WO2023216762A1 - Moteur à déflagration - Google Patents

Moteur à déflagration Download PDF

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Publication number
WO2023216762A1
WO2023216762A1 PCT/CN2023/085521 CN2023085521W WO2023216762A1 WO 2023216762 A1 WO2023216762 A1 WO 2023216762A1 CN 2023085521 W CN2023085521 W CN 2023085521W WO 2023216762 A1 WO2023216762 A1 WO 2023216762A1
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WO
WIPO (PCT)
Prior art keywords
rotating cylinder
combustion chamber
deflagration
rotating
engine
Prior art date
Application number
PCT/CN2023/085521
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English (en)
Chinese (zh)
Inventor
龙全洪
Original Assignee
龙全洪
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Publication date
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Publication of WO2023216762A1 publication Critical patent/WO2023216762A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/075—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with multiple pulse-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • FIG. 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
  • Figure 12 9a - end wall of the horizontal rotating rotor, 1 - casing, 6a, 6b, 6c, 6d - horizontal rotating shaft, 2 - fixed shaft.
  • 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.
  • FIG. 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
  • FIG 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.
  • 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.
  • FIG 18 1 - casing, 11b - shaft, 16a - air inlet communication port, 28 - deflagration baffle, 29a - deflagration communication port, 30a - fuel injection inlet, 34a - exhaust port.
  • 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.
  • 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.
  • FIG. 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.
  • 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.
  • the rotating cylinder receives fuel injected from the fuel injector and continues to rotate.
  • the rotating cylinder rotates to a position where it is 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 produce huge energy and work.
  • 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.
  • 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 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
  • 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.
  • 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.
  • the oncoming flow from the inlet can enter the rotating cylinder and push through
  • the rotating cylinder partition pushes the rotor to rotate at high speed.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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
  • 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.
  • the deflagration baffle also has deflagration communication ports 29a, 29b, fuel injection ports 30a, 30b, vent ports 34a, 34b.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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.
  • 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
  • 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.
  • the rotary cylinder 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.
  • 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.
  • 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.
  • 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.
  • a deflagration flat-rotating engine that produces rotational power.
  • 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 34
  • 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.
  • the gas is discharged from the exhaust port 21b.
  • 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.
  • the rotating cylinder 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.
  • 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
  • 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.
  • 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.
  • the rotating cylinder continues to rotate and leaves the fixed combustion chamber, it is left behind in the fixed combustion chamber.
  • the rotating cylinder 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.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

L'invention concerne un moteur à déflagration ayant une extrémité d'admission d'air qui n'est pas en communication avec une chambre de combustion fixe, le moteur à déflagration comprenant un conduit d'admission d'air, un palier, un arbre et un aéronef. Le moteur à déflagration comprend en outre un carter, un cylindre rotatif, une chambre de combustion fixe, des parois d'extrémité des deux extrémités du cylindre rotatif, une cloison de cylindre rotatif, une paroi circulaire interne du cylindre rotatif, un injecteur de carburant sans interruption, un allumeur, un conduit de jet et un conduit de purge. Un flux entrant de tête, entrant à partir du conduit d'admission d'air, entre dans le cylindre rotatif pour pousser un rotor afin qu'il tourne à une vitesse élevée. Après que le cylindre rotatif a tourné à travers la position de l'injecteur de carburant sans interruption pour recevoir du carburant injecté, le cylindre rotatif continue à tourner pour atteindre une position qui est en communication avec la chambre de combustion fixe. Une onde de choc explosive dans la chambre de combustion fixe comprime de manière explosive un mélange de carburant et d'air dans le cylindre rotatif, de telle sorte que le mélange de carburant et d'air déflagre pour produire une onde de choc explosive, de façon à provoquer une éjection à partir du conduit de jet. Après que le cylindre rotatif a tourné pour ne pas être en communication avec la chambre de combustion fixe, les gaz d'échappement restant dans le cylindre rotatif sont purgés, pour entrer dans le cycle de travail suivant.
PCT/CN2023/085521 2022-05-07 2023-03-31 Moteur à déflagration WO2023216762A1 (fr)

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CN202210659862.X 2022-05-07
CN202210659862.XA CN116201657A (zh) 2022-05-07 2022-05-07 爆燃发动机

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WO2023216762A1 true WO2023216762A1 (fr) 2023-11-16

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5946903A (en) * 1997-04-03 1999-09-07 Marquard; Michael Mason Internal combustion engine having a separate rotary combustion chamber
US6536403B1 (en) * 2001-09-27 2003-03-25 Magdi M Elsherbini Direct drive rotary engine
CN104929762A (zh) * 2015-06-29 2015-09-23 蔡勇 压缩比可调的转子发动机
CN106593642A (zh) * 2017-01-19 2017-04-26 龙全洪 平转发动机
CN107489457A (zh) * 2017-09-08 2017-12-19 龙全洪 多功能发动机
CN107559103A (zh) * 2017-09-14 2018-01-09 王闯业 一种双转子冲压发动机
CN107701301A (zh) * 2017-10-29 2018-02-16 龙全洪 简易内燃机

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5946903A (en) * 1997-04-03 1999-09-07 Marquard; Michael Mason Internal combustion engine having a separate rotary combustion chamber
US6536403B1 (en) * 2001-09-27 2003-03-25 Magdi M Elsherbini Direct drive rotary engine
CN104929762A (zh) * 2015-06-29 2015-09-23 蔡勇 压缩比可调的转子发动机
CN106593642A (zh) * 2017-01-19 2017-04-26 龙全洪 平转发动机
CN107489457A (zh) * 2017-09-08 2017-12-19 龙全洪 多功能发动机
CN107559103A (zh) * 2017-09-14 2018-01-09 王闯业 一种双转子冲压发动机
CN107701301A (zh) * 2017-10-29 2018-02-16 龙全洪 简易内燃机

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