CN108167089A - Supersonic speed internal combustion aero-engine - Google Patents
Supersonic speed internal combustion aero-engine Download PDFInfo
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- CN108167089A CN108167089A CN201710849783.4A CN201710849783A CN108167089A CN 108167089 A CN108167089 A CN 108167089A CN 201710849783 A CN201710849783 A CN 201710849783A CN 108167089 A CN108167089 A CN 108167089A
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- Prior art keywords
- internal combustion
- engine
- combustion engine
- punching press
- flabellum group
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 231
- 238000004080 punching Methods 0.000 claims abstract description 63
- 230000006835 compression Effects 0.000 claims abstract description 16
- 238000007906 compression Methods 0.000 claims abstract description 16
- 239000000446 fuel Substances 0.000 claims abstract description 11
- 241000883990 Flabellum Species 0.000 claims description 91
- 238000001816 cooling Methods 0.000 claims description 47
- 239000003921 oil Substances 0.000 claims description 47
- 238000005461 lubrication Methods 0.000 claims description 13
- 239000000314 lubricant Substances 0.000 claims description 7
- 239000010687 lubricating oil Substances 0.000 claims description 7
- 239000004519 grease Substances 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- 239000007858 starting material Substances 0.000 claims description 5
- 238000005119 centrifugation Methods 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 15
- 239000000203 mixture Substances 0.000 description 6
- 238000007789 sealing Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 4
- 239000000956 alloy Substances 0.000 description 3
- 230000001050 lubricating effect Effects 0.000 description 3
- 238000009792 diffusion process Methods 0.000 description 2
- 230000010006 flight Effects 0.000 description 2
- 239000002828 fuel tank Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 240000007594 Oryza sativa Species 0.000 description 1
- 235000007164 Oryza sativa Nutrition 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- CSDREXVUYHZDNP-UHFFFAOYSA-N alumanylidynesilicon Chemical compound [Al].[Si] CSDREXVUYHZDNP-UHFFFAOYSA-N 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- -1 pump Substances 0.000 description 1
- 235000009566 rice Nutrition 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
- F02K5/02—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan the engine being of the reciprocating-piston type
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of aero-engine, specially a kind of supersonic speed internal combustion aero-engine.Purpose is the efficiency in order to improve aero-engine, reduce cost, maintenance expense and the fuel cost of aero-engine, structure includes fuselage, centrifugal compressor, internal combustion engine unit are equipped in fuselage, piston IC engine, air jet system, centrifugal compressor is located at the forepart of fuselage, and the internal combustion engine unit is located at waist, and air jet system is located at fuselage afterbody.At the forepart of internal combustion engine fuselage and middle part, centrifugal compressor is installed, air is compressed using Systems of Centrifugal Compressor Unit, piston internal combustion unit is for burning and expansion work, portion's setting compression and combustion expansion nozzle or tail portion setting punching press burning expansion jet pipe within the engine, generate thrust.Aero-engine gross efficiency can reach 95%.And maintenance expense and manufacturing expenses all greatly reduce.
Description
Technical field
The present invention relates to a kind of aero-engine, specially a kind of supersonic speed internal combustion aero-engine.
Background technology
At present, existing aero-engine mainly has three categories：Piston IC engine, gas turbine and ramjet propulsion.
Piston IC engine is generally only used for smaller power and the aircraft of relatively low flying speed, in equal relatively low flight speed
Under degree, engine thermal efficiency ratio gas turbine itself is high, but thrust-weight ratio is small；
Gas turbine, due to belonging to external-combustion engine, under relatively low flying speed, the thermal efficiency itself is less than the internal combustion engine of Same Efficieney,
Cost is high.The advantages of prominent：Thrust-weight ratio is big, single-machine capacity is big；
Ramjet propulsion thermal efficiency highest, thrust-weight ratio in high-speed flight is maximum, low cost, but shortcoming is：During low-speed operations
The thermal efficiency is ultralow, can not voluntarily start to take off under stationary condition.
Invention content
The invention aims to improve the efficiency of aero-engine, reduce the cost of aero-engine, maintenance expense and
Fuel cost provides a kind of supersonic speed internal combustion aero-engine.
The technical scheme is that a kind of supersonic speed internal combustion aero-engine, it is characterised in that：Structure includes fuselage,
Centrifugal compressor, internal combustion engine unit, piston IC engine, air jet system are equipped in fuselage, centrifugal compressor is located at the forepart of fuselage,
The internal combustion engine unit is located at waist, and air jet system is located at fuselage afterbody.
Compared with the prior device, innovation of the invention is：At the forepart of internal combustion engine fuselage and middle part, installation centrifugation
Compressor compresses air using Systems of Centrifugal Compressor Unit, and piston internal combustion unit is for burning and expansion work, in engine
Middle part sets compression and combustion expansion nozzle or tail portion setting punching press burning expansion jet pipe, generates thrust.If installing flabellum group,
Piston IC engine can also drive flabellum rotation to generate thrust；Itself exhaust injection also generates a small amount of thrust.
The centrifugal compressor include Systems of Centrifugal Compressor Unit spiral case, Systems of Centrifugal Compressor Unit impeller, gearbox, it is described from
Internal combustion engine main shaft is equipped in the middle part of heart compressor set spiral case, internal combustion engine main shaft is equipped with Systems of Centrifugal Compressor Unit impeller, in centrifugal compressed
Gearbox is equipped between unit impeller and Systems of Centrifugal Compressor Unit spiral case, Systems of Centrifugal Compressor Unit impeller outer end is equipped with centrifugal compressor leaf
Wheel cap is connected with Systems of Centrifugal Compressor Unit front fairing in fore-body.
The internal combustion unit is located at waist, and internal combustion unit includes internal combustion engine cabinet, in the internal combustion engine cabinet
Equipped with cylinder of internal-combustion engine, internal combustion engine, internal combustion mainshaft bearing, IC engine link rod, I. C. engine crankshaft, internal combustion engine main shaft umbrella tooth
It takes turns, internal combustion engine main shaft, IC engine link rod one end connection internal combustion engine, other end connection I. C. engine crankshaft, outside I. C. engine crankshaft
End is equipped with cone tooth, internal combustion engine main shaft bevel gear is equipped on internal combustion engine main shaft, the cone tooth and internal combustion engine main shaft bevel gear are nibbled
It closes, fuel injection valve for internal combustion engines, internal combustion engine high pressure oil pipe, sparking plug for internal combustion engine, intake lines of combustion engines, internal combustion is equipped in cylinder of internal-combustion engine
Machine cylinder bottom is equipped with I. C. engine exhaust door, internal combustion engine intake valve, I. C. engine exhaust door connection I. C. engine exhaust door oil cooling electromagnetism
Actuator, internal combustion engine intake valve connection internal combustion engine intake valve oil cooling electromagnetic actuator, internal combustion engine intake valve connection air-intake of combustion engine
Pipe is equipped in internal combustion engine cooling wind inlet and internal combustion engine lubrication oil cooling pipe, internal combustion engine cooling wind inlet in fuselage outer side and is equipped with
Lubricant pump of internal combustion engine, lubricant pump of internal combustion engine connection internal combustion engine lubrication oil cooling pipe.
The air jet system includes the I. C. engine exhaust jet pipe of taper, I. C. engine exhaust jet pipe rear portion connection internal combustion engine row
Gas blowout mouth is externally provided with internal combustion engine cooling air channel in internal combustion engine ejector exhaust pipe.
Punching press burning expansion nozzle combustion room is equipped on the outside of internal combustion engine cooling air channel, in punching press burning expansion nozzle combustion room
Before in punching press burning expansion jet pipe atomizer and punching press burning expansion jet pipe spark plug, punching press burning expansion nozzle combustion room
End is equipped with punching press burning expansion jet pipe into gas ring shape duct, and rear end is equipped with spout, and punching press burning expansion jet pipe is into gas ring shape duct
It is interior to be equipped with punching press burning expansion jet pipe duct entrance guiding piece, it is equipped with stamping combustion chamber in spout and exports flow deflector.
Fan is additionally provided in front fuselage, fan includes flabellum group duct shell, flabellum group axis, set in flabellum group axis outer end
There is a shaft core radome fairing, ecto-entad is equipped with 1 grade of movable vane of flabellum group, 1 grade of stator blade of flabellum group, 2 grades of flabellum group successively on flabellum group axis
Movable vane, 2 grades of stator blades of flabellum group；Flabellum group axis inner terminal connects internal combustion engine main shaft；
It is connected between described 2 grades of stator blades of 1 grade of stator blade of flabellum group and flabellum group and flabellum group axis by flabellum group bearing, flabellum group
2 grades of stator blade outer ends of 1 grade of stator blade and flabellum group and flabellum group duct cage connection.
Flabellum group grease-box, flabellum group grease pump, the cooling of flabellum group lubricating oil are equipped on flabellum group duct shell
Pipe, flabellum group grease pump pump out the lubricating oil in flabellum group grease-box, and lubricate oil cooling pipe by flabellum group and note
Enter into 7 flabellum group bearings.
Compared with existing aero-engine, existing aero-engine is limited by high-temperature alloy material, gas turbine
Ignition temperature is difficult more than 1600 DEG C.And technical scheme can readily exceed due to the use of combustion in IC engine temperature
2500 DEG C, fuel efficiency is high.Cylinder can be cooled down effectively, itself temperature is not high (≤300 DEG C), do not needed to special high temperature and closed
Golden material can substantially reduce the cost and maintenance expense of aero-engine using this technology.Using the internal combustion engine of this technology to combustion
Oil can reduce fuel cost without particular/special requirement.
Aero-engine gross efficiency using 3 times of sonic flights of this technology can reach 95%, more than it is existing at first
Into 85%；Cost and maintenance expense are down to 20%.Supersonic speed aero-engine single-machine capacity can reach 300000kw, and thrust surpasses
Cross 30 tons, and its outer diameter≤1.6 meter.For particularly supersonic speed aero-engine in subsonic flight, efficiency is than existing turbofan
Aero-engine efficiency doubles.Its thrust-weight ratio is suitable with existing turbofan aero-engine (or bigger), outer diameter and length
Quite.
Description of the drawings
Fig. 1 is one of structure chart of the present invention；
Fig. 2 is the two of the structural map of the present invention；
Fig. 3 is the A-A sectional views of Fig. 1；
Fig. 4 is the B-B sectional views of Fig. 1；
Fig. 5 is the C-C sectional views of Fig. 4；
In figure：1 shaft core radome fairing, 2 flabellum group axis, 3 flabellum group, 1 grade of movable vane, 4 flabellum group duct shells, 5 flabellum group, 1 grade of stator blade,
62 grades of flabellum group movable vanes, 7 flabellum group bearings, 8 flabellum group, 2 grades of stator blades, 9 flabellum groups lubrication oil cooling pipe, 10 flabellum group lubricating oil
Case, the sealing of 11 impeller eyes, 12 flabellum group grease pumps, 13 Systems of Centrifugal Compressor Unit impellers, 14 gearboxes, 15 Systems of Centrifugal Compressor Unit
Spiral case, 16 internal combustion engines cooling wind inlet, 17 lubricant pump of internal combustion engine, 18 internal combustion engine lubrication oil cooling pipes, 19 cylinder of internal-combustion engine, 20
Internal combustion engine, 21 cylinder jacket of diesel engine, 22 I. C. engine exhaust doors, 23 internal combustion engine intake valves, 24 I. C. engine exhaust jet pipes, 25 punchings
Compression ignition burn expansion nozzle duct entrance guiding piece, 26 stamping combustion chambers outlet flow deflector, 27 internal combustion engine cooling air channel spouts, in 28
Combustion engine jet exhaust, 29 punching press burning expansion jet pipe spouts, 30 thermal insulation materials, 31 punching press burning expansion nozzle combustion rooms, 32 punchings
Compression ignition burns expansion nozzle spark plug, 33 punching press burning expansion nozzle flame stabilizers, 34 punching press burning expansion jet pipe atomizers, 35
I. C. engine exhaust door oil cooling electromagnetic actuator, 36 internal combustion engine intake valve oil cooling electromagnetic actuators, 37 punching press burning expansion jet pipes into
Gas ring shape duct, 38 combustion engine cylinder heads, 39 starter motors, 40 generators, 41 internal combustion mainshaft bearings, 42 IC engine link rods,
43 I. C. engine crankshafts, 44 internal combustion engine main shaft bevel gears, 45 motor mounts, 46 IC engine link rod bearing caps, 47 main shafts middle part
Bearing, 48 internal combustion engine main shafts, 49 Systems of Centrifugal Compressor Unit high pressure sealing gas vents, 50 Systems of Centrifugal Compressor Unit high pressure sealings, 51 centrifugations
Compressor impeller lid, 52 Centrufugal compressor impeller locking nuts, 53 Systems of Centrifugal Compressor Unit front fairings, the expansion spray of 54 compression and combustions
Pipe Centrufugal compressor impeller inlet seal, 55 internal combustion engine cabinets, 56 intake lines of combustion engines, 57 fuel injection valve for internal combustion engines, 58 internal combustion engines
High-pressure oil pipe, 59 sparking plug for internal combustion engine, 60 compression and combustion expansion nozzle Centrufugal compressor impeller lids, 61 compression and combustion expansion nozzles
Centrufugal compressor impeller.
Specific embodiment
As schematically shown in Figure 1, 2, a kind of supersonic speed internal combustion aero-engine, structure include fuselage, centrifugation pressure are equipped in fuselage
Contracting machine, internal combustion unit, air jet system, centrifugal compressor are located at the forepart of fuselage, and the internal combustion unit is located at waist,
Air jet system is located at the rear portion of fuselage.
Centrifugal compressor include Systems of Centrifugal Compressor Unit spiral case 15, Systems of Centrifugal Compressor Unit impeller 13, gearbox 14, it is described from
The middle part of heart compressor set spiral case 15 is equipped with internal combustion engine main shaft 48, internal combustion engine main shaft 48 is equipped with Systems of Centrifugal Compressor Unit impeller 13,
Gearbox 14,13 outer end of Systems of Centrifugal Compressor Unit impeller are equipped between Systems of Centrifugal Compressor Unit impeller 13 and Systems of Centrifugal Compressor Unit spiral case 15
Equipped with Centrufugal compressor impeller lid 51, Systems of Centrifugal Compressor Unit front fairing 53 is connected in fore-body.
Specifically, for air-intake of combustion engine Systems of Centrifugal Compressor Unit by impeller intake cover, 1 grade of impeller, diffusion return channel,
The composition such as 2 grades of impellers, spiral case, high pressure sealing, impeller axle, bearings (when can also use 1 grade of compression, particularly supersonic flight,
1 grade enough).Structural principle is identical with common oblique flow centrifugal compressor.Its lubricating and cooling system is shared with flabellum group.Impeller axle is led to
Gearbox is crossed with main shaft to be connected.High pressure sealing uses labyrinth seal, and gas leakage returns impeller air inlet or internal combustion engine cooling air channel.
From front to back, impeller intake cover, 1 grade of impeller, diffusion return channel, 2 grades of impellers, spiral cases are followed successively by, are used between each other
It is bolted.High pressure sealing is between spiral case and axis.
Gearbox is between centrifugal compressor and internal combustion engine.It if, can be with using high-speed internal combustion engine (>=12000rpm)
Cancel this device.Suitable to supersonic speed engine using high-speed internal combustion engine, flabellum, centrifugal compressor, internal combustion engine may be used together
A piece axis reduces engine weight.
The internal combustion unit is located at waist, and internal combustion unit includes internal combustion engine cabinet 55, set in internal combustion engine cabinet 55
There are cylinder of internal-combustion engine 19, internal combustion engine 20, internal combustion mainshaft bearing 41, IC engine link rod 42, I. C. engine crankshaft 43, internal combustion engine
Main shaft bevel gear 44, internal combustion engine main shaft 48,42 one end of IC engine link rod connection internal combustion engine 20, other end connection internal combustion engine are bent
Axis 43,43 outer end of I. C. engine crankshaft are equipped with cone tooth, internal combustion engine main shaft bevel gear 44, the cone are equipped on internal combustion engine main shaft 48
Tooth and internal combustion engine main shaft bevel gear 44 engage, be equipped in cylinder of internal-combustion engine 19 fuel injection valve for internal combustion engines 57, internal combustion engine high pressure oil pipe 58,
Sparking plug for internal combustion engine 59, intake lines of combustion engines 56,19 bottom of cylinder of internal-combustion engine are equipped with I. C. engine exhaust door 22, internal combustion engine intake valve
23, I. C. engine exhaust door 22 connects I. C. engine exhaust door oil cooling electromagnetic actuator 35, internal combustion engine intake valve 23 connect internal combustion engine into
Valve oil cooling electromagnetic actuator 36, internal combustion engine intake valve 23 connect intake lines of combustion engines 56, fuselage outer side be equipped with internal combustion engine into
Tracheae 56,56 one end of intake lines of combustion engines are connected with internal combustion engine intake valve 23, and the other end is connected with Systems of Centrifugal Compressor Unit spiral case 15.
Fuselage outer side be equipped with internal combustion engine cooling wind inlet 16 and internal combustion engine lubrication oil cooling pipe 18, internal combustion engine cooling wind into
Lubricant pump of internal combustion engine 17 is equipped in mouth 16, lubricant pump of internal combustion engine 17 connects internal combustion engine lubrication oil cooling pipe 18.Internal combustion owner
48 inner terminal of axis is equipped with starter motor 39, generator 40.
Internal combustion unit installation group can by multiple cylinders that are in juxtaposition, piston, connecting rod, bent axle, bevel gear, main shaft, cabinet,
Inlet valve, exhaust valve, lubricating and cooling system, Electrocontrolled high-pressure fuel system, electric control valve system, air inlet pipe, ejector exhaust pipe, cooling
The compositions such as air duct, starter motor (hydraulic pressure or electric notor), generator, electric controller.Its structure and pot type piston internal combustion
Machine is similar.
Its difference is：There is no compression stroke and induction stroke, air inlet is with doing work as same one-stroke, only two strokes；
Using electric control valve, simplify valve mechanism, expansion ratio is adjusted flexibly, control delivery temperature.
In order to reduce engine diameters (reduce flight resistance) as possible, during more than 4 cylinders, two sections of arrangement (work(can be divided to
The subsonic flight aero-engine of rate >=10000kw).When cylinder bore is too big, since piston inertia is too big, internal combustion can be limited
The maximum speed of machine.When cylinder bore is more than Φ 300mm, each cylinder can set the exhaust valve of 2 or more, to increase valve
Response speed.Middle low power (≤5000kw) engine, 4 cylinders of setting are proper.Appropriate small stroke (it is straight to be less than cylinder
Diameter), be conducive to save space.Piston uses Oil injection cooling, and the silicon aluminum alloy material that density can be used small reduces its inertia.
Supersonic speed aero-engine 3.5~6.5MPa of inlet pressure of internal combustion engines of the present invention, burn exhaust hood in gas
2100~2500 DEG C of temperature.
Single internal combustion engine principle：Descent of piston：Air inlet (5~20% strokes), oil spout ignition, expansion are done
Work(；Piston stroking upward：A cycle is completed in exhaust.
Electric control fuel system is by fuel tank, oil transfer pump, high-pressure oil pump, piezoelectric ceramics atomizer, oil pipe, electric-controlled plate, cable etc.
Composition.Wherein, fuel tank, oil transfer pump, high-pressure oil pump, electric-controlled plate etc. are not resided on engine body.
Electric control valve (can also but use air-cooled) electromagnetic coil to drive using oil cooling, spring return function.
The cooling of cylinder is using air-cooled.Cold wind enters from the aperture (or crack) of fairing midsection surrounding, from tail portion annular
Spout (center is jet exhaust, periphery is punching press spout) sprays, and generates a small amount of thrust.
Air inlet pipe front end is connect with the scroll casing of centrifugal compressor positioned at engine forepart, and rear end connects with internal combustion engine intake valve
It connects, using double layer heat preservation pipe.Internal combustion engine cabinet is connect with scroll casing of centrifugal compressor.
Bevel gear on bent axle is engaged with the bevel gear on internal combustion engine main shaft.The speed ratio of main shaft and bent axle can be more than 1,
1, i.e. speedup or deceleration can be less than.Cylinder is circumferentially evenly arranged.Cylinder-bore axis is parallel with engine spindle line.Bent axle exists
Before, cylinder is rear, convenient for exhaust.Ejector exhaust pipe positioned at tail portion center generates certain thrust.
Starter motor, generator and main shaft tail end connect, and speed reducer and clutch or ratchet can be set between main shaft.
Lubricant pump of internal combustion engine is located at below cabinet inside.Internal combustion engine cabinet, that is, grease-box.Lubrication oil cooling pipe is located at
Outside cabinet, inside radome fairing.Using the oil pump of electric drive or hydraulic-driven.
During middle low-speed operations, cylinder is efficient using low-temp low-pressure exhaust (≤600 DEG C ,≤0.2MPa).During high-speed flight,
In order to increase exhaust spray speed, it is suitable to be vented using high temperature and pressure, but can not too high (≤1300 DEG C), in order to avoid increase cost, drop
Low efficiency.
Air jet system includes the I. C. engine exhaust jet pipe 24 of taper, 24 rear portion of I. C. engine exhaust jet pipe connection I. C. engine exhaust
Spout 28 is externally provided with internal combustion engine cooling air channel 27 in internal combustion engine ejector exhaust pipe 24.
The high-temperature high-pressure fuel gas that internal combustion unit generates is sprayed by I. C. engine exhaust jet pipe 24, so as to generate thrust.
As schematically shown in Figure 1, a kind of structure of supersonic speed aero-engine, 27 outside of internal combustion engine cooling air channel are equipped with punching press and fire
Expansion nozzle combustion chamber 31 is burnt, 31 are equipped with punching press burning expansion jet pipe atomizer 34 and punching in punching press burning expansion nozzle combustion room
Compression ignition burns expansion nozzle spark plug 32,31 Inner Front End of punching press burning expansion nozzle combustion room is equipped with punching press burning expansion jet pipe air inlet
Annular duct 37, rear end are equipped with spout, and punching press burning expansion jet pipe is equipped with punching press burning expansion jet pipe into gas ring shape duct 37 is interior
Duct entrance guiding piece 25, the interior stamping combustion chamber that is equipped with of spout export flow deflector 26.
As schematically shown in Figure 2, another structure of supersonic speed aero-engine is equipped with punching press burning expansion in the outside of fuselage
Nozzle combustion room 31, punching press burning expansion nozzle combustion room 31 is interior to be equipped with punching press burning expansion jet pipe atomizer 34 and punching press burning
Expansion nozzle spark plug 32,31 Inner Front End of punching press burning expansion nozzle combustion room are equipped with punching press burning expansion jet pipe and contain into gas ring shape
Road 37, rear end are equipped with spout, and punching press burning expansion jet pipe enters into gas ring shape duct 37 is interior equipped with punching press burning expansion jet pipe duct
Mouth flow deflector 25, the interior stamping combustion chamber that is equipped with of spout export flow deflector 26.
Compression and combustion expansion nozzle Centrufugal compressor impeller 61, the compression and combustion are additionally provided on internal combustion engine main shaft 48
Expansion nozzle Centrufugal compressor impeller 61 is located at 31 front end of punching press burning expansion nozzle combustion room.In high-speed flight, can give
Punching press burning expansion nozzle combustion room 31 provides sufficient air and promotes burning.
Punching press burning expansion jet pipe is located at engine tail portion, outside internal combustion engine cooling air channel, by into gas ring shape duct, burning
Room, flameholder, atomizer, oil transfer pump, high-pressure oil pump, oil pipe, high pressure generator, spark plug, cable, electric control
The compositions such as device, jet pipe.Structure is similar to common punching engine.In high-speed flight, main thrust is provided.
Duct entrance inlet porting flow deflector allows air-flow to be rotated in combustion chamber, to increase combustion path, fully burns.
Combustor exit (temperature≤850 DEG C herein) setting outlet flow deflector, allows air-flow to be sprayed along the parallel direction of axis.If using
Nozzle exit accumulates adjustable structure and is more advantageous to efficient under variable working condition, can also change jet-impingement direction.
Atomizer is located at the front of flameholder, close to entrance guiding piece, so that fuel oil and air are sufficiently mixed.Spark
Plug is located at below flameholder, is conducive to light a fire successfully.
Chamber temperature also should not be (≤1500 DEG C too high.At 1300 DEG C, 90%) thermal efficiency alreadys exceed, in order to avoid increase spray
Mouth temperature, reduces efficiency.Annular firing indoor and outdoor has cooling, is not required to special high temperature alloy.Inner Wall of Combustion Chamber and flame are steady
Ceramic material (heatproof >=2000 DEG C) can also be used by determining device.Supersonic speed Laval nozzle may be used in jet pipe, reduces nozzle temperature
(≤300 DEG C) increase the thermal efficiency.During middle low-speed operations, punching press burner nozzle lacks oil spout or not oil spout, improves engine complete machine
Fuel efficiency.
Compression and combustion expansion nozzle is by centrifugal compressor, combustion chamber, flameholder, atomizer, oil transfer pump, high pressure oil
The compositions such as pump, oil pipe, high pressure generator, spark plug, cable, electric controller, jet pipe.During using high-speed internal combustion engine, pressure
Contracting machine and internal combustion engine same root main shaft.In addition to compressor is increased, other parts are similar to punching press burning expansion nozzle structure.Especially
It is suitable for ten thousand metres height, the aero-engine and 30000 meters or more height of 1~2 times of sonic flight, 2~4 times of sonic flights
Aero-engine.When the characteristics of maximum is high speed, thrust-weight ratio is big, can be more than 25.During low-speed operations, thrust is smaller.10000
During the following height hypervelocity flight of rice, gross efficiency is not so good as punching press burning expansion jet pipe.During subsonic flight, gross efficiency is not so good as flabellum
Group.
As schematically shown in Figure 1, fan being additionally provided in front fuselage, fan includes flabellum group duct shell 4, flabellum group axis 2,
2 outer end of flabellum group axis is equipped with shaft core radome fairing 1, and ecto-entad is equipped with 1 grade of movable vane 3 of flabellum group, flabellum group successively on flabellum group axis 2
1 grade of stator blade 5,2 grades of movable vanes 6 of flabellum group, 2 grades of stator blades 8 of flabellum group；2 inner terminal of flabellum group axis connection internal combustion engine main shaft 48；
It is connected, fanned by flabellum group bearing 7 between described 2 grades of stator blades 8 of 1 grade of stator blade 5 of flabellum group and flabellum group and flabellum group axis 2
2 grades of 8 outer ends of stator blade of 1 grade of stator blade 5 of leaf group and flabellum group are connect with flabellum group duct shell 4；
Flabellum group grease-box 10, flabellum group grease pump 12, the cooling of flabellum group lubricating oil are equipped on flabellum group duct shell 4
Pipe 9, flabellum group grease pump 12 pump out the lubricating oil in flabellum group grease-box 10, and are cooled down by flabellum group lubricating oil
Pipe 9 is injected into flabellum group bearing 7.
In short, flabellum group is by 2 grades of movable vanes, 2 grades of stator blades, flabellum axle, flabellum bearing, duct shell, lubricating and cooling system etc.
Composition.Flabellum axle can be coaxial with main shaft or coaxial with centrifugal compressor, can also be separately through gearbox and other axis phases
Even.During middle low speed (subsonic speed) flight, flabellum generates main thrust.Structural principle is identical with common turbofan aero-engine.Profit
Oil pump, grease-box are located at duct shell lower inner.Lubrication oil cooling pipe is located at duct enclosure.Using electric drive or
The oil pump of hydraulic-driven.
Claims (10)
1. a kind of supersonic speed internal combustion aero-engine, it is characterised in that：Structure includes fuselage, be equipped in fuselage centrifugal compressor,
Internal combustion unit, air jet system, centrifugal compressor are located at the forepart of fuselage, and the internal combustion unit is located at waist, jet
Device is located at the rear portion of fuselage.
2. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：Centrifugal compressor includes centrifugation and presses
Contracting unit spiral case (15), Systems of Centrifugal Compressor Unit impeller (13), gearbox (14), the Systems of Centrifugal Compressor Unit spiral case (15) middle part
Systems of Centrifugal Compressor Unit impeller (13) is equipped with equipped with internal combustion engine main shaft (48), internal combustion engine main shaft (48), in Systems of Centrifugal Compressor Unit leaf
Take turns and gearbox (14) be equipped between (13) and Systems of Centrifugal Compressor Unit spiral case (15), Systems of Centrifugal Compressor Unit impeller (13) outer end equipped with from
Heart compressor impeller lid (51) is connected with Systems of Centrifugal Compressor Unit front fairing (53) in fore-body.
3. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：The internal combustion unit is located at machine
In the middle part of body, internal combustion unit includes internal combustion engine cabinet (55), cylinder of internal-combustion engine (19) is equipped in internal combustion engine cabinet (55), internal combustion engine is lived
It fills in (20), internal combustion mainshaft bearing (41), IC engine link rod (42), I. C. engine crankshaft (43), internal combustion engine main shaft bevel gear (44),
Internal combustion engine main shaft (48), IC engine link rod (42) one end connection internal combustion engine (20), other end connection I. C. engine crankshaft (43),
I. C. engine crankshaft (43) outer end is equipped with cone tooth, and internal combustion engine main shaft bevel gear (44) is equipped on internal combustion engine main shaft (48), described
Tooth and internal combustion engine main shaft bevel gear (44) engagement are bored, it is high to be equipped with fuel injection valve for internal combustion engines (57), internal combustion engine in cylinder of internal-combustion engine (19)
Pressuring oil pipe (58), sparking plug for internal combustion engine (59), intake lines of combustion engines (56), cylinder of internal-combustion engine (19) bottom are equipped with I. C. engine exhaust
Door (22), internal combustion engine intake valve (23), I. C. engine exhaust door (22) connection I. C. engine exhaust door oil cooling electromagnetic actuator (35) are interior
Combustion engine inlet valve (23) connection internal combustion engine intake valve oil cooling electromagnetic actuator (36), internal combustion engine intake valve (23) connect internal combustion engine into
Tracheae (56) is equipped with intake lines of combustion engines (56), intake lines of combustion engines (56) one end and internal combustion engine intake valve in fuselage outer side
(23) it connects, the other end is connected with Systems of Centrifugal Compressor Unit spiral case (15).
4. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：Air jet system includes the interior of taper
Combustion engine ejector exhaust pipe (24), I. C. engine exhaust jet pipe (24) rear portion connection I. C. engine exhaust spout (28), spray in I. C. engine exhaust
Pipe (24) is externally provided with internal combustion engine cooling air channel (27).
5. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：Further include the spray of punching press burning expansion
Guard system, internal combustion engine cooling air channel (27) outside are equipped with punching press burning expansion lance system, punching press burning expansion lance system packet
Punching press burning expansion nozzle combustion room (31) is included, (31) are equipped with punching press burning expansion jet pipe in punching press burning expansion nozzle combustion room
Atomizer (34) and punching press burning expansion jet pipe spark plug (32), punching press burning expansion nozzle combustion room (31) Inner Front End are equipped with punching
Compression ignition burns expansion nozzle into gas ring shape duct (37), and rear end is equipped with spout, and punching press burning expansion jet pipe is into gas ring shape duct (37)
It is interior to be equipped with punching press burning expansion jet pipe duct entrance guiding piece (25), it is equipped with stamping combustion chamber outlet flow deflector (26) in spout.
6. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：Punching press is equipped in the outside of fuselage
Burning expansion lance system, punching press burning expansion lance system include punching press burning expansion nozzle combustion room (31), punching press burning
Punching press burning expansion jet pipe atomizer (34) and punching press burning expansion jet pipe spark plug are equipped in expansion nozzle combustion chamber (31)
(32), punching press burning expansion nozzle combustion room (31) Inner Front End is equipped with punching press burning expansion jet pipe into gas ring shape duct (37), after
End is equipped with spout, and punching press burning expansion jet pipe is equipped with punching press burning expansion jet pipe duct entrance guiding into gas ring shape duct (37) is interior
Piece (25), spout is interior to be equipped with stamping combustion chamber outlet flow deflector (26).
7. supersonic speed internal combustion aero-engine according to claim 6, it is characterised in that：On internal combustion engine main shaft (48) also
Equipped with compression and combustion expansion nozzle Centrufugal compressor impeller (61), the compression and combustion expansion nozzle Centrufugal compressor impeller
(61) positioned at punching press burning expansion nozzle combustion room (31) front end.
8. supersonic speed internal combustion aero-engine according to claim 1, it is characterised in that：Wind is additionally provided in front fuselage
Fan, fan include flabellum group duct shell (4), flabellum group axis (2), and shaft core radome fairing (1) is equipped in flabellum group axis (2) outer end,
Ecto-entad is equipped with 1 grade of movable vane (3) of flabellum group, 1 grade of stator blade (5) of flabellum group, 2 grades of movable vanes of flabellum group successively on flabellum group axis (2)
(6), 2 grades of stator blades (8) of flabellum group；Flabellum group axis (2) inner terminal connection internal combustion engine main shaft (48)；Described 1 grade of stator blade of flabellum group
(5) and between 2 grades of stator blades (8) of flabellum group and flabellum group axis (2) it is connected by flabellum group bearing (7), 1 grade of stator blade (5) of flabellum group
And 2 grades of stator blade (8) outer ends of flabellum group are connect with flabellum group duct shell (4).
9. supersonic speed internal combustion aero-engine according to claim 8, it is characterised in that：In flabellum group duct shell (4)
It is equipped with flabellum group grease-box (10), flabellum group grease pump (12), flabellum group lubrication oil cooling pipe (9), flabellum group lubrication
Oil pump (12) pumps out the lubricating oil in flabellum group grease-box (10), and lubricates oil cooling pipe (9) by flabellum group and inject
In to flabellum group bearing (7).
10. supersonic speed internal combustion aero-engine according to claim 3, it is characterised in that：Internal combustion is equipped in fuselage outer side
Internal combustion engine lubrication is equipped in machine cooling wind inlet (16) and internal combustion engine lubrication oil cooling pipe (18), internal combustion engine cooling wind inlet (16)
Oil pump (17), lubricant pump of internal combustion engine (17) connection internal combustion engine lubrication oil cooling pipe (18), internal combustion engine main shaft (48) inner terminal are set
There are starter motor (39), generator (40).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710849783.4A CN108167089B (en) | 2017-09-08 | 2017-09-08 | Supersonic internal combustion aircraft engine |
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|---|---|---|---|
| CN201710849783.4A CN108167089B (en) | 2017-09-08 | 2017-09-08 | Supersonic internal combustion aircraft engine |
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| CN108167089B CN108167089B (en) | 2021-07-20 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2446286Y (en) * | 2000-08-18 | 2001-09-05 | 李新 | Rotary-cylinder engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN103291496A (en) * | 2012-02-27 | 2013-09-11 | 魏九洲 | Cock engine |
| CN104145104A (en) * | 2011-10-12 | 2014-11-12 | 工程推进***有限公司 | An aerodiesel engine |
| CN104775895A (en) * | 2015-03-09 | 2015-07-15 | 北京动力机械研究所 | Aviation turbocharged internal combustion engine |
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2017
- 2017-09-08 CN CN201710849783.4A patent/CN108167089B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2446286Y (en) * | 2000-08-18 | 2001-09-05 | 李新 | Rotary-cylinder engine |
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN104145104A (en) * | 2011-10-12 | 2014-11-12 | 工程推进***有限公司 | An aerodiesel engine |
| CN103291496A (en) * | 2012-02-27 | 2013-09-11 | 魏九洲 | Cock engine |
| CN104775895A (en) * | 2015-03-09 | 2015-07-15 | 北京动力机械研究所 | Aviation turbocharged internal combustion engine |
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| Publication number | Publication date |
|---|---|
| CN108167089B (en) | 2021-07-20 |
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Effective date of registration: 20210819 Address after: 035400 Industrial Zone, Qiucun village, Jizhuang Township, Dingxiang County, Xinzhou City, Shanxi Province Patentee after: XINZHOU LIBO EQUIPMENT MANUFACTURING Co.,Ltd. Address before: 035400 Qiucun Industrial Park, Dingxiang County, Xinzhou City, Shanxi Province Patentee before: Zou Guoquan Patentee before: Zhang Yingchen |
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