CN208763800U - The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet - Google Patents
The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet Download PDFInfo
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- CN208763800U CN208763800U CN201820819586.8U CN201820819586U CN208763800U CN 208763800 U CN208763800 U CN 208763800U CN 201820819586 U CN201820819586 U CN 201820819586U CN 208763800 U CN208763800 U CN 208763800U
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- nozzle
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- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 239000000295 fuel oil Substances 0.000 claims abstract description 49
- 238000002485 combustion reaction Methods 0.000 claims abstract description 45
- 238000000889 atomisation Methods 0.000 claims abstract description 25
- 239000003921 oil Substances 0.000 claims abstract description 12
- 230000000712 assembly Effects 0.000 claims abstract description 8
- 238000000429 assembly Methods 0.000 claims abstract description 8
- 238000002347 injection Methods 0.000 claims description 24
- 239000007924 injection Substances 0.000 claims description 24
- 230000009977 dual effect Effects 0.000 claims description 11
- 239000007921 spray Substances 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 238000009434 installation Methods 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 11
- 230000000694 effects Effects 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 239000008246 gaseous mixture Substances 0.000 description 2
- 230000003116 impacting effect Effects 0.000 description 2
- 239000003595 mist Substances 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
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 239000002352 surface water Substances 0.000 description 1
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- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The utility model discloses the Heavy End Aviation Fuel engines and aircraft of a kind of in-cylinder direct-jet, including cylinder body, piston component, cylinder head, fuel oil ejection assemblies and compressed air system, fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, there are jet and the compressed air inlet of fuel nozzle in premixer, the oil-air mixing nozzle 8 is connected to the combustion chamber that the mixed oil and gas after the atomization that premixer forms fuel oil and compressed air in premixer is sent into engine；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 that heavy oil in dynamic property, economy and the emission performance for being applied to engine, realizes energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
Description
Technical field
The utility model relates to engine and application, in particular to the Heavy End Aviation Fuel engine of a kind of in-cylinder direct-jet 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, also allows for heavy oil application
It is unable to reach the effect of expectation in the dynamic property, economy and emission performance of engine, to make the application of heavy oil can not be a wide range of
It is universal.
Therefore, it is necessary to improve to existing heavy fuel burning engine, heavy oil is enabled to realize more adequately atomization, and
The burning of fuel-efficient can be organized, guarantees that heavy oil in dynamic property, economy and the emission performance for being applied to engine, realizes heavy oil
Applied to the energy-saving and environmental protection and low cost 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 in-cylinder direct-jet and aviations
Device enables to heavy oil to realize more adequately atomization, and can organize the burning of fuel-efficient, guarantees 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.
The Heavy End Aviation Fuel engine of the in-cylinder direct-jet of the utility model, including the injection of cylinder body, piston component, cylinder head, fuel oil
Component and compressed air system, the fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, the premix
There are jet and the compressed air inlet of fuel nozzle in interior, and the oil-air mixing nozzle is connected to premixer for fuel oil and compression
Mixed oil and gas after the atomization that air is formed in premixer is sent into the combustion chamber of engine；It is being premixed using auxiliary low pressure air
Indoor realization premix and the fuel oil that further atomizing fuel nozzle sprays, guarantee to be formed more more after later period direct-injection enters combustion chamber
Adequately atomization, to realize the full combustion and utilization of heavy oil；It not only ensure that the further atomization of fuel droplet, moreover it is possible to protect
Card auxiliary air and droplet between it is uniform mix, into combustion chamber after being capable of homogenous combustion；Fuel nozzle generally uses EFI
Mode, 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, the characteristic with high-energy ignition guarantees engine various in conjunction with air-assisted atomization above-mentioned and premix scheme
Operating condition igniting reliable and secure under the conditions of further decreases engine volume relative to traditional heavy oil compression ignition engine
And weight, it is suitable for aircraft use.
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 compressed air system includes compressor and constant-voltage equipment, the compressed air outlet of the compressor
It is connected to the premixer by constant-voltage equipment, guarantees the stability of pressure, to guarantee the stable operation of engine.
Further, the compressor is driven by crankshaft；It is directly driven by crankshaft, conducive to compressor according to the fortune of engine
Row situation provides compressed air, ensure that the automatic control of gas and oil mixed fuel；The driving method of crankshaft generally uses belt to pass
The common mechanical drive modes such as dynamic, chain conveyer；It further include the structure that crankshaft directly drives compressor by cam, herein no longer
It repeats.
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 spark plug I, spark plug II and oil-air mixing nozzle is substantially coplanar, and this it is coplanar with
Plane where inlet and exhaust valve is spatially substantially vertical, and co-planar arrangement refers to oil-air mixing nozzle, spark plug II and spark
The central axis of plug I is located on the same face, and the plane where inlet and exhaust valve refers to that the axis of inlet and 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 lesser inclination and dislocation have no effect on to we
The coplanar and vertical understanding of case；The structure ensure that the simple-arranged of all parts on cylinder head, while be conducive to air inlet and combustion gas
Be sufficiently mixed, be further atomized conducive to tumble flow is formed, ensure that the burning of uniform high-efficiency.
Further, the premixer has compressed air inlet, and the atomizer gos deep into premixer and jet is more than pressure
Contracting air intake；The structure not only facilitates the compact layout of all parts, also make compressed air enter premixer be to be formed it is disorderly
Streaming impact is conducive to further atomization and uniformly mixing, reaches atomization and mixed dual purpose, to be the direct-injection in later period
Preferable basic role is played with burning.
Further, the oil spout direction of the atomizer and the injection channel direction of oil-air mixing nozzle are consistent, the oil spout
Spacing between the jet and oil-air mixing nozzle entrance of mouth is 5-8mm, ensure that mounting structure neatly compactly, and guarantee
The efficient injection of fuel oil is conducive to air and forms impact and turbulent flow；Suitable spacing range, conducive to heavy oil it is abundant atomization and it is equal
Enter oil-air mixing nozzle after even 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 in-cylinder direct-jet
Engine.
The utility model has the beneficial effects that the Heavy End Aviation Fuel engine and aircraft of the in-cylinder direct-jet of the utility model, hair
The structure that motivation is atomized and is premixed using auxiliary air enables to heavy oil to realize more adequately atomization, good mixed
Uniform combustion mixture is formed after conjunction, additionally it is possible to organize the burning of fuel-efficient, guarantee that heavy oil is being applied to the dynamic of engine
Power, economy and emission performance 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 cross-sectional view of the utility model；
Fig. 2 is fuel oil ejection assemblies structural schematic diagram；
Fig. 3 is the external engine structural schematic diagram of the utility model.
Specific embodiment
It is as shown in the figure: the Heavy End Aviation Fuel engine of the in-cylinder direct-jet of the present embodiment, including cylinder body 1, piston component 5, cylinder head
2, fuel oil ejection assemblies a and compressed air system, the fuel oil ejection assemblies include fuel nozzle 6, premixer 7 and air-fuel mixture
Nozzle 8 has the jet and compressed air inlet (the namely pressure of air compression system of fuel nozzle 6 in the premixer 7
Contracting air outlet slit), the oil-air mixing nozzle 8 is connected to the atomization that premixer 7 forms fuel oil and compressed air in premixer
Mixed oil and gas afterwards is sent into the combustion chamber of engine；It is realized in premixer using auxiliary low pressure air and premixes and be further atomized
The fuel oil that fuel nozzle sprays guarantees that later period direct-injection enters behind combustion chamber to be formed and is more more fully atomized, to realize heavy oil
Full combustion and utilization；This premix atomization is different from the impact atomization of the simple pressure air of the prior art, not only protects
Demonstrate,proved the further atomization of fuel droplet, moreover it is possible to guarantee between auxiliary air and droplet it is uniform mix, into combustion chamber after energy
Enough homogenous combustions；Fuel nozzle generally uses EFI mode, and details are not described herein.
As shown, fuel oil ejection assemblies are successively tightly connected shape by fuel nozzle 6, premixer 7 and oil-air mixing nozzle 8
At, it is tightly connected to be formed by mounting base 10 between fuel nozzle 6 and oil-air mixing nozzle 8 and fix, and premixer is directly formed
It is simple and compact for structure in mounting base 10；Fuel nozzle is equipped with fuel inlet fitting 61, and premixer 7 is empty by pneumatic fitting 9, compression
The compressed air outlet of 16 connect compressor of tracheae；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 compressed air system includes compressor 14 and constant-voltage equipment, the compression of the compressor 14
Air outlet slit is connected to the premixer 7 by constant-voltage equipment, guarantees the stability of pressure, to guarantee that stablizing for engine is transported
Row；As shown, the gas outlet of compressor 14 is provided with constant-voltage equipment i.e. pressure-regulating valve 15, connected by compressed air hose 16
Premixer 7.
In the present embodiment, the compressor is driven by crankshaft；It is directly driven by crankshaft, is conducive to compressor according to engine
Operation conditions provide compressed air, ensure that the automatic control of gas and oil mixed fuel；The driving method of crankshaft generally uses skin
The common mechanical drive mode such as V belt translation, chain conveyer, the present embodiment use driving pulley 12, the belt being directly connected to crankshaft
11 and driven pulley 13 form belt drive structure；It in actual use further include the knot that crankshaft directly drives compressor by cam
Structure, details are not described herein.
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, the center line of the spark plug I 3, spark plug II 4 and oil-air mixing nozzle 8 is substantially coplanar, and should
Plane where the coplanar door with inlet and outlet is spatially substantially vertical, and co-planar arrangement refers to oil-air mixing nozzle 8, spark plug
II 4 and the central axis of spark plug I 3 be located on the same face, the plane where inlet and exhaust valve refers to the axis position of inlet and exhaust valve
In same plane, it is substantially coplanar and it is substantially vertical refer to allow to have certain error, such as lesser inclination and dislocation, not
Influence understanding coplanar to this programme and vertical；The structure ensure that the simple-arranged of all parts on cylinder head, be conducive to simultaneously
Being sufficiently mixed for air inlet and combustion gas, is further atomized conducive to tumble flow is formed, ensure that the burning of uniform high-efficiency.
In the present embodiment, the premixer 7 has compressed air inlet 91, and the atomizer 6 gos deep into premixer and oil spout
Mouth is more than compressed air inlet 91；As shown, the center line of the compressed air inlet 91 and with the jet of atomizer 6
Centerline substantially vertical (it is of course also possible to appropriate tilting, vertically further facilitate layout and is conducive to mist in same plane
Change), which not only facilitates the compact layout of all parts, and also making compressed air enter premixer is to form turbulent flow type punching
It hits, is conducive to further atomization and uniformly mixing, reaches atomization and mixed dual purpose, to be the direct-injection and burning in later period
Play preferable basic role.
In the present embodiment, the oil spout direction of the atomizer 6 and the injection channel direction of oil-air mixing nozzle 8 are consistent, institute
The spacing stated between the jet of atomizer and oil-air mixing nozzle entrance 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 guarantee injection pressure, ensure that mounting structure neatly compactly, and guarantee
The efficient injection of fuel oil is conducive to air and forms impact and turbulent flow.
It further include precombustion chamber 17 in the present embodiment, the precombustion chamber 17 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 3 and spark plug II 4, and the spark plug are installed on cylinder head
I 4 be located at top of combustion chamber middle position or near, precombustion chamber is set at spark plug I 4 and I 4 ignition power of the spark plug
Precombustion chamber is protruded into pole；Main spark plug is in the middle part of combustion chamber or nearby, the burning gases that precombustion chamber sprays are more conducively to whole
The mixed Daqu of a combustion chamber disturbs and full combustion.
The invention also discloses a kind of aircraft, the aircraft is equipped with the Heavy End Aviation Fuel of the in-cylinder direct-jet
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 in-cylinder direct-jet, it is characterised in that: including cylinder body, piston component, cylinder head, fuel oil injection
Component and compressed air system, the fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, the premix
There are jet and the compressed air inlet of fuel nozzle in interior, and the oil-air mixing nozzle is connected to premixer for fuel oil and compression
Mixed oil and gas after the atomization that air is formed in premixer is sent into the combustion chamber of engine；Installation is by spark plug on the cylinder head
I and spark plug II formed dual ignition plug；The compressed air system includes compressor and constant-voltage equipment, the pressure of the compressor
Contracting air outlet slit is connected to the premixer by constant-voltage equipment；The compressor is driven by crankshaft.
2. the Heavy End Aviation Fuel engine of in-cylinder direct-jet according to claim 1, it is characterised in that: the oil-air mixing nozzle
I two sides of spark plug are respectively in spark plug II；The injection direction of the oil-air mixing nozzle is 16 ° -20 °；The point of spark plug II
Fiery angle is 40 ° -50 °.
3. the Heavy End Aviation Fuel engine of in-cylinder direct-jet 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 of the spark plug I, spark plug II and oil-air mixing nozzle is substantially total
Face, and this is coplanar spatially substantially vertical with plane where inlet and exhaust valve.
4. the Heavy End Aviation Fuel engine of in-cylinder direct-jet according to claim 1, it is characterised in that: the fuel nozzle gos deep into
Premixer and jet are more than compressed air inlet.
5. the Heavy End Aviation Fuel engine of in-cylinder direct-jet according to claim 2, it is characterised in that: the spray of the fuel nozzle
Oily direction is consistent with the injection channel direction of oil-air mixing nozzle, the jet and oil-air mixing nozzle entrance of the fuel nozzle
Between spacing be 5-8mm.
6. the Heavy End Aviation Fuel engine of in-cylinder direct-jet 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 combustion chamber.
7. the Heavy End Aviation Fuel engine of in-cylinder direct-jet according to claim 6, it is characterised in that: and I, the spark plug
In 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 in the cylinder of claim 1 to 7 any claim directly
The Heavy End Aviation Fuel engine of spray.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820819586.8U CN208763800U (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820819586.8U CN208763800U (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208763800U true CN208763800U (en) | 2019-04-19 |
Family
ID=66126394
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820819586.8U Expired - Fee Related CN208763800U (en) | 2018-05-29 | 2018-05-29 | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet |
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| CN (1) | CN208763800U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488018A (en) * | 2018-05-29 | 2018-09-04 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet |
| 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 |
-
2018
- 2018-05-29 CN CN201820819586.8U patent/CN208763800U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108488018A (en) * | 2018-05-29 | 2018-09-04 | 重庆隆鑫发动机有限公司 | The Heavy End Aviation Fuel engine and aircraft of in-cylinder direct-jet |
| 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 |
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Granted publication date: 20190419 |