WO2014183651A1 - Moteur à gaz de type turbine pour canalisation d'avion - Google Patents

Moteur à gaz de type turbine pour canalisation d'avion Download PDF

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Publication number
WO2014183651A1
WO2014183651A1 PCT/CN2014/077548 CN2014077548W WO2014183651A1 WO 2014183651 A1 WO2014183651 A1 WO 2014183651A1 CN 2014077548 W CN2014077548 W CN 2014077548W WO 2014183651 A1 WO2014183651 A1 WO 2014183651A1
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WIPO (PCT)
Prior art keywords
duct
wheel
engine
power wheel
pipe
Prior art date
Application number
PCT/CN2014/077548
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English (en)
Chinese (zh)
Inventor
林钧浩
Original Assignee
Lin Junhao
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Filing date
Publication date
Application filed by Lin Junhao filed Critical Lin Junhao
Publication of WO2014183651A1 publication Critical patent/WO2014183651A1/fr

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Classifications

    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/56—Combustion chambers having rotary flame tubes
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an aircraft pipeline wheel gas engine, belonging to the technical field of aviation engines. Background technique
  • the object of the present invention is to overcome the shortcomings of the prior art described above, and to provide an aviation engine with simple structure, small size, low cost, high efficiency, multiple functions, wide application range, and can adapt to various special situations and needs to adapt. Energy-saving emission reduction and development of aircraft pipeline wheel gas engines using new energy technology requirements.
  • An aircraft pipeline wheel gas engine including a casing, an engine intake port, an engine exhaust passage, an engine rotor, a rotor drive shaft, a compressor duct wheel, and an air duct wheel Disk, air duct wheel air inlet, air duct wheel side wall air outlet, air duct wheel air duct, air duct wheel reversing deceleration air duct, fuel storage tank, fuel storage tank discharge port, characterized by The type of pipeline combustion power wheel, the combustion power wheel is composed of a combustion power wheel and a flame gas tube, the combustion power wheel disk is connected with the rotor drive shaft, and the front part of the flame gas pipe is driven from the front to the rear by the combustion power wheel.
  • the steering winding is fixed on the combustion power wheel, and the rear part of the flame gas pipe is close to the exit portion of the flame gas pipe.
  • the reverse combustion power wheel is turned and tangentially placed on the combustion power wheel, and the flame gas pipe outlet direction is opposite to the combustion power wheel rotation tangential direction.
  • the flame gas pipe outlet is in communication with the engine exhaust passage, and the flame gas pipe inlet is connected to the duct pipe reversing deceleration duct.
  • Feed tank discharge opening in communication with the engine intake.
  • the fuel storage tank discharge port is disposed at an inner side wall of the engine intake port close to the inlet of the air duct wheel duct, and the fuel storage tank outlet outlet direction is inclined to point to the engine inlet airflow direction.
  • the flame gas pipe outlet is provided with a rotary tangential gas nozzle.
  • a pulverizing deflector is arranged inside the engine intake passage, and the pulverizing deflector is composed of a static pulverizing deflector and a dynamic static pulverizing deflector, and the static pulverizing deflector and the engine inlet are provided.
  • the side wall is connected with the side wall of the inlet rectifying cone, and the radial front end of the dynamic and static pulverizing deflector is provided with a pulverizing deflector sleeve, and the radial end of the dynamic and static pulverizing deflector is not connected with the side wall of the engine inlet.
  • the radial front end is connected with the crushing deflector bushing, and the inner side of the crushing deflector bushing is provided with a switch pin, and the opening and closing of the switch pin is used to control the connection and separation of the crusher deflector bushing and the rotor drive shaft. .
  • an intake port material inlet is arranged below the engine intake passage, and a material inlet plug door which can be adjusted to be closed is provided on the inlet material inlet.
  • the flame gas pipe is provided with a gunpowder filler port, and the gunpowder filler port is provided with a gunpowder filler port valve.
  • the aircraft pipeline wheel gas engine of the present invention is quite different from the existing various aeroengine structural principles, and the structural component terminology and functional use are quite different from those currently popular. For the sake of narration, the expression is accurate and clear, and several noun terms are explained here:
  • the radial part of the air duct near the end of the duct is the root of the duct, referred to as the duct root.
  • the radial end of the duct is called the top of the duct, which is referred to as the top of the duct; the part of the duct close to the root of the duct is called the lower part or the bottom of the duct.
  • the top of the duct near the top of the duct is called the upper part of the duct.
  • the outer edge of the duct wheel is the radial edge of the duct wheel.
  • the axial side edge of the duct wheel is called the axial edge of the duct wheel.
  • the axial edge of the duct wheel is divided into the axial edge of the duct wheel and the axial edge of the duct wheel.
  • the side wall of the rotor with the central axis pointing is the axial side wall of the duct wheel, and other relevant parts of the body are called and so on.
  • the side of the air inlet end of the whole body is the front side or the front or the front side, and the other side opposite to the front side is the rear side or the rear or the rear.
  • the direction of rotation of the engine rotor is circumferential, and the direction of rotation of the forward rotor is forward or circumferentially forward, and the direction of rotation of the rotor is rotated rearward or circumferentially rearward, and the reference of other relevant parts of the body is similar.
  • the aircraft pipeline wheel gas engine mainly includes two parts of the engine casing and the engine rotor, and the casing does not have a stator component such as a complicated rectifying diversion.
  • the engine rotor consists of a compressor duct wheel, a combustion power wheel and a rotor drive shaft.
  • the engine can directly compress the gas without directly relying on the function of the rectifying and diverting stator components, and directly burns the flame gas to directly expand the work.
  • the pipeline wheel compressor is the foundation and core component of the aircraft pipeline wheel gas engine. It is because of this pipeline wheel compressor that the entire aircraft pipeline wheel gas engine can be constructed and its own unique characteristics are realized. (Refer to the circulating pressurized pipeline compressor, patent number ZL20091 0216953. 0 )
  • the pipeline wheel compressor is composed of a duct pipe and a rotor drive shaft, and the duct pipe is composed of a duct coil and a duct tube duct.
  • the air duct wheel is connected with the rotor drive shaft, and the air duct wheel is steered and fixed on the air duct wheel by the front and rear wind tube rounds along the axial direction of the air duct wheel, and the air duct wheel can be rotated to process the compressed gas.
  • the body can allow various mixed gases (including a mixture of solid particles containing a large volume) to pass freely, and the friction loss is small, so the pipe wheel compressor can not only pump compressed pure air, but also suction Processing compressed fuel air mixed gas; due to processing compressed fuel air mixed gas, fuel and air can be mixed and fully hooked, thus ensuring hair
  • the motivation is full and the combustion efficiency is high.
  • the pipeline wheel compressor has a simple structure and few wear parts. All of these can make the pipeline wheel engine consume less energy and have higher efficiency, and meet the requirements of energy saving and emission reduction. More importantly, the pipeline wheel compressor can be sucked and discharged and compressed.
  • the mixture of solid fuels can cause the engine to burn a variety of solid powder fuels, thus making the pipeline wheel engine more adaptable to the era of developing new energy sources.
  • the pipe wheel compressor used in the invention comprises a cylindrical duct wheel disk, an air inlet of the duct pipe (and an axial side wall air inlet of the duct pipe), and a full seal combination.
  • the duct pipe and the duct wheel are provided with a duct tube duct and a reversing deceleration duct, and a duct tube duct outlet.
  • the absorbed energy increases the pressure and speed, and then is discharged into the deflating duct of the duct to reverse the wind turbine wheel to steer the flow, and the counter-rotating flow absorbs the energy transmitted by the reaction force of the rotating force, and the airflow is Compress and decelerate.
  • the ducted wheel compressor is used to process the compressed gas by using the working principle, that is, the gas is first accelerated by the duct wind pipe, and then the deceleration duct is compressed by the duct wheel to decelerate and pressurize, and then the duct wheel is passed. The air duct is accelerated, and then the air duct is reversing and the deceleration air duct is compressed to decelerate and pressurize, and the compressor is finally used to process and use the required high pressure extra-high pressure gas.
  • the duct pipe pipe according to the present invention refers to a duct pipe wind pipe or a duct pipe reversing deceleration air pipe, and the air duct wheel air duct and the air duct wheel reversing deceleration air duct have the same structure.
  • the pipeline wheel compressor does not have a static and complicated rectifying flow guiding component. It can directly process and compress high-pressure extra-high pressure gas only by the rotary motion of the pipeline wheel rotor.
  • the structure is simple, the material is small, the weight is light, the processing efficiency is high, and the pipeline wheel is compressed.
  • the longitudinal direction of the duct pipe is continuous, which can process compressed pure air and process compressed gas solid mixture. It has special functions and wide application range.
  • Pipe wheel compressors are unmatched by existing aero engines using axial flow compressors and centrifugal compressors.
  • the invention does not have a dedicated burner and a dedicated gas turbine, and does not divide the combustion function and the power function into two independent systems, but sets a rotary duct combustion power wheel to unify the combustion function and the power function in one component.
  • a single pipe burns the power wheel to generate heat energy, and turns the heat energy into kinetic energy to push the rotor to rotate.
  • the pipe wheel compressor duct pipe is rotating.
  • the pipe combustion power wheel pipe is also rotating.
  • the coaxial and the steering are dynamically connected with the rotating speed.
  • the pipeline combustion power wheel is composed of a cylindrical combustion power wheel and a flame gas tube.
  • the force wheel is connected with the rotor drive shaft, and the front part of the flame gas pipe is axially driven along the pipe.
  • the axial direction of the power wheel is steered and fixed on the combustion power wheel by the front and the rear.
  • the flame gas pipe inlet is connected with the pipe compressor duct reversing deceleration duct, and the flame gas pipe outlet is connected with the engine exhaust duct.
  • the rear portion of the flame gas pipe is placed on the combustion power wheel in a tangential (or circumferential direction) direction of the reverse combustion power wheel near the exit portion.
  • the cylindrical combustion power wheel is connected to the cylindrical duct wheel, and the inner side (inner chamber) communicates with the air inlet of the duct.
  • the flame gas pipe may be a fully-sealed pipe, may be a semi-open pipe, may be a curved semi-annular pipe body, and may be a single-ring double-ring multi-annular pipe body.
  • the number of gas pipes in the entire pipeline burning power wheel can be single-tube or multi-tube.
  • the longitudinal passage of the flame gas tube may be of equal cross section and may be gradually expanded.
  • the high-temperature flame gas generated by the combustion of the flame gas pipe immediately produces the work to push the combustion power wheel to rotate, and the temperature itself cools down, that is, the flame gas is cooled as soon as it is generated, so the flame gas pipe outlet temperature is relatively low.
  • the flame gas pipe outlet direction may be circumferential, may be inclined circumferential direction, and may be a tangential direction of the rotating circle.
  • Rotating the circle tangentially may add a gas pipe nozzle at the end thereof, and the gas pipe nozzle injection generates a reaction force to push the combustion power wheel to rotate.
  • the combustion power wheel After the tangential nozzle is added to the end outlet of the flame gas pipe, the combustion power wheel has the torque generated by the combustion and expansion of the rotating flame gas pipe to push the combustion power wheel to rotate, and the torque of the tangential nozzle injection reaction force at the end of the flame gas pipe is pushed.
  • the combustion power wheel rotates to do work, so that the combustion power wheel rotates to make the function more powerful, the external work effect will be better, and the work efficiency will be higher.
  • the flame gas pipe outlet can be directly connected to the engine exhaust passage or through the gas pipe nozzle to communicate with the engine exhaust passage.
  • the present invention eliminates the need to install a gas turbine that is expensive and inefficient.
  • the invention can make the aviation engine combustion power system simple in structure, low in cost, convenient in use and maintenance, high in efficiency and energy saving.
  • the aircraft pipeline wheel engine is further provided with a fuel storage tank, the fuel storage tank is provided with a fuel storage tank discharge port, the fuel storage tank discharge port is connected with the engine axial front inlet port, and the fuel storage tank fuel is discharged through the fuel storage tank.
  • the material inlet enters the engine air inlet duct, and then enters the air duct air duct of the pipeline compressor to enter the air duct air duct of the pipeline compressor.
  • the discharge port of the fuel storage tank is disposed on the inner side wall of the fuel storage tank at the air inlet of the air duct of the air duct in the intake port of the engine, and the outlet direction thereof is inclined to the flow direction of the air inlet of the engine.
  • a spray pump can be added to the fuel storage tank, but the fuel injected from the fuel storage tank outlet can be injected into the fuel by the negative pressure generated by the high-speed air inlet of the engine inlet, that is, the jet is sucked by the jet suction principle.
  • the fuel, the injected fuel is atomized by the high-speed airflow of the intake air of the engine inlet, and then is brought into the airflow of the air duct of the air duct, and is mixed with the gas in the air duct of the air duct of the duct, the fuel air
  • the mixed gas stream mixed with the hook is sent to the combustion tube of the combustion power wheel for combustion.
  • the discharge port of the combustion storage tank is adjustable, and the flow rate can be adjusted according to the needs of use. ⁇ Injecting fuel with the jet suction principle can simplify the engine structure and reduce the weight of the engine.
  • the present invention also has a high-energy circulating thrust tube, and the high-energy circulating thrust tube is provided with a high-energy circulating thrust tube inlet and a high-energy circulating thrust tube outlet.
  • the high-energy circulation thrust pipe inlet is connected to the downstream air duct wind pipe of the air pipe wheel.
  • the high-pressure high-temperature airflow in the air passage is connected in countercurrent flow, and the high-energy circulating thrust pipe outlet is connected to the upper air duct of the air duct and the low-pressure low-temperature airflow of the air duct.
  • the high-energy circulating thrust pipe can extract high-pressure, high-temperature and high-energy airflow from the downstream air duct wind pipe of the wind turbine wheel and feed it into the upstream air duct of the wind pipe wheel.
  • the air pipe advances the low-pressure low-temperature low-energy airflow. In this way, it can be ensured that the gas flow pressure of the air duct of the ducted duct is always high and then low (higher upstream, lower downstream), and never reverses, and will not surge.
  • the high-energy circulating thrust tube can be used in various structural forms, and its cross section can be round, square, etc., and its longitudinal direction can be equal-section, can be expanded, can be contracted, and the number of pipes can be single. Tube, can be multi-tube.
  • the high-energy circulation thrust tube is also required to be set on the combustion power wheel of the invention. After the high-energy circulation thrust tube is arranged on the combustion power wheel, the high-energy circulation thrust tube is sucked from the rear pipe of the combustion flame tube to take high-temperature and high-pressure gas, and then the inlet of the combustion flame tube is cis. The flow enters the front duct of the combustion flame tube (igniting and pushing the high-pressure fuel-air mixture gas to flow downstream), so that the combustion flame tube can be prevented from burning backflow, and the combustion power wheel can be smoothly and fully burned to avoid the surge of the engine.
  • Aircraft pipeline wheel engine because the compressor duct runner is in the form of pipeline body structure, the pipeline combustion power wheel runner is also in the form of pipeline body structure, and the connection between the duct wheel compressor duct outlet and the pipeline combustion power wheel inlet is synchronized. connection.
  • the entire engine from the compressor inlet to the pipe combustion power wheel outlet is a longitudinally unified whole pipe structure.
  • Such pipe body flow passages are unobstructed from front to back, so that the uniform pipe inner flow passage allows solid particles from beginning to end. The substance passed.
  • a multi-purpose pulverizing deflector is provided in such an engine intake duct, such an engine intake duct sucks solid materials such as garbage and waste, and the solid materials are pulverized by the multi-functional crushing deflector. It is then fed into the air duct of the compressor duct and compressed and blended with the fuel mixture gas, and then sent to the pipeline to burn the power wheel to do work, thus avoiding the compressor being blocked and saving energy.
  • the multi-function crushing deflector installed in the intake pipe of the engine is composed of a static crushing deflector, a static and static crushing deflector and a crushing deflector bushing.
  • the static crushing deflector and the engine inlet side wall and the intake port The side wall of the rectifying cone is connected, and the radial end of the dynamic and static pulverizing deflector is not connected to the side wall of the engine inlet.
  • the radial front end is connected with the crushing deflector bushing, and the switching pin is provided inside the crushing deflector, and the connecting and separating of the crushing guide bushing and the rotor driving shaft are controlled by the opening and closing of the switch pin.
  • the crusher deflector bushing is connected with the rotating shaft, and the dynamic and static crushing guide vane rotates with the rotor drive shaft.
  • the solid material entering the engine intake port can be crushed by the crushing of the static crushing deflector, and then statically crushed.
  • the flow guide is guided into the air duct of the compressor duct; the crusher guide bushing is separated from the rotor drive shaft, and the dynamic and static crushing guide vanes are stationary, and the air intake airflow of the engine intake port is given together with the static crushing deflector. It is introduced into the air duct of the compressor duct by finishing.
  • the aircraft engine can have many special functions.
  • the missile will fly close to the ground grass, fly close to the forest tree top, and fly close to the farm crops.
  • the grass branches can be continuously sucked into the engine intake, and the grass branches that are sucked in will be crushed by the multi-functional crushing deflector at any time, and then sent to the air duct of the compressor duct to be processed together with the air. Compressed and blended, and then sent to the pipeline to burn the power wheel for combustion work.
  • Such a cruise missile can travel long distances with only a small amount of supplementary fuel. Since its fuel is mainly taken from the outside during the voyage process, it does not need to carry a large amount of fuel by itself, so its volume is small and its weight is light. Although it burns bio-energy with low combustion value, it can also achieve high speed. Such cruise missiles must fly at low altitude in order to ingest fuel, and fly on the ground. Even if they are sucked into the gravel bricks, they can be used as usual. jobs. Such a cruise missile can fly without flying at low altitude, and the radar can't find it at all, so it has good security.
  • a flying vehicle that is equated with such a pipeline wheel engine can take fuel over the mountain and cross the mountain, and cross the swamp forest and other areas where the general vehicle cannot pass.
  • the flying vehicle equipped with such a pipeline wheel engine is especially suitable for wartime marching and transportation. Rescue and disaster relief use.
  • a special material inlet can be arranged below the engine inlet, and a valve for adjusting the switch can be arranged on the material inlet.
  • the multi-functional pulverizing deflector is only possible to set the lining wheel of the present invention, and the other various aeroengines cannot be set. Therefore, the existing various aviations are not provided. It is impossible for the engine to have the above special functions.
  • the flame gas pipe can simultaneously burn and simultaneously rotate the rotor, so the invention is suitable for setting a gunpowder filler port on the combustion power wheel flame gas pipe, and the gunpowder filler port is provided with a gunpowder filler port valve.
  • the gunpowder in the flame gas pipe is ignited, and the gunpowder is burned and burned.
  • the flame gas is generated to push the combustion power wheel to push the engine rotor to rotate, so that the engine can be fully started.
  • the invention can also be started with an electric motor.
  • a combustion power wheel side air outlet is arranged on the cylindrical combustion power wheel, and the power wheel is burned.
  • the side wall air outlet is connected with the combustion power wheel flame gas pipe gap, and the side wall air outlet of the combustion power wheel sucks cold air from the inside of the cylindrical combustion power wheel (connected with the air inlet of the air duct) by rotating centrifugal force.
  • the combustion power wheel flame gas pipe is cooled. The cold air rotates through the flame gas pipe gap, and is then discharged to the engine exhaust passage through the combustion power wheel to cool the exhaust gas outlet, and then discharged into the atmosphere.
  • the present invention also needs to cool the air duct wheel, and the cooling technology is basically the same as the combustion power wheel cooling technology, that is, in the circle
  • the tubular air duct wheel is provided with a side wall auxiliary air outlet of the duct, and the side wall auxiliary air outlet of the air duct is connected with the air duct gap of the air duct, and the side wall auxiliary air outlet of the air duct is rotated by centrifugal action.
  • the inside of the duct coil is sucked with cold air between the duct duct gaps to cool the duct tube duct.
  • the cooling gas rotates and flows through the combustion gas wheel flame gas pipe gap, cools the flame gas pipe (or merges with the original cooling gas of the flame gas pipe gap to cool the flame gas pipe), and then is discharged to the engine row through the combustion power wheel cooling exhaust gas outlet The airway is then discharged into the atmosphere.
  • Figure 1 is a schematic view showing the structure of a first embodiment of the present invention
  • Figure 2 is a schematic view showing the structure of an engine rotor according to a first embodiment of the present invention
  • Figure 3 is a schematic view showing the structure of the working principle of the engine according to the first embodiment of the present invention
  • Figure 4 Schematic diagram of the structure of the first embodiment of the present invention.
  • Figure 5 Schematic diagram of the structure of the first embodiment of the present invention
  • Figure 6 is a schematic view showing the structure of an engine rotor according to a third embodiment of the present invention
  • Figure 7 is a schematic structural view showing the working principle of the engine of the third embodiment of the present invention.
  • Figure 8 is a schematic structural view of a fourth embodiment of the present invention.
  • Figure 9 is a schematic view showing the structure of an engine rotor according to a fourth embodiment of the present invention.
  • Fig. 10 is a structural schematic view showing the working principle of the engine according to the fourth embodiment of the present invention.
  • Embodiment 1 referring to FIG. 1, FIG. 2, FIG. 3, an aircraft pipeline wheel combustion engine, including an organic casing 1, an engine intake 2, an engine exhaust passage 3, an engine rotor 4, a rotor drive shaft 5, and compression Air duct tube 6, duct tube wheel 7, air duct wheel inlet 8, duct air duct side wall air outlet 9, full-sealed combined spiral duct tube duct 10 (in the axial direction of the duct wheel)
  • the spiral plate is fixedly wound forward and backward to form a spiral groove, and the radial end of such groove is covered to form a full-sealed combined spiral duct wind pipe, and the radial end cover surface of the groove is called wind Tube wheel radial end side wall 36), duct wheel reversing deceleration duct 11, combustion power wheel 17, combustion power wheel 18, flame gas tube 20, flame gas tube inlet 21, flame gas tube outlet 11, gas tube nozzle 23.
  • the full-sealed combined spiral duct pipe duct 10 is axially fixed from the front to the rear by the wind turbine wheel. The steering winding is fixed on the duct pin 6 for two weeks.
  • a full-sealed combined spiral duct wheel reversing deceleration duct 11 is also provided, and the duct reversing deceleration duct 11 is constructed in the same manner as the duct tube duct, but it is entangled with the wind turbine wheel axially opposite the duct wheel. It is fixed on the duct wheel 6.
  • Air duct reversing deceleration duct 1 1 is connected in series with the duct tube duct.
  • the flame gas pipe 20 is a one-time formed full-sealed round pipe, and the front part of the circular-shaped flame gas pipe is entangled and wound on the combustion power wheel 17 from the front to the rear along the axial direction of the combustion power wheel.
  • the rear part of the gas pipe 20 is close to the exit portion of the flame gas pipe, and the reverse combustion power wheel 17 is turned and tangentially placed on the combustion power wheel 17, and the flame gas pipe outlet 22 is connected to the engine exhaust passage 3, and the flame gas pipe outlet 22 is followed by
  • the combustion power wheel rotates in the opposite direction, the flame gas pipe inlet 21 is connected with the air duct reverse speed deflating air duct 11, and the flame gas pipe outlet 22 is provided with a rotary tangential gas pipe nozzle 23, the fuel storage tank discharge port 26 and the engine Intake port 1 is connected.
  • the high-energy circulating thrust pipe 13 is also arranged on the combustion power wheel, and the high-energy circulating thrust pipe inlet 14 is connected to the rear (downstream) pipe of the flame gas pipe 20 in reverse flow direction, and the high-energy circulating thrust pipe outlet 15 is connected with the front of the flame gas pipe 20 (upstream)
  • the pipeline is connected to the downstream.
  • an engine and associated control system 16 is also provided inside the rectifying cone of the engine intake to regulate the operation of the entire engine.
  • Compressor duct wind pipe 1 0, duct pipe reversing deceleration duct 11.
  • the combustion power wheel flame gas pipe should be 6 pieces. For the sake of brevity and clarity, only one pipe is drawn in the embodiment drawings.
  • This example uses diesel fuel as fuel.
  • the gunpowder filling port valve 35 on the flame gas pipe of the burning power wheel fill the starting gunpowder for the flame gas pipe through the gunpowder filling port 34, close the valve of the gunpowder filling port, and then ignite the flame by electric spark.
  • the starting gunpowder in the gas pipe the gunpowder burns to produce the flame gas, the flame gas steers the gas pipe to the expansion to do the work, pushes the engine rotor to rotate, and fully starts the engine.
  • the duct wheel rotates, and the inlet of the duct pipe produces a negative pressure to suck the outside air into the duct of the duct, and the duct of the duct is pumped to promote the formation of an outflow from the outside to the inside of the engine intake.
  • the longitudinal airflow of the air inlet of the air duct which merges with the fuel injected by the fuel injection nozzle of the engine inlet side (the fuel storage tank outlet 26), and then flows into the air inlet 8 of the air duct, and then The air outlet of the side wall of the duct wheel enters the air passage of the air duct 10 and rotates.
  • the diesel air mixture flows in the duct pipe, and is accelerated by the air duct 10 for two weeks.
  • the gas pipe 20 is burned, the oil and gas mixed gas is burned to generate flame gas, the flame gas is expanded to generate torque, the rotor is rotated to perform work, and the high temperature gas in the flame gas pipe is rotated for two weeks to release energy for work.
  • the temperature is lowered, and then enter the flame gas pipe outlet round tangential nozzle 23 to spray, continue to push the impeller to rotate work, spray the flame gas pipe outlet round tangential nozzle 23 low temperature gas, and then through the engine tail nozzle finishing jet, resulting in vertical Thrust, pushing the engine to propel the aircraft forward.
  • the high-energy circulating thrust pipe 13 draws high-temperature gas from the rear pipe (downstream pipe) of the flame gas pipe 20 to the front pipe of the flame gas pipe, and the high temperature
  • the gas temperature is high and the pressure is high, which can ignite the oil and gas in the front part of the gas pipe, and promote the combustion, and can also promote the flame gas to avoid the generation of the flame gas pipe.
  • Backflow With the help of the high-energy circulation thrust tube, it can not only promote the normal and stable combustion of the flame gas tube, but also ensure the normal and steady flow expansion of the flame gas to do work, avoid backflow blockage and avoid surge.
  • the compressed air flow passage of the pipeline wheel is in the form of a pipeline body structure, and the entire airflow passage is unobstructed, and there is no static diversion (lateral blocking) component, and the structure is simple, and the airflow passage is Closed-type, liquid fuel passing through it will not cause leakage loss of the bond, so in this example, the fuel storage tank discharge port 26 (injector) can directly input fuel into the duct pipe, and the duct wind After the pipe is fed into the fuel, the fuel and the air are simultaneously compressed, so that the fuel and the air can be fully blended, so that the fuel can be fully burned and a good combustion effect can be obtained.
  • the pipeline combustion power wheel 17 When the engine is working, the pipeline combustion power wheel 17 is burned while using the flame gas generated by the combustion to drive its own rotation.
  • the rotor drive shaft 5 drives the pipeline compressor and other components to do work.
  • the high temperature flame gas directly pushes the pipeline combustion power wheel to rotate, and then directly
  • the jet is injected into the exhaust pipe of the engine to generate longitudinal thrust. Since the flame gas is directly discharged from the flame gas pipe of the pipe burning power wheel and is injected into the tail pipe of the engine exhaust pipe, the injection temperature is high, and thus the generated gas is generated.
  • the thrust is also large.
  • this example uses a simple-construction pipe-wheel compressor with a combination of combustion and dynamics of a pipe-burning power wheel.
  • the entire engine structure is extremely simple, and there are few friction components, so the friction loss is small.
  • this example is simple in structure, small in size, light in weight, high in combustion efficiency, low in friction loss, and energy efficient.
  • the plant powder solid fuel can also be burned, and the solid fuel has a high density and a large jet mass, so that the thrust ratio is large.
  • This example has a very broad development prospect.
  • This example is suitable for the production of cruise missile engines and aircraft engines.
  • Embodiment 2 Referring to FIG. 4, this example is substantially the same as Example 1. The difference is that the engine intake port 2 is provided with a crushing deflector 27, and the crushing deflector 27 is composed of a static crushing deflector 28, which is static and dynamic.
  • the pulverizing baffle 29 and the pulverizing deflector bushing 30 are formed.
  • the stationary pulverizing baffle 28 is connected to the engine intake side wall 31 and the inlet rectifying cone side wall, and the dynamic static pulverizing baffle 29 is provided at the radial front end.
  • the damper guide bushing 30 is smashed, and the radial end of the dynamic pulverizing deflector 29 is not connected to the engine intake side wall 31, and the radial front end is connected with the pulverizing deflector bushing 30, and the pulverizing deflector bushing is disposed inside.
  • the second difference in this example is that there is a material inlet 32 below the engine inlet, a material inlet bolt door 33 is provided, and the material inlet bolt door is provided with an adjustment switch, and the adjustment switch can regulate the material inlet bolt door to open the material inlet 32. With off.
  • the pulverizing deflector bushing switch in the engine intake The pin is closed, the crusher deflector sleeve 30 is separated from the rotor drive shaft 5, and the dynamic and static crushing deflector 29 of the crushing deflector is stationary, and the static crushing deflector of the crushing deflector is combined with the engine intake port.
  • the longitudinal airflow is used to organize the diversion.
  • the switch pin in the crusher guide bushing is automatically opened, and the crusher guide bushing is closed with the rotor drive shaft, and the flow is shattered. The bushing will rotate with the rotor drive shaft 29 along with the rotor drive shaft.
  • the static and dynamic pulsation guide vanes rotate and then squeeze by the static crushing baffle, which will be able to suck the plants into the engine inlet.
  • the pulverized solid foreign matter powder particles will enter the compressor duct wind pipe along with the engine inlet air flow, and be processed and compressed together with the oil and gas mixed gas.
  • the smashing deflector bushing switch pin is automatically closed, the pulverizing deflector bushing 30 is separated from the rotor drive shaft 5, and the dynamic and static pulverizing deflector is in a stationary state, followed by static pulverization.
  • the baffles together continue to align the longitudinal airflow to the engine intake.
  • the engine made in this example is assembled on the aircraft.
  • the engine intake is not afraid of pumping solid foreign objects such as plant leaves and birds.
  • the aircraft is flying on the ground or taking off, it is not afraid of the engine inlet sucking into the sediments.
  • Garbage waste the aircraft assembled in this case can avoid many air crashes, allowing the aircraft to take off or land on any ground.
  • this example can also directly ingest nature's biomass as a fuel during flight.
  • the dynamic crushing deflector 29 of the crushing deflector in the intake port of the engine is adjusted to a rotating operation state, and the material inlet bolt door 33 below the engine intake port is pulled open, so that The material inlet 32 is in a fully open state.
  • the intake port of the engine draws the intake air in a longitudinal direction, and the flow rate of the air flow is 4 ⁇ , and the high-speed airflow generates a high negative pressure at the material inlet of the engine intake port, and the material inlet 32 is pumped from the outside by the negative pressure.
  • the injected fuel is brought into the pipeline of the compressor duct wheel 6 by the longitudinal high-speed airflow.
  • the compressor duct is sucked into the airflow with the fine powder of the vegetation and the fuel, and then processed and compressed to make the branches and leaves of the vegetation.
  • the fine powder, fuel and air are blended and then sent to the pipeline to burn the power wheel to produce flame gas.
  • the flame gas expands and works to push the pipeline to burn the power wheel to rotate, and the pipeline compressor rotates the compressed gas to drive the engine.
  • the attached parts work.
  • the flame gas expansion works to push the pipe to burn the power wheel and then flow out of the pipe to burn the power wheel outlet.
  • the engine tail nozzle sprays to generate longitudinal thrust to propel the aircraft to fly
  • the fuel can be taken from the natural space outside the machine like oxygen.
  • the fuel is only auxiliary fuel, which can greatly reduce the load weight of the aircraft, greatly increase the thrust ratio of the engine, and enhance the life of the aircraft. ability.
  • This example is taken from the fuels of nature's vegetation, whether dry or wet. Adaptation, if fresh grass leaves are used, the crushing deflector of the engine air inlet pipe is pulverized into solid liquid fines, and then sent to the compressor for compression processing, with the increase of pressure, the temperature rises, in the fine The water will turn into super-high temperature superheated steam, superheated steam and air, solid powder fuel, fuel droplets blended, and then sent together into the pipeline combustion power wheel for combustion expansion work.
  • This example is suitable for use on assembly cruise missiles and drones.
  • the assembled cruise missiles can fly over the upper surface of the forest grassland with ultra low altitude. Due to the high wind speed of the engine inlet, the material inlet pressure is large, flying. During the process, the tops of the suction tree, the weeds and the crop straws can be picked up into the engine inlet, crushed into fine powder by the crushing deflector, and then fed into the compressor for compression and mixing, and finally sent to the pipeline for combustion. The power wheel burns and works.
  • the cruise missile assembled in this example is available in the sea surface of the desert river, it is possible to operate the fuel tank oil pump to increase the fuel injection to the engine intake, mainly relying on fuel for fuel.
  • Such cruise missiles can fly at low altitudes in any surface environment. Because of this ultra-low altitude flight, radar search can be completely avoided, and it is possible to smoothly cross enemy air defense areas and strike targets that need to be struck.
  • the cruise missile assembled in this example will be all-weather and multi-functional.
  • the drones equipped with this example because they can fly at low altitudes, search for military economic intelligence, and detect natural disasters and other unexpected information, the effect will be better, use such drones to transport arms or other rescues. Materials are safer and more reliable.
  • Embodiment 3 referring to FIG. 5, FIG. 6, and FIG. 7, this example is basically the same as Example 2, except that the combustion power wheel 17 of this example has a large axial dimension, and the flame gas pipe 20 is wound around the combustion power wheel for two weeks.
  • the second difference is that the combustion power wheel 18 is provided with a combustion power wheel side wall air outlet 1 9, and the axial side wall of the air tube wheel air duct is provided with a wind tube wheel air duct axial side wall.
  • the tuyere 24, the fuel-air mixed airflow directly flows from the axial side wall air inlet 24 of the duct pipe duct to the air duct of the duct pipe 10.
  • a cooling exhaust air outlet 38 is provided at the rear end of the combustion power wheel.
  • This example starts with a motor.
  • the combustion power wheel rotates, and the cold air from the air inlet 8 of the air duct can pass through the action of the centrifugal force of rotation.
  • the side wall air outlet 19 of the combustion power wheel penetrates between the radially outer flame gas pipe 20 of the combustion power wheel, cools the flame gas pipe 20, and cools the exhaust gas after cooling the flame gas pipe and then cools the exhaust gas outlet through the combustion power wheel. 38
  • the combustion power wheel is exhausted, and is discharged together with the gas exhaust gas to the engine exhaust passage 3, and then discharged into the atmosphere.
  • the fuel is auxiliary fuel.
  • the mixed work of grass powder, fuel and air is used to push the pipe to burn the power wheel. It is directly rotated to discharge the flame gas pipe, but is reversed by the flame gas pipe tail to reverse the tangential nozzle 23 to generate a larger thrust to push the impeller again, and then flow into the engine exhaust passage, and then discharged to the body.
  • This example is suitable for use with drones, helicopters, propellers and flying vehicles.
  • the assembled drones have a long battery life due to the fact that the fuel is mainly taken from the outside world, and it is also a very low-altitude flight. It is concealed, safe and reliable.
  • the helicopters and general propeller aircraft assembled in this case are also mainly due to the fact that the fuel mainly relies on the natural space outside, the endurance is large, and because it is ultra-low altitude, close to the vegetation surface, close to the surface, it can fly at any time. Take off and land, no need to use a dedicated airport, and more importantly, due to the extremely low flight, close to the vegetation surface, close to the surface of the flight. Even if there are mechanical failures and meteorological obstacles, there will be no air disasters caused by machine damage.
  • the helicopters and propellers assembled in this case are particularly suitable for military transport and civilian rescue and disaster relief.
  • this kind of car has a road, no low-altitude flight, close to the surface of the vegetation, close to the surface, close to the rivers and lakes Flying over the sea surface.
  • This kind of flying car can be close to the vegetation surface, flying over the forest grassland, farmland, swamp, wetland, picking up grass and making fuel for flight. It can pick up the grass and branches of the mountain slope and make fuel for mountain climbing. It can burn its own fuel and cross the river. Because the fuel is mainly taken from nature, the flying car has a strong endurance. This type of flying car can avoid the road and can avoid the traffic accidents in the crowded urban areas of the city, thus avoiding traffic accidents.
  • a flying vehicle is most suitable for military transportation and rescue and disaster relief.
  • Embodiment 4 referring to Fig. 8, Fig. 9, Fig. 10, this example is basically the same as Example 3, except that the duct wheel compressor duct 6 of this example has a large axial dimension, the duct tube duct 10 and the duct
  • the wheel-changing deceleration duct 1 1 uses a one-time formed full-sealed round tube, and the duct tube duct 10 is entangled and twisted from the front to the rear downwind tube wheel in the axial direction of the duct tube for 10 weeks to be fixed on the duct wheel ( In order to clear the problem, the drawing is only shown for 4 weeks.
  • the duct reversing deceleration duct 11 is rotatably wound on the duct pin 6 from the front to the rear downwind tube wheel in the axial direction of the duct wheel. Draw for 3 weeks), the side wall of the duct of the duct on the gap between the duct pipe duct 10 of the duct pipe and the duct deceleration duct 1 1 is provided with the side wall of the duct wheel Tuyere 12.
  • the second difference is that the high-energy circulating thrust pipe 13 is arranged on the air duct wheel, the high-energy circulating thrust pipe inlet 14 and the high-energy circulating thrust pipe outlet 15 are arranged on the high-energy circulating thrust pipe, and the high-energy circulating thrust pipe inlet 14 is followed by the air duct.
  • the high-pressure high-temperature airflow in the duct of the rear (downstream) of the wheel is connected in reverse flow, and the high-energy circulating thrust pipe outlet 15 communicates with the low-pressure low-temperature airflow in the duct pipe of the front (upstream) of the duct wheel.
  • This example starts with a motor.
  • the air duct wheel sucks in the fuel-air mixture gas through the axial side wall air inlet 24 of the duct tube air duct, and accelerates through the air duct of the duct tube for 10 weeks, and the deceleration air duct is retracted by the duct wheel for 5 weeks.
  • Pressure a total of 15 weeks of processing, can achieve extremely high wind pressure.
  • duct pipe The rear side of the duct wheel side auxiliary air outlet 12 is sucked between the air duct wheel air inlet 8 and the duct tube reversing deceleration duct by the action of the rotating centrifugal force, and the rotary flow absorption Heat, cool the ducted duct and ducted reversing duct.
  • the temperature is not too high, it will not reach the fuel ignition temperature, and will not cause combustion in the pipe at the rear of the duct wheel, thus ensuring high pressure fuel.
  • the air mixture gas enters the flame gas pipe of the combustion power wheel for combustion.
  • the cooling exhaust gas of the duct tube 10 and the reversing deceleration duct 11 continues to flow from the front to the rear in the axial direction, passes through the gap of the combustion power wheel flame gas tube 20, and merges with the cooling air in the gap of the flame gas tube to continue cooling the flame.
  • the gas pipe 20 is then discharged to the engine exhaust passage 3 through the combustion power wheel cooling exhaust gas outlet 38, it is discharged into the atmosphere.
  • the high-energy circulating thrust pipe 13 draws high-pressure high-temperature and high-energy airflow from the rear (downstream) pipe of the duct wheel into the front of the duct wheel (upstream)
  • the duct pipe wind turbine drives the low pressure low temperature and low energy airflow forward, so that the gas flow pressure of the air duct air duct is always high and then low (upstream high and low downstream), and can never be produced. Backflow, will not go out of breath. Thanks to the high-energy circulating thrust tube, the compressor duct wheel will always be in a smooth working condition.
  • the axial length of the duct wheel is large, and the duct pipe is wound around the duct tube for 15 weeks.
  • the absolute length is large, and the processing gas has high wind pressure, which is suitable for the production of a high-power aircraft gas engine.
  • the invention has the advantages of simple structure, wide application range, and can be adapted to various special situations, and the power of the cruise missile and the unmanned aircraft assembled by the machine can far exceed the power of the existing ultra-high altitude ultra-high speed aircraft.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

La présente invention concerne un moteur à gaz de type turbine pour canalisation d'avion, pourvu d'une turbine de travail à combustion de canalisation rotative (17). La turbine de travail à combustion (17) est formée par un disque de turbine de travail à combustion (18) et un tuyau de gaz de flamme (20). Le disque de turbine de travail à combustion (18) est connecté à un arbre de transmission (5) d'un rotor. Une partie avant du tuyau de gaz de flamme (20) est enroulée et fixée sur la turbine de travail à combustion (17) le long d'une direction de fonctionnement de la turbine de travail à combustion (17) de l'avant vers l'arrière le long d'une direction axiale de la turbine de travail à combustion (17). Une partie arrière du tuyau de gaz de flamme (20), proche d'une partie orifice de sortie du tuyau de gaz de flamme, est repliée contre la direction de fonctionnement de la turbine de travail à combustion (17) et est disposée sur la turbine de travail à combustion (17) le long d'une direction tangentielle. Une direction d'un orifice de sortie (22) du tuyau de gaz de flamme est opposée à une direction tangentielle rotative de la turbine de travail à combustion (17). L'orifice de sortie (22) du tuyau de gaz de flamme est en communication avec un passage d'échappement (3) d'un moteur. Un orifice d'entrée (21) du tuyau de gaz de flamme est en communication avec un tuyau d'air à inversion et réduction (11) d'une turbine de tuyau d'air. Un trou de décharge (26) d'un réservoir de stockage de carburant est en communication avec un passage d'admission (2) du moteur. Le moteur à gaz de type turbine pour canalisation d'avion a une structure simple et une large gamme d'applications et peut satisfaire aux exigences d'utilisation de diverses situations spéciales.
PCT/CN2014/077548 2013-05-15 2014-05-15 Moteur à gaz de type turbine pour canalisation d'avion WO2014183651A1 (fr)

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CN201310178265.6 2013-05-15

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US20030051484A1 (en) * 2001-09-17 2003-03-20 Chii-Ron Kuo Gas turbine engine with compressor and turbine inside a hollow shaft
CN101749257A (zh) * 2009-12-29 2010-06-23 林钧浩 环流增压管道压缩机
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CN113250802B (zh) * 2021-07-15 2021-09-21 四川迅联达智能科技有限公司 控流散热组件、智能温度管理系统及其散热方法和发动机

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