WO2023216762A1 - Deflagration engine - Google Patents
Deflagration engine Download PDFInfo
- 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
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotating cylinder
- combustion chamber
- deflagration
- rotating
- engine
- Prior art date
Links
- 238000004200 deflagration Methods 0.000 title claims abstract description 139
- 238000002485 combustion reaction Methods 0.000 claims abstract description 128
- 239000000446 fuel Substances 0.000 claims abstract description 79
- 238000005192 partition Methods 0.000 claims abstract description 49
- 238000004891 communication Methods 0.000 claims abstract description 42
- 239000000203 mixture Substances 0.000 claims abstract description 24
- 230000035939 shock Effects 0.000 claims abstract description 15
- 239000002360 explosive Substances 0.000 claims abstract description 9
- 239000007789 gas Substances 0.000 claims description 73
- 238000002347 injection Methods 0.000 claims description 41
- 239000007924 injection Substances 0.000 claims description 41
- 238000004880 explosion Methods 0.000 claims description 16
- 230000005540 biological transmission Effects 0.000 claims description 15
- 238000001816 cooling Methods 0.000 claims description 12
- 239000011229 interlayer Substances 0.000 claims description 9
- 238000005474 detonation Methods 0.000 claims description 7
- 230000000694 effects Effects 0.000 claims description 7
- 230000007246 mechanism Effects 0.000 claims description 7
- 230000000903 blocking effect Effects 0.000 claims description 6
- 239000000567 combustion gas Substances 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 230000004888 barrier function Effects 0.000 claims 1
- 239000000112 cooling gas Substances 0.000 description 18
- 238000000034 method Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Classifications
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- 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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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
本技术属于发动机技术领域This technology belongs to the field of engine technology
现有的像涡喷发动机、涡扇发动机和冲压发动机之类的三通喷气发动机都是通过燃烧室连通进气端和喷气端,燃烧室前部压强必须远大于后部压强才能正常工作,如果燃烧室内的气体压强过大,平转压气机就无法把空气推压进入燃烧室,从而导致无法采用使喷气口比进气口小很多的手段去使喷气口喷出几十马赫或上百马赫的气流,即用三通喷气发动机做推进器的飞行器,无法实现高超音速飞行,其燃烧效果也不好。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.
发明内容Contents of the invention
针对上述技术存在的缺陷,本人设计了一种进气端不跟固定燃烧室连通的爆燃发动机。本发明采取的技术方案如下: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:
一种进气道与固定燃烧室之间有旋转气缸阻隔、并且固定燃烧室内的气体压强远大于进气端能产生的气体压强的爆燃发动机,包括有轴,其特征是该爆燃发动机还包括有机壳,旋转气缸,固定燃烧室,泄气道,本爆燃发动机工作时,气体压强远低于固定燃烧室内的气体压强的助燃气体从进气端进入旋转气缸,当该旋转气缸继续转动到达不与进气道连通的位置后,该旋转气缸接收燃料喷器喷入燃料的同时继续转动,当该旋转气缸转动到达与固定燃烧室连通的位置后,该旋转气缸里的助燃气体与燃料的混合体与固定燃烧室里的高压燃烧气体爆燃产生巨大的能量做功,该旋转气缸继续转动到达不与固定燃烧室连通的位置后,通过泄气道泄掉遗留在旋转气缸里的废气进入下一工作循环。
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.
本发明爆燃发动机的优势Advantages of the deflagration engine of the present invention
1、本爆燃发动机是空气跟燃料混合均匀后,该混合体才受到在先产生的爆燃冲击波冲压并跟爆火混合后才爆燃,其燃烧效果是其他喷气发动机无法达到的,燃烧效果好就能确定本爆燃发动机具有高效节能的优势。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、本爆燃发动机的进气端不跟固定燃烧室连通,是通过旋转气缸把进气端的空气一缸一缸的运输到固定燃烧室,因此,不管固定燃烧室内部的压强有多大,都不会影响进气端的空气有效的进入固定燃烧室,因此,可以把本爆燃发动机的喷气道做得很小,可以小到喷气道只有进气道的十几分之一,从而就能使固定燃烧室内产生巨大的压强,使喷气道喷出的气流速度达到几十马赫或上百马赫,从而本爆燃发动机就能推动飞行器实现高超音速飞行,把本爆燃发动机产生的能量高效的转化为推进能量。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、只要本爆燃发动机所在的飞行器时速达到300公里,就能启动本爆燃发动机,因此本爆燃发动机所在的飞行器既可以高超音速飞行,又可以超音速飞行,也可以亚声速飞行。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、本爆燃发动机的结构简单,工作原理简单,能量的有效利用率特别高,除了供油机构外,其余的机构一般机械厂家都能制造,制造成本不到涡扇发动机的1/10,本爆燃发动机的推重比可以超越100,是其他任何喷气发动机都无法达到的,本爆燃发动机可以喷出几十马赫或上百马赫的气流。本爆燃发动机有很多种实施方式,既可做成零前进速度启动的爆燃喷气发动机,也可以做成专门产生旋转动力的爆燃发动机,本爆燃发动机可以应用到多个领域。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、可以用冷却气体有效的冷却本爆燃发动机的转子内部的夹层空间,从而就能提高本爆燃发动机转子能承受的最高温度。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.
图1、图2、图3、图4、图5、图6、图7、图8、图9、图10、图11、图12、图13、图14、图15、图16、图17、图18、图19、图20、图21、图22是本设计爆燃发动机的结构示意图。在图1中,77—飞行器,50a—进气道,78—不间断式燃料喷器,1—机壳,89—导气器,17—旋转气缸,11a—轴,35a—喷气道,44a—固定燃烧室,25—旋转气缸的内圆壁,18—旋转气缸隔板,45a—点火器,51a、51b—泄气道。在图2中,50a—进气道,1—机壳,10a、10b—轴承,44a—固定燃烧室,18—旋转气缸隔板,88—阻隔板,25—旋转气缸的内圆壁,52a、52b—旋转气缸两端的端壁,35a—喷气道,11a—轴。在图3中:1—机壳,13—固定档板,16a、16b—进气连通口,11a—轴。在图4中:1—机壳,27a—旋转气缸的外圆壁,17—旋转气缸,18—旋转气缸隔板,11a—轴,25—旋转气缸的内圆壁。在图5中:1—机壳,35a、35b—喷气道,29a、29b—爆燃连通口,11a—轴,30a、30b—燃料喷入口,34a、34b—泄气口,28—爆燃挡板。在图6中:3—传动轴,47—压气风扇,81—使燃料从燃料喷入口喷入旋转气缸的机构,46—扩压器,43—附机,13—固定挡板,37a、37b—伞齿轮,10a、10b—轴承,1—机壳,80—环形隔板,27a、27b—旋转气缸的外圆壁,79a、79b—连接板,29a、29b—爆燃连通口,28—爆燃挡板,17—旋转气缸,25—旋转气缸的内圆壁,45a、45b—点火器,42a、42b—固定燃烧室的内圆壁,44a、44b—固定燃烧室,35a、35b—喷气道,11a—轴。在图7中,28—爆燃挡板,54a、54b—冷却气体通道,1—机壳,29a—爆燃连通口,55—冷却气体进口,11a—轴,16a—进气连通口,30a—燃料喷入口。在图8中:17—旋转气缸,56—转子喷气口,54a、54b—冷却气体通道,35a—喷气道,1—机壳,18—旋转气缸隔板,27a、27b—旋转气缸的外圆壁,25—旋转气缸的内圆壁,11a—轴。在图9中:57a、57b—旋转气缸
右端的底壳板,58a、58b—冷却气体出口,11a—轴。在图10中:54、54b—冷却气体通道,1—机壳,11a—轴。在图11中:54a、54b—冷却气体通道,62—平转压气机,27a、27b—旋转气缸的外圆壁,25—旋转气缸的内圆壁,81—使燃料从燃料喷入口喷入旋转气缸的机构,29a—爆燃连通口,17—旋转气缸,44a—固定燃烧室,28—爆燃挡板,60—推力轴承,57a、57b—旋转气缸右端的底壳板,35a—喷气道,10b—轴承,11a—轴,59—与轴承套为一体的轴承支架,16a—进气连通口。在图12中:9a—平转转子端壁,1—机壳,6a、6b、6c、6d—平转轴,2—固定轴。在图13中:1—机壳,21a、21b—排气口,22a、22b、22c、22d—堵流塞,5a、5b、5c、5d—平转活塞,86a、86b—平转气缸,6a、6b、6c、6d—平转轴,20a、20b—进气口,2—固定轴,24a、24b—隘口,8—分界器,68—平转压气机。在图14中:1—机壳,6a、6b、6c、6d—平转轴,7a、7b、7c、7d—平转齿轮,15a、15b、15c、15d—传动齿轮,4a、4b、4c、4d—传动齿轮轴,26—固定齿轮,11b—轴。在图15中:1—机壳,2—固定轴,4a、4c—传动齿轮轴,5a、5c—平转活塞,6a、6c—平转轴,7a、7b—平转齿轮,8—分界器,9a、9b—平转转子端壁,10a、10b—轴承,11a、11b—轴,15a、15c—传动齿轮,16a—进气连通口,17—旋转气缸,23a、23b—储气冷却槽,25—旋转气缸的内圆壁,26—固定齿轮,27a、27b—旋转气缸的外圆壁,28—爆燃挡板,29a—爆燃连通口,35a—喷气道,44a—固定燃烧室,54b—冷却气体通道,57a、57b—旋转气缸右端的底壳板,59—与轴承套为一体的轴承支架,60—推力轴承,68—平转压气机。在图16中:1—机壳,2—固定轴,5a、5b、5c、5d—平转活塞,6a、6b、6c、6d—平转轴,8—分界器,20a、20b—进气口,21a、21b—排气口,22a、22b、22c、22d—堵流塞,24a—隘口,86a、86b—平转气缸,69—平转发动机。在图17
中:1—机壳,11b—轴,17—旋转气缸,18—旋转气缸隔板,25—旋转气缸的内圆壁,27a—旋转气缸的外圆壁。在图18中:1—机壳,11b—轴,16a—进气连通口,28—爆燃挡板,29a—爆燃连通口,30a—燃料喷入口,34a—泄气口。在图19中:1—机壳,2—固定轴,4a、4c—传动齿轮轴,5a、5c—平转活塞,6a、6c—平转轴,7a、7b—平转齿轮,8—分界器,9a、9b—平转转子端壁,10a、10b—轴承,11a、11b—轴,15a、15c—传动齿轮,16a—进气连通口,17—旋转气缸,25—旋转气缸的内圆壁,26—固定齿轮,27a、27b—旋转气缸的外圆壁,28—爆燃挡板,29a—爆燃连通口,44a—固定燃烧室,57a—旋转气缸右端的底壳板,60—推力轴承,66—爆火连通口,69—平转发动机。在图20中:86a、86b—平转气缸,1—机壳,2—固定轴,5a、5b、5c、5d—平转活塞,6a、6b、6c、6d—平转轴,8—分界器,21a、21b—排气口,22a、22b、22c、22d—堵流塞,24a、24b—隘口,68—平转压气机,50b—进气道。在图21中:1—机壳,11a—轴,17—旋转气缸,18—旋转气缸隔板,25—旋转气缸的内圆壁,35a—喷气道,40—高压气体进口,44a—固定燃烧室,45a—点火器,50a—进气道,51a、51b—泄气道,78—不间断式燃料喷器。在图22中:1—机壳,2—固定轴,4b、4d—传动齿轮轴,5b、5d—平转活塞,6b、6d—平转轴,7c、7d—平转齿轮,8—分界器,9a、9b—平转转子端壁,10a、10b、10c—轴承,11a、11b—轴,15b、15d—传动齿轮,18—旋转气缸隔板,25—旋转气缸的内圆壁,26—固定齿轮,35a—喷气道,44a—固定燃烧室,50、50b—进气道,52a、52b—旋转气缸两端的端壁,68—平转压气机,43—附机。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.
1、一种进气道与固定燃烧室之间有旋转气缸阻隔、并且固定燃烧室内的气
体压强远大于进气端能产生的气体压强的爆燃发动机,即一种进气端不跟固定燃烧室连通,燃烧室后部压强远大于前部压强的爆燃发动机,包括有轴11a,其特征是该爆燃发动机还包括有机壳1,旋转气缸17,固定燃烧室44a,泄气道51b、51a,本爆燃发动机工作时,气体压强远低于固定燃烧室44a内的气体压强的助燃气体从进气端进入旋转气缸17,当该旋转气缸继续转动到达不与进气道连通的位置后,该旋转气缸接收燃料喷器喷入燃料的同时继续转动,当该旋转气缸转动到达与固定燃烧室连通的位置后,该旋转气缸里的助燃气体与燃料的混合体与固定燃烧室里的高压燃烧气体爆燃产生巨大的能量做功,该旋转气缸继续转动到达不与固定燃烧室连通的位置后,通过泄气道泄掉遗留在旋转气缸里的废气进入下一工作循环。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、一种进气端不跟固定燃烧室连通、燃烧室后部压强远大于前部压强的爆燃发动机,该方式的具体结构如图1、图2所示,该爆燃发动机,包括有进气道50a,导气器89,轴承10a、10b,轴11a和飞行器77等应该有的现有技术,其特征是该爆燃发动机还包括有机壳1、旋转气缸17、固定燃烧室44a、旋转气缸两端的端壁52a、52b、旋转气缸隔板18、旋转气缸的内圆壁25、不间断式燃料喷器78、点火器45a、喷气道35a、阻隔板88、泄气道51a、51b;通过旋转气缸两端的端壁把旋转气缸的内圆壁固定连接在轴上形成一个环形槽,再通过12块旋转气缸隔板把该环形槽等分成12个完全相同的旋转气缸,旋转气缸隔板的两端与旋转气缸两端的端壁密封固定连接,内侧与旋转气缸的内圆壁密封固定连接,旋转气缸隔板是空心板,即旋转气缸隔板有夹层空间,冷却空气从旋转气缸左端的端壁上的气孔中进入旋转气缸的内圆壁内部的左侧空间后,再进入旋转气缸隔板的夹层空间冷却旋转气缸隔板,然后再经过旋转气缸的内圆壁内部的右侧空间和旋转气缸右端的端壁上的气孔排放到外界;
由轴、旋转气缸两端的端壁、旋转气缸的内圆壁和旋转气缸隔板组成转子,机壳内壁与转子转动时的运动轨迹切合,即:机壳内壁与转子之间的间隙特别小,但机壳内壁不阻碍转子转动,转子两端的轴承被相应的轴承套限定在机壳上;轴承套、机壳、进气道、固定燃烧室、喷气道和泄气道是一个固定连接的整体,该固定连接的整体固定安装在飞行器上,当安装本爆燃发动机的飞行器的飞行速度大于300公里每小时后,从进气道进入的迎面来流即速差冲压气流就能进入旋转气缸并通过推动旋转气缸隔板推动转子高速转动,当旋转气缸转动到不间断式燃料喷器的位置时,该旋转气缸外缘与机壳内壁切合,其内部空间不与外界连通,不间断式燃料喷器喷入的燃料瞬间就与已进入旋转气缸内的剧烈运动的空气混合均匀,当该旋转气缸继续转动到其内部空间与固定燃烧室连通后,固定燃烧室里的爆炸冲击波就会对该旋转气缸里的剧烈运动的燃料和空气的混合体进行爆炸式压缩,使燃料和空气的混合体爆散到固定燃烧室中爆燃,随后该爆燃冲击波又引爆后面的旋转气缸里的燃料和空气的混合体爆燃,本爆燃发动机就是像这样以爆引爆,爆爆相连,产生特高压气流以几十马赫或上百马赫的速度从喷气道中爆喷到飞行器后方,从而产生巨大的推进力推动飞行器高超音速或超音速飞行,如有必要也可以亚音速飞行,当该旋转气缸继续转动到不与固定燃烧室连通,只与泄气道连通时,剩余在旋转气缸里的燃烧过的气体就从泄气道中泄出,当该旋转气缸继续转动到既与泄气道连通,又与进气道连通时,从进气道中进入的冲压气流就会进入旋转气缸清扫该旋转气缸,使遗留在该旋转气缸内的废气完全从泄气道中流出,当该旋转气缸继续转动到只与进气道连通时,冲压气流就会重新进入该旋转气缸,并推动转子高速转动进入下一个工作循环;本爆燃发动机是空气跟燃料混合均匀后,该混合体才受到在先产生的爆燃冲击波冲压并跟爆火混合后才爆燃,其燃烧效果是其他喷气发动机
无法达到的,燃烧效果好就能确定本爆燃发动机具有高效节能的优势;本爆燃发动机的进气端不跟固定燃烧室连通,是通过旋转气缸把进气端的空气一缸一缸的运输到固定燃烧室,因此,不管固定燃烧室内部的压强有多大,都不会影响进气端的空气有效的进入固定燃烧室,因此,可以把本爆燃发动机的喷气道做得很小,可以小到喷气道只有进气道的十几分之一,从而就能使固定燃烧室内产生巨大的压强,使喷气道喷出的气流速度达到几十马赫或上百马赫,从而本爆燃发动机就能推动飞行器实现高超音速飞行,把本爆燃发动机产生的能量高效的转化为推进能量。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、一种零前进速度启动的扇压爆燃发动机,该方式的具体结构如图3、图4、图5、图6所示。扇压爆燃发动机包括有机壳1,轴承10a、10b,传动轴3,连接板79a、79b,伞齿轮37a、37b,点火器45a、45b,压气风扇47,扩压器46,使燃料从燃料喷入口喷入旋转气缸的机构81,附机43,轴11a,其特征是本扇压爆燃发动机还包括有固定挡板13,进气连通口16a、16b,旋转气缸的外圆壁27a、27b,旋转气缸隔板18,环形隔板80,旋转气缸17,旋转气缸的内圆壁25,爆燃挡板28,爆燃连通口29a、29b,喷气道35a、35b,燃料喷入口30a、30b,泄气口34a、34b,固定燃烧室的内圆壁42a、42b,固定燃烧室44a、44b;通过固定在轴11a上的连接板79a、79b把旋转气缸的内圆壁25固定连接在轴11a上,通过固定连接在旋转气缸的内圆壁25上的15块旋转气缸隔板18、把旋转气缸的外圆壁27a、27b固定连接在旋转气缸的内圆壁25上,15块旋转气缸隔板把旋转气缸的内圆壁25与旋转气缸的外圆壁27a、27b之间的环形空间等分成15个旋转气缸,该固定连接体与固定在轴11a上的伞齿轮37a、环形隔板80和压气扇47组合成本发动机的转子,通过一条长方形钢板把一块旋转气缸隔板18的夹层空间分成左侧空间和右侧空间,冷却空气从轴
孔中进入环形隔板80的左侧空间再通过旋转气缸隔板18的左侧夹层空间进入旋转气缸的外圆壁的夹层空间并向右运动,向右运动的冷却空气再通过其后面的一块旋转气缸隔板的右侧夹层空间进入环形隔板80的右侧空间,然后再通过轴孔排放到外界,从而就有效的冷却了转子内部所需要冷却的部位,保障不会因为转子内部温度过高而损坏转子,压气风扇就是涡扇发动机的风扇,只是按比例缩小了很多,扩压器中部的与扩压器为一体的轴承套套在轴承10a上,轴承10a套在轴11a上,扩压器的外缘与机壳固定连接,旋转气缸前端的固定挡板13的外缘与机壳固定连接,固定挡板13上还固定连接有两个轴承套限定套在传动轴上的两个轴承,使与传动轴固定连接的伞齿轮37b和固定在轴上的伞齿轮37a齿合,保障产生旋转动力的附机43产生的旋转动力能有效的传递到转子上去,旋转气缸前端的固定挡板上有进气连通口16a、16b,还有能穿过轴11a的轴孔,旋转气缸与固定燃烧室之间的爆燃挡板28的外缘与机壳固定连接,中部的轴孔套在轴11a上,该爆燃挡板上还有爆燃连通口29a、29b,燃料喷入口30a、30b,泄气口34a、34b,转子转动时,组成旋转气缸的各部件的左端与进气端的固定挡板13切合,右端与爆燃挡板28切合,切合即间隙小,相擦而过;本扇压爆燃发动机工作时,进气端不与固定燃烧室连通,是靠旋转气缸一气缸一气缸的把压气风扇产生的压缩空气运送到燃料喷入口的位置接受喷入的燃料后,才运送到与固定燃烧室连通的位置接受固定燃烧的爆炸冲击波的爆炸式压缩,受到爆炸式压缩的燃料和空气混合体才爆燃喷进固定燃烧室并从固定燃烧室后方的喷气道喷出,从而获得巨大的推力推动该扇压爆燃发动机所在的飞行器高超音速或超音速飞行,该旋转气缸转动到不与固定燃烧室连通后,遗留在旋转气缸里的废气就会通过与泄气口联通的气道排泄到后方的外界,泄了废弃的旋转气缸转动到与进气连通口连通的位置时,又重新接收压气扇产生的
压缩空气,进入下一个工作循环,因为本扇压爆燃发动机有附机43和亚气风扇44,所以,本扇压爆燃发动机是在其所在飞行器零前进速度的情况下启动。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、一种爆燃转喷发动机,该方式的具体结构如图7、图8、图9、图10、图11所示,爆燃转喷发动机包括有机壳1,轴承10b,轴11a,平转压气机68,使燃料从燃料喷入口喷入旋转气缸的机构81,其特征是本爆燃转喷发动机还包括有爆燃挡板28,冷却气体通道54a、54b,爆燃连通口29a,冷却气体进口55,燃料喷入口30a,进气连通口16a,喷气道35a,转子喷气口56,旋转气缸17,旋转气缸隔板18,旋转气缸的内圆壁25,旋转气缸的外圆壁27a、27b,旋转气缸右端的底壳板57a、57b,冷却气体出口58a、58b,固定燃烧室44a,推力轴承60,与轴承套为一体的轴承支架59;平转压气机68可以是涡扇发动机的低压平转压气机部分或其它的平转压气机,平转压气机包括启动马达在内,平转压气机可以共用轴11a并设置轴承支撑轴11a,不需要平转压气机产生太大的气体压力,先把旋转气缸右端的底壳板57a、57b固定连接在轴11a上,再把旋转气缸的内圆壁25和旋转气缸的外圆壁27a、27b固定连接在旋转气缸右端的底壳板上,然后再把10块旋转气缸隔板18固定连接在旋转气缸的内圆壁与旋转气缸的外圆壁之间的环形槽里,10块旋转气缸隔板把该环形槽等分成10个形状相同的旋转气缸,上述连接在一起的固定连接体与平转压气机68中应该固定连接在轴11a上的部件组成本爆燃转喷发动机的转子,转子转动时,组成旋转气缸的部件的左端与爆燃挡板切合,爆燃挡板28中部的抽孔套在轴11a上,外缘与机壳固定连接,与轴承套为一体的轴承支架59的外缘与机壳固定连接,中部的轴承套套在轴承10b上,冷却气体从冷却气体进口55进入旋转气缸的内圆壁25与轴11a之间的环形空间,再经过旋转气缸隔板18的夹层空间进入旋转气缸的外圆壁27a、27b的夹层
空间,然后再从冷却气体出口58a、58b流出,每一个旋转气缸的旋转气缸的外圆壁上都设置有一个转子喷气口56,如果本爆然转喷发动机是用去做产生旋转动力的机器,要做成切向喷出的转子喷气口,并且,喷气道35a的气体出口要做得大一些,如果本爆然转喷发动机是用去做喷气发动机,转子喷气口的中心线与半径的交角要做成130度左右,并且喷气道35a的气体出口要做得小一些,在没有前进速度的状态下,可以通过启动马达启动本爆然转喷发动机,启动本爆燃转喷发动机后,平转压气机68产生的压缩空气就会从进气连通口16a进入旋转气缸,当本爆燃转喷发动机的旋转气缸转动到与进气连通口16a连通时,经过平转压气机68增压后的压缩空气就会快速的进入该旋转气缸,当该旋转气缸继续转动离开进气连通口到达燃料喷入口30a的位置接受从燃料喷入口喷入的燃料后,该旋转气缸开始与固定燃烧室连通,固定燃烧室里的爆火从一侧进入该旋转气缸对该旋转气缸内的燃料和空气混合体爆炸式压缩燃烧,然后定容加热,当该旋转气缸转到其开口完全对着固定燃烧室时,该旋转气缸里的燃烧过的燃料和空气混合体膨胀爆炸进入固定燃烧室,并从与固定燃烧室连通的转子喷气口喷入喷气道,从而获得旋转推力推动转子转动,与此同时,喷入喷气道的爆燃气体从喷气道中向后方喷出,从而获得巨大的推进力推动本爆燃转喷发动机所在的飞行器高超音速飞行,该旋转气缸继续转动到不与固定燃烧室连通后,该旋转气缸内遗留的气体继续从转子喷气口喷出,当该旋转气缸转动到转子喷气口被机壳内壁堵住时,旋转气缸内的气体基本喷完,当该旋转气缸转动到与进气连通口16a连通时,经过平转压气机68增压后的压缩空气又快速地进入该旋转气缸,进入下一个工作循环。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、一种平压爆燃发动机,该方式的具体结构如图12、图13、图14、图7、图8、图9、图15所示,包括有机壳1,平转转子端壁9a、9b,固定轴2,
平转气缸86a、86b,平转轴6a、6b、6c、6d,平转齿轮7a、7b、7c、7d,传动齿轮15a、15b、15c、15d,传动齿轮轴4a、4b、4c、4d,固定齿轮26、冷却气体通道54a、54b,轴11a、11b,冷却气体进口55,爆燃挡板28,爆燃连通口29a,进气连通口16a,燃料喷入口30a,旋转气缸17,转子喷气口56,喷气道35a,旋转气缸隔板18,旋转气缸的外圆壁27a、27b,旋转气缸的内圆壁25,旋转气缸右端的底壳板57a、57b,冷却气体出口58a、58b,轴承10a、10b,固定燃烧室44a,与轴承套为一体的轴承支架59,推力轴承60,平转压气机68,其特征是本平压爆燃发动机还包括有进气口20a、20b,排气口21a、21b,堵流塞22a、22b、22c、22d,隘口24a、24b,平转活塞5a、5b、5c、5d,分界器8,储气冷却槽23a、23b;通过齿轮限定平转轴和平转活塞只能平行转动,即在转动过程中的平转活塞的上边缘所对的方向始终不变,平转齿轮7a、平转轴6a和平转活塞5a是一个固定连接体,堵流塞22a、22b、22c、22d固定在平转转子端壁9a和平转转子端壁9b之间,平转转子端壁9a、9b固定连接在轴11a上,通过固定轴把分界器固定连接在机壳上,把分界器与机壳之间的最狭窄的通道称为隘口24a、24b,该隘口只让平转活塞、平转轴和堵流塞通过,不让气体通过,本平压爆燃发动机转动时,从进气口20a进入平转气缸86b的空气被平转活塞5c压缩后经过与排气口21b连通的气体通道进入储气冷却槽23a、23b中,从进气口20b进入平转气缸86a的空气被平转活塞5a压缩后经过与排气口21a连通的气体通道进入储气冷却槽23a、23b中,当旋转气缸转动到能通过进气连通口16a与储气冷却槽连通时,储气冷却槽内的压缩气体就会通过进气连通口快速的进入该旋转气缸,当该旋转气缸继续转动,离开进气连通口并到达燃料喷入口30a的位置接受从燃料喷入口喷入的燃料后,该旋转气缸开始与固定燃烧室连通,固定燃烧室里的爆火对
该旋转气缸内的燃料和空气混合体爆炸式压缩燃烧加热,当该旋转气缸转动到其开口完全对着固定燃烧室时,该旋转气缸里的混合燃烧气体膨胀爆炸进入固定燃烧室,并从与固定燃烧室连通的转子喷气口喷入喷气道,从而就获得旋转动力推动转子转动,与此同时,喷入喷气道的爆燃气体从喷气道中喷出,从而获得巨大的推进力推动本平压爆燃发动机所在的飞行器高超音速飞行,该旋转气缸继续转动到其转子喷气口的喷口被机壳内壁堵住,其内部的气体基本喷完后,就到达进气连通口16a的位置重新接收储气冷却槽里的压缩气体进入下一个工作循环。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、一种生产旋转动力的爆燃平转发动机,该方式的具体结构如图12、图16、图14、图18、图17、图9、图19所示,本爆燃平转发动机包括有机壳1,平转转子端壁9a、9b,固定轴2,平转活塞5a、5b、5c、5d,平转轴6a、6b、6c、6d,分界器8,进气口20a、20b,排气口21a、21b,堵流塞22a、22b、22c、22d,隘口24a,平转气缸86a、86b,平转齿轮7a、7b、7c、7d,传动齿轮15a、15b、15c、15d,传动齿轮轴4a、4b、4c、4d,轴承10a、10b,固定齿轮26,固定燃烧室44a,进气连通口16a,爆燃挡板28,爆燃联通口29a,轴11a、11b,燃料喷入口30a,泄气口34a,旋转气缸17,旋转气缸隔板18,旋转气缸的内圆壁25,推力轴承60,旋转气缸的外圆壁27a、27b,旋转气缸右端的底壳板57a、57b,冷却气体出口58a、58b,其特征是本爆然平转发动机还包括有爆火连通口66,平转发动机69;一块平转活塞、一根平转轴和一个平转齿轮组成一个固定连接体,通过齿轮传动限定该固定连接体只能平行转动,本爆燃平转发动机转动时,从进气口20b进入平转气缸86b的空气被平行转动的平转活塞5a推压成压缩空气后从排气口21a排出,从排气口21a排出的压缩空气经过与排气口21a和进气连通口16a连通的气体通道进入旋转
气缸,当已经进入压缩空气的该旋转气缸转动到燃料喷入口30a的位置接受从燃料喷入口喷入的燃料后,该旋转气缸逐渐与固定燃烧室连通,其内部的压缩空气和燃料混合体受到固定燃烧室的爆火爆炸式压缩引爆产生爆炸冲击波,该爆炸冲击波通过爆火连通口66与进气口20a之间的气体通道进入平转气缸86a推动平转活塞平行转动对外界做功,推动平转活塞平行转动的气体做功完毕后就从排气口21b排出,该旋转气缸内的混合体被引爆后,该旋转气缸继续转动离开固定燃烧室,遗留在该旋转气缸内的燃气从泄气口34a泻出到外界去以后,该旋转气缸重新接收平转活塞压缩的气体,进入下一个工作循环。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、一种爆燃发动机,该方式的具体结构如图12、图20、图14、图21、图22所示,本爆燃发动机包括有机壳1,平转转子端壁9a、9b,平转轴6a、6b、6c、6d,固定轴2,平转气缸86a、86b,平转活塞5a、5b、5c、5d,分界器8,排气口21a、21b,堵流塞22a、22b、22c、22d,隘口24a、24b,平转压气机68,平转压气机68的技术来源于本人的发明专利:《平转发动机》,专利号:2017100556514,进气道50a、50b,平转齿轮7a、7b、7c、7d,传动齿轮15a、15b、15c、15d,传动齿轮轴4a、4b、4c、4d,旋转气缸17,旋转气缸隔板18,旋转气缸的内圆壁25,喷气道35a,固定燃烧室44a,点火器45a,泄气道51a、51b,不间断式燃料喷器78,轴承10a、10b、10c,轴11a、11b,固定齿轮26,旋转气缸两端的端壁52a、52b,附机43,其特征是本爆燃发动机还包括有高压气体进口40;一块平转活塞、一根平转轴和一个平转齿轮组合成一个固定连接体,通过齿轮传动限定平转活塞只能平行转动,从排气口21a和排气口21b排出的高压空气,通过气体通道从高压气体进口40进入旋转气缸,本爆燃发动机推动飞行器高超音速飞行时,进气道50a、50b的开口对着前方,迎面来流从进气道50a进入旋转气缸,迎面来流从进气道50b进入平转压气机68内被压成高压气体后,通过气体通道进入旋转气缸与从进气道50a进入的气体混合,使旋转气缸里有充足的高压气体,当该旋转气缸转动经过不间断式燃
料喷器78接受喷入的燃料后,该旋转气缸逐渐与固定燃烧室44a连通,固定燃烧室的爆火对该旋转气缸里的高压气体和燃料的混合体爆炸式压缩并引爆,高压气体和燃料的混合体爆燃产生剧烈的冲击波从喷气道35a喷出,从而获得巨大的推进力推动本爆燃发动机所在的飞行器高超音速或超音速飞行,当该旋转气缸继续转动离开固定燃烧室,遗留在该旋转气缸里的废气从泄气道51a、51b泄出后,该旋转气缸重新接收从进气道进入的迎面来流,进入下一个工作循环,因为本爆燃发动机有附机带动平转压气机产生高压气体,所以本爆燃发动机可以在没有前进速度的时候启动,本爆燃发动机也可以用氧气助燃协助启动。
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 (4)
- 一种进气道与固定燃烧室之间有旋转气缸阻隔、并且固定燃烧室内的气体压强远大于进气端能产生的气体压强的爆燃发动机,包括有轴(11a),其特征是该爆燃发动机还包括有机壳(1),旋转气缸(17),固定燃烧室(44a),泄气道(51b、51a),本爆燃发动机工作时,气体压强远低于固定燃烧室(44a)内的气体压强的助燃气体从进气端进入旋转气缸(17),当该旋转气缸继续转动到达不与进气道连通的位置后,该旋转气缸接收燃料喷器喷入燃料的同时继续转动,当该旋转气缸转动到达与固定燃烧室连通的位置后,该旋转气缸里的助燃气体与燃料的混合体与固定燃烧室里的高压燃烧气体爆燃产生巨大的能量做功,该旋转气缸继续转动到达不与固定燃烧室连通的位置后,通过泄气道泄掉遗留在旋转气缸里的废气进入下一工作循环。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.
- 一种进气端不跟固定燃烧室连通、燃烧室后部压强远大于前部压强的爆燃发动机,包括有进气道(50a),导气器(89),轴承(10a、10b),轴(11a)和飞行器(77),其特征是该爆燃发动机还包括有机壳(1)、旋转气缸(17)、固定燃烧室(44a)、旋转气缸两端的端壁(52a、52b)、旋转气缸隔板(18)、旋转气缸的内圆壁(25)、不间断式燃料喷器(78)、点火器(45a)、喷气道(35a)、阻隔板(88)、泄气道(51a、51b);通过旋转气缸两端的端壁把旋转气缸的内圆壁固定连接在轴上形成一个环形槽,再通过12块旋转气缸隔板把该环形槽等分成12个完全相同的旋转气缸,旋转气缸隔板的两端与旋转气缸两端的端壁密封固定连接,内侧与旋转气缸的内圆壁密封固定连接,旋转气缸隔板是空心板,即旋转气缸隔板有夹层空间,冷却空气从旋转气缸左端的端壁上的气孔中进入旋转气缸的内圆壁内部的左侧空间后,再进入旋转气缸隔板的夹层空间冷却旋转气缸隔板,然后再经过旋转气缸的内圆壁内部的右侧空间和旋转气缸右端的端壁上的气孔排放到外界;由轴、旋转气缸两端的端壁、旋转气缸的内圆壁和旋转气缸隔板 组成转子,机壳内壁与转子转动时的运动轨迹切合,即:机壳内壁与转子之间的间隙特别小,但机壳内壁不阻碍转子转动,转子两端的轴承被相应的轴承套限定在机壳上;轴承套、机壳、进气道、固定燃烧室、喷气道和泄气道是一个固定连接的整体,该固定连接的整体固定安装在飞行器上,当安装本爆燃发动机的飞行器的飞行速度大于300公里每小时后,从进气道进入的迎面来流即速差冲压气流就能进入旋转气缸并通过推动旋转气缸隔板推动转子高速转动,当旋转气缸转动到不间断式燃料喷器的位置时,该旋转气缸外缘与机壳内壁切合,其内部空间不与外界连通,不间断式燃料喷器喷入的燃料瞬间就与已进入旋转气缸内的剧烈运动的空气混合均匀,当该旋转气缸继续转动到其内部空间与固定燃烧室连通后,固定燃烧室里的爆炸冲击波就会对该旋转气缸里的剧烈运动的燃料和空气的混合体进行爆炸式压缩,使燃料和空气的混合体爆散到固定燃烧室中爆燃,随后该爆燃冲击波又引爆后面的旋转气缸里的燃料和空气的混合体爆燃,本爆燃发动机就是像这样以爆引爆,爆爆相连,产生特高压气流以几十马赫或上百马赫的速度从喷气道中爆喷到飞行器后方,从而产生巨大的推进力推动飞行器高超音速或超音速飞行,如有必要也可以亚音速飞行,当该旋转气缸继续转动到不与固定燃烧室连通,只与泄气道连通时,剩余在旋转气缸里的燃烧过的气体就从泄气道中泄出,当该旋转气缸继续转动到既与泄气道连通,又与进气道连通时,从进气道中进入的冲压气流就会进入旋转气缸清扫该旋转气缸,使遗留在该旋转气缸内的废气完全从泄气道中流出,当该旋转气缸继续转动到只与进气道连通时,冲压气流就会重新进入该旋转气缸,并推动转子高速转动进入下一个工作循环;本爆燃发动机是空气跟燃料混合均匀后,该混合体才受到在先产生的爆燃冲击波冲压并跟爆火混合后才爆燃,其燃烧效果是其他喷气发动机无法达到的,燃烧效果好就能确定本爆燃发动机具有高效节能的 优势;本爆燃发动机的进气端不跟固定燃烧室连通,是通过旋转气缸把进气端的空气一缸一缸的运输到固定燃烧室,因此,不管固定燃烧室内部的压强有多大,都不会影响进气端的空气有效的进入固定燃烧室,因此,可以把本爆燃发动机的喷气道做得很小,可以小到喷气道只有进气道的十几分之一,从而就能使固定燃烧室内产生巨大的压强,使喷气道喷出的气流速度达到几十马赫或上百马赫,从而本爆燃发动机就能推动飞行器实现高超音速飞行,把本爆燃发动机产生的能量高效的转化为推进能量。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.
- 一种零前进速度启动的扇压爆燃发动机,包括有机壳(1),轴承(10a、10b),传动轴(3),连接板(79a、79b),伞齿轮(37a、37b),点火器(45a、45b),压气风扇(47),扩压器(46),使燃料从燃料喷入口喷入旋转气缸的机构(81),附机(43),轴(11a),其特征是本扇压爆燃发动机还包括有固定挡板(13),进气连通口(16a、16b),旋转气缸的外圆壁(27a、27b),旋转气缸隔板(18),环形隔板(80),旋转气缸(17),旋转气缸的内圆壁(25),爆燃挡板(28),爆燃连通口(29a、29b),喷气道(35a、35b),燃料喷入口(30a、30b),泄气口(34a、34b),固定燃烧室的内圆壁(42a、42b),固定燃烧室(44a、44b);通过固定在轴(11a)上的连接板(79a、79b)把旋转气缸的内圆壁(25)固定连接在轴(11a)上,通过固定连接在旋转气缸的内圆壁(25)上的15块旋转气缸隔板(18)、把旋转气缸的外圆壁(27a、27b)固定连接在旋转气缸的内圆壁(25)上,15块旋转气缸隔板把旋转气缸的内圆壁(25)与旋转气缸的外圆壁(27a、27b)之间的环形空间等分成15个旋转气缸,该固定连接体与固定在轴(11a)上的伞齿轮(37a)、环形隔板(80)和压气扇(47)组合成本发动机的转子;本扇压爆燃发动机工作时,进气端不与固定燃烧室连通,是靠旋转气缸一气缸一气缸的把压气风扇产生的压缩空气运送到燃料喷入口的位置接受喷入的燃料后,才运送到与固定燃烧室联通的位置接受固定燃烧的 爆炸冲击波的爆炸式压缩,受到爆炸式压缩的燃料和空气混合体才爆燃喷进固定燃烧室并从固定燃烧室后方的喷气道喷出,从而获得巨大的推力推动该扇压爆燃发动机所在的飞行器高超音速或超音速飞行,该旋转气缸转动到不与固定燃烧室联通后,遗留在该旋转气缸里的废气就会通过与泄气口连通的气道排泄到后方的外界,泄了废弃的旋转气缸转动到与进气连通口连通的位置时,又重新接收压气扇产生的压缩空气,进入下一个工作循环。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.
- 一种爆燃发动机,本爆燃发动机包括有机壳(1),平转转子端壁(9a、9b),平转轴(6a、6b、6c、6d),固定轴(2),平转气缸(86a、86b),平转活塞(5a、5b、5c、5d),分界器(8),排气口(21a、21b),堵流塞(22a、22b、22c、22d),隘口(24a、24b),平转压气机(68),进气道(50a、50b),平转齿轮(7a、7b、7c、7d),传动齿轮(15a、15b、15c、15d),传动齿轮轴(4a、4b、4c、4d),旋转气缸(17),旋转气缸隔板(18),旋转气缸的内圆壁(25),喷气道(35a),固定燃烧室(44a),点火器(45a),泄气道(51a、51b),不间断式燃料喷器(78),轴承(10a、10b、10c),轴(11a、11b),固定齿轮(26),旋转气缸两端的端壁(52a、52b),附机(43),其特征是本爆燃发动机还包括有高压气体进口(40);一块平转活塞、一根平转轴和一个平转齿轮组合成一个固定连接体,通过齿轮传动限定平转活塞只能平行转动,从排气口(21a)和排气口(21b)排出的高压空气,通过气体通道从高压气体进口(40)进入旋转气缸,本爆燃发动机推动飞行器高超音速飞行时,进气道(50a、50b)的开口对着前方,迎面来流从进气道(50a)进入旋转气缸,迎面来流从进气道(50b)进入平转压气机(68)内被压成高压气体后,通过气体通道进入旋转气缸与从进气道(50a)进入的气体混合,使旋转气缸里有充足的高压气体,当该旋转气缸转动经过不间断式燃料喷器(78)接受喷入的燃料后,该旋转气缸逐渐与固定燃烧室(44a)连通,固定燃烧室的爆 火对该旋转气缸里的高压气体和燃料的混合体爆炸式压缩并引爆,高压气体和燃料的混合体爆燃产生剧烈的冲击波从喷气道(35a)喷出,从而获得巨大的推进力推动本爆燃发动机所在的飞行器高超音速或超音速飞行,当该旋转气缸继续转动离开固定燃烧室,遗留在该旋转气缸里的废气从泄气道(51a、51b)泄出后,该旋转气缸重新接收从进气道进入的迎面来流,进入下一个工作循环,因为本爆燃发动机包括有附机和平转压气机,所以本爆燃发动机可以在没有前进速度的时候启动。 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.
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WO2023216762A1 true WO2023216762A1 (en) | 2023-11-16 |
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PCT/CN2023/085521 WO2023216762A1 (en) | 2022-05-07 | 2023-03-31 | Deflagration engine |
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Citations (7)
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 (en) * | 2015-06-29 | 2015-09-23 | 蔡勇 | Rotary engine having adjustable compression ratio |
CN106593642A (en) * | 2017-01-19 | 2017-04-26 | 龙全洪 | Parallel rotating engine |
CN107489457A (en) * | 2017-09-08 | 2017-12-19 | 龙全洪 | Multifunctional engine |
CN107559103A (en) * | 2017-09-14 | 2018-01-09 | 王闯业 | A kind of birotor punching engine |
CN107701301A (en) * | 2017-10-29 | 2018-02-16 | 龙全洪 | Simple internal combustion engine |
-
2022
- 2022-05-07 CN CN202210659862.XA patent/CN116201657A/en active Pending
-
2023
- 2023-03-31 WO PCT/CN2023/085521 patent/WO2023216762A1/en unknown
Patent Citations (7)
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 (en) * | 2015-06-29 | 2015-09-23 | 蔡勇 | Rotary engine having adjustable compression ratio |
CN106593642A (en) * | 2017-01-19 | 2017-04-26 | 龙全洪 | Parallel rotating engine |
CN107489457A (en) * | 2017-09-08 | 2017-12-19 | 龙全洪 | Multifunctional engine |
CN107559103A (en) * | 2017-09-14 | 2018-01-09 | 王闯业 | A kind of birotor punching engine |
CN107701301A (en) * | 2017-10-29 | 2018-02-16 | 龙全洪 | Simple internal combustion engine |
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CN116201657A (en) | 2023-06-02 |
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