CN208793086U - 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
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- CN208793086U CN208793086U CN201820819589.1U CN201820819589U CN208793086U CN 208793086 U CN208793086 U CN 208793086U CN 201820819589 U CN201820819589 U CN 201820819589U CN 208793086 U CN208793086 U CN 208793086U
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- 239000000446 fuel Substances 0.000 title claims abstract description 78
- 238000002347 injection Methods 0.000 title claims abstract description 61
- 239000007924 injection Substances 0.000 title claims abstract description 61
- 239000002131 composite material Substances 0.000 title claims abstract description 32
- 239000000295 fuel oil Substances 0.000 claims abstract description 58
- 238000002485 combustion reaction Methods 0.000 claims abstract description 51
- 238000000889 atomisation Methods 0.000 claims abstract description 23
- 238000005507 spraying Methods 0.000 claims abstract description 8
- 239000003921 oil Substances 0.000 claims description 24
- 239000007921 spray Substances 0.000 claims description 13
- 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 7
- 230000007613 environmental effect Effects 0.000 abstract description 6
- 238000004134 energy conservation Methods 0.000 abstract 1
- 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
- 230000000149 penetrating effect Effects 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000005516 engineering process Methods 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
- 230000003116 impacting effect Effects 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002352 surface water Substances 0.000 description 1
Classifications
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- 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
Landscapes
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The utility model 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 the utility model 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, guarantee heavy oil in the dynamic property for being applied to engine, economy and emission performance, realize the energy conservation that heavy oil is applied to after engine, environmental protection and low cost.
Description
Technical field
The utility model relates to engine and application, in particular to the Heavy End Aviation Fuel engine of a kind of composite injection and aviation
Device.
Background technique
Fuel of the heavy oil as engine will become 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 guarantee that heavy fuel burning engine can have good atomization and starting, 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 the abundant atomization of fuel oil, effect is better than first two side
Formula.But opportunity, overall structure and the air degree of participation of air addition could not be optimized, original EFI is still 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, cause astatki can not improve it is final be mixed into ratio so that engine power cannot effectively improve, 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 be unable to reach the effect of expectation, thus make heavy oil application can not popularize on a large scale.
Therefore, it is necessary to improve 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, guarantees that heavy oil is being applied to engine
Dynamic property, economy and emission performance realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
Utility model content
In view of this, the purpose of the utility model is to provide a kind of Heavy End Aviation Fuel engine of composite injection and aviations
Device enables to heavy oil to realize more adequately atomization, can effectively adjust and improve heavy oil mixed ratio, and can organize fuel
Efficient burning guarantees that heavy oil in dynamic property, economy and the emission performance for being applied to engine, realizes that heavy oil is applied to engine
Energy-saving and environmental protection and low cost afterwards.
The Heavy End Aviation Fuel engine of the composite injection of the utility model, 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；Using the structure of composite injection oil inlet, in-cylinder direct-jet structure can be assisted to burning by low-pressure air
Indoor injection mixed oil and gas so that the heavy oil of in-cylinder direct-jet obtains effectively being atomized and uniformly mixing, and can be initially entered into air simultaneously
Mixing；Meanwhile air intake duct electric injection system guarantees the mixed ratio of fuel oil in the structure of intake port injection fuel oil, in-cylinder direct-jet
The mixed oil and gas that the power of mixed oil and gas enters combustion chamber for inlet valve carries out secondary pulse, forms effective atomization and
Even mixing, 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 by fuel oil ejection assemblies into combustion chamber
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
Jet and compressed air inlet, oil-air mixing nozzle connection premixer is 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 in premixer using auxiliary low pressure air simultaneously
The fuel oil that further atomizing fuel nozzle I sprays guarantees to be formed after later period direct-injection enters combustion chamber to be more more fully atomized, from
And realize the full combustion and utilization of heavy oil；Not only ensure that the further atomization of fuel droplet, moreover it is possible to guarantee 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 by fuel nozzle II into air intake duct
Enter the combustion chamber of engine after fuel by inlet valve；The air intake duct electric injection system further includes oil supply system, is belonged 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 mentioned using dual ignition plug
For igniting, in conjunction with air-assisted atomization above-mentioned and premix scheme, guarantee engine various operating conditions and under the conditions of reliably pacify
Full igniting.
Further, the oil-air mixing nozzle and spark plug II are respectively in I two sides of spark plug, the oil-air mixing nozzle
Injection direction is 16 ° -20 °；The igniting angle of spark plug II is 40 ° -50 °；The gaseous mixture that the structure enters in-cylinder direct-jet
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 combustion 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 of dual ignition plug is adapted to, tissue igniting and final full combustion are conducive to.
Further, the spark plug I be located at top of combustion chamber middle position or near, due to spark plug I be located at centre
Position or near, which, which ensure that, also is located at middle 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 allow to have certain error, such as lesser 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 jet is more than compressed air inlet；The structure not only facilitates
The compact layout of all parts, also make 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, so that the direct-injection and burning for the later period play preferable basic role.
Further, the oil spout direction of the fuel nozzle I and the injection channel direction of oil-air mixing nozzle are consistent, the combustion
Spacing between the jet 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, conducive to the abundant mist of heavy oil
Change and enter oil-air mixing nozzle after evenly mixing, and guarantees injection pressure.
It 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 is the mouth for Laval nozzle, rather than with combustion chamber) igniting after, expand and pass through Lavalle
Jet pipe rapidly sprays (speed more higher than combustion explosion), and further impacting to have to the fuel combination for entering combustion chamber makes gas
Well-mixed effect, conducive to uniform combustion mixture is formed, meanwhile, precombustion chamber can accelerate flame transmission, improve combustion
Efficiency is burnt, engine power is promoted and reduces risk for knock, additionally it is possible to organize the burning of fuel-efficient, guarantee that heavy oil is being applied to
Dynamic property, economy and the emission performance of engine realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
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 top of combustion chamber middle position 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, and the burning gases that precombustion chamber sprays are more conducive to entirely firing
Burn the mixed Daqu disturbance and full combustion of room.
The invention also discloses a kind of aircraft, the aircraft is equipped with the Heavy End Aviation Fuel of the composite injection
Engine.
The utility model has the beneficial effects that the Heavy End Aviation Fuel engine of the composite injection of the composite injection of the utility model and
Aircraft, the structure that engine is atomized and is premixed using auxiliary air enable to heavy oil to realize more adequately atomization,
Uniform combustion mixture is formed after good mixing, additionally it is possible to organize the burning of fuel-efficient, guarantee that heavy oil is being applied to hair
Dynamic property, economy and the emission performance of motivation realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
Detailed description of the invention
The utility model is further described with reference to the accompanying drawings and examples.
Fig. 1 is the engine overall structure diagram of the utility model；
Fig. 2 is the chamber structure schematic diagram of the utility model；
Fig. 3 is fuel oil ejection assemblies structural schematic diagram.
Specific embodiment
It is 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 (certainly further including crankshaft 15, details are not described herein), the composite fuel spray
Penetrating system is the fuel oil composite injection system formed by in-cylinder direct-jet system and air intake duct electric injection 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 guarantees 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 substitution.
In the present embodiment, the in-cylinder direct-jet system is equipped with fuel oil ejection assemblies a and passes through 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 jet 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 guarantees that later period direct-injection enters behind combustion chamber to be formed and is more more fully atomized, to realize the full combustion and utilization of heavy oil；
Not only ensure that the further atomization of fuel droplet, moreover it is possible to guarantee 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 passes through 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 successively tightly connected by fuel nozzle I 6, premixer 7 and oil-air mixing nozzle 8
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 protrude on cylinder head 2
Combustion chamber is lighted a fire, and details are not described herein for mounting structure, provides igniting using dual ignition plug, the characteristic with high-energy ignition,
In conjunction with air-assisted atomization above-mentioned and premix scheme, guarantee engine various operating conditions 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 two 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；Igniting side of the gaseous mixture that the structure enters in-cylinder direct-jet after top land and cylinder body wall surface water conservancy diversion, with spark plug
Position is corresponding, dense combustion gas mixing area is formed about in spark plug, and be conducive to further mix with combustion air, to be formed efficient
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 conducive to tissue igniting and final full combustion.
In the present embodiment, the spark plug I 3 be located at top of combustion chamber middle position or near, due to I 3, spark plug
In middle 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 middle 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 allow to have certain error, such as it is lesser
Inclination and dislocation, 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 conducive to being sufficiently mixed for air inlet and combustion gas, it is further atomized conducive to tumble flow is formed, ensure that uniform high-efficiency
Burning.
In the present embodiment, the premixer 7 has compressed air inlet 91, and the fuel nozzle I 6 gos deep into premixer and spray
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, and also making compressed air enter premixer is to form turbulent flow
Formula impact, be conducive to further atomization and uniformly mixing, reach atomization and mixed dual purpose, thus for the later period direct-injection and
Preferable basic role is played in burning.
In the present embodiment, the oil spout direction of the fuel nozzle I 6 and the injection channel direction of oil-air mixing nozzle 8 are consistent,
Spacing between the jet 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, conducive to heavy oil
It is sufficiently atomized and enters oil-air mixing nozzle after evenly mixing, and guarantee 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.
It further include precombustion chamber 12 in the present embodiment, the precombustion chamber 12 is (to refer 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 pass through throat by Laval nozzle jet port spray (ratio
The higher speed of combustion explosion), further impacting to have to the fuel combination for entering combustion chamber 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
Machine power simultaneously reduces risk for knock, additionally it is possible to organize the burning of fuel-efficient, guarantee heavy oil the dynamic property for being applied to engine,
Economy and emission performance realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
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 top of combustion chamber middle position 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, and the burning gases that precombustion chamber sprays are more conducive to entirely firing
Burn the mixed Daqu disturbance and full combustion of room.
The invention also discloses a kind of aircraft, the aircraft is equipped with the Heavy End Aviation Fuel of the composite injection
Engine.
Finally, it is stated that above embodiments are merely intended for describing the technical solutions of the present application, but not for limiting the present application, although ginseng
The utility model is described in detail according to preferred embodiment, those skilled in the art should understand that, it can be to this
The technical solution of utility model is modified or replaced equivalently, without departing from the objective and model of technical solutions of the utility model
It encloses, should all cover in the scope of the claims of the utility model.
Claims (8)
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；
The in-cylinder direct-jet system is equipped with fuel oil ejection assemblies and sprays fuel, fuel oil into combustion chamber by fuel oil ejection assemblies
Ejection assemblies include fuel nozzle I, premixer and oil-air mixing nozzle, have in the premixer jet of fuel nozzle I with
And compressed air inlet, the atomization that oil-air mixing nozzle connection premixer forms fuel oil and compressed air in premixer
Mixed oil and gas afterwards is sent into the combustion chamber of engine；
The air intake duct electric injection system is equipped with fuel nozzle II and passes through after spraying fuel into air intake duct by fuel nozzle II
Inlet valve enters the combustion chamber of engine.
2. the Heavy End Aviation Fuel engine of composite injection according to claim 1, 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 and spark plug II are respectively in I two sides of spark plug；
The injection direction of the oil-air mixing nozzle is 16 ° -20 °；The igniting angle of spark plug II is 40 ° -50 °.
3. the Heavy End Aviation Fuel engine of composite injection according to claim 2, it is characterised in that: the spark plug I is located at
The middle position of top of combustion chamber or near；The center line and oil-air mixing nozzle of the center line of the spark plug I, spark plug II
Center line it is substantially coplanar, and this is coplanar spatially substantially vertical with plane where inlet and exhaust valve.
4. the Heavy End Aviation Fuel engine of composite injection according to claim 1, it is characterised in that: the fuel nozzle I is deep
Enter premixer and jet is more than compressed air inlet.
5. the Heavy End Aviation Fuel engine of composite injection according to claim 1, 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 jet and oil-air mixing nozzle of the fuel nozzle I
Spacing between entrance is 5-8mm.
6. the Heavy End Aviation Fuel engine of composite injection according to claim 1, it is characterised in that: it 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.
7. the Heavy End Aviation Fuel engine of composite injection according to claim 6, 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 middle position or near,
Precombustion chamber is set at spark plug I and I ignitor of the spark plug protrudes into precombustion chamber.
8. a kind of aircraft, it is characterised in that: the aircraft is equipped with the compound spray of claim 1 to 7 any claim
The Heavy End Aviation Fuel engine penetrated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820819589.1U CN208793086U (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 |
|---|---|---|---|
| CN201820819589.1U CN208793086U (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208793086U true CN208793086U (en) | 2019-04-26 |
Family
ID=66200525
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820819589.1U Expired - Fee Related CN208793086U (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
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| Country | Link |
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| CN (1) | CN208793086U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108468587A (en) * | 2018-05-29 | 2018-08-31 | 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 CN201820819589.1U patent/CN208793086U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108468587A (en) * | 2018-05-29 | 2018-08-31 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of composite injection |
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