CN108468587A - The Heavy End Aviation Fuel engine and aircraft of composite injection - Google Patents
The Heavy End Aviation Fuel engine and aircraft of composite injection Download PDFInfo
- Publication number
- CN108468587A CN108468587A CN201810535754.5A CN201810535754A CN108468587A CN 108468587 A CN108468587 A CN 108468587A CN 201810535754 A CN201810535754 A CN 201810535754A CN 108468587 A CN108468587 A CN 108468587A
- Authority
- CN
- China
- Prior art keywords
- fuel
- oil
- spark plug
- engine
- nozzle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 79
- 238000002347 injection Methods 0.000 title claims abstract description 62
- 239000007924 injection Substances 0.000 title claims abstract description 62
- 239000002131 composite material Substances 0.000 title claims abstract description 34
- 239000000295 fuel oil Substances 0.000 claims abstract description 57
- 238000002485 combustion reaction Methods 0.000 claims abstract description 45
- 238000000889 atomisation Methods 0.000 claims abstract description 24
- 238000005507 spraying Methods 0.000 claims abstract description 6
- 239000003921 oil Substances 0.000 claims description 24
- 239000007921 spray Substances 0.000 claims description 14
- 230000009977 dual effect Effects 0.000 claims description 12
- 230000000712 assembly Effects 0.000 claims description 11
- 238000000429 assembly Methods 0.000 claims description 11
- 238000009434 installation Methods 0.000 claims description 3
- 150000001875 compounds Chemical class 0.000 claims 1
- 239000000203 mixture Substances 0.000 abstract description 8
- 230000007613 environmental effect Effects 0.000 abstract description 6
- 239000007789 gas Substances 0.000 description 16
- 230000000694 effects Effects 0.000 description 9
- 239000000567 combustion gas Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000008246 gaseous mixture Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000002352 surface water Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B19/00—Engines characterised by precombustion chambers
- F02B19/10—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder
- F02B19/1019—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber
- F02B19/1023—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber pre-combustion chamber and cylinder being fed with fuel-air mixture(s)
- F02B19/1028—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber pre-combustion chamber and cylinder being fed with fuel-air mixture(s) pre-combustion chamber and cylinder having both intake ports or valves, e.g. HONDS CVCC
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B19/00—Engines characterised by precombustion chambers
- F02B19/10—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder
- F02B19/1019—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber
- F02B19/1023—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber pre-combustion chamber and cylinder being fed with fuel-air mixture(s)
- F02B19/1028—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber pre-combustion chamber and cylinder being fed with fuel-air mixture(s) pre-combustion chamber and cylinder having both intake ports or valves, e.g. HONDS CVCC
- F02B19/1057—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber pre-combustion chamber and cylinder being fed with fuel-air mixture(s) pre-combustion chamber and cylinder having both intake ports or valves, e.g. HONDS CVCC with fuel injectors disposed upstream of intake valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B19/00—Engines characterised by precombustion chambers
- F02B19/10—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder
- F02B19/1019—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber
- F02B19/108—Engines characterised by precombustion chambers with fuel introduced partly into pre-combustion chamber, and partly into cylinder with only one pre-combustion chamber with fuel injection at least into pre-combustion chamber, i.e. injector mounted directly in the pre-combustion chamber
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F1/00—Cylinders; Cylinder heads
- F02F1/24—Cylinder heads
- F02F1/242—Arrangement of spark plugs or injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M29/00—Apparatus for re-atomising condensed fuel or homogenising fuel-air mixture
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M39/00—Arrangements of fuel-injection apparatus with respect to engines; Pump drives adapted to such arrangements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses the Heavy End Aviation Fuel engines and aircraft of a kind of composite injection, including cylinder body, piston component, cylinder head, composite fuel spraying system and air inlet system and exhaust system, composite fuel spraying system is the fuel oil composite injection system formed by in-cylinder direct-jet system and air intake duct electric injection system, the structure that inventive engine is atomized and is premixed using auxiliary air, heavy oil is enabled to realize more adequately atomization, uniform combustion mixture is formed after good mixing, it can also efficiently organize to burn, ensure heavy oil in the dynamic property applied to engine, economy and emission performance, it realizes energy saving after heavy oil is applied to engine, environmental protection and low cost.
Description
Technical field
The present invention relates to engine and application, more particularly to the Heavy End Aviation Fuel engine and aircraft of a kind of composite injection.
Background technology
Fuel of the heavy oil as engine, will be as the power trend of middle-size and small-size aircraft；But heavy oil viscosity is high, low temperature stream
Dynamic property is poor, causes atomizing effect poorer than common light oil, affects combustion efficiency, even result in engine start difficulty with
And discharge is not up to standard.
In the prior art, in order to ensure that heavy fuel burning engine can have good atomization and startup, have and use carburetion
The fuel system such as device+auxiliary preheating technology, mechanical injection (fuel direct injection), electronic fuel injection；Wherein electronic fuel injection is adopted
With auxiliary air, fuel particles are impacted using pressure-air, realize that the abundant atomization of fuel oil, effect are better than first two side
Formula.But opportunity, overall structure and the air degree of participation of air addition could not be optimized, it is still original EFI in structure
Mode then cannot achieve the reliable atomization of heavy oil and fuel combination can not be organized efficiently to burn, and adding due to air
Enter, causes astatki that can not improve and final be mixed into ratio so that engine power cannot effectively improve, and also just limit certainly
The use of engine is made；This series of problems finally allows for dynamic property, economy and the discharge that heavy oil is applied to engine
Property is unable to reach the effect of expectation, to make the application of heavy oil not popularize on a large scale.
Therefore, it is necessary to be improved to existing heavy fuel burning engine, heavy oil is enabled to realize more adequately atomization, energy
Heavy oil mixed ratio is effectively adjusted and improved, and the burning of fuel-efficient can be organized, ensures heavy oil applied to engine
Dynamic property, economy and emission performance realize the energy-saving and environmental protection after heavy oil is applied to engine and low cost.
Invention content
In view of this, the object of the present invention is to provide the Heavy End Aviation Fuel engine and aircraft of a kind of composite injection, energy
Enough so that heavy oil realizes more adequately atomization, heavy oil mixed ratio can be effectively adjusted and improve, and fuel-efficient can be organized
Burning, ensure heavy oil in the dynamic property, economy and emission performance applied to engine, after realizing that heavy oil is applied to engine
Energy-saving and environmental protection and low cost.
The Heavy End Aviation Fuel engine of the composite injection of the present invention, including the injection of cylinder body, piston component, cylinder head, composite fuel
System and air inlet system and exhaust system, the composite fuel spraying system are the combustion formed by in-cylinder direct-jet system and air intake duct electric injection system
Oily composite injection system；Using the structure of composite injection oil inlet, in-cylinder direct-jet structure can be assisted into combustion chamber by low-pressure air
Spray mixed oil and gas so that the heavy oil of in-cylinder direct-jet obtains effectively atomization and uniformly mixing, and can be initially entered into air and mix；
Meanwhile air intake duct electric injection system ensures the mixed ratio of fuel oil, the miscella of in-cylinder direct-jet in the structure of intake port injection fuel oil
The power of gas enters inlet valve the mixed oil and gas progress secondary pulse of combustion chamber, forms effective atomization and uniformly mixes
It closes, for efficiently organizing burning to have the effect of can not be substituted.
Further, the in-cylinder direct-jet system is equipped with fuel oil ejection assemblies and is sprayed into combustion chamber by fuel oil ejection assemblies
Fuel is penetrated, fuel oil ejection assemblies include fuel nozzle I, premixer and oil-air mixing nozzle, there is fuel nozzle I in the premixer
Injector and compressed air inlet, the oil-air mixing nozzle be connected to premixer by fuel oil and compressed air in premixer
Mixed oil and gas after the atomization of formation is sent into the combustion chamber of engine；Premix is realized simultaneously in premixer using auxiliary low pressure air
The fuel oil that further atomizing fuel nozzle I sprays ensures to be formed after later stage direct-injection enters combustion chamber to be more more fully atomized, from
And realize the abundant burning and utilization of heavy oil；Not only ensure that the further atomization of fuel droplet, moreover it is possible to ensure auxiliary air with
Uniform mixing between droplet, into combustion chamber after being capable of homogenous combustion；Fuel nozzle I generally uses EFI mode, herein not
It repeats again；In-cylinder direct-jet system further includes oil supply system and air supply system certainly, using the structure of the prior art, herein not
It repeats again.
Further, the air intake duct electric injection system is equipped with fuel nozzle II and is sprayed into air intake duct by fuel nozzle II
Enter the combustion chamber of engine after fuel by inlet valve；The air intake duct electric injection system further includes oil supply system, belongs to existing
Technology, details are not described herein.
Further, the dual ignition plug formed by spark plug I and spark plug II is installed on the cylinder head, is carried using dual ignition plug
For igniting, in conjunction with air-assisted atomization above-mentioned and premix scheme, ensure engine various operating modes and under the conditions of reliably pacify
Full igniting.
Further, the oil-air mixing nozzle is respectively in I both sides of spark plug with spark plug II, the oil-air mixing nozzle
Injection direction is 16 ° -20 °；The igniting angle of spark plug II is 40 ° -50 °；The structure makes the gaseous mixture that in-cylinder direct-jet enters
It is corresponding with the igniting orientation of spark plug, it is formed about dense combustion gas mixing area in spark plug, is further mixed conducive to burning air
It closes, to organize the burning of fuel-efficient；The injection direction of oil-air mixing nozzle be suitable in heavy oil atomization property and
The sparking mode for adapting to dual ignition plug is fully burnt conducive to tissue igniting and final obtain.
Further, the spark plug I be located at top of combustion chamber centre position or near, due to spark plug I be located at centre
Position or near, which ensure that also is located at center line in spark plug II and oil-air mixing nozzle structure arrangement, injection and point
It is conducive to be sufficiently mixed and adequately burn after fire.
Further, the center line of the center line of the spark plug I, the center line of spark plug II and oil-air mixing nozzle is basic
It is coplanar, and this is coplanar spatially substantially vertical with plane where inlet and exhaust valve, co-planar arrangement refer to oil-air mixing nozzle,
The central axis of spark plug II and spark plug I is located on the same face, and the plane where inlet and exhaust valve refers to the axis of inlet and exhaust valve
Line is generally aligned in the same plane, it is substantially coplanar and it is substantially vertical refer to the error for allowing to have certain, such as smaller inclination and dislocation,
Have no effect on understanding coplanar to this programme and vertical；The structure ensure that the simple-arranged of all parts on cylinder head, simultaneously
Conducive to being sufficiently mixed for air inlet and combustion gas, further it is atomized conducive to tumble flow is formed, ensure that the burning of uniform high-efficiency.
Further, the fuel nozzle I gos deep into premixer and injector is more than compressed air inlet；The structure not only facilitates
The compact layout of all parts, also so that compressed air enter premixer be to be formed turbulent flow type impact, be conducive to further atomization with
And uniformly mixing, reach atomization and mixed dual purpose, preferable basic role is played in direct-injection and the burning to be the later stage.
Further, the oil spout direction of the fuel nozzle I is consistent with the injection channel direction of oil-air mixing nozzle, the combustion
Spacing between the injector and oil-air mixing nozzle entrance of oil burner nozzle I is 5-8mm, ensure that mounting structure neatly compactly,
And ensure that the efficient injection of fuel oil, it is conducive to air and forms impact and turbulent flow；Suitable spacing range is conducive to the abundant mist of heavy oil
Change and enter oil-air mixing nozzle after evenly mixing, and ensures injection pressure.
Further, further include precombustion chamber, the precombustion chamber is the Laval nozzle knot along plug ignition direction
Structure, the Laval nozzle structure are formed directly into cylinder head and jet port connection combustion chamber；The precombustion chamber course of work is, mixed
Close after fuel is injected into combustion chamber, while entering precombustion chamber, by spark plug (ignition point is located at the inlet end of Laval nozzle,
The inlet end be for Laval nozzle, rather than with the mouth of combustion chamber) igniting after, expand and pass through Lavalle
Jet pipe rapidly sprays (speed more higher than combustion explosion), and the fuel combination to entering combustion chamber, which further impacts to have, makes gas
Well-mixed effect, conducive to uniform combustion mixture is formed, meanwhile, precombustion chamber can accelerate flame transmission, improve combustion
Burn efficiency, promoting engine power simultaneously reduces risk for knock, additionally it is possible to organize the burning of fuel-efficient, ensure heavy oil applied to
Dynamic property, economy and the emission performance of engine realize the energy-saving and environmental protection after heavy oil is applied to engine and low cost.
Further, the dual ignition plug formed by spark plug I and spark plug II, and the spark plug I are installed on the cylinder head
Positioned at the centre position of top of combustion chamber or near, precombustion chamber is set at spark plug I and I ignitor of the spark plug is stretched
Enter precombustion chamber；Main spark plug is in the middle part of combustion chamber or nearby, the burning gases that precombustion chamber sprays are more conducively to entirely firing
Burn the mixed Daqu disturbance and fully burning of room.
The invention also discloses a kind of aircraft, the Heavy End Aviation Fuel that the aircraft is equipped with the composite injection starts
Machine.
Beneficial effects of the present invention：The Heavy End Aviation Fuel engine and aircraft of the composite injection of the composite injection of the present invention,
The structure that engine is atomized and is premixed using auxiliary air enables to heavy oil to realize more adequately atomization, good
Uniform combustion mixture is formed after mixing, additionally it is possible to organize the burning of fuel-efficient, ensure heavy oil applied to engine
Dynamic property, economy and emission performance realize the energy-saving and environmental protection after heavy oil is applied to engine and low cost.
Description of the drawings
The invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is the engine overall structure diagram of the present invention；
Fig. 2 is the chamber structure schematic diagram of the present invention；
Fig. 3 is fuel oil ejection assemblies structural schematic diagram.
Specific implementation mode
As shown in the figure：The Heavy End Aviation Fuel engine of the composite injection of the present embodiment, including cylinder body 1, piston component 5, cylinder head
2, composite fuel spraying system and air inlet system and exhaust system (further including bent axle 15 certainly, details are not described herein), the composite fuel spray
It is the fuel oil composite injection system formed by in-cylinder direct-jet system and air intake duct electric injection system to penetrate system；Using composite injection oil inlet
Structure can assist in-cylinder direct-jet structure to spray mixed oil and gas into combustion chamber 11 so that the weight of in-cylinder direct-jet by low-pressure air
Oil obtains effectively being atomized and uniformly mixing, and can be initially entered into air and mix；Meanwhile air intake duct electric injection system is sprayed in air intake duct
The structure for penetrating fuel oil ensures that the mixed ratio of fuel oil, the power of the mixed oil and gas of in-cylinder direct-jet enter combustion chamber for inlet valve
Mixed oil and gas carry out secondary pulse, form effective atomization and uniformly mixing, can not for efficiently organizing burning to have
The effect of replacement.
In the present embodiment, the in-cylinder direct-jet system is equipped with fuel oil ejection assemblies a and by fuel oil ejection assemblies a to burning
Indoor injection fuel, fuel oil ejection assemblies include fuel nozzle I 6, premixer 7 and oil-air mixing nozzle 8, in the premixer 7
There are the injector and compressed air inlet (the namely compressed air outlet of air compression system) of fuel nozzle I 6, the oil
Gas mixing nozzle 8 is connected to the mixed oil and gas after the atomization that premixer 7 forms fuel oil and compressed air in premixer and is sent into hair
The combustion chamber of motivation；Premix and the combustion that further atomizing fuel nozzle I sprays are realized in premixer using auxiliary low pressure air
Oil ensures that later stage direct-injection enters behind combustion chamber to be formed and is more more fully atomized, to realize the abundant burning of heavy oil and utilize；
Not only ensure that the further atomization of fuel droplet, moreover it is possible to ensure between auxiliary air and droplet it is uniform mix, into burning
It being capable of homogenous combustion behind room；Fuel nozzle I 6 generally uses EFI mode, and details are not described herein；In-cylinder direct-jet system is also wrapped certainly
Oil supply system and air supply system are included, using the structure of the prior art, details are not described herein.
In the present embodiment, the air intake duct electric injection system is equipped with fuel nozzle II 14 and by fuel nozzle II 14 to air inlet
Enter the combustion chamber 11 of engine in road 13 after injection fuel by inlet valve；The air intake duct electric injection system further includes fuel feeding system
System, belongs to the prior art, details are not described herein.
As shown, fuel oil ejection assemblies are tightly connected by fuel nozzle I 6, premixer 7 and oil-air mixing nozzle 8 successively
It is formed, is tightly connected to be formed by mounting base 10 between fuel nozzle I 6 and oil-air mixing nozzle 8 and fix, and the direct shape in premixer
It is simple and compact for structure in mounting base 10；Fuel nozzle I is equipped with fuel inlet fitting 61, and premixer 7 passes through pneumatic fitting 9, compression
The compressed air outlet of 16 connect compressor of air hose；The air inlet 91 of premixer is the gas outlet of pneumatic fitting 9.
The dual ignition plug formed by spark plug I 3 and spark plug II 4 is installed, the mounting structure of spark plug is to stretch on cylinder head 2
Combustion chamber is lighted a fire, and details are not described herein for mounting structure, and igniting is provided using dual ignition plug, the characteristic with high-energy ignition,
In conjunction with air-assisted atomization above-mentioned and premix scheme, ensure engine various operating modes and under the conditions of reliable and secure point
Fire further decreases engine volume and weight relative to traditional heavy oil compression ignition engine, is suitable for aircraft use.
In the present embodiment, the oil-air mixing nozzle 8 is respectively in I 3 both sides of spark plug with spark plug II 4, and the oil gas is mixed
The injection direction for closing nozzle is 16 ° -20 °, preferably 18 °；The igniting angle of spark plug II is 40 ° -50 °, preferably 45 °, igniting folder
Angle refers to the angle of the axis direction of spark plug；What angle here referred to is all the angle with cylinder center line, no longer superfluous herein
It states；The structure makes the gaseous mixture that in-cylinder direct-jet enters after top land and cylinder body wall surface water conservancy diversion, the igniting side with spark plug
Position is corresponding, is formed about dense combustion gas mixing area in spark plug, and further mix conducive to burning air, efficient to be formed
Tissue burning；The injection direction of oil-air mixing nozzle is suitable for the point of atomization property and adaptation dual ignition plug in heavy oil
Fiery mode is fully burnt conducive to tissue igniting and final obtain.
In the present embodiment, the spark plug I 3 be located at top of combustion chamber centre position or near, due to I 3, spark plug
In centre position or near, the structure ensure that spark plug II 4 and 8 structure of oil-air mixing nozzle arrangement on also is located at center line, spray
It is conducive to be sufficiently mixed and adequately burn after penetrating and lighting a fire.
In the present embodiment, center line, the center line of spark plug II 4 and the center of oil-air mixing nozzle of the spark plug I 3
Line is substantially coplanar, and this is coplanar spatially substantially vertical with plane where inlet and exhaust valve, and co-planar arrangement refers to that oil gas is mixed
Close nozzle 8, the central axis of spark plug II 4 and spark plug I 3 is located on the same face, the plane where inlet and exhaust valve refer into
The axis of exhaust valve is generally aligned in the same plane, it is substantially coplanar and it is substantially vertical refer to the error for allowing to have certain, such as it is smaller
It tilts and misplaces, have no effect on understanding coplanar to this programme and vertical；The structure ensure that the letter of all parts on cylinder head
Single arrangement, while being sufficiently mixed conducive to air inlet and combustion gas, are further atomized conducive to tumble flow is formed, ensure that uniform high-efficiency
Burning.
In the present embodiment, there is compressed air inlet 91, the fuel nozzle I 6 to go deep into premixer and spray for the premixer 7
Hydraulic fluid port is more than compressed air inlet 91；As shown, the center line of the compressed air inlet 91 and the spray with fuel nozzle I 6
The centerline of hydraulic fluid port in same plane, and it is substantially vertical (it is of course also possible to appropriate tilting, vertically further facilitate layout and
Conducive to atomization), which not only facilitates the compact layout of all parts, also so that it is to form turbulent flow that compressed air, which enters premixer,
Formula impact, be conducive to further atomization and uniformly mixing, reach atomization and mixed dual purpose, to for the later stage direct-injection and
Preferable basic role is played in burning.
In the present embodiment, the oil spout direction of the fuel nozzle I 6 is consistent with the injection channel direction of oil-air mixing nozzle 8,
Spacing between the injector and oil-air mixing nozzle entrance of the fuel nozzle I is 5-8mm, ensure that installation neatly compactly
Structure, and ensure that the efficient injection of fuel oil, it is conducive to air and forms impact and turbulent flow；Suitable spacing range is conducive to heavy oil
It is fully atomized and enters oil-air mixing nozzle after evenly mixing, and ensure injection pressure, ensure that mounting structure neatly compactly,
And ensure that the efficient injection of fuel oil, it is conducive to air and forms impact and turbulent flow.
Further include precombustion chamber 12 in the present embodiment, the precombustion chamber 12 is (to be referred to along plug ignition direction
Spark plug axis direction) Laval nozzle structure formed, the Laval nozzle structure is formed directly into cylinder head and jet port
It is connected to combustion chamber；The precombustion chamber course of work is, after fuel combination is injected into combustion chamber, while entering precombustion chamber, fiery
Hua Sai (ignition point is located at the inlet end of Laval nozzle, the inlet end be for Laval nozzle, rather than with burning
Room connection mouth) igniting after, expand simultaneously by Laval nozzle rapidly by throat by Laval nozzle jet port spray (ratio
The higher speed of combustion explosion), the fuel combination to entering combustion chamber, which further impacts to have, makes the well-mixed effect of gas,
Conducive to the uniform combustion mixture of formation, meanwhile, precombustion chamber can accelerate flame transmission, improve efficiency of combustion, and promotion is started
Acc power simultaneously reduces risk for knock, additionally it is possible to organize the burning of fuel-efficient, ensure heavy oil applied to engine dynamic property,
Economy and emission performance realize the energy-saving and environmental protection after heavy oil is applied to engine and low cost.
In the present embodiment, the dual ignition plug formed by spark plug I and spark plug II, and the spark plug I are installed on cylinder head
Positioned at the centre position of top of combustion chamber or near, precombustion chamber is set at spark plug I and I ignitor of the spark plug is stretched
Enter precombustion chamber；Main spark plug is in the middle part of combustion chamber or nearby, the burning gases that precombustion chamber sprays are more conducively to entirely firing
Burn the mixed Daqu disturbance and fully burning of room.
The invention also discloses a kind of aircraft, the Heavy End Aviation Fuel that the aircraft is equipped with the composite injection starts
Machine.
Finally illustrate, the above examples are only used to illustrate the technical scheme of the present invention and are not limiting, although with reference to compared with
Good embodiment describes the invention in detail, it will be understood by those of ordinary skill in the art that, it can be to the skill of the present invention
Art scheme is modified or replaced equivalently, and without departing from the objective and range of technical solution of the present invention, should all be covered at this
In the right of invention.
Claims (10)
1. a kind of Heavy End Aviation Fuel engine of composite injection, it is characterised in that：Including cylinder body, piston component, cylinder head, composite fuel
Spraying system and air inlet system and exhaust system, the composite fuel spraying system are to be formed by in-cylinder direct-jet system and air intake duct electric injection system
Fuel oil composite injection system.
2. the Heavy End Aviation Fuel engine of composite injection according to claim 1, it is characterised in that：The in-cylinder direct-jet system
Fuel is sprayed into combustion chamber equipped with fuel oil ejection assemblies and by fuel oil ejection assemblies, fuel oil ejection assemblies include fuel nozzle
I, premixer and oil-air mixing nozzle have injector and the compressed air inlet of fuel nozzle I, the oil in the premixer
Gas mixing nozzle is connected to premixer and starts the mixed oil and gas feeding after atomization that fuel oil and compressed air are formed in premixer
The combustion chamber of machine.
3. the Heavy End Aviation Fuel engine of composite injection according to claim 1, it is characterised in that：Air intake duct EFI system
System sprays into air intake duct the combustion for entering engine after fuel by inlet valve equipped with fuel nozzle II and by fuel nozzle II
Burn room.
4. the Heavy End Aviation Fuel engine of composite injection according to claim 2, it is characterised in that：On the cylinder head installation by
The dual ignition plug that spark plug I and spark plug II are formed；The oil-air mixing nozzle is respectively in I both sides of spark plug with spark plug II；
The injection direction of the oil-air mixing nozzle is 16 ° -20 °；The igniting angle of spark plug II is 40 ° -50 °.
5. the Heavy End Aviation Fuel engine of composite injection according to claim 4, it is characterised in that：The spark plug I is located at
The centre position of top of combustion chamber or near；The center line of the spark plug I, the center line and oil-air mixing nozzle of spark plug II
Center line it is substantially coplanar, and this is coplanar spatially substantially vertical with plane where inlet and exhaust valve.
6. the Heavy End Aviation Fuel engine of composite injection according to claim 2, it is characterised in that：The fuel nozzle I is deep
It is more than compressed air inlet to enter premixer and injector.
7. the Heavy End Aviation Fuel engine of composite injection according to claim 2, it is characterised in that：The fuel nozzle I
Oil spout direction is consistent with the injection channel direction of oil-air mixing nozzle, the injector and oil-air mixing nozzle of the fuel nozzle I
Spacing between entrance is 5-8mm.
8. the Heavy End Aviation Fuel engine of composite injection according to claim 1, it is characterised in that：Further include precombustion chamber,
The precombustion chamber is the Laval nozzle structure along plug ignition direction, and the Laval nozzle structure is formed directly into
Cylinder head and jet port connection engine chamber.
9. the Heavy End Aviation Fuel engine of composite injection according to claim 8, it is characterised in that：On the cylinder head installation by
The dual ignition plug that spark plug I and spark plug II are formed, and the spark plug I be located at top of combustion chamber centre position or near,
Precombustion chamber is set at spark plug I and I ignitor of the spark plug stretches into precombustion chamber.
10. a kind of aircraft, it is characterised in that：The aircraft is equipped with the compound spray of claim 1 to 9 any claim
The Heavy End Aviation Fuel engine penetrated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535754.5A CN108468587A (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535754.5A CN108468587A (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108468587A true CN108468587A (en) | 2018-08-31 |
Family
ID=63260603
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810535754.5A Withdrawn CN108468587A (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108468587A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110953106A (en) * | 2019-09-30 | 2020-04-03 | 广西擎芯动力科技有限公司 | Gas auxiliary fuel supply system and method for direct injection engine in ignition type heavy oil cylinder |
| CN112727621A (en) * | 2021-01-04 | 2021-04-30 | 航天时代飞鸿技术有限公司 | Oil injection control system and method for two-stroke aviation piston engine |
| CN113374608A (en) * | 2021-06-28 | 2021-09-10 | 大连理工大学 | Fuel-air integrated injector and ignition chamber system comprising same |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4123592A1 (en) * | 1991-07-17 | 1993-01-21 | Daimler Benz Ag | Improved burn IC engine with two spark plugs - uses staggered ignition for enhanced compression of fuel-air mixture in main combustion chamber |
| JPH10159567A (en) * | 1996-11-27 | 1998-06-16 | Toyota Motor Corp | In-cylinder injection type spark ignition engine |
| JP2002030937A (en) * | 2000-04-28 | 2002-01-31 | Gureitochiren:Kk | Engine and system |
| US20040079322A1 (en) * | 2002-10-29 | 2004-04-29 | Hitachi, Ltd. | Control apparatus for internal combustion engine and control method for internal combustion engine combustion method for internal combustion engine and direct injection engine |
| JP2005291065A (en) * | 2004-03-31 | 2005-10-20 | Osaka Gas Co Ltd | Engine |
| JP2010255508A (en) * | 2009-04-24 | 2010-11-11 | Toyota Motor Corp | Fuel injection control device for spark ignition internal combustion engine |
| CN208793086U (en) * | 2018-05-29 | 2019-04-26 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
-
2018
- 2018-05-29 CN CN201810535754.5A patent/CN108468587A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4123592A1 (en) * | 1991-07-17 | 1993-01-21 | Daimler Benz Ag | Improved burn IC engine with two spark plugs - uses staggered ignition for enhanced compression of fuel-air mixture in main combustion chamber |
| JPH10159567A (en) * | 1996-11-27 | 1998-06-16 | Toyota Motor Corp | In-cylinder injection type spark ignition engine |
| JP2002030937A (en) * | 2000-04-28 | 2002-01-31 | Gureitochiren:Kk | Engine and system |
| US20040079322A1 (en) * | 2002-10-29 | 2004-04-29 | Hitachi, Ltd. | Control apparatus for internal combustion engine and control method for internal combustion engine combustion method for internal combustion engine and direct injection engine |
| JP2005291065A (en) * | 2004-03-31 | 2005-10-20 | Osaka Gas Co Ltd | Engine |
| JP2010255508A (en) * | 2009-04-24 | 2010-11-11 | Toyota Motor Corp | Fuel injection control device for spark ignition internal combustion engine |
| CN208793086U (en) * | 2018-05-29 | 2019-04-26 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110953106A (en) * | 2019-09-30 | 2020-04-03 | 广西擎芯动力科技有限公司 | Gas auxiliary fuel supply system and method for direct injection engine in ignition type heavy oil cylinder |
| CN112727621A (en) * | 2021-01-04 | 2021-04-30 | 航天时代飞鸿技术有限公司 | Oil injection control system and method for two-stroke aviation piston engine |
| CN113374608A (en) * | 2021-06-28 | 2021-09-10 | 大连理工大学 | Fuel-air integrated injector and ignition chamber system comprising same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106014694B (en) | Air assisted gas injector, large-diameter gas machine precombustion chamber combustion system and method | |
| CN101571069B (en) | Dual-fuel combustion system for internal combustion engines | |
| WO2012000307A1 (en) | Multi-fuel pre-mixed combustion system of internal combustion engine | |
| CN108590871A (en) | The cylinder head and aero-engine of heavy fuel burning engine | |
| CN109441626A (en) | A kind of dual fuel engine and its burning tissues method using major-minor fuel injector and manifold multi-injection | |
| CN108468587A (en) | The Heavy End Aviation Fuel engine and aircraft of composite injection | |
| CN108547697A (en) | A kind of rotary engine using high-energy ignition technology | |
| CN105673281B (en) | In a kind of gas/liquid double fuel cylinder/cylinder outer pair of injection apparatus and control method | |
| CN101440742A (en) | Direct spraying composite flow guide laminating combustion system in spark ignition methanol cylinder | |
| CN111305977A (en) | Hydrogen natural gas full-proportion variable dual-fuel engine | |
| CN208763799U (en) | Heavy fuel burning engine fuel injection equipment (FIE) and aero-engine | |
| CN208763800U (en) | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet | |
| CN208294663U (en) | The cylinder head and aero-engine of heavy fuel burning engine | |
| CN108488018A (en) | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet | |
| CN108468588A (en) | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine | |
| CN102996223A (en) | Premixed combustion system of diesel engine | |
| CN208793086U (en) | The Heavy End Aviation Fuel engine and aircraft of composite injection | |
| CN208763745U (en) | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine | |
| CN208763798U (en) | Heavy fuel burning engine fuel injection system and aero-engine | |
| CN107939517A (en) | Engine superelevation compression ratio combustion control device and method based on jet initiation | |
| CN208763763U (en) | The dual ignition plug cylinder head assembly and aero-engine of heavy fuel burning engine | |
| CN204921139U (en) | Directly spout formula diesel engine burner | |
| CN110821638B (en) | Ignition chamber type engine with high-energy ignition fuel and control method thereof | |
| CN108757255A (en) | Heavy fuel burning engine fuel injection equipment (FIE) and aero-engine | |
| CN108757203A (en) | The dual ignition plug cylinder head assembly and aero-engine of heavy fuel burning engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180831 |