CN116201657A

CN116201657A - Deflagration engine

Info

Publication number: CN116201657A
Application number: CN202210659862.XA
Authority: CN
Inventors: 龙全洪
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-05-07
Filing date: 2022-05-07
Publication date: 2023-06-02
Also published as: WO2023216762A1

Abstract

The deflagration engine with the air inlet end not communicated with the fixed combustion chamber comprises an air inlet channel, a bearing, a shaft and an aircraft, and is characterized by further comprising a shell, a rotary cylinder, the fixed combustion chamber, end walls at two ends of the rotary cylinder, a rotary cylinder partition plate, an inner circular wall of the rotary cylinder, an uninterrupted fuel injector, an igniter, an air injection channel and an air leakage channel; the incoming flow entering from the air inlet channel enters into the rotary cylinder to push the rotor to rotate at a high speed, the rotary cylinder rotates to receive the injected fuel through the position of the uninterrupted fuel injector, the rotary cylinder continues to rotate to reach the position communicated with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber can carry out explosion compression on the mixture of the fuel and the air in the rotary cylinder, the mixture of the fuel and the air detonates to generate explosion shock wave, the explosion shock wave is sprayed out from the air injection channel, and the rotary cylinder rotates to be not communicated with the fixed combustion chamber, and then the waste gas left in the rotary cylinder is discharged to enter into the next working cycle.

Description

Deflagration engine

1. Technical field

The technology belongs to the engine

2. Background art

The existing three-way jet engines like turbojet engines, turbofan engines and ramjet engines are communicated with an air inlet end and an air injection end through a combustion chamber, the front pressure of the combustion chamber is far higher than the rear pressure to work normally, if the air pressure in the combustion chamber is too high, an air compressor cannot push air into the combustion chamber, so that an air jet port cannot jet out air flow of dozens of Mach or hundreds of Mach by adopting a means that the air jet port is much smaller than an air inlet, namely, an aircraft using the three-way jet engine as a propeller cannot realize hypersonic flight, the combustion effect is poor, the rocket has the defects that an oxidant is required to be carried, and the working medium of the rocket lacks the reverse thrust of nitrogen.

3. Summary of the invention

Aiming at the defects of the technology, the deflagration engine with an air inlet end not communicated with a fixed combustion chamber is designed.

The technical scheme adopted by the invention is as follows:

the deflagration engine with the air inlet end not communicated with the fixed combustion chamber and the rear pressure of the combustion chamber far higher than the front pressure comprises an air inlet channel, an air guide, a bearing, a shaft, an aircraft and the like, and is characterized by also comprising a shell, a rotary cylinder, the fixed combustion chamber, end walls at two ends of the rotary cylinder, a rotary cylinder baffle plate, an inner circular wall of the rotary cylinder, an uninterrupted fuel injector, an igniter, an air injection channel, a baffle plate and an air leakage channel; the inner circular wall of the rotary cylinder is fixedly connected to the shaft through the end walls at the two ends of the rotary cylinder to form an annular groove, the annular groove is equally divided into 12 identical rotary cylinders through 12 rotary cylinder partition boards, the two ends of the rotary cylinder partition boards are fixedly connected with the end walls at the two ends of the rotary cylinder in a sealing way, the inner side of the rotary cylinder partition boards are fixedly connected with the inner circular wall of the rotary cylinder in a sealing way, namely, the rotary cylinder partition boards are hollow plates, a space between the left side space and the right side space in the inner circular wall of the rotary cylinder is provided with a baffle board, the left side space in the inner circular wall is communicated with the left side interlayer space in the rotary cylinder partition board, the right side space in the inner circular wall is communicated with the right side interlayer space in the rotary cylinder partition board, and cooling air enters the interlayer space in the rotary cylinder partition board to cool the rotary cylinder partition boards after entering the left side space in the inner circular wall of the rotary cylinder partition boards from air holes in the end wall at the left end of the rotary cylinder, and then is discharged to the outside through the right side space in the inner circular wall of the rotary cylinder and the air holes in the end wall at the right end of the rotary cylinder partition boards; the rotor is formed by a shaft, end walls at two ends of a rotary cylinder, an inner circular wall of the rotary cylinder and a rotary cylinder partition plate, and the inner wall of a shell is engaged with a movement track when the rotor rotates, namely: the gap between the inner wall of the shell and the rotor is particularly small, but the inner wall of the shell does not prevent the rotor from rotating, and the bearings at the two ends of the rotor are limited on the shell by corresponding bearing sleeves; the bearing sleeve, the shell, the air inlet channel, the fixed combustion chamber, the air spraying channel and the air leakage channel are a fixedly connected whole, the fixedly connected whole is fixedly arranged on the aircraft, the air inlet channel is a gas channel for entering a deflagration engine by the incoming flow of the aircraft during the flight, namely, the speed difference ram air flow, whether a diffuser is required to be arranged in the gas channel is determined through experiments, whether an air guide is required to be arranged in the fixed combustion chamber is determined through experiments, the uninterrupted fuel injector comprises all devices for realizing the functions of the uninterrupted fuel injector, the nozzle of the uninterrupted fuel injector is fixed on the fixed combustion chamber, fuel is sprayed out from one gap of the uninterrupted fuel injector, the whole surface of the gap of the rotary cylinder, which faces the sprayed fuel, obtains the fuel after the rotary cylinder rotates through the uninterrupted fuel injector, the gas in the rotary cylinder passing through the uninterrupted fuel injector is subjected to the action of intense impact force, rebound force and centrifugal force within one hundredth of a second, so that the gas in the cylinder is intensely moved and forms intense movement airflow vortex, the intense movement gas is instantly and uniformly mixed with fuel obtained on the whole surface of the rotary cylinder, an igniter is fixed on a fixed combustion chamber, the igniter comprises other parts for realizing the functions of the igniter, the igniter does not need to be ignited again as long as the igniter is successfully ignited, the gas spraying channel is a gas channel for blasting deflagration gas in the fixed combustion chamber to the rear outside, the gas discharging channel is a gas channel for discharging high-pressure gas left in the rotary cylinder to the rear after the rotary cylinder is rotated to the rotary cylinder and is not communicated with the fixed combustion chamber, when the flying speed of an aircraft provided with the deflagration engine is greater than 120 km/h, when the rotary cylinder rotates to the position of the uninterrupted fuel injector, the outer edge of the rotary cylinder is meshed with the inner wall of the shell, the inner space of the rotary cylinder is not communicated with the outside, the fuel injected by the uninterrupted fuel injector is instantly mixed with the violently moving air which enters the rotary cylinder, after the rotary cylinder continues to rotate to the inner space of the rotary cylinder and is communicated with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber explosively compresses the violently moving mixture of the fuel and the air in the rotary cylinder, so that the mixture of the fuel and the air is exploded and scattered into the fixed combustion chamber to detonate, and then the explosion shock wave detonates the subsequent mixture of the fuel and the air in the rotary cylinder to detonate, the deflagration engine is connected with the explosion, generates extra-high pressure air flow to be sprayed to the rear of the aircraft from the air spraying channel at the speed of tens of Mach or hundreds of Mach, thereby generating huge propelling force to push the aircraft to fly at hypersonic or supersonic speed, subsonic speed can be set to fly if necessary, when the rotary cylinder continues to rotate to be not communicated with the fixed combustion chamber and only communicated with the air discharging channel, the burnt air remained in the rotary cylinder is discharged from the air discharging channel, when the rotary cylinder continues to rotate to be communicated with the air discharging channel and also communicated with the air inlet channel, the punching air entering from the air inlet channel enters the rotary cylinder to clean the rotary cylinder, so that waste gas remained in the rotary cylinder completely flows out from the air discharging channel, when the rotary cylinder continues to rotate to be communicated with the air inlet channel only, the punching air flows reenter the rotary cylinder, and pushes the rotor to rotate at high speed into the next working cycle.

The invention has the advantage 1 that the deflagration engine is characterized in that after air and fuel are uniformly mixed, the mixture is subjected to

The detonation shock wave generated in advance is stamped and mixed with the detonation fire to detonate, the combustion effect is not achieved by other jet engines, and the advantage of high efficiency and energy conservation of the detonation engine can be determined by good combustion effect.

2. The air inlet end of the deflagration engine is not communicated with the fixed combustion chamber, and the air inlet end is transported to the fixed combustion chamber by the rotary cylinder, so that no matter how large the pressure in the fixed combustion chamber is, the air at the air inlet end can not be influenced to effectively enter the fixed combustion chamber, the air injection passage of the deflagration engine can be made to be very small, and the air injection passage can be made to be as small as one tenth of that of an air inlet passage, so that huge pressure can be generated in the fixed combustion chamber, the air flow speed sprayed out by the air injection passage can reach dozens of Mach or hundreds of Mach, and the deflagration engine can push an aircraft to realize hypersonic flight, and the energy generated by the deflagration engine is efficiently converted into propulsion energy.

3. The detonation engine can be started as long as the speed per hour of the aircraft where the detonation engine is positioned reaches 120 km, so that the aircraft where the detonation engine is positioned can fly hypersonic, supersonic and subsonic; if the deflagration engine is used as an airplane propeller, a downhill runway is arranged at an airport, the deflagration engine can be started after the electromagnetic catapult or other propulsion mechanisms push the airplane to advance downwards for 120 km, and the airplane can take off after the deflagration engine pushes the airplane to advance on a horizontal runway and the speed of the plane can reach the take-off speed.

4. The deflagration engine has simple structure, simple working principle and extremely high energy effective utilization rate, other mechanisms except the oil supply mechanism can be manufactured by common mechanical manufacturers, the manufacturing cost is less than 1/10 of that of the turbofan engine, the thrust-weight ratio of the deflagration engine can exceed 100, and the deflagration engine can not reach any other jet engine, and can jet airflow of dozens of Mach or hundreds of Mach. The deflagration engine has various embodiments, can be made into deflagration jet engine started at zero forward speed, can be made into deflagration engine specially generating rotary power, and can be applied to various fields.

5. The interlayer space inside the rotor of the deflagration engine can be effectively cooled by using cooling gas, so that the highest temperature which can be born by the rotor of the deflagration engine can be improved.

4. Description of the drawings

Fig. 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, and 22 are schematic structural views of the deflagration engine of the present design. In FIG. 1, 77-aircraft, 50 a-inlet, 78-uninterruptible fuel injector, 1-enclosure, 89-air guide, 17-rotary cylinder, 11 a-shaft, 35 a-injection port, 44 a-stationary combustion chamber, 25-rotary cylinder inner wall, 18-rotary cylinder partition, 45 a-igniter, 51a, 51 b-bleed port. In fig. 2, 50 a-intake duct, 1-housing, 10a, 10 b-bearing, 44 a-stationary combustion chamber, 18-rotary cylinder partition, 88-baffle, 25-inner circular wall of rotary cylinder, 52a, 52 b-end walls at both ends of rotary cylinder, 35 a-jet duct, 11 a-axis. In fig. 3: 1-shell, 13-fixed baffle, 16a, 16 b-inlet communication port, 11 a-shaft. In fig. 4: 1-casing, 27 a-outer circular wall of rotary cylinder, 17-rotary cylinder, 18-rotary cylinder partition, 11 a-shaft, 25-inner circular wall of rotary cylinder. In fig. 5: 1-shell, 35a, 35 b-air injection passage, 29a, 29 b-deflagration communication port, 11 a-shaft, 30a, 30 b-fuel injection port, 34a, 34 b-air leakage port, 28-deflagration baffle. In fig. 6: 3-transmission shaft, 47-air compressor fan, 81-mechanism for injecting fuel from fuel injection port into rotary cylinder, 46-diffuser, 43-auxiliary machine, 13-fixed baffle, 37a, 37 b-bevel gear, 10a, 10 b-bearing, 1-casing, 80-annular baffle, 27a, 27 b-outer circular wall of rotary cylinder, 79a, 79 b-connecting plate, 29a, 29 b-detonation communication port, 28-detonation baffle, 17-rotary cylinder, inner circular wall of 25-rotary cylinder, 45a, 45 b-igniter, 42a, 42 b-inner circular wall of fixed combustion chamber, 44a, 44 b-fixed combustion chamber, 35a, 35 b-air injection passage, 11 a-axis. In FIG. 7, 28-deflagration baffle, 54a, 54 b-cooling gas passage, 1-housing, 29 a-deflagration port, 55-cooling gas inlet, 11 a-shaft, 16 a-intake port, 30 a-fuel injection port. In fig. 8: 17-rotary cylinder, 56-rotor air jet, 54a, 54 b-cooling air channel, 35 a-air jet channel, 1-casing, 18-rotary cylinder partition, 27a, 27 b-rotary cylinder outer circular wall, 25-rotary cylinder inner circular wall, 11 a-axis. In fig. 9: 57a, 57 b-bottom housing plates at the right end of the rotary cylinder, 58a, 58 b-cooling gas outlet, 11 a-axis. In fig. 10: 54. 54 b-cooling gas channel, 1-housing, 11 a-axis. In fig. 11: 54a, 54 b-cooling gas passages, 62-compressors, 27a, 27 b-outer circumferential walls of rotary cylinders, 25-inner circumferential walls of rotary cylinders, 81-means for injecting fuel from a fuel injection port into rotary cylinders, 29 a-knock communication ports, 17-rotary cylinders, 44 a-stationary combustion chambers, 28-knock baffles, 60-thrust bearings, bottom plates at right ends of 57a, 57 b-rotary cylinders, 35 a-injection passages, 10 b-bearings, 11 a-shafts, 59-bearing holders in-body with bearing bushes, 16 a-intake communication ports. In fig. 12: 9 a-end wall of the horizontal rotating rotor, 1-casing, 6a, 6b, 6c, 6 d-horizontal rotating shaft, 2-fixed shaft. In fig. 13: 1-casing, 21a, 21 b-exhaust port, 22a, 22b, 22c, 22 d-plug, 5a, 5b, 5c, 5 d-flat-turning piston, 86a, 86 b-flat-turning cylinder, 6a, 6b, 6c, 6 d-flat-turning shaft, 20a, 20 b-air inlet, 2-fixed shaft, 24a, 24 b-choke, 8-demarcation device, 68-flat-turning compressor. In fig. 14: 1-casing, 6a, 6b, 6c, 6 d-flat shaft, 7a, 7b, 7c, 7 d-flat gear, 15a, 15b, 15c, 15 d-drive gear, 4a, 4b, 4c, 4 d-drive gear shaft, 26-fixed gear, 11 b-shaft. In fig. 15: the device comprises a 1-shell, a 2-fixed shaft, 4a, 4 c-transmission gear shafts, 5a, 5 c-flat rotating pistons, 6a, 6 c-flat rotating shafts, 7a, 7 b-flat rotating gears, 8-demarcation devices, 9a, 9 b-flat rotating rotor end walls, 10a, 10 b-bearings, 11a, 11 b-shafts, 15a, 15 c-transmission gears, 16 a-air inlet communication ports, 17-rotating cylinders, 23a, 23 b-air storage cooling grooves, inner circular walls of 25-rotating cylinders, 26-fixed gears, 27a, 27 b-outer circular walls of rotating cylinders, 28-baffle plates, 29 a-explosion communication ports, 35 a-air spraying passages, 44 a-fixed combustion chambers, 54 b-cooling air passages, bottom shell plates at the right ends of 57a, 57 b-rotating cylinders, 59-bearing brackets with bearing sleeves as bodies, 60-thrust bearings and 68-flat rotating compressors. In fig. 16: 1-casing, 2-fixed axle, 5a, 5b, 5c, 5 d-flat-turning piston, 6a, 6b, 6c, 6 d-flat-turning axle, 8-demarcation device, 20a, 20 b-air inlet, 21a, 21 b-air outlet, 22a, 22b, 22c, 22 d-blocking, 24 a-choke, 86a, 86 b-flat-turning cylinder, 69-flat-turning engine. In fig. 17: 1-shell, 11 b-shaft, 17-rotary cylinder, 18-rotary cylinder partition, 25-inner circular wall of rotary cylinder, 27 a-outer circular wall of rotary cylinder. In fig. 18: 1-casing, 11 b-shaft, 16 a-intake communication port, 28-knock baffle, 29 a-knock communication port, 30 a-fuel injection port, 34 a-bleed port. In fig. 19: 1-casing, 2-fixed axle, 4a, 4 c-transmission gear axle, 5a, 5 c-flat rotary piston, 6a, 6 c-flat rotary axle, 7a, 7 b-flat rotary gear, 8-demarcation device, 9a, 9 b-flat rotary rotor end wall, 10a, 10 b-bearing, 11a, 11 b-axle, 15a, 15 c-transmission gear, 16 a-air inlet communication port, 17-revolving cylinder, 25-revolving cylinder inner circular wall, 26-fixed gear, 27a, 27 b-revolving cylinder outer circular wall, 28-deflagration baffle, 29 a-deflagration communication port, 44 a-fixed combustion chamber, 57 a-revolving cylinder right end bottom shell plate, 60-thrust bearing, 66-deflagration communication port, 69-flat forward engine. In fig. 20: 86a, 86 b-flat turning cylinders, 1-casing, 2-fixed shaft, 5a, 5b, 5c, 5 d-flat turning pistons, 6a, 6b, 6c, 6 d-flat turning shafts, 8-delimiters, 21a, 21 b-exhaust ports, 22a, 22b, 22c, 22 d-plug flow, 24a, 24 b-choke, 68-flat turning compressor, 50 b-inlet duct. In fig. 21: 1-shell, 11 a-shaft, 17-rotary cylinder, 18-rotary cylinder partition, 25-inner circular wall of rotary cylinder, 35 a-jet channel, 40-high-pressure gas inlet, 44 a-fixed combustion chamber, 45 a-igniter, 50 a-inlet channel, 51a, 51 b-gas discharge channel, 53-oxygen inlet and 78-uninterrupted fuel injector. In fig. 22: 1-casing, 2-fixed shaft, 4b, 4 d-transmission gear shaft, 5b, 5 d-flat rotating piston, 6b, 6 d-flat rotating shaft, 7c, 7 d-flat rotating gear, 8-demarcation device, 9a, 9 b-flat rotating rotor end wall, 10a, 10b, 10 c-bearing, 11a, 11 b-shaft, 15b, 15 d-transmission gear, 18-revolving cylinder baffle, 25-revolving cylinder inner circular wall, 26-fixed gear, 35 a-spraying channel, 44 a-fixed combustion chamber, 50 b-air inlet channel, 52a, 52 b-revolving cylinder end wall, 68-flat rotating compressor, 43-appendage.

5. Detailed description of the preferred embodiments

1. A fan-pressure deflagration engine started at zero forward speed is shown in the specific structure of figures 3, 4, 5 and 6. The fan-pressure deflagration engine comprises a casing 1,

bearings

10a and 10b, a transmission shaft 3, connecting

plates

79a and 79b,

bevel gears

37a and 37b,

igniters

45a and 45b, a compressed air fan 47, a diffuser 46, a mechanism 81 for injecting fuel into a rotary cylinder from a fuel injection port, an auxiliary machine 43 and a shaft 11a, and is characterized by further comprising fixed baffles 13, air

inlet communication ports

16a and 16b, outer

circular walls

27a and 27b of the rotary cylinder, rotary cylinder partition plates 18, annular partition plates 80, rotary cylinders 17, inner circular walls 25 of the rotary cylinder, deflagration baffles 28,

deflagration communication ports

29a and 29b,

air injection channels

35a and 35b,

fuel injection ports

30a and 30b,

air leakage ports

34a and 34b, inner circular walls 42a and 42b of

fixed combustion chambers

44a and 44b; the inner circular wall 25 of the rotary cylinder is fixedly connected to the shaft 11a through the

connection plates

79a, 79b fixed to the shaft 11a, the outer

circular wall

27a, 27b of the rotary cylinder is fixedly connected to the inner circular wall 25 of the rotary cylinder through 15 rotary cylinder partition plates 18 fixedly connected to the inner circular wall 25 of the rotary cylinder, the 15 rotary cylinder partition plates divide the annular space between the inner circular wall 25 of the rotary cylinder and the outer

circular wall

27a, 27b of the rotary cylinder into 15 rotary cylinders, the fixed connection body is combined with the bevel gear 37a fixed to the shaft 11a, the annular partition plates 80 and the air compressing fan 47 to form the rotor of the engine, the interlayer space of one rotary cylinder partition plate 18 is divided into a left space and a right space through a rectangular steel plate, cooling air enters the left space of the annular partition plate 80 from the shaft hole and then enters the interlayer space of the outer circular wall of the rotary cylinder through the left interlayer space of the rotary cylinder partition plate 18 and moves rightward, the cooling air moving rightward enters the right space of the annular partition plate 80 through the right interlayer space of the rotary cylinder partition plate behind the cooling air, and is discharged to the outside through the shaft hole, so that the part needing cooling inside the rotor is effectively cooled, the rotor is not damaged due to the fact that the temperature inside the rotor is too high, the air compressing fan is a fan of a turbofan engine, only a large number of air compressing fans are reduced in proportion, a bearing sleeve which is arranged in the middle of the diffuser and is integrated with the diffuser into a whole is sleeved on a bearing 10a, the bearing 10a is sleeved on a shaft 11a, the outer edge of the diffuser is fixedly connected with a casing, the outer edge of a fixed baffle plate 13 at the front end of the rotary cylinder is fixedly connected with the casing, two bearings which are sleeved on a transmission shaft are limited by two bearing sleeves are fixedly connected with the fixed baffle plate 13, so that a bevel gear 37b fixedly connected with the transmission shaft is meshed with a bevel gear 37a fixed on the shaft, the rotary power generated by the auxiliary machine 43 for generating rotary power can be effectively transmitted to the rotor, the fixed baffle at the front end of the rotary cylinder is provided with air

inlet communication ports

16a and 16b, a shaft hole capable of penetrating through the shaft 11a is arranged on the fixed baffle, the outer edge of the deflagration baffle 28 between the rotary cylinder and the fixed combustion chamber is fixedly connected with the shell, the shaft hole in the middle part is sleeved on the shaft 11a,

deflagration communication ports

29a and 29b are arranged on the deflagration baffle, the

fuel injection ports

30a and 30b and the

air discharge ports

34a and 34b, and when the rotor rotates, the left end of each part forming the rotary cylinder is meshed with the fixed baffle 13 at the air inlet end, the right end is meshed with the deflagration baffle 28, and the clearance is small after the meshing; when the fan-pressure deflagration engine works, the air inlet end is not communicated with the fixed combustion chamber, compressed air generated by the air compressing fan is conveyed to the position of the fuel injection port by one cylinder of the rotary cylinder to receive injected fuel, then the injected fuel is conveyed to the position communicated with the fixed combustion chamber to receive the explosive compression of the explosion shock wave of the fixed combustion, the fuel and air mixture subjected to the explosive compression is deflagrated into the fixed combustion chamber and is sprayed out from the air injection passage behind the fixed combustion chamber, so that huge thrust is obtained to push an aircraft where the fan-pressure deflagration engine is positioned to fly at hypersonic or supersonic speed, the rotary cylinder rotates to the outside after the rotary cylinder is not communicated with the fixed combustion chamber, the waste gas left in the rotary cylinder is discharged to the outside behind through the air passage communicated with the air discharge port, and the compressed air generated by the air compressing fan is received again when the abandoned rotary cylinder rotates to the position communicated with the air inlet port, and enters the next working cycle, and the fan-pressure deflagration engine is started under the condition of zero forward speed of the aircraft where the fan-pressure deflagration engine is positioned.

2. The specific structure of the deflagration rotary jetting engine is as shown in fig. 7, 8, 9, 10 and 11, the deflagration rotary jetting engine comprises a shell 1, a bearing 10b, a shaft 11a, a gas compressor 62, a mechanism 81 for jetting fuel from a fuel jetting port into a rotary cylinder, and the deflagration rotary jetting engine is characterized by further comprising a deflagration baffle 28,

cooling gas passages

54a and 54b, a deflagration communication port 29a, a cooling gas inlet 55, a fuel jetting port 30a, an air inlet communication port 16a, a gas jetting passage 35a, a rotor jetting port 56, the rotary cylinder 17, a rotary cylinder partition plate 18, an inner circular wall 25 of the rotary cylinder, outer

circular walls

27a and 27b of the rotary cylinder,

bottom shell plates

57a and 57b at the right end of the rotary cylinder,

cooling gas outlets

58a and 58b, a fixed combustion chamber 44a and a thrust bearing 60 and a bearing bracket 59 integrated with a bearing sleeve; the compressor 62 may be a low-pressure compressor part of a turbofan engine or other compressors, the compressor includes a start motor, the compressor may share the shaft 11a and is provided with a bearing support shaft 11a, the compressor is not required to generate too much gas pressure, first,

bottom shell plates

57a and 57b at the right end of the rotary cylinder are fixedly connected to the shaft 11a, then, the inner circular wall 25 of the rotary cylinder and outer

circular walls

27a and 27b of the rotary cylinder are fixedly connected to the bottom shell plates at the right end of the rotary cylinder, then, 10 rotary cylinder separators 18 are fixedly connected to an annular groove between the inner circular wall of the rotary cylinder and the outer circular wall of the rotary cylinder, the annular groove is equally divided into 10 rotary cylinders with the same shape by the 10 rotary cylinder separators, the fixedly connected parts of the compressor 62 and the fixedly connected to the shaft 11a form a rotor of the deflagration rotary jet engine, when the rotor rotates, the left end of the component forming the rotary cylinder is meshed with the deflagration baffle, the pumping hole in the middle of the deflagration baffle 28 is sleeved on the shaft 11a, the outer edge of the deflagration baffle 28 is fixedly connected with the shell, the outer edge of the bearing bracket 59 integrated with the bearing sleeve is fixedly connected with the shell, the bearing sleeve in the middle is sleeved on the bearing 10b, cooling gas enters the annular space between the inner circular wall 25 of the rotary cylinder and the shaft 11a from the cooling gas inlet 55, then enters the interlayer space of the outer

circular walls

27a and 27b of the rotary cylinder through the interlayer space of the rotary cylinder partition 18, then flows out from the

cooling gas outlets

58a and 58b, a rotor air nozzle 56 is arranged on the outer circular wall of the rotary cylinder of each rotary cylinder, if the rotary jet engine is used as a machine for generating rotary power, the rotor air nozzle for tangential ejection is needed, and the air outlet of the air duct 35a is needed to be made larger, if the detonation transfer engine is used as a jet engine, the intersection angle of the center line of the rotor jet opening and the radius is about 130 degrees, the gas outlet of the jet air duct 35a is smaller, the detonation transfer engine can be started by a starting motor under the condition of no forward speed, compressed air generated by the air compressor 62 enters the rotary cylinder from the air inlet communication port 16a after the detonation transfer engine is started, when the rotary cylinder of the detonation transfer engine rotates to be communicated with the air inlet communication port 16a, compressed air pressurized by the air compressor 62 quickly enters the rotary cylinder, when the rotary cylinder continues to rotate away from the air inlet communication port to receive fuel injected from the fuel injection port 30a, the rotary cylinder starts to be communicated with the fixed combustion chamber, the explosion fire in the fixed combustion chamber enters the rotary cylinder from one side to perform explosive compression combustion on the fuel and air mixture in the rotary cylinder, then the fixed volume is heated, when the rotary cylinder rotates to the position that the opening of the rotary cylinder completely faces the fixed combustion chamber, the combusted fuel and air mixture in the rotary cylinder expands and explodes to enter the fixed combustion chamber, and the explosion fire is sprayed into the air spraying channel from the rotor air spraying port communicated with the fixed combustion chamber, so that rotary thrust is obtained to push the rotor to rotate, meanwhile, the deflagration gas sprayed into the air spraying channel is sprayed backward from the air spraying channel, so that huge propulsive force is obtained to push an aircraft where the deflagration rotary jet engine is positioned to perform hypersonic flight, after the rotary cylinder continues to rotate and is not communicated with the fixed combustion chamber, the gas remained in the rotary cylinder continues to be sprayed from the rotor port, and when the rotary cylinder rotates to the rotor air spraying port is blocked by the inner wall of the casing, the gas in the rotary cylinder is basically sprayed, when the rotary cylinder rotates to communicate with the intake communication port 16a, the compressed air pressurized by the compressor 62 rapidly enters the rotary cylinder again to enter the next working cycle.

3. A flat-pressure deflagration engine, the specific structure of which is shown in fig. 12, 13, 14, 7, 8, 9 and 15, comprises a shell 1, flat-rotating

rotor end walls

9a and 9b, a fixed shaft 2, flat-rotating

cylinders

86a and 86b, flat-rotating

shafts

6a, 6b, 6c and 6d, flat-

rotating gears

7a, 7b, 7c and 7d,

transmission gears

15a, 15b, 15c and 15d,

transmission gear shafts

4a, 4b, 4c and 4d, fixed gears 26,

cooling gas channels

54a and 54b,

shafts

11a and 11b, cooling gas inlets 55, deflagration baffles 28, deflagration communication ports 29a, air inlet ports 16a, fuel injection ports 30a, rotating cylinders 17, rotor ports 56, air injection channels 35a, rotating cylinder separators 18, outer

circular walls

27a and 27b of the rotating cylinders, inner circular walls 25 of the rotating cylinders,

bottom shell plates

57a and 57b at the right ends of the rotating cylinders,

cooling gas outlets

58a and 58b,

bearing chambers

10a and 10b, bearings 20a and 24b, and air inlet ports 5b, and air-

piston housings

20a and 20b, and air-

intake ports

20b, and 20 c and 20b, respectively; the flat rotary shaft and the flat rotary piston are limited by gears and can only rotate in parallel, namely, the direction opposite to the upper edge of the flat rotary piston in the rotating process is always unchanged, the flat rotary gear 7a, the flat rotary shaft 6a and the flat rotary piston 5a are fixed connectors, the

flow blocking plugs

22a, 22b, 22c and 22d are fixed between the flat rotary end wall 9a and the flat rotary end wall 9b, the flat

rotary end walls

9a and 9b are fixedly connected on the shaft 11a, the delimiter is fixedly connected on the shell through a fixed shaft, the narrowest channel between the delimiter and the shell is called a choke 24a and 24b, the choke only allows the flat rotary piston, the flat rotary shaft and the flow blocking plug to pass, and when the flat compression deflagration engine rotates, air entering the flat rotary cylinder 86b from the air inlet 20a is compressed by the flat rotary piston 5c and then enters the air

storage cooling grooves

23a and 23b through the air channels communicated with the air outlet 21b, air entering the horizontal rotary cylinder 86a from the air inlet 20b is compressed by the horizontal rotary piston 5a and then enters the air

storage cooling grooves

23a and 23b through the air channel communicated with the air outlet 21a, when the rotary cylinder rotates to be communicated with the air storage cooling grooves through the air inlet communication port 16a, compressed air in the air storage cooling grooves can quickly enter the rotary cylinder through the air inlet communication port, when the rotary cylinder continues to rotate, after the rotary cylinder leaves the air inlet communication port and reaches the position of the fuel injection port 30a to receive fuel injected from the fuel injection port, the rotary cylinder starts to be communicated with the fixed combustion chamber, the explosion fire in the fixed combustion chamber explosively compresses and combusts the fuel and air mixture in the rotary cylinder, when the rotary cylinder rotates to the position that the rotary cylinder is completely opposite to the fixed combustion chamber, the mixed combustion gas in the rotary cylinder expands and explodes into the fixed combustion chamber, and is injected into the air injection passage from the rotor port communicated with the fixed combustion chamber, the rotary cylinder continues to rotate until the nozzle of the rotor jet is blocked by the inner wall of the shell, and after the gas in the rotary cylinder is basically completely sprayed, the compressed gas in the gas storage cooling tank is received again to enter the next working cycle at the position reaching the air inlet communication port 16 a.

4. The deflagration flat-forward engine for producing rotary power is characterized by that, as shown in figures 12, 16, 14, 18, 17, 9 and 19, it includes a casing 1, flat-

rotor end walls

9a, 9b, a fixed shaft 2, flat-rotating

pistons

5a, 5b, 5c and 5d, flat-rotating

shafts

6a, 6b, 6c and 6d, a demarcation device 8,

air inlets

20a and 20b,

air outlets

21a and 21b, flow-blocking

plugs

22a, 22b, 22c and 22d, choke 24a, flat-rotating

cylinders

86a and 86b, flat-rotating

gears

7a, 7b, 7c and 7d,

transmission gears

15a, 15b and 15c and 15d, the engine is characterized by further comprising a detonation communication port 66 and a flat forwarding engine 69, wherein the detonation flat forwarding engine comprises a detonation communication port 30, a fuel injection port 30a, a gas leakage port 34a, a rotary cylinder 17, a rotary cylinder partition 18, an inner circular wall 25 of the rotary cylinder, a thrust bearing 60, outer

circular walls

27a and 27b of the rotary cylinder,

bottom shell plates

57a and 57b at the right end of the rotary cylinder and

cooling gas outlets

58a and 58 b; when the rotary cylinder having entered the compressed air rotates to the position of the fuel injection port 30a and receives the fuel injected from the fuel injection port, the rotary cylinder is gradually communicated with the fixed combustion chamber, the compressed air and the fuel mixture in the rotary cylinder are subjected to explosion compression detonation of the fixed combustion chamber to generate explosion shock waves, the explosion shock waves enter the rotary cylinder 86a through a gas channel between the explosion port 66 and the air inlet 20a to push the rotary piston to do work on the outside in parallel, the compressed air discharged from the air outlet 21a enters the rotary cylinder through a gas channel communicated with the air outlet 21a and the air inlet communication port 16a, and after the compressed air enters the rotary cylinder rotates to the position of the fuel injection port 30a and receives the fuel injected from the fuel injection port, the rotary cylinder is gradually communicated with the fixed combustion chamber, the compressed air and the fuel mixture in the rotary cylinder are subjected to explosion compression detonation of the fixed combustion chamber to generate explosion shock waves, the explosion shock waves enter the rotary cylinder 86a between the explosion port 66 and the air inlet 20a to push the rotary piston to do work on the outside in parallel, the compressed air discharged from the air outlet 21b after the work on the rotary cylinder is completed, the mixed body in the rotary cylinder is rotated to the rotary cylinder is discharged from the rotary cylinder and the rotary cylinder to continue to rotate to the rotary cylinder after the rotary combustion chamber is discharged from the rotary cylinder and the compressed air is discharged from the rotary cylinder.

5. A deflagration engine, the specific structure of which is shown in fig. 12, 20, 14, 21 and 22, the deflagration engine comprises a casing 1, flat

rotor end walls

9a and 9b, flat rotating

shafts

6a, 6b, 6c and 6d, a fixed shaft 2, flat rotating

cylinders

86a and 86b, flat rotating

pistons

5a, 5b, 5c and 5d, a demarcation device 8,

exhaust ports

21a and 21b, blocking

plugs

22a, 22b, 22c and 22d, choke ports 24a and 24b, a flat rotating compressor 68,

air inlets

50a and 50b, flat rotating

gears

7a, 7b, 7c and 7d,

transmission gears

15a and 15b, 15c and 15d,

transmission gear shafts

4a, 4b, 4c and 4d, a rotary cylinder 17, a rotary cylinder partition 18, an inner circular wall 25 of the rotary cylinder, an air passage 35a, a fixed combustion chamber 44a, an igniter 45a,

air release passages

51a and 51b, uninterrupted fuel injectors 78,

bearings

10a and 10b, 10a and 11b, and high pressure air inlet ports 52, and high pressure engine inlet ports 52, respectively, and high pressure air inlets 52; a flat-turning piston, a flat-turning shaft and a flat-turning gear set are combined into a fixed connecting body, the flat-turning piston is limited to only rotate in parallel through gear transmission, a gas switch on an oxygen inlet 53 is closed in normal time, the gas switch on the oxygen inlet is opened only when the gas entering the rotary cylinder cannot meet the explosion requirement, oxygen enters the rotary cylinder to support combustion, the gas switch on the oxygen inlet is closed when oxygen is not needed to support combustion, high-pressure air exhausted from an exhaust port 21a and an exhaust port 21b enters the rotary cylinder from a high-pressure gas inlet 40 through a gas channel, when the deflagration engine pushes an aircraft to fly at hypersonic speed, the openings of

air inlets

50a and 50b face to the front, incoming flows enter the rotary cylinder from the air inlet 50a, incoming flows enter the flat-

turning cylinders

86a and 86b from the air inlet 50b, the gas entering the parallel rotating

cylinders

86a, 86b is pushed into high-pressure gas by the parallel rotating

pistons

5a, 5c and then enters the rotating cylinders through the gas channels to be mixed with the gas entering from the air inlet channel 50a, so that sufficient high-pressure gas exists in the rotating cylinders, when the rotating cylinders rotate and receive injected fuel through the uninterrupted fuel injector 78, the rotating cylinders are gradually communicated with the fixed combustion chamber 44a, the explosion fire of the fixed combustion chamber explosively compresses and detonates the mixture of the high-pressure gas and the fuel in the rotating cylinders, the mixture of the high-pressure gas and the fuel detonates to generate severe shock waves to be ejected from the air inlet channel 35a, thereby obtaining huge propelling force to push the aircraft where the detonation engine is located to fly hypersonic or supersonic speed, when the rotating cylinders continue to rotate and leave the fixed combustion chamber, the waste gas left in the rotating cylinders leaks out of the

air outlet channels

51a, 51b, the rotating cylinders receive the incoming face incoming flow from the air inlet channel again, the next cycle is entered, and the deflagration engine can be started without forward speed because the deflagration engine comprises an auxiliary engine and a flat compressor.

Claims

1. The deflagration engine with the air inlet end not communicated with a fixed combustion chamber and the pressure at the rear part of the combustion chamber being far higher than the pressure at the front part comprises an air inlet channel (50 a), an air guide (89), bearings (10 a and 10 b), a shaft (11 a), an aircraft (77) and the like, which are the prior art, and is characterized by further comprising a shell (1), a rotary cylinder (17), a fixed combustion chamber (44 a), end walls (52 a and 52 b) at the two ends of the rotary cylinder, a rotary cylinder baffle plate (18), an inner circular wall (25) of the rotary cylinder, an uninterrupted fuel injector (78), an igniter (45 a), an air injection channel (35 a), a baffle plate (88) and air leakage channels (51 a and 51 b); the inner circular wall of the rotary cylinder is fixedly connected to the shaft through the end walls at the two ends of the rotary cylinder to form an annular groove, the annular groove is equally divided into 12 identical rotary cylinders through 12 rotary cylinder partition boards, the two ends of the rotary cylinder partition boards are fixedly connected with the end walls at the two ends of the rotary cylinder in a sealing way, the inner side of the rotary cylinder partition boards are fixedly connected with the inner circular wall of the rotary cylinder in a sealing way, namely, the rotary cylinder partition boards are hollow plates, namely, interlayer spaces are reserved in the rotary cylinder partition boards, cooling air enters the left side space inside the inner circular wall of the rotary cylinder from air holes in the end wall at the left end of the rotary cylinder, then enters the interlayer spaces of the rotary cylinder partition boards to cool the rotary cylinder partition boards, and then the cooling air is discharged to the outside through the right side space inside the inner circular wall of the rotary cylinder and the air holes in the end wall at the right end of the rotary cylinder; the rotor is formed by a shaft, end walls at two ends of a rotary cylinder, an inner circular wall of the rotary cylinder and a rotary cylinder partition plate, and the inner wall of a shell is engaged with a movement track when the rotor rotates, namely: the gap between the inner wall of the shell and the rotor is particularly small, but the inner wall of the shell does not prevent the rotor from rotating, and the bearings at the two ends of the rotor are limited on the shell by corresponding bearing sleeves; the bearing sleeve, the shell, the air inlet channel, the fixed combustion chamber, the air spraying channel and the air discharging channel are a fixedly connected whole, the fixedly connected whole is fixedly arranged on the aircraft, when the flying speed of the aircraft provided with the deflagration engine is greater than 120 km/h, the incoming flow entering from the air inlet channel, namely, the speed difference stamping airflow, can enter the rotary cylinder and push the rotor to rotate at high speed by pushing the rotary cylinder baffle, when the rotary cylinder rotates to the position of the uninterrupted fuel injector, the outer edge of the rotary cylinder is engaged with the inner wall of the shell, the inner space of the rotary cylinder is not communicated with the outside, the fuel sprayed by the uninterrupted fuel injector is instantly and uniformly mixed with the air which enters the rotary cylinder and moves vigorously, the explosion shock wave in the fixed combustion chamber can explosively compress the mixture of the fuel and the air which move vigorously in the rotary cylinder, so that the mixture of the fuel and the air is exploded and scattered into the fixed combustion chamber to be detonated, then the explosion shock wave detonates the mixture of the fuel and the air in the rotary cylinder behind the fixed combustion chamber to detonate, the detonation engine is exploded and detonated in such a way, the explosion is connected, ultrahigh-pressure airflow is generated to be exploded and sprayed from the air spraying channel to the rear of the aircraft at the speed of dozens of Mach or hundreds of Mach, so that huge propelling force is generated to push the aircraft to perform hypersonic or supersonic flight, if necessary, subsonic flight can be realized, when the rotary cylinder continues to rotate to be not communicated with the fixed combustion chamber, the burnt gas remained in the rotary cylinder leaks from the air discharging channel when the rotary cylinder continues to rotate to be communicated with the air discharging channel and the air inlet channel, the punching air flow entering from the air inlet channel enters the rotary cylinder to clean the rotary cylinder, so that waste gas left in the rotary cylinder completely flows out of the air leakage channel, and when the rotary cylinder continues to rotate until the rotary cylinder is communicated with the air inlet channel only, the punching air flow can reenter the rotary cylinder and push the rotor to rotate at a high speed to enter the next working cycle; the deflagration engine is characterized in that after air and fuel are uniformly mixed, the mixture is stamped by the deflagration shock wave generated in advance and is mixed with the detonation fire to deflagrate, the combustion effect is not achieved by other jet engines, and the advantages of high efficiency and energy conservation of the deflagration engine can be determined with good combustion effect; the air inlet end of the deflagration engine is not communicated with the fixed combustion chamber, and the air inlet end is transported to the fixed combustion chamber by the rotary cylinder, so that no matter how large the pressure in the fixed combustion chamber is, the air at the air inlet end can not be influenced to effectively enter the fixed combustion chamber, the air injection passage of the deflagration engine can be made to be very small, and the air injection passage can be made to be as small as one tenth of that of an air inlet passage, so that huge pressure can be generated in the fixed combustion chamber, the air flow speed sprayed out by the air injection passage can reach dozens of Mach or hundreds of Mach, and the deflagration engine can push an aircraft to realize hypersonic flight, and the energy generated by the deflagration engine is efficiently converted into propulsion energy.

2. A fan-pressure deflagration engine started at zero forward speed, comprising a casing (1), bearings (10 a, 10 b), a transmission shaft (3), connection plates (79 a, 79 b), bevel gears (37 a, 37 b), igniters (45 a, 45 b), a compressed air fan (47), a diffuser (46), a mechanism (81) for injecting fuel from a fuel injection port into a rotary cylinder, an auxiliary machine (43) and a shaft (11 a), and being characterized by further comprising a fixed baffle (13), air inlet communication ports (16 a, 16 b), outer circumferential walls (27 a, 27 b) of the rotary cylinder, a rotary cylinder partition plate (18), an annular partition plate (80), a rotary cylinder (17), inner circumferential walls (25) of the rotary cylinder, a deflagration baffle (28), deflagration ports (29 a, 29 b), air injection channels (35 a, 35 b), fuel injection ports (30 a, 30 b), air release ports (34 a, 34 b), inner circumferential walls (42 a, 42 b) of a fixed combustion chamber, and fixed combustion chamber (44 a, 44 b); the inner circular wall (25) of the rotary cylinder is fixedly connected to the shaft (11 a) through connecting plates (79 a, 79 b) fixed to the shaft (11 a), the outer circular wall (27 a, 27 b) of the rotary cylinder is fixedly connected to the inner circular wall (25) of the rotary cylinder through 15 rotary cylinder partition plates (18) fixedly connected to the inner circular wall (25) of the rotary cylinder, the 15 rotary cylinder partition plates divide the annular space between the inner circular wall (25) of the rotary cylinder and the outer circular walls (27 a, 27 b) of the rotary cylinder into 15 rotary cylinders, and the fixed connecting body is combined with a bevel gear (37 a), an annular partition plate (80) and a compressed air fan (47) fixed to the shaft (11 a) to form the rotor of the engine; when the fan-pressure deflagration engine works, the air inlet end is not communicated with the fixed combustion chamber, compressed air generated by the air compressing fan is conveyed to the position of the fuel injection port by one cylinder of the rotary cylinder to receive injected fuel, then the injected fuel is conveyed to the position communicated with the fixed combustion chamber to receive the explosive compression of the explosion shock wave of the fixed combustion, the fuel and air mixture subjected to the explosive compression is deflagrated into the fixed combustion chamber and is sprayed out from the air injection channel behind the fixed combustion chamber, so that huge thrust is obtained to push an aircraft where the fan-pressure deflagration engine is positioned to fly hypersonic or hypersonic, the rotary cylinder rotates to the outside of the rear through the air passage which is not communicated with the fixed combustion chamber, and the waste gas left in the rotary cylinder is discharged to the outside through the air passage which is communicated with the air discharge port, and the compressed air generated by the air compressing fan is received again when the rotary cylinder rotates to the position communicated with the air inlet communication port, and then the next working cycle is started.

3. The deflagration rotary jetting engine comprises a casing (1), a bearing (10 b), a shaft (11 a), a gas compressor (62) and a mechanism (81) for jetting fuel into a rotary cylinder from a fuel jetting port, and is characterized by further comprising deflagration baffles (28), cooling gas channels (54 a and 54 b), a deflagration communication port (29 a), a cooling gas inlet (55), a fuel jetting port (30 a), an air inlet communication port (16 a), a gas jetting channel (35 a), a rotor jet port (56), the rotary cylinder (17), a rotary cylinder partition plate (18), an inner circular wall (25) of the rotary cylinder, outer circular walls (27 a and 27 b) of the rotary cylinder, bottom shell plates (57 a and 57 b) at the right end of the rotary cylinder, cooling gas outlets (58 a and 58 b), a fixed combustion chamber (44 a), a thrust bearing (60) and a bearing bracket (59) integrated with a bearing sleeve; the method comprises the steps of fixedly connecting bottom shell plates (57 a, 57 b) at the right end of a rotary cylinder to a shaft (11 a), fixedly connecting inner circular walls (25) of the rotary cylinder and outer circular walls (27 a, 27 b) of the rotary cylinder to the bottom shell plates at the right end of the rotary cylinder, fixedly connecting 10 rotary cylinder partition plates (18) to an annular groove between the inner circular walls of the rotary cylinder and the outer circular walls of the rotary cylinder, dividing the annular groove into 10 rotary cylinders with the same shape by the 10 rotary cylinder partition plates, forming a rotor of the deflagration rotary jet engine by the fixedly connected parts of a gas compressor (62) which are fixedly connected to the shaft (11 a), starting the deflagration rotary jet engine by a starting motor in a state without a forward speed, enabling compressed air generated by the gas compressor (62) to enter the rotary cylinder from an air inlet (16 a) to be communicated with the rotary cylinder, enabling the compressed air generated by the gas compressor (62) to enter the rotary cylinder to be communicated with the rotary cylinder when the rotary cylinder is rotated to the annular groove between the inner circular wall of the rotary cylinder and the outer circular wall of the rotary cylinder, enabling the rotary cylinder to enter the rotary cylinder to be completely communicated with the rotary cylinder through the gas compressor (62), enabling the compressed air to enter the rotary cylinder to be completely communicated with the combustion chamber from the rotary cylinder to the rotary cylinder through the rotary cylinder to the rotary cylinder, and the rotary cylinder to be completely combusted in a combustion chamber, and the rotary cylinder is completely communicated with the combustion chamber through the rotary cylinder after the rotary cylinder and the rotary cylinder has been cooled to the rotary cylinder, the burnt fuel and air mixture in the rotary cylinder expands and explodes and enters the fixed combustion chamber, and is sprayed into the air spraying passage from the rotor air spraying opening communicated with the fixed combustion chamber, so that rotary thrust is obtained to push the rotor to rotate, meanwhile, deflagration gas sprayed into the air spraying passage is sprayed backward from the air spraying passage, so that huge thrust is obtained to push an aircraft where the deflagration rotary spraying engine is located to hypersonic flight, after the rotary cylinder continues to rotate until the rotary cylinder is not communicated with the fixed combustion chamber, gas left in the rotary cylinder continues to be sprayed from the rotor air spraying opening, when the rotary cylinder rotates until the rotor air spraying opening is blocked by the inner wall of the shell, the gas in the rotary cylinder is basically sprayed, and when the rotary cylinder rotates to be communicated with the air inlet communication opening (16 a), compressed air pressurized by the gas compressor (62) rapidly enters the rotary cylinder again and enters the next working cycle.

4. A flat-pressure deflagration engine comprises a shell (1), flat-rotating rotor end walls (9 a, 9 b), a fixed shaft (2), flat-rotating cylinders (86 a, 86 b), flat-rotating shafts (6 a, 6b, 6c, 6 d), flat-rotating gears (7 a, 7b, 7c, 7 d), transmission gears (15 a, 15b, 15c, 15 d), transmission gear shafts (4 a, 4b, 4c, 4 d), fixed gears (26), cooling gas channels (54 a, 54 b), shafts (11 a, 11 b), cooling gas inlets (55), deflagration baffles (28), deflagration communication ports (29 a), air inlet communication ports (16 a), fuel injection ports (30 a), rotating cylinders (17), rotor air injection ports (56), air injection channels (35 a), rotating cylinder partitions (18), outer circular walls (27 a, 27 b) of the rotating cylinders, inner circular walls (25) of the rotating cylinders, bottom shell plates (57 a, 57 b) at right ends of the rotating cylinders), cooling gas outlets (58 a, 58 b), bearings (10 a, 10 b), bearings (20 a, 10 b), combustion chambers (44), bearings (20 a, 24 b), a, 20 b), a, and a piston carriers (20 b), and (20 a, 24 b), which are a, 20b, and a-pressure-air-blocking devices (20 b) which are integrated with the bearings (20 a, 20 b), 5c, 5 d), a demarcation device (8), a gas storage cooling tank (23 a, 23 b); the flat rotary shaft and the flat rotary piston are limited by the gears and can only rotate in parallel, namely, the directions of the upper edges of the flat rotary piston in the rotating process are always unchanged, the flat rotary gear (7 a), the flat rotary shaft (6 a) and the flat rotary piston (5 a) are fixed connection bodies, the flow blocking plugs (22 a, 22b, 22c and 22 d) are fixed between the flat rotary end wall (9 a) and the flat rotary end wall (9 b), the flat rotary end wall (9 a and 9 b) are fixedly connected to the shaft (11 a) through the fixed shafts, the demarcation device is fixedly connected to the shell through the fixed shafts, the narrowest channel between the demarcation device and the shell is called a choke (24 a and 24 b), the choke only allows the flat rotary piston, the flat rotary shaft and the flow blocking plugs to pass through, and no gas passes through, when the flat detonation engine rotates, air entering the flat rotary cylinder (86 b) from the air inlet (20 a) enters the cooling grooves (23 a) through gas channels communicated with the exhaust ports (21 b) after being compressed, and the air channels communicated with the air outlet (21 b), and when the air entering the cooling cylinders (23 a) from the flat rotary cylinder (23 a) through the air inlet channels (23 a) are continuously communicated with the air inlet channels (23 a) through the rotary cylinders, the air inlet channels (23 b) which can be continuously rotated and can be cooled through the rotary cylinders, after the fuel injected from the fuel injection port is received at the position which leaves the air inlet communication port and reaches the fuel injection port (30 a), the rotary cylinder starts to be communicated with the fixed combustion chamber, the explosion fire in the fixed combustion chamber heats the fuel and air mixture in the rotary cylinder through explosive compression combustion, when the rotary cylinder rotates until the opening of the rotary cylinder completely faces the fixed combustion chamber, the mixed combustion gas in the rotary cylinder expands and explodes to enter the fixed combustion chamber, and is injected into the gas injection passage from the rotor gas injection port communicated with the fixed combustion chamber, so that rotary power is obtained to push the rotor to rotate, and at the same time, the deflagration gas injected into the gas injection passage is injected from the gas injection passage, so that huge propelling force is obtained to push the aircraft where the flat-pressure engine is located to fly at high supersonic speed, the rotary cylinder continues to rotate until the nozzle of the rotor gas injection port is blocked by the inner wall of the casing, and after the internal gas is basically injected, the compressed gas in the gas storage cooling groove is received again at the position which reaches the air inlet communication port (16 a) to enter the next working cycle.

5. A deflagration flat-forward engine for producing rotary power comprises a casing (1), flat-rotating rotor end walls (9 a, 9 b), a fixed shaft (2), flat-rotating pistons (5 a, 5b, 5c, 5 d), flat-rotating shafts (6 a, 6b, 6c, 6 d), a demarcation device (8), air inlets (20 a, 20 b), air outlets (21 a, 21 b), flow blocking plugs (22 a, 22b, 22c, 22 d), choke ports (24 a), flat-rotating cylinders (86 a, 86 b), flat-rotating gears (7 a, 7b, 7c, 7 d), transmission gears (15 a, 15b, 15c, 15 d), transmission gear shafts (4 a, 4b, 4c, 4 d), bearings (10 a, 10 b), fixed gears (26), fixed combustion chambers (44 a), air inlet communication ports (16 a), deflagration baffles (28), deflagration communication ports (29 a), shafts (11 a, 11 b), fuel injection ports (30 a), air discharge ports (34 a), rotary cylinders (17), rotary cylinder partition plates (18), inner circular walls (25) of the rotary cylinders, thrust bearings (60), outer circular walls (27 a, 27 b) of the rotary cylinders, bottom shell plates (57 a, 57 b) at the right ends of the rotary cylinders, cooling gas outlets (58 a, 58 b), and the rotary-piston-type engine is characterized by further comprising a deflagration communication port (66) and a flat-piston engine (69); a flat rotary piston, a flat rotary shaft and a flat rotary gear form a fixed connecting body, the fixed connecting body can only rotate in parallel through gear transmission, when the flat rotary motor rotates, air entering the flat rotary cylinder (86 b) from an air inlet (20 b) is pushed into compressed air by the flat rotary piston (5 a) which rotates in parallel and then is discharged from an air outlet (21 a), the compressed air discharged from the air outlet (21 a) enters a rotary cylinder through a gas channel communicated with the air outlet (21 a) and an air inlet communication port (16 a), after the rotary cylinder which has entered the compressed air rotates to the position of a fuel injection port (30 a) and receives fuel injected from the fuel injection port, the rotary cylinder is gradually communicated with a fixed combustion chamber, the compressed air and the fuel mixture in the rotary cylinder are subjected to explosion compression detonation of the fixed combustion chamber, the explosion shock wave pushes the flat rotary piston to do work on the outside through a gas channel between the explosion fire port (66) and the air inlet (20 a), the flat rotary piston is pushed to rotate in parallel and work on the air outlet, the rotary cylinder rotates in parallel to the rotary cylinder is rotated again, and then the rotary cylinder is rotated to be discharged from the rotary cylinder (21 b) after the rotary cylinder is rotated, and the rotary cylinder is continuously discharged from the rotary cylinder is rotated to the rotary cylinder after the rotary cylinder is rotated.

6. A deflagration engine comprising a casing (1), a flat rotor end wall (9 a, 9 b), a flat rotating shaft (6 a, 6b, 6c, 6 d), a fixed shaft (2), a flat rotating cylinder (86 a, 86 b), a flat rotating piston (5 a, 5b, 5c, 5 d), a delimiter (8), an exhaust port (21 a, 21 b), a plug (22 a, 22b, 22c, 22 d), a choke (24 a, 24 b), a flat rotating compressor (68), an air intake (50 a, 50 b), a flat rotating gear (7 a, 7b, 7c, 7 d), a transmission gear (15 a, 15b, 15c, 15 d), a transmission gear shaft (4 a, 4b, 4c, 4 d), a rotating cylinder (17), a rotating cylinder partition (18), an inner circular wall (25) of a rotating cylinder, a jet channel (35 a), a fixed combustion chamber (44 a), an igniter (45 a), a vent channel (51 a, 51 b), an uninterrupted fuel injector (78), a bearing (10 a, 10b, 11 b), a gear (11 b), a high pressure air intake (52) and a high pressure engine (52) with an intake; a flat rotary piston, a flat rotary shaft and a flat rotary gear set are combined into a fixed connecting body, the flat rotary piston is limited to rotate in parallel through gear transmission, a gas switch on an oxygen inlet (53) is closed in normal time, the gas switch on the oxygen inlet is opened only when gas entering the rotary cylinder cannot meet the explosion requirement, oxygen enters the rotary cylinder to support combustion, the gas switch on the oxygen inlet is closed when oxygen is not needed for supporting combustion, high-pressure air discharged from an exhaust port (21 a) and an exhaust port (21 b) enters the rotary cylinder through a gas channel from a high-pressure gas inlet (40), when the deflagration engine pushes an aircraft to fly hypersonic, the opening of an air inlet (50 a, 50 b) faces to the front, incoming flow enters the rotary cylinder from the air inlet (50 a), the incoming flow enters the flat rotary cylinder (86 a, 86 b) from the air inlet (50 b), the gas entering the flat rotary cylinder (86 a, 86 b) is pushed into the high-pressure gas through the gas channel, the high-pressure gas inlet is pushed into the rotary cylinder to rotate, the high-pressure gas channel is discharged from the rotary cylinder (50 a) to form high-pressure gas, the high-pressure gas channel is gradually compressed into a mixed gas from the rotary cylinder (35) and the high-pressure air inlet is sprayed into the rotary cylinder, the high-pressure air chamber is gradually compressed by the high-pressure explosion chamber (35) and the high-pressure explosion chamber is compressed, and the high-pressure combustion chamber is gradually mixed with the high-pressure combustion chamber is compressed and the high-pressure combustion air jet air chamber (35) and the high-pressure combustion chamber is compressed, so that huge propelling force is obtained to push an aircraft where the deflagration engine is located to fly hypersonic or supersonic speed, when the rotary cylinder continues to rotate to leave the fixed combustion chamber, the waste gas left in the rotary cylinder is discharged from the air discharge channels (51 a and 51 b), the rotary cylinder receives the incoming flow entering from the air inlet channels again and enters the next working cycle, and the deflagration engine comprises an auxiliary engine and a flat compressor, so that the deflagration engine can be started when no advancing speed exists.