WO2023216762A1

WO2023216762A1 - Deflagration engine

Info

Publication number: WO2023216762A1
Application number: PCT/CN2023/085521
Authority: WO
Inventors: 龙全洪
Original assignee: 龙全洪
Priority date: 2022-05-07
Filing date: 2023-03-31
Publication date: 2023-11-16
Also published as: CN116201657A

Abstract

A deflagration engine having an air intake end not in communication with a fixed combustion chamber, the deflagration engine comprising an air intake duct, a bearing, a shaft, and an aircraft. The deflagration engine further comprises a casing, a rotating cylinder, a fixed combustion chamber, end walls of both ends of the rotating cylinder, a rotating cylinder partition, an inner circular wall of the rotating cylinder, an uninterrupted fuel injector, an igniter, a jet duct, and a bleed duct. A head-on incoming flow entering from the air intake duct enters the rotating cylinder to push a rotor to rotate at a high speed. After the rotating cylinder rotates through the position of the uninterrupted fuel injector to receive injected fuel, the rotating cylinder continues to rotate to reach a position that is in communication with the fixed combustion chamber. An explosive shock wave in the fixed combustion chamber will explosively compress a mixture of fuel and air in the rotating cylinder, such that the mixture of fuel and air deflagrates to produce an explosive shock wave, so as to eject from the jet duct. After the rotating cylinder rotates to not be in communication with the fixed combustion chamber, exhaust gas left in the rotating cylinder is bled off, to enter the next working cycle.

Description

deflagration engine

Technical field

This technology belongs to the field of engine technology

Background technique

Existing three-way jet engines such as turbojet engines, turbofan engines and ramjet engines connect the intake end and the injection end through the combustion chamber. The pressure in the front of the combustion chamber must be much greater than the pressure in the rear to work properly. If If the gas pressure in the combustion chamber is too high, the flat-rotating compressor cannot push the air into the combustion chamber. As a result, it is impossible to use the method of making the jet port much smaller than the air inlet to make the jet port eject tens of Machs or hundreds of Machs. The airflow, that is, an aircraft using a three-way jet engine as a propeller, cannot achieve hypersonic flight, and its combustion effect is not good.

Contents of the invention

In view of the shortcomings of the above technology, I designed a deflagration engine in which the intake end is not connected to the fixed combustion chamber. The technical solutions adopted by the present invention are as follows:

A deflagration engine with a rotating cylinder blocking the air inlet and a fixed combustion chamber, and the gas pressure in the fixed combustion chamber being much greater than the gas pressure that can be generated at the intake end, including a shaft, and characterized in that the deflagration engine also includes a The casing, rotating cylinder, fixed combustion chamber, and exhaust duct. When the deflagration engine is working, the combustion-supporting gas with a gas pressure much lower than the gas pressure in the fixed combustion chamber enters the rotating cylinder from the intake end. When the rotating cylinder continues to rotate to the point where it does not match the After the intake port is connected, the rotating cylinder continues to rotate while receiving fuel injected from the fuel injector. When the rotating cylinder rotates to a position connected to the fixed combustion chamber, the mixture of combustion-supporting gas and fuel in the rotating cylinder Deflagration with the high-pressure combustion gas in the fixed combustion chamber generates huge energy to do work. After the rotating cylinder continues to rotate to a position that is not connected to the fixed combustion chamber, the exhaust gas left in the rotating cylinder is released through the exhaust passage and enters the next working cycle.

Advantages of the deflagration engine of the present invention

1. In this deflagration engine, after air and fuel are evenly mixed, the mixture is impacted by the previously generated deflagration shock wave and mixed with the detonation before deflagration. Its combustion effect is unachievable by other jet engines, and the combustion effect is good. It is determined that this deflagration engine has the advantage of high efficiency and energy saving.

2. The intake end of this deflagration engine is not connected to the fixed combustion chamber. The air at the intake end is transported to the fixed combustion chamber cylinder by cylinder through the rotating cylinder. Therefore, no matter how high the pressure inside the fixed combustion chamber is, it will not It will affect the air at the intake end to effectively enter the fixed combustion chamber. Therefore, the jet duct of the deflagration engine can be made very small, so small that the jet duct is only one tenth of the intake duct, so that the fixed combustion can be achieved. A huge pressure is generated in the chamber, causing the airflow speed ejected from the jet channel to reach tens of Machs or hundreds of Machs, so that the deflagration engine can propel the aircraft to achieve hypersonic flight and efficiently convert the energy generated by the deflagration engine into propulsion energy.

3. As long as the speed of the aircraft in which the deflagration engine is located reaches 300 kilometers per hour, the deflagration engine can be started. Therefore, the aircraft in which the deflagration engine is located can fly at hypersonic speed, supersonic speed, and subsonic speed.

4. The structure of this deflagration engine is simple, the working principle is simple, and the effective utilization rate of energy is particularly high. Except for the oil supply mechanism, the rest of the mechanisms can be manufactured by general machinery manufacturers, and the manufacturing cost is less than 1/10 of the turbofan engine. The thrust-to-weight ratio of the deflagration engine can exceed 100, which is unreachable by any other jet engine. This deflagration engine can eject airflow of dozens of Mach or hundreds of Mach. This deflagration engine has many implementation modes. It can be made into a deflagration jet engine that starts at zero forward speed, or it can be made into a deflagration engine that specifically generates rotational power. This deflagration engine can be applied to many fields.

5. The cooling gas can be used to effectively cool the interlayer space inside the rotor of the deflagration engine, thereby increasing the maximum temperature that the rotor of the deflagration engine can withstand.

Description of drawings

Figure 1, Figure 2, Figure 3, Figure 4, Figure 5, Figure 6, Figure 7, Figure 8, Figure 9, Figure 10, Figure 11, Figure 12, Figure 13, Figure 14, Figure 15, Figure 16, Figure 17 , Figure 18, Figure 19, Figure 20, Figure 21, and Figure 22 are schematic structural diagrams of the deflagration engine of this design. In Figure 1, 77—aircraft, 50a—inlet duct, 78—continuous fuel injector, 1—casing, 89—air guide, 17—rotating cylinder, 11a—shaft, 35a—jet duct, 44a — Fixed combustion chamber, 25 — inner circular wall of the rotating cylinder, 18 — rotating cylinder partition, 45a — igniter, 51a, 51b — exhaust duct. In Figure 2, 50a—inlet duct, 1—casing, 10a, 10b—bearings, 44a—fixed combustion chamber, 18—rotating cylinder partition, 88—baffle plate, 25—inner circular wall of the rotating cylinder, 52a , 52b—end walls at both ends of the rotating cylinder, 35a—jet channel, 11a—shaft. In Figure 3: 1—casing, 13—fixed baffle, 16a, 16b—air inlet communication port, 11a—shaft. In Figure 4: 1—casing, 27a—the outer circular wall of the rotating cylinder, 17—the rotating cylinder, 18—the rotating cylinder partition, 11a—the shaft, 25—the inner circular wall of the rotating cylinder. In Figure 5: 1 - casing, 35a, 35b - jet duct, 29a, 29b - deflagration communication port, 11a - shaft, 30a, 30b - fuel injection port, 34a, 34b - exhaust port, 28 - deflagration baffle. In Figure 6: 3—drive shaft, 47—compressor fan, 81—a mechanism for injecting fuel from the fuel injection inlet into the rotating cylinder, 46—diffuser, 43—attached machine, 13—fixed baffle, 37a, 37b - Bevel gear, 10a, 10b - bearing, 1 - casing, 80 - annular partition, 27a, 27b - outer wall of the rotating cylinder, 79a, 79b - connecting plate, 29a, 29b - deflagration communication port, 28 - deflagration Baffle, 17—rotating cylinder, 25—inner circular wall of rotating cylinder, 45a, 45b—igniter, 42a, 42b—inner circular wall of fixed combustion chamber, 44a, 44b—fixed combustion chamber, 35a, 35b—injection channel , 11a-axis. In Figure 7, 28—deflagration baffle, 54a, 54b—cooling gas channels, 1—casing, 29a—deflagration communication port, 55—cooling gas inlet, 11a—shaft, 16a—air inlet communication port, 30a—fuel Squirt into mouth. In Figure 8: 17—rotating cylinder, 56—rotor air jet, 54a, 54b—cooling gas channel, 35a—air jet channel, 1—casing, 18—rotating cylinder partition, 27a, 27b—external circle of rotating cylinder Wall, 25—inner circular wall of the rotating cylinder, 11a—shaft. In Figure 9: 57a, 57b—rotating cylinder Bottom shell plate at the right end, 58a, 58b - cooling gas outlet, 11a - shaft. In Figure 10: 54, 54b—cooling gas channel, 1—casing, 11a—shaft. In Figure 11: 54a, 54b—cooling gas passage, 62—flat-rotating compressor, 27a, 27b—the outer circular wall of the rotating cylinder, 25—the inner circular wall of the rotating cylinder, 81—injecting fuel from the fuel injection port The mechanism of the rotating cylinder, 29a—deflagration communication port, 17—rotating cylinder, 44a—fixed combustion chamber, 28—deflagration baffle, 60—thrust bearing, 57a, 57b—bottom shell plate at the right end of the rotating cylinder, 35a—jet channel, 10b—bearing, 11a—shaft, 59—bearing bracket integrated with the bearing sleeve, 16a—air inlet communication port. In Figure 12: 9a - end wall of the horizontal rotating rotor, 1 - casing, 6a, 6b, 6c, 6d - horizontal rotating shaft, 2 - fixed shaft. In Figure 13: 1—casing, 21a, 21b—exhaust port, 22a, 22b, 22c, 22d—blocking plug, 5a, 5b, 5c, 5d—translational piston, 86a, 86b—translational cylinder, 6a, 6b, 6c, 6d—flat-rotating shaft, 20a, 20b—air inlet, 2—fixed shaft, 24a, 24b—pass, 8—divider, 68—flat-rotating compressor. In Figure 14: 1—casing, 6a, 6b, 6c, 6d—flat rotating shaft, 7a, 7b, 7c, 7d—flat rotating gear, 15a, 15b, 15c, 15d—transmission gear, 4a, 4b, 4c, 4d—transmission gear shaft, 26—fixed gear, 11b—shaft. In Figure 15: 1—casing, 2—fixed shaft, 4a, 4c—transmission gear shaft, 5a, 5c—flat-rotating piston, 6a, 6c—flat-rotating shaft, 7a, 7b—flat-rotating gear, 8—divider , 9a, 9b—flat-rotating rotor end wall, 10a, 10b—bearing, 11a, 11b—shaft, 15a, 15c—transmission gear, 16a—air inlet communication port, 17—rotating cylinder, 23a, 23b—gas storage cooling Groove, 25—inner circular wall of the rotating cylinder, 26—fixed gear, 27a, 27b—outer circular wall of the rotating cylinder, 28—deflagration baffle, 29a—deflagration communication port, 35a—jet channel, 44a—fixed combustion chamber, 54b—cooling gas channel, 57a, 57b—bottom shell plate at the right end of the rotating cylinder, 59—bearing bracket integrated with the bearing sleeve, 60—thrust bearing, 68—flat-rotating compressor. In Figure 16: 1—casing, 2—fixed shaft, 5a, 5b, 5c, 5d—flat-rotating pistons, 6a, 6b, 6c, 6d—flat-rotating shaft, 8—divider, 20a, 20b—air inlet , 21a, 21b—exhaust port, 22a, 22b, 22c, 22d—blocking plug, 24a—pass, 86a, 86b—flat-rotating cylinder, 69—flat-rotating engine. In Figure 17 Center: 1—casing, 11b—shaft, 17—rotating cylinder, 18—rotating cylinder partition, 25—inner circular wall of rotating cylinder, 27a—outer circular wall of rotating cylinder. In Figure 18: 1 - casing, 11b - shaft, 16a - air inlet communication port, 28 - deflagration baffle, 29a - deflagration communication port, 30a - fuel injection inlet, 34a - exhaust port. In Figure 19: 1—casing, 2—fixed shaft, 4a, 4c—transmission gear shaft, 5a, 5c—flat-rotating piston, 6a, 6c—flat-rotating shaft, 7a, 7b—flat-rotating gear, 8—divider , 9a, 9b—flat-rotating rotor end wall, 10a, 10b—bearing, 11a, 11b—shaft, 15a, 15c—transmission gear, 16a—air inlet communication port, 17—rotating cylinder, 25—inner circle of rotating cylinder Wall, 26—fixed gear, 27a, 27b—outer circular wall of the rotating cylinder, 28—deflagration baffle, 29a—deflagration communication port, 44a—fixed combustion chamber, 57a—bottom shell plate at the right end of the rotating cylinder, 60—thrust bearing , 66—explosion communication port, 69—flat-rotating engine. In Figure 20: 86a, 86b - translation cylinder, 1 - casing, 2 - fixed shaft, 5a, 5b, 5c, 5d - translation piston, 6a, 6b, 6c, 6d - translation shaft, 8 - divider , 21a, 21b—exhaust port, 22a, 22b, 22c, 22d—blocking plug, 24a, 24b—pass, 68—flat-rotating compressor, 50b—inlet duct. In Figure 21: 1—casing, 11a—shaft, 17—rotating cylinder, 18—rotating cylinder partition, 25—inner circular wall of rotating cylinder, 35a—jet duct, 40—high pressure gas inlet, 44a—fixed combustion Chamber, 45a—igniter, 50a—inlet duct, 51a, 51b—bleeder duct, 78—continuous fuel injector. In Figure 22: 1—casing, 2—fixed shaft, 4b, 4d—transmission gear shaft, 5b, 5d—flat-rotating piston, 6b, 6d—flat-rotating shaft, 7c, 7d—flat-rotating gear, 8—divider , 9a, 9b—flat-rotating rotor end wall, 10a, 10b, 10c—bearing, 11a, 11b—shaft, 15b, 15d—transmission gear, 18—rotating cylinder partition, 25—inner circular wall of the rotating cylinder, 26 —Fixed gear, 35a—jet duct, 44a—fixed combustion chamber, 50, 50b—inlet duct, 52a, 52b—end walls at both ends of the rotating cylinder, 68—flat-rotating compressor, 43—attached machine.

Detailed ways

1. A rotating cylinder blocks the air inlet from the fixed combustion chamber, and the air in the fixed combustion chamber is A deflagration engine in which the body pressure is much greater than the gas pressure that can be generated at the intake end, that is, a deflagration engine in which the intake end is not connected to a fixed combustion chamber and the pressure at the rear of the combustion chamber is much greater than the pressure at the front, including a shaft 11a, which is characterized by The deflagration engine also includes an organic casing 1, a rotating cylinder 17, a fixed combustion chamber 44a, and exhaust passages 51b, 51a. When the deflagration engine is working, the combustion-supporting gas with a gas pressure far lower than the gas pressure in the fixed combustion chamber 44a enters the combustion chamber 44a. The gas end enters the rotating cylinder 17. When the rotating cylinder continues to rotate and reaches a position where it is not connected to the intake passage, the rotating cylinder receives fuel injected from the fuel injector and continues to rotate. When the rotating cylinder rotates to a position where it is connected to the fixed combustion chamber. After reaching the position, the mixture of combustion-supporting gas and fuel in the rotating cylinder deflagrates with the high-pressure combustion gas in the fixed combustion chamber to produce huge energy and work. After the rotating cylinder continues to rotate to a position that is not connected to the fixed combustion chamber, it is vented through The exhaust gas left in the rotating cylinder is released and enters the next working cycle.

2. A deflagration engine in which the air intake end is not connected to the fixed combustion chamber and the pressure at the rear of the combustion chamber is much greater than the pressure at the front. The specific structure of this method is shown in Figures 1 and 2. The deflagration engine includes an air intake Channel 50a, air guide 89, bearings 10a, 10b, shaft 11a and aircraft 77 should have existing technology, which is characterized in that the deflagration engine also includes an organic casing 1, a rotating cylinder 17, a fixed combustion chamber 44a, a rotating cylinder The end walls 52a, 52b at both ends, the rotating cylinder partition 18, the inner circular wall 25 of the rotating cylinder, the continuous fuel injector 78, the igniter 45a, the injection passage 35a, the baffle plate 88, the exhaust passages 51a, 51b; by rotating The end walls at both ends of the cylinder fixedly connect the inner circular wall of the rotating cylinder to the shaft to form an annular groove, and then the annular groove is divided into 12 identical rotating cylinders through 12 rotating cylinder partitions. The end is sealed and fixedly connected to the end walls of both ends of the rotating cylinder, and the inner side is sealed and fixedly connected to the inner circular wall of the rotating cylinder. The rotating cylinder partition is a hollow plate, that is, the rotating cylinder partition has an interlayer space, and the cooling air flows from the end wall of the left end of the rotating cylinder. After entering the left space inside the inner circular wall of the rotating cylinder through the air hole, it then enters the interlayer space of the rotating cylinder partition to cool the rotating cylinder partition, and then passes through the right space inside the inner circular wall of the rotating cylinder and the rotating cylinder. The air hole on the right end wall discharges to the outside world; The rotor consists of the shaft, the end walls at both ends of the rotating cylinder, the inner circular wall of the rotating cylinder and the rotating cylinder partition. The inner wall of the casing matches the motion trajectory of the rotor when it rotates, that is, the gap between the inner wall of the casing and the rotor is extremely small. However, the inner wall of the casing does not hinder the rotation of the rotor, and the bearings at both ends of the rotor are limited to the casing by corresponding bearing sleeves; the bearing sleeve, casing, air inlet, fixed combustion chamber, jet channel and exhaust channel are a fixedly connected whole. The fixed connection is integrally fixedly installed on the aircraft. When the flight speed of the aircraft equipped with the deflagration engine is greater than 300 kilometers per hour, the oncoming flow from the inlet, that is, the speed difference ram airflow, can enter the rotating cylinder and push through The rotating cylinder partition pushes the rotor to rotate at high speed. When the rotating cylinder rotates to the position of the continuous fuel injector, the outer edge of the rotating cylinder is in contact with the inner wall of the casing, and its internal space is not connected to the outside world. The continuous fuel injector injects The incoming fuel is instantly mixed evenly with the violently moving air that has entered the rotating cylinder. When the rotating cylinder continues to rotate until its internal space is connected to the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber will hit the rotating cylinder. The violently moving mixture of fuel and air is explosively compressed, causing the mixture of fuel and air to explode into the fixed combustion chamber and deflagrate. Then the deflagration shock wave detonates the mixture of fuel and air in the following rotating cylinder to deflagrate. This deflagration engine detonates with explosions like this, and the explosions are connected to produce ultra-high-pressure airflow that explodes from the jet duct to the rear of the aircraft at a speed of tens of Machs or hundreds of Machs, thus generating huge propulsion force to push the aircraft to hypersonic or supersonic speeds. Flying, if necessary, it can also fly at subsonic speed. When the rotating cylinder continues to rotate until it is not connected to the fixed combustion chamber and is only connected to the exhaust passage, the burned gas remaining in the rotating cylinder will be released from the exhaust passage. When the rotating cylinder continues to rotate until it is connected to both the exhaust passage and the intake passage, the ram airflow entering from the intake passage will enter the rotating cylinder to clean the rotating cylinder, so that the exhaust gas left in the rotating cylinder is completely discharged from the exhaust passage. When the rotating cylinder continues to rotate until it is only connected to the intake port, the ram airflow will re-enter the rotating cylinder and push the rotor to rotate at high speed and enter the next working cycle; in this deflagration engine, after the air and fuel are evenly mixed, The mixture is impacted by the previously generated deflagration shock wave and mixed with the detonation before deflagration. Its combustion effect is the same as that of other jet engines. If the combustion effect is good, it can be determined that this deflagration engine has the advantage of high efficiency and energy saving; the intake end of this deflagration engine is not connected to the fixed combustion chamber, and the air at the intake end is transported to the fixed combustion chamber one cylinder at a time by rotating the cylinder. combustion chamber, therefore, no matter how high the pressure inside the fixed combustion chamber is, it will not affect the air at the intake end effectively entering the fixed combustion chamber. Therefore, the jet duct of the deflagration engine can be made very small, and can be as small as the jet duct. It is only one-tenth of the size of the intake duct, which can generate huge pressure in the fixed combustion chamber and make the airflow speed ejected from the jet duct reach tens of Mach or hundreds of Mach. Therefore, this deflagration engine can propel the aircraft to achieve superb performance. Sonic flight efficiently converts the energy generated by this deflagration engine into propulsion energy.

3. A fan-pressure deflagration engine started at zero forward speed. The specific structure of this method is shown in Figures 3, 4, 5 and 6. The fan-pressure deflagration engine includes an organic casing 1, bearings 10a, 10b, a transmission shaft 3, connecting plates 79a, 79b, bevel gears 37a, 37b, igniters 45a, 45b, a compressor fan 47, and a diffuser 46. The injection port injects into the mechanism 81 of the rotating cylinder, the attached machine 43, and the shaft 11a. The characteristic is that this fan-pressure deflagration engine also includes a fixed baffle 13, air intake communication ports 16a, 16b, and outer circular walls 27a, 27b of the rotating cylinder. , rotating cylinder partition 18, annular partition 80, rotating cylinder 17, inner circular wall 25 of the rotating cylinder, deflagration baffle 28, deflagration communication ports 29a, 29b, injection passages 35a, 35b, fuel injection inlets 30a, 30b, exhaust The ports 34a, 34b fix the inner circular walls 42a, 42b of the combustion chamber, and fix the combustion chambers 44a, 44b; the inner circular wall 25 of the rotating cylinder is fixedly connected to the shaft 11a through the connecting plates 79a, 79b fixed on the shaft 11a. The outer circular walls 27a and 27b of the rotating cylinder are fixedly connected to the inner circular wall 25 of the rotating cylinder through 15 rotating cylinder partitions 18 fixedly connected to the inner circular wall 25 of the rotating cylinder. The 15 rotating cylinder partitions handle The annular space between the inner circular wall 25 of the rotating cylinder and the outer circular walls 27a and 27b of the rotating cylinder is equally divided into 15 rotating cylinders. The fixed connector is connected with the bevel gear 37a fixed on the shaft 11a, the annular partition 80 and the compressed air. The fan 47 is assembled into the rotor of this engine. A rectangular steel plate divides the mezzanine space of a rotating cylinder partition 18 into the left space and the right space. The cooling air flows from the shaft The hole enters the left space of the annular partition 80 and then enters the interlayer space of the outer circular wall of the rotating cylinder through the left interlayer space of the rotating cylinder partition 18 and moves to the right. The cooling air moving to the right passes through a block behind it. The mezzanine space on the right side of the rotating cylinder partition enters the right side space of the annular partition 80, and then is discharged to the outside through the shaft hole, thereby effectively cooling the parts that need to be cooled inside the rotor and ensuring that the internal temperature of the rotor will not be excessive. high and damage the rotor. The compressor fan is the fan of the turbofan engine, but it is much reduced in proportion. The bearing sleeve in the middle of the diffuser that is integrated with the diffuser is sleeved on the bearing 10a. The bearing 10a is sleeved on the shaft 11a. The diffuser The outer edge of the device is fixedly connected to the casing. The outer edge of the fixed baffle 13 at the front end of the rotating cylinder is fixedly connected to the casing. The fixed baffle 13 is also fixedly connected with two bearing sleeves to define the two bearings that are sleeved on the transmission shaft. , the bevel gear 37b fixedly connected to the transmission shaft and the bevel gear 37a fixed on the shaft are meshed, ensuring that the rotational power generated by the attached machine 43 that generates rotational power can be effectively transmitted to the rotor, and the fixed baffle at the front end of the rotating cylinder There are air inlet communication ports 16a, 16b, and an axis hole that can pass through the shaft 11a. The outer edge of the deflagration baffle 28 between the rotating cylinder and the fixed combustion chamber is fixedly connected to the casing, and the central axis hole is sleeved on the shaft. On 11a, the deflagration baffle also has deflagration communication ports 29a, 29b, fuel injection ports 30a, 30b, vent ports 34a, 34b. When the rotor rotates, there are fixed baffles 13 at the left end and the intake end of each component that make up the rotating cylinder. The right end is in contact with the deflagration baffle 28, and the gap is small and they pass by each other; when the fan-pressure deflagration engine is working, the air inlet end is not connected with the fixed combustion chamber, and the air fan is compressed by rotating the cylinder-cylinder-cylinder handle. The generated compressed air is transported to the position of the fuel injection inlet to receive the injected fuel, and then transported to a position connected to the fixed combustion chamber to receive explosive compression of the explosion shock wave of the fixed combustion. The explosively compressed fuel and air mixture is The deflagration is injected into the fixed combustion chamber and ejected from the jet duct behind the fixed combustion chamber, thereby obtaining huge thrust to propel the aircraft where the fan-pressure deflagration engine is located to fly at hypersonic or supersonic speeds. The rotating cylinder rotates so that it is not connected to the fixed combustion chamber. Finally, the waste gas left in the rotating cylinder will be discharged to the outside world at the rear through the air passage connected to the exhaust port. When the discharged and abandoned rotating cylinder rotates to a position connected to the air inlet communication port, it will again receive the exhaust gas generated by the compressor fan. The compressed air enters the next working cycle. Because the fan-pressure deflagration engine has an attached machine 43 and a sub-air fan 44, the fan-pressure deflagration engine is started at zero forward speed of the aircraft in which it is located.

4. A deflagration rotary injection engine. The specific structure of this method is shown in Figures 7, 8, 9, 10, and 11. The deflagration rotary injection engine includes a casing 1, a bearing 10b, a shaft 11a, and a horizontal rotation The compressor 68 is a mechanism 81 that injects fuel from the fuel injection port into the rotating cylinder. It is characterized in that the deflagration rotary injection engine also includes a deflagration baffle 28, cooling gas channels 54a, 54b, a deflagration communication port 29a, and a cooling gas inlet 55. , fuel injection port 30a, air intake communication port 16a, injection passage 35a, rotor injection port 56, rotating cylinder 17, rotating cylinder partition 18, inner circular wall 25 of the rotating cylinder, outer circular walls 27a, 27b of the rotating cylinder, rotating Bottom shell plates 57a, 57b at the right end of the cylinder, cooling gas outlets 58a, 58b, fixed combustion chamber 44a, thrust bearing 60, bearing bracket 59 integrated with the bearing sleeve; the flat-rotating compressor 68 can be a low-pressure flat-rotating turbofan engine The compressor part or other flat-rotating compressors. The flat-rotating compressor includes the starter motor. The flat-rotating compressor can share the shaft 11a and be provided with a bearing support shaft 11a. There is no need for the flat-rotating compressor to generate too much gas pressure. First, The bottom shell plates 57a and 57b at the right end of the rotating cylinder are fixedly connected to the shaft 11a, and then the inner circular wall 25 of the rotating cylinder and the outer circular walls 27a and 27b of the rotating cylinder are fixedly connected to the bottom shell plate at the right end of the rotating cylinder, and then Then 10 rotating cylinder partitions 18 are fixedly connected in the annular groove between the inner circular wall of the rotating cylinder and the outer circular wall of the rotating cylinder. The 10 rotating cylinder partitions divide the annular groove into 10 rotating cylinders with the same shape. Cylinder, the above-mentioned fixed connection body and the components in the flat-rotating compressor 68 that should be fixedly connected to the shaft 11a form the rotor of the deflagration rotary injection engine. When the rotor rotates, the left end of the components that make up the rotating cylinder and the deflagration baffle Fittingly, the drawing hole in the middle of the deflagration baffle 28 is sleeved on the shaft 11a, the outer edge is fixedly connected to the casing, the outer edge of the bearing bracket 59 integrated with the bearing sleeve is fixedly connected to the casing, and the middle bearing sleeve is sleeved on the bearing 10b. , the cooling gas enters the annular space between the inner circular wall 25 of the rotating cylinder and the shaft 11a from the cooling gas inlet 55, and then passes through the interlayer space of the rotating cylinder partition 18 into the interlayer of the outer circular walls 27a and 27b of the rotating cylinder. space, and then flows out from the cooling gas outlets 58a, 58b. Each rotary cylinder is provided with a rotor jet port 56 on the outer wall of the rotary cylinder. If the explosive rotary jet engine is used as a machine for generating rotational power , to make a tangential ejection rotor jet, and the gas outlet of the jet channel 35a should be larger. If the explosive rotary jet engine is used as a jet engine, the center line and radius of the rotor jet should be The intersection angle should be about 130 degrees, and the gas outlet of the jet channel 35a should be smaller. When there is no forward speed, the explosive rotary injection engine can be started by the starter motor. After starting the deflagration rotary injection engine, the normal The compressed air generated by the rotary compressor 68 will enter the rotating cylinder from the air inlet communication port 16a. When the rotary cylinder of the deflagration rotary injection engine rotates to communicate with the air inlet communication port 16a, the compressed air after being supercharged by the flat rotary compressor 68 will The compressed air will quickly enter the rotating cylinder. When the rotating cylinder continues to rotate away from the intake communication port and reaches the position of the fuel injection port 30a to accept the fuel injected from the fuel injection port, the rotating cylinder begins to communicate with the fixed combustion chamber. The detonation in the fixed combustion chamber enters the rotating cylinder from one side, and the fuel and air mixture in the rotating cylinder is explosively compressed and burned, and then heated at a constant volume. When the rotating cylinder turns to have its opening completely facing the fixed combustion chamber , the burned fuel and air mixture in the rotating cylinder expands and explodes into the fixed combustion chamber, and is injected into the jet channel from the rotor jet port connected to the fixed combustion chamber, thereby obtaining rotational thrust to push the rotor to rotate. At the same time, the injection The deflagration gas entering the jet duct is ejected from the jet duct to the rear, thereby obtaining a huge propulsion force to propel the aircraft in which the deflagration rotary jet engine is located to fly at hypersonic speed. After the rotating cylinder continues to rotate until it is no longer connected to the fixed combustion chamber, the rotating cylinder The remaining gas in the rotor continues to be ejected from the rotor air outlet. When the rotary cylinder rotates until the rotor air outlet is blocked by the inner wall of the casing, the gas in the rotary cylinder is basically sprayed out. When the rotary cylinder rotates to the air inlet communication port 16a When connected, the compressed air supercharged by the flat-rotating compressor 68 quickly enters the rotating cylinder and enters the next working cycle.

5. A flat-pressure deflagration engine. The specific structure of this method is shown in Figures 12, 13, 14, 7, 8, 9, and 15. It includes an organic casing 1 and a flat-rotating rotor end wall. 9a, 9b, fixed shaft 2, Translation cylinders 86a, 86b, translation shafts 6a, 6b, 6c, 6d, translation gears 7a, 7b, 7c, 7d, transmission gears 15a, 15b, 15c, 15d, transmission gear shafts 4a, 4b, 4c, 4d, fixed Gear 26, cooling gas passages 54a, 54b, shafts 11a, 11b, cooling gas inlet 55, deflagration baffle 28, deflagration communication port 29a, air intake communication port 16a, fuel injection port 30a, rotating cylinder 17, rotor injection port 56, Jet channel 35a, rotating cylinder partition 18, outer circular walls 27a, 27b of the rotating cylinder, inner circular wall 25 of the rotating cylinder, bottom shell plates 57a, 57b at the right end of the rotating cylinder, cooling gas outlets 58a, 58b, bearings 10a, 10b , a fixed combustion chamber 44a, a bearing bracket 59 integrated with the bearing sleeve, a thrust bearing 60, and a flat-rotating compressor 68. The characteristic is that the flat-pressure deflagration engine also includes air inlets 20a, 20b, and exhaust ports 21a, 21b. , blocking plugs 22a, 22b, 22c, 22d, narrow openings 24a, 24b, flat-rotating pistons 5a, 5b, 5c, 5d, divider 8, gas storage cooling grooves 23a, 23b; the flat-rotating axis can only be limited by the gear. Parallel rotation, that is, the direction facing the upper edge of the translation piston remains unchanged during the rotation. The translation gear 7a, the translation shaft 6a, and the translation piston 5a are a fixed connection body, and the blocking plugs 22a, 22b, 22c, 22d is fixed between the flat-rotating rotor end wall 9a and the flat-rotating rotor end wall 9b. The flat-rotating rotor end walls 9a and 9b are fixedly connected to the shaft 11a. The divider is fixedly connected to the casing through the fixed shaft. The narrowest passages between the divider and the casing are called passes 24a and 24b. These passes only allow the flat-rotating piston, the flat-rotating shaft and the flow plug to pass through, and do not allow gas to pass through. When the flat-pressure deflagration engine rotates, it passes from the inlet The air entering the horizontal rotation cylinder 86b from the air port 20a is compressed by the horizontal rotation piston 5c and then enters the air storage cooling grooves 23a and 23b through the gas channel connected with the exhaust port 21b. The air entering the horizontal rotation cylinder 86a from the air inlet 20b is compressed by the horizontal rotation piston 5c. After being compressed, the flat-rotating piston 5a enters the gas storage cooling tank 23a, 23b through the gas channel connected to the exhaust port 21a. When the rotating cylinder rotates to be able to communicate with the gas storage cooling tank through the air inlet communication port 16a, the gas storage cooling tank The compressed gas inside will quickly enter the rotary cylinder through the air intake communication port. When the rotary cylinder continues to rotate, leaves the air intake communication port and reaches the position of the fuel injection port 30a to accept the fuel injected from the fuel injection port, the The rotating cylinder begins to communicate with the fixed combustion chamber, and the explosion in the fixed combustion chamber The fuel and air mixture in the rotating cylinder is heated by explosive compression combustion. When the rotating cylinder rotates to its opening completely facing the fixed combustion chamber, the mixed combustion gas in the rotating cylinder expands and explodes into the fixed combustion chamber, and passes from the fixed combustion chamber to the fixed combustion chamber. The rotor jets connected to the fixed combustion chamber are injected into the jet duct, thereby obtaining rotational power to push the rotor to rotate. At the same time, the deflagration gas injected into the jet duct is ejected from the jet duct, thereby obtaining huge propulsion force to promote the flat pressure deflagration. When the aircraft where the engine is located flies at hypersonic speed, the rotating cylinder continues to rotate until the nozzle of the rotor jet is blocked by the inner wall of the casing. After the gas inside is basically sprayed out, it reaches the position of the air inlet communication port 16a to receive the stored air for cooling again. The compressed gas in the tank enters the next working cycle.

6. A deflagration flat-rotating engine that produces rotational power. The specific structure of this method is shown in Figures 12, 16, 14, 18, 17, 9, and 19. This deflagration flat-rotating engine includes an organic Shell 1, translation rotor end walls 9a, 9b, fixed shaft 2, translation pistons 5a, 5b, 5c, 5d, translation shafts 6a, 6b, 6c, 6d, divider 8, air inlets 20a, 20b, exhaust Air ports 21a, 21b, blocking plugs 22a, 22b, 22c, 22d, narrow mouth 24a, translation cylinders 86a, 86b, translation gears 7a, 7b, 7c, 7d, transmission gears 15a, 15b, 15c, 15d, transmission gears Shafts 4a, 4b, 4c, 4d, bearings 10a, 10b, fixed gear 26, fixed combustion chamber 44a, air inlet communication port 16a, deflagration baffle 28, deflagration communication port 29a, shafts 11a, 11b, fuel injection port 30a, exhaust Port 34a, rotating cylinder 17, rotating cylinder partition 18, inner circular wall 25 of the rotating cylinder, thrust bearing 60, outer circular walls 27a, 27b of the rotating cylinder, bottom shell plates 57a, 57b at the right end of the rotating cylinder, cooling gas outlet 58a , 58b, which is characterized in that the explosive flat-rotating engine also includes an explosion communication port 66 and a flat-rotating engine 69; a flat-rotating piston, a flat-rotating shaft and a flat-rotating gear form a fixed connection body, and the gear transmission is used to limit the The fixed connector can only rotate in parallel. When the deflagration flat-rotating engine rotates, the air entering the flat-rotating cylinder 86b from the air inlet 20b is pushed by the parallel-rotating flat-rotating piston 5a into compressed air and then discharged from the exhaust port 21a. The compressed air discharged from the exhaust port 21a enters the rotating air through the gas channel connected with the exhaust port 21a and the air intake communication port 16a. Cylinder, when the rotating cylinder that has entered the compressed air rotates to the position of the fuel injection port 30a to accept the fuel injected from the fuel injection port, the rotating cylinder gradually communicates with the fixed combustion chamber, and the compressed air and fuel mixture inside it is affected by The detonation explosion compression detonation of the fixed combustion chamber generates an explosion shock wave. The explosion shock wave enters the flat-rotating cylinder 86a through the gas channel between the detonation communication port 66 and the air inlet 20a to push the flat-rotating piston to rotate in parallel to do work to the outside world. After the parallel rotation of the rotating piston is completed, the gas is discharged from the exhaust port 21b. After the mixture in the rotating cylinder is detonated, the rotating cylinder continues to rotate and leaves the fixed combustion chamber, and the gas left in the rotating cylinder is discharged from the exhaust port 34a. After being discharged to the outside world, the rotating cylinder re-receives the gas compressed by the flat-rotating piston and enters the next working cycle.

7. A deflagration engine. The specific structure of this method is shown in Figures 12, 20, 14, 21, and 22. This deflagration engine includes an organic casing 1, flat rotor end walls 9a, 9b, and flat rotor end walls 9a and 9b. Rotating shafts 6a, 6b, 6c, 6d, fixed shaft 2, translating cylinders 86a, 86b, translating pistons 5a, 5b, 5c, 5d, divider 8, exhaust ports 21a, 21b, blocking plugs 22a, 22b, 22c , 22d, pass 24a, 24b, flat-rotating compressor 68, the technology of flat-rotating compressor 68 comes from my invention patent: "Flat-rotating Engine", patent number: 2017100556514, air inlet 50a, 50b, flat-rotating gear 7a , 7b, 7c, 7d, transmission gears 15a, 15b, 15c, 15d, transmission gear shafts 4a, 4b, 4c, 4d, rotating cylinder 17, rotating cylinder partition 18, inner circular wall 25 of the rotating cylinder, injection passage 35a, Fixed combustion chamber 44a, igniter 45a, exhaust passages 51a, 51b, continuous fuel injector 78, bearings 10a, 10b, 10c, shafts 11a, 11b, fixed gear 26, end walls 52a, 52b at both ends of the rotating cylinder, attached Engine 43 is characterized in that the deflagration engine also includes a high-pressure gas inlet 40; a flat-rotating piston, a flat-rotating shaft and a flat-rotating gear are combined into a fixed connection body, and the flat-rotating piston can only rotate in parallel through gear transmission, so that The high-pressure air discharged from the exhaust port 21a and the exhaust port 21b enters the rotating cylinder from the high-pressure gas inlet 40 through the gas channel. When the deflagration engine propels the aircraft to fly at hypersonic speed, the openings of the inlet 50a and 50b face the front, and the incoming air ducts 50a and 50b face the front. The flow enters the rotating cylinder from the inlet port 50a, and the oncoming flow enters the flat-rotating compressor 68 from the inlet port 50b and is compressed into high-pressure gas. It then enters the rotating cylinder through the gas channel and mixes with the gas entering from the inlet port 50a, so that There is sufficient high-pressure gas in the rotating cylinder. When the rotating cylinder rotates through the uninterrupted combustion After the fuel injector 78 receives the injected fuel, the rotating cylinder gradually communicates with the fixed combustion chamber 44a. The explosion of the fixed combustion chamber explosively compresses and detonates the mixture of high-pressure gas and fuel in the rotating cylinder. The high-pressure gas and The deflagration of the fuel mixture produces a violent shock wave that is ejected from the jet channel 35a, thereby obtaining a huge propulsion force to propel the aircraft in which the deflagration engine is located to fly at hypersonic or supersonic speeds. When the rotating cylinder continues to rotate and leaves the fixed combustion chamber, it is left behind in the fixed combustion chamber. After the exhaust gas in the rotating cylinder is discharged from the exhaust passages 51a and 51b, the rotating cylinder receives the oncoming flow from the intake passage again and enters the next working cycle, because this deflagration engine has an attached machine to drive the flat-rotating compressor to generate high pressure. gas, so the deflagration engine can be started when there is no forward speed, and the deflagration engine can also be started with oxygen combustion assistance.

Claims

A deflagration engine in which there is a rotating cylinder barrier between the inlet and the fixed combustion chamber, and the gas pressure in the fixed combustion chamber is much greater than the gas pressure that can be generated at the intake end, including a shaft (11a), characterized in that the deflagration engine It also includes an organic casing (1), a rotating cylinder (17), a fixed combustion chamber (44a), and a vent passage (51b, 51a). When the deflagration engine is working, the gas pressure is much lower than the gas in the fixed combustion chamber (44a). The high-pressure combustion-supporting gas enters the rotating cylinder (17) from the air intake end. When the rotating cylinder continues to rotate and reaches a position that is not connected to the intake port, the rotating cylinder receives fuel injected from the fuel injector and continues to rotate. When the rotating cylinder After the cylinder rotates to a position connected to the fixed combustion chamber, the mixture of combustion-supporting gas and fuel in the rotating cylinder deflagrates with the high-pressure combustion gas in the fixed combustion chamber to generate huge energy to do work. The rotating cylinder continues to rotate to a position where it is no longer connected to the fixed combustion chamber. After the chamber is connected, the exhaust gas left in the rotating cylinder is released through the exhaust passage and enters the next working cycle.
A deflagration engine in which the air inlet end is not connected to a fixed combustion chamber and the pressure at the rear of the combustion chamber is much greater than the pressure at the front, includes an air inlet (50a), an air guide (89), bearings (10a, 10b), and a shaft. (11a) and aircraft (77), characterized in that the deflagration engine also includes an organic casing (1), a rotating cylinder (17), a fixed combustion chamber (44a), end walls (52a, 52b) at both ends of the rotating cylinder, a rotating Cylinder partition (18), inner circular wall of the rotating cylinder (25), continuous fuel injector (78), igniter (45a), injection passage (35a), baffle plate (88), exhaust passage (51a, 51b); The inner circular wall of the rotating cylinder is fixedly connected to the shaft through the end walls at both ends of the rotating cylinder to form an annular groove, and then the annular groove is divided into 12 identical rotating cylinders through 12 rotating cylinder partitions. The two ends of the cylinder partition are sealed and fixedly connected to the end walls of the rotating cylinder, and the inner side is sealed and fixedly connected to the inner circular wall of the rotating cylinder. The rotating cylinder partition is a hollow plate, that is, the rotating cylinder partition has an interlayer space, and the cooling air flows from the rotating cylinder. After entering the left space inside the inner circular wall of the rotating cylinder through the air hole on the end wall of the left end of the cylinder, it then enters the interlayer space of the rotating cylinder partition to cool the rotating cylinder partition, and then passes through the right space inside the inner circular wall of the rotating cylinder. The air holes in the side space and the end wall at the right end of the rotating cylinder are discharged to the outside world; they are discharged to the outside world by the shaft, the end walls at both ends of the rotating cylinder, the inner circular wall of the rotating cylinder and the rotating cylinder partition To form a rotor, the inner wall of the casing matches the motion trajectory of the rotor when it rotates. That is, the gap between the inner wall of the casing and the rotor is extremely small, but the inner wall of the casing does not hinder the rotation of the rotor. The bearings at both ends of the rotor are limited to the machine by corresponding bearing sleeves. on the shell; the bearing sleeve, casing, inlet duct, fixed combustion chamber, jet duct and exhaust duct are a fixedly connected whole. The fixedly connected whole is fixedly installed on the aircraft. When the aircraft equipped with this deflagration engine flies at a certain speed After the speed exceeds 300 kilometers per hour, the oncoming flow from the intake port, that is, the speed difference ram airflow, can enter the rotating cylinder and push the rotor to rotate at high speed by pushing the rotating cylinder partition. When the rotating cylinder rotates to the position of the continuous fuel injector, position, the outer edge of the rotating cylinder is in contact with the inner wall of the casing, and its internal space is not connected to the outside world. The fuel injected by the continuous fuel injector is instantly mixed evenly with the violently moving air that has entered the rotating cylinder. When the rotating cylinder After the rotating cylinder continues to rotate until its internal space is connected to the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber will explosively compress the violently moving fuel and air mixture in the rotating cylinder, causing the fuel and air to mix. Then the deflagration shock wave detonates the mixture of fuel and air in the rotating cylinder behind and deflagrates. This deflagration engine detonates with explosions like this, and the explosions are connected to generate ultra-high-pressure airflow with tens of The speed of Mach or hundreds of Mach bursts from the jet duct to the rear of the aircraft, thus generating huge propulsion force to push the aircraft to fly at hypersonic or supersonic speeds. If necessary, it can also fly at subsonic speeds. When the rotating cylinder continues to rotate to the point where it is no longer fixed, When the combustion chamber is connected to the exhaust duct only, the burned gas remaining in the rotating cylinder will be released from the exhaust duct. When the rotating cylinder continues to rotate until it is connected to both the exhaust duct and the intake duct, from The ram airflow entering the intake passage will enter the rotating cylinder to clean the rotating cylinder, so that the exhaust gas left in the rotating cylinder completely flows out from the exhaust passage. When the rotating cylinder continues to rotate until it is only connected to the intake passage, the ram airflow will It will re-enter the rotating cylinder and push the rotor to rotate at high speed to enter the next working cycle; in this deflagration engine, after the air and fuel are evenly mixed, the mixture is impacted by the deflagration shock wave generated previously and mixed with the detonation before deflagration. Its combustion effect cannot be achieved by other jet engines. Good combustion effect can determine that this deflagration engine is highly efficient and energy-saving. Advantages: The intake end of this deflagration engine is not connected to the fixed combustion chamber. The air at the intake end is transported to the fixed combustion chamber cylinder by cylinder through the rotating cylinder. Therefore, no matter how high the pressure inside the fixed combustion chamber is, it will not It will affect the air at the intake end to effectively enter the fixed combustion chamber. Therefore, the jet duct of the deflagration engine can be made very small, so small that the jet duct is only one tenth of the intake duct, so that the fixed combustion can be achieved. A huge pressure is generated in the chamber, causing the airflow speed ejected from the jet channel to reach tens of Machs or hundreds of Machs, so that the deflagration engine can propel the aircraft to achieve hypersonic flight and efficiently convert the energy generated by the deflagration engine into propulsion energy.
A fan-pressure deflagration engine started at zero forward speed, including a casing (1), bearings (10a, 10b), transmission shaft (3), connecting plates (79a, 79b), bevel gears (37a, 37b), and ignition (45a, 45b), compressor fan (47), diffuser (46), a mechanism (81) for injecting fuel from the fuel injection port into the rotating cylinder, an attached machine (43), and a shaft (11a), which are characterized by: The fan-pressure deflagration engine also includes a fixed baffle (13), an air inlet communication port (16a, 16b), an outer circular wall (27a, 27b) of the rotating cylinder, a rotating cylinder partition (18), and an annular partition (80 ), rotating cylinder (17), inner circular wall of the rotating cylinder (25), deflagration baffle (28), deflagration communication port (29a, 29b), injection passage (35a, 35b), fuel injection port (30a, 30b) , the exhaust port (34a, 34b), the inner circular wall (42a, 42b) of the fixed combustion chamber, the fixed combustion chamber (44a, 44b); the rotating cylinder is connected through the connecting plate (79a, 79b) fixed on the shaft (11a) The inner circular wall (25) of the rotating cylinder is fixedly connected to the shaft (11a), and the outer circular wall (27a) of the rotating cylinder is connected through 15 rotating cylinder partitions (18) fixedly connected to the inner circular wall (25) of the rotating cylinder. , 27b) is fixedly connected to the inner circular wall (25) of the rotating cylinder. The 15 rotating cylinder partitions separate the annular space between the inner circular wall (25) of the rotating cylinder and the outer circular wall (27a, 27b) of the rotating cylinder. Divided into 15 rotating cylinders, the fixed connector is combined with the bevel gear (37a), annular partition (80) and the compressor fan (47) fixed on the shaft (11a) to form the rotor of this engine; this fan pressure deflagration engine works When the air intake end is not connected to the fixed combustion chamber, the compressed air generated by the compressor fan is transported cylinder by cylinder to the position of the fuel injection inlet to receive the injected fuel, and then transported to the fixed combustion chamber. position accepts fixed burning Due to the explosive compression of the explosion shock wave, the explosively compressed fuel and air mixture is deflagrated and sprayed into the fixed combustion chamber and ejected from the jet channel behind the fixed combustion chamber, thereby obtaining huge thrust to propel the aircraft where the fan-pressure deflagration engine is located. During hypersonic or supersonic flight, after the rotating cylinder rotates to the point where it is no longer connected to the fixed combustion chamber, the exhaust gas left in the rotating cylinder will be discharged to the outside world behind through the air passage connected to the exhaust port, draining the abandoned rotating cylinder. When it rotates to the position connected to the air inlet communication port, it receives the compressed air generated by the compressor fan again and enters the next working cycle.
A deflagration engine. The deflagration engine includes an organic casing (1), a flat-rotating rotor end wall (9a, 9b), a flat-rotating shaft (6a, 6b, 6c, 6d), a fixed shaft (2), and a flat-rotating cylinder ( 86a, 86b), translational piston (5a, 5b, 5c, 5d), divider (8), exhaust port (21a, 21b), blocking plug (22a, 22b, 22c, 22d), narrow mouth (24a, 24b), counter-rotating compressor (68), air inlet (50a, 50b), counter-rotating gears (7a, 7b, 7c, 7d), transmission gears (15a, 15b, 15c, 15d), transmission gear shaft (4a , 4b, 4c, 4d), rotating cylinder (17), rotating cylinder partition (18), inner circular wall of the rotating cylinder (25), injection passage (35a), fixed combustion chamber (44a), igniter (45a) , exhaust passages (51a, 51b), continuous fuel injectors (78), bearings (10a, 10b, 10c), shafts (11a, 11b), fixed gears (26), end walls (52a, 52a, 52b), attached engine (43), characterized in that the deflagration engine also includes a high-pressure gas inlet (40); a flat-rotating piston, a flat-rotating shaft and a flat-rotating gear are combined into a fixed connection body, and the flat rotation is limited through gear transmission. The rotary piston can only rotate in parallel. The high-pressure air discharged from the exhaust port (21a) and the exhaust port (21b) enters the rotary cylinder from the high-pressure gas inlet (40) through the gas channel. When this deflagration engine propels the aircraft to fly at hypersonic speed, The openings of the inlet ducts (50a, 50b) face the front, the oncoming flow enters the rotating cylinder from the inlet duct (50a), and the oncoming flow enters the flat-rotating compressor (68) from the inlet duct (50b) and is compressed into After the high-pressure gas enters the rotating cylinder through the gas channel, it mixes with the gas entering from the intake port (50a), so that there is sufficient high-pressure gas in the rotating cylinder. When the rotating cylinder rotates and receives injection through the continuous fuel injector (78) After entering the fuel, the rotating cylinder gradually communicates with the fixed combustion chamber (44a), and the explosion of the fixed combustion chamber The fire explosively compresses and detonates the mixture of high-pressure gas and fuel in the rotating cylinder. The mixture of high-pressure gas and fuel deflagrates and generates violent shock waves ejected from the jet channel (35a), thus obtaining huge propulsion force to promote the deflagration. When the aircraft where the engine is located is flying at hypersonic or supersonic speeds, when the rotating cylinder continues to rotate and leaves the fixed combustion chamber, and the exhaust gas left in the rotating cylinder is discharged from the exhaust passage (51a, 51b), the rotating cylinder receives air from the intake again. The oncoming flow that enters the channel enters the next working cycle. Because the deflagration engine includes an attached machine and a flat-turning compressor, the deflagration engine can be started when there is no forward speed.