that subsequent fuel gasification is facilitated, the molecular movement rate is increased, and the air and the fuel gas are mixed more uniformly. Therefore, only a gaseous fuel such as natural gas or other gaseous fuel needs to be introduced at the initial stage.

As a preferred embodiment, a plurality of elongated ribs provided in the radial direction are provided inside the fifth annular gap 5a, the fourth annular gap 4a, the third annular gap 3a, and the first annular gap 1a, and the ribs divide the fifth annular gap 5a and the fourth annular gap 4a into a plurality of gas passages; because the knocking process is a process with high requirements for the strength of the device, a plurality of reinforcing ribs along the length direction of the cylinder body need to be arranged in the fifth annular gap 5a, the fourth annular gap 4a, the third annular gap 3a and the first annular gap 1a, so that the strength of the machine body is enhanced, and the machine body is prevented from being damaged.

As a preferred embodiment, the rotating casing 9 is provided with a diversion hole 95; the diversion hole 95 on the rotary protective shell 9 is used as a diversion hole of air flow, so that a part of air enters the machine head through the rotary protective shell 9 to cool the driving motor 8.

As a preferred embodiment, a pure oxygen inlet pipe 96 is arranged at the joint of the rotary protective shell 9 and the fifth annular gap 5 a; when the engine is in an ultra-high altitude or an outer space, and the engine cannot suck air into the engine body due to lack of outside air, oxygen needs to be artificially supplemented into the engine body through the pure oxygen inlet pipe 96 to ensure sufficient reaction of fuel in the second annular gap 2a, so as to ensure normal operation of the engine, prevent the problem that the energy conversion efficiency is influenced due to insufficient reaction or non-reaction, so as to ensure that the engine is independent of the dependence on the air or oxygen concentration of a working environment, and increase the universality of the engine.

As a preferred embodiment, the device further comprises a temperature sensor arranged in the fifth annular gap 5a and an air pressure sensor arranged on the sixth cylinder 6 and positioned corresponding to the rotary casing 9; the temperature sensor and the air pressure sensor play a role in monitoring the working condition in the machine body in real time, so that the introduction amount of fuel and air can be conveniently adjusted, and the device can be in the optimal working state at any time.

As a preferred embodiment, the cross sections of the fixed guide blades 13 and the impeller blades are both hollow crescent-shaped, and the rotating impeller 93 is connected with the output shaft of the driving motor 8 through the second driving disk 82; after the air passes through the fixed guide blades 13, because the shapes of the two sides of the fixed guide blades 13 are asymmetric, an angle deviating from the central axis of the machine body is formed, and the air is driven by the detonation waves to push the impeller blades; according to the Bernoulli principle, because the left side and the right side of the impeller blade are asymmetric in shape, the streamline on one side is dense, the flow rate is high, the streamline on the other side is comfortable, the flow rate is low, the pressure on one side of the impeller blade is high, the pressure on the other side of the impeller blade is low, a lateral pushing force is generated on the impeller blade, and meanwhile, because an included angle exists between the impeller blade and the airflow pushed by the detonation wave, the airflow directly generates a lateral pushing force on the impeller blade, and the impeller blade is facilitated to rotate under the action of the two pushing forces; meanwhile, compared with the traditional twisted impeller blade, the crescent straight blade is lower in manufacturing cost.

As a preferred embodiment, the second driving disk 82 is a solid disk and is provided with a plurality of through holes on the disk surface; after the air in the first cylinder 1 meets the second driving disk 82, because the second driving disk 82 is a solid disk, and only a plurality of through holes are arranged on the disk surface, the air pressure is increased, the air flow is divided into two parts, one part passes through the second driving disk 82 along the through holes and then is discharged along the air injection tail 94, and the other part is discharged along the gap between the air injection tail 94 and the fourth cylinder 4 after being discharged to the gap between the air injection tail 94 and the fourth cylinder 4 through the hollow centrifugal air compression blade, so that the cooling effect on the rotary impeller 93 is realized.

As a preferred embodiment, the centrifugal compressor blade 91 is in an inverted S shape and the length direction thereof is parallel to the central axis; rotation through centrifugal compressor blade 91 causes gas to advance along centrifugal compressor blade 91 'S bending direction, and form the pressure differential between the atmospheric environment, make outside air constantly be inhaled in the aircraft nose, simultaneously drive air advances along anti-S-shaped centrifugal compressor blade 91 under driving motor 8' S rotation, partly through reposition of redundant personnel hole 95 to driving motor 8 cool down back along gas pocket 17 along the inside jet-propelled tail 94 of passing through of first barrel 1 discharge, another part provides the air for the detonation reaction of fuselage constantly.

As a preferred embodiment, the right end of the fourth cylinder 4 is folded toward the central axis; so that the explosive gas driven by the detonation wave and the cooling gas exhausted by the impeller blades can better output work outwards.

Claims (9)

1. The pulse detonation engine is characterized by comprising a machine body and a machine head, wherein the machine body comprises six layers of cylinders which are sequentially arranged from inside to outside, a first sealing ring (11) is arranged at the right end of a first cylinder (1) at the innermost layer, an annular gap is reserved between a second cylinder (2) and the first sealing ring (11), the annular gap is sealed by a blade fixing ring (12) in a fixed impeller, and the fixed impeller further comprises a plurality of hollow fixed guide blades (13) which vertically penetrate through the blade fixing ring (12); a first annular gap (1 a) between the first cylinder (1) and the second cylinder (2) is communicated with a third annular gap (3 a) between the third cylinder (3) and the fourth cylinder (4) through the fixed guide vane (13), the right end of the third annular gap (3 a) is sealed, and the left end of the third annular gap is communicated with a second annular gap (2 a) between the second cylinder (2) and the third cylinder (3); the device is characterized by further comprising a fourth annular gap (4 a) between the fourth barrel (4) and the fifth barrel (5) and a fifth annular gap (5 a) between the fifth barrel (5) and the sixth barrel (6), wherein the left end of the fourth annular gap (4 a) is communicated with the second annular gap (2 a) through a mixing air chamber (7), and the right end of the fourth annular gap (4 a) is communicated with the right end of the fifth annular gap (5 a); the fuel inlet pipe (14) is communicated to the first annular gap (1 a) from the outside of the machine body, and the fuel enters the second annular gap (2 a) from the left side of the third annular gap (3 a) after passing through the first annular gap (1 a), the fixed guide vane (13) and the third annular gap (3 a) from the fuel inlet pipe (14) in sequence; the left end between the second cylinder (2) and the fifth cylinder (5) is sealed by a second sealing ring (21); the machine head comprises a driving motor (8) arranged at the left end of a central axis of the first barrel (1) and a hemispherical rotary protective shell (9) connected with a first driving disc (81) arranged on an output shaft of the driving motor (8), the outer wall of the rotary protective shell (9) is provided with a plurality of centrifugal air compression blades (91), a pressure expansion opening (92) is reserved between the rotary protective shell (9) and the sixth barrel (6), and the pressure expansion opening (92) is communicated with the fifth annular gap (5 a); an output shaft of the driving motor (8) penetrates through the first cylinder (1) along the central axis of the first cylinder (1) and then is fixedly connected with a rotating impeller (93), a plurality of impeller blades are arranged on the circumference of the rotating impeller (93), and the tail end of the rotating impeller (93) is connected with a conical air injection tail (94); the output shafts of the driving motors (8) are connected with the left end and the right end of the first cylinder (1) through inner rings of fixed bearings (15), and outer rings of the fixed bearings (15) are connected with the inner wall of the first cylinder (1); the fuel inlet pipe is characterized by further comprising a third sealing ring (16) arranged at the tail of the left end fixed bearing (15), the left end of the first annular gap (1 a) is sealed at the left side of the fuel inlet pipe (14) by the third sealing ring (16), an air hole (17) is further formed in the wall, located at the left side of the third sealing ring (16), of the first cylinder body (1), and the air hole (17) is connected with a diffusion opening (92) and the inner space of the first cylinder body (1); also comprises a pulse electronic igniter (22) inserted into the second annular gap (2 a) from the outside of the body.

2. A pulse detonation engine according to claim 1, characterised in that inside the fifth annular gap (5 a) and the fourth annular gap (4 a) are provided a plurality of radially arranged elongated ribs separating the fifth annular gap (5 a) and the fourth annular gap (4 a) into a plurality of gas passages.

3. A pulse detonation engine according to claim 1, characterised in that the rotating casing (9) is provided with a splitter aperture (95).

4. A pulse detonation engine according to claim 1, characterised in that a pure oxygen inlet duct (96) is provided at the junction of the rotating shroud (9) and the fifth annular gap (5 a).

5. A pulse detonation engine according to claim 1, characterised in that it further comprises a temperature sensor arranged in the fifth annular gap (5 a) and an air pressure sensor on the sixth cylinder (6) in a position corresponding to the rotating casing (9).

6. A pulse detonation engine according to claim 1, characterised in that the stationary guide vanes (13) and the impeller blades are hollow crescent shaped in cross-section and the rotating impeller (93) is connected to the output shaft of the drive motor (8) by a second drive disc (82).

7. A pulse detonation engine according to claim 6, characterised in that said second drive disc (82) is a solid disc with through holes in the disc face.

8. A pulse detonation engine as in claim 1, characterised in that said centrifugal compressor blades (91) are reverse S-shaped and have their length direction parallel to the central axis.

9. A pulse detonation engine as claimed in claim 1, characterised in that the circumferential central axis of the right end of the fourth cylinder (4) is convergent.

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