CN208763745U - Heavy End Aviation Fuel engine cylinder head assembly and aero-engine - Google Patents
Heavy End Aviation Fuel engine cylinder head assembly and aero-engine Download PDFInfo
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- CN208763745U CN208763745U CN201820819537.4U CN201820819537U CN208763745U CN 208763745 U CN208763745 U CN 208763745U CN 201820819537 U CN201820819537 U CN 201820819537U CN 208763745 U CN208763745 U CN 208763745U
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- oil
- cylinder head
- fuel
- spark plug
- nozzle
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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
Abstract
The utility model discloses a kind of Heavy End Aviation Fuel engine cylinder head assembly and aero-engines, including cylinder head and the spark plug being mounted on cylinder head and fuel oil ejection assemblies, fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, the jet of fuel nozzle and the compressed air outlet of compressed air system are respectively positioned on premixer, the mixed oil and gas that the oil-air mixing nozzle connection premixer forms fuel oil and air in premixer is sent into the combustion chamber of engine, the fuel injection configuration for being atomized and being premixed using auxiliary air is installed on the utility model engine cylinder head, 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 that heavy oil is applied to Energy-saving and environmental protection and low cost after engine.
Description
Technical field
The utility model relates to engine and application, in particular to a kind of Heavy End Aviation Fuel engine cylinder head assembly and aviation hair
Motivation.
Background technique
Fuel of the heavy oil as engine will become the power trend of small and medium size unmanned aerial vehicles；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 cylinder head assembly and engine,
It enables to heavy oil to realize more adequately atomization, and the burning of fuel-efficient can be organized, guarantee that heavy oil is being applied to start
Dynamic property, economy and the emission performance of machine realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
The Heavy End Aviation Fuel engine cylinder head assembly of the utility model, including the spray of cylinder body, piston component, cylinder head, crankshaft, fuel oil
Penetrate component and compressed air system, the fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, described pre-
There are the jet and compressed air inlet (the namely compressed air outlet of air compression system) of fuel nozzle, institute in mixed interior
Mixed oil and gas after stating the atomization that oil-air mixing nozzle connection premixer forms fuel oil and compressed air in premixer is sent into
The combustion chamber of engine；Premix and the combustion that further atomizing fuel nozzle 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 generally uses EFI mode, and 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 unmanned plane 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 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 outlet door 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 fuel nozzle gos deep into premixer and jet is more than
Compressed air inlet；The structure not only facilitates the compact layout of all parts, and also making compressed air enter premixer is to be formed
Turbulent flow type impact reaches atomization and mixed dual purpose conducive to further atomization and uniformly mixing, to be the straight of later period
Preferable basic role is played in spray and burning.
Further, the oil spout direction of the fuel nozzle 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 is 5-8mm, ensure that mounting structure neatly compactly, and
It ensure that the efficient injection of fuel oil, be conducive to air and form impact and turbulent flow；Suitable spacing range, conducive to the abundant atomization of heavy oil
And enter oil-air mixing nozzle after evenly mixing, and guarantee injection pressure.
Further, precombustion chamber is also machined on the cylinder head, the precombustion chamber is along plug ignition direction
The jet port of Laval nozzle structure, the Laval nozzle structure is connected to combustion chamber；The precombustion chamber course of work is to mix
After fuel is injected into combustion chamber, while entering precombustion chamber, (ignition point is located at the inlet end of Laval nozzle, should by spark plug
Inlet end is the mouth for Laval nozzle, rather than with combustion chamber) igniting after, expand simultaneously by Lavalle spray
Pipe rapidly sprays (speed more higher than combustion explosion), and further impacting to have to the fuel combination for entering combustion chamber fills gas
Divide mixed effect, conducive to uniform combustion mixture is formed, meanwhile, precombustion chamber can accelerate flame transmission, improve burning
Efficiency promotes engine power and reduces risk for knock, 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.
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 aero-engine, the aero-engine is equipped with the Heavy End Aviation Fuel hair
Motivation cylinder head assembly.
The utility model has the beneficial effects that the Heavy End Aviation Fuel engine cylinder head assembly and aero-engine of the utility model,
The fuel injection configuration for being atomized and being premixed using auxiliary air is installed on engine cylinder head, heavy oil is enabled to realize more
Adequately atomization, forms uniform combustion mixture after good mixing, additionally it is possible to organize the burning of fuel-efficient, guarantee weight
Oil be applied to engine dynamic property, economy and emission performance, realize heavy oil be applied to engine after energy-saving and environmental protection and
Low cost.
Detailed description of the invention
The utility model is further described with reference to the accompanying drawings and examples.
Fig. 1 is that the cylinder head assembly of the utility model is installed on engine structure schematic diagram；
Fig. 2 is fuel oil ejection assemblies structural schematic diagram.
Specific embodiment
As shown in the figure: the Heavy End Aviation Fuel engine cylinder head assembly of the present embodiment including cylinder head 2 and is mounted on cylinder head 2
Spark plug and fuel oil ejection assemblies, the fuel oil ejection assemblies include fuel nozzle 6, premixer 7 and oil-air mixing nozzle 8, institute
Stating the jet for having fuel nozzle 6 in premixer 7 and compressed air inlet, (compressed air of namely air compression system goes out
Mouthful), the oil-air mixing nozzle 8 is connected to the mixing after the atomization that premixer 7 forms fuel oil and compressed air in premixer
The combustion chamber of oil gas feeding engine；Premix and further atomizing fuel nozzle are realized in premixer using auxiliary low pressure air
The fuel oil of ejection guarantees that later period direct-injection enters behind combustion chamber to be formed and is more more fully atomized, to realize the abundant combustion of heavy oil
It burns and utilizes；This premix atomization is different from the impact atomization of the simple pressure air of the prior art, not only ensure that fuel oil
The further atomization of droplet, moreover it is possible to guarantee between auxiliary air and droplet it is uniform mix, into combustion chamber after can uniformly fire
It burns；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 used by pneumatic fitting 9
When, pneumatic fitting 9 is connected to the compressed air outlet of compressor by compressed air hose；The air inlet 91 of premixer is air
The gas outlet of connector 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 unmanned plane 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, 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 fuel nozzle 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 jet with atomizer 6
Centerline in same plane, and substantially vertical (it is of course also possible to appropriate tilting, vertically further facilitate layout and be 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 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 fuel nozzle 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 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.
In the present embodiment, precombustion chamber 17 is also machined on the cylinder head, the precombustion chamber 17 is along spark plug point
The Laval nozzle structure of fiery direction (referring to spark plug axis direction) is formed, and the jet port of the Laval nozzle structure connects
Logical combustion chamber；The precombustion chamber course of work is, after fuel combination is injected into combustion chamber, while entering precombustion chamber, by spark
(ignition point is located at the inlet end of Laval nozzle to plug, which is rather than the and combustion chamber for Laval nozzle
The mouth of connection) igniting after, expand simultaneously by Laval nozzle rapidly pass through throat by Laval nozzle jet port spray (than fire
Decrepitate fries higher speed), further impacting to have to the fuel combination for entering combustion chamber makes the well-mixed effect of gas, benefit
In the uniform combustion mixture of formation, meanwhile, precombustion chamber can accelerate flame transmission, improve efficiency of combustion, promote engine
Power simultaneously reduces risk for knock, additionally it is possible to organize the burning of fuel-efficient, guarantee heavy oil in the dynamic property applied to engine, warp
Ji property and emission performance realize energy-saving and environmental protection and low cost that heavy oil is applied to after engine.
In the present embodiment, precombustion chamber is set at spark plug I and I ignitor of the spark plug protrudes into precombustion chamber；
Main spark plug is in the middle part of combustion chamber or nearby, gaseous mixture of the burning gases that precombustion chamber sprays more conducively to entire combustion chamber
Form disturbance and full combustion.
The invention also discloses a kind of aero-engine, the aero-engine is equipped with the Heavy End Aviation Fuel hair
Motivation cylinder head assembly, as shown, further include cylinder body 1 and piston component 5, and the engine be suitable for aircraft (someone or
It is unmanned).
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 (9)
1. a kind of Heavy End Aviation Fuel engine cylinder head assembly, it is characterised in that: including cylinder head and the spark plug being mounted on cylinder head and
Fuel oil ejection assemblies, the fuel oil ejection assemblies include fuel nozzle, premixer and oil-air mixing nozzle, are had in the premixer
The jet of fuel nozzle and compressed air inlet, oil-air mixing nozzle connection premixer exist fuel oil and compressed air
Mixed oil and gas after the atomization formed in premixer is sent into the combustion chamber of engine.
2. Heavy End Aviation Fuel engine cylinder head assembly according to claim 1, it is characterised in that: installation is by fire on the cylinder head
The dual ignition plug that flower plug I and spark plug II are formed.
3. Heavy End Aviation Fuel engine cylinder head assembly according to claim 2, it is characterised in that: the oil-air mixing nozzle with
Spark plug II is respectively in I two sides of spark plug；The injection direction of the oil-air mixing nozzle is 16 ° -20 °；The igniting of spark plug II
Angle is 40 ° -50 °.
4. Heavy End Aviation Fuel engine cylinder head assembly according to claim 1, it is characterised in that: the spark plug I is located at combustion
Burn ceiling portion middle position or near；The center line of the spark plug I, spark plug II and oil-air mixing nozzle is substantially coplanar,
And the plane where the coplanar door with inlet and outlet is spatially substantially vertical.
5. Heavy End Aviation Fuel engine cylinder head assembly according to claim 1, it is characterised in that: the fuel nozzle gos deep into pre-
Mixed room and jet are more than compressed air inlet.
6. Heavy End Aviation Fuel engine cylinder head assembly according to claim 1, it is characterised in that: the oil spout of the fuel nozzle
Direction is consistent with the injection channel direction of oil-air mixing nozzle, the jet of the fuel nozzle and oil-air mixing nozzle entrance it
Between spacing be 5-8mm.
7. Heavy End Aviation Fuel engine cylinder head assembly according to claim 1, it is characterised in that: be also machined on the cylinder head
Precombustion chamber, the precombustion chamber are the Laval nozzle structure along plug ignition direction, the Laval nozzle structure
Jet port be connected to combustion chamber.
8. Heavy End Aviation Fuel engine cylinder head assembly according to claim 7, it is characterised in that: installation is by fire on the cylinder head
Flower plug I and spark plug II formed dual ignition plug, and the spark plug I be located at top of combustion chamber middle position or near, in advance
Combustion chamber is set at spark plug I and I ignitor of the spark plug protrudes into precombustion chamber.
9. a kind of aero-engine, it is characterised in that: the engine is equipped with the boat of claim 1 to 8 any claim
Bare weight oil turbine cylinder head assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820819537.4U CN208763745U (en) | 2018-05-29 | 2018-05-29 | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820819537.4U CN208763745U (en) | 2018-05-29 | 2018-05-29 | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208763745U true CN208763745U (en) | 2019-04-19 |
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ID=66126388
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820819537.4U Active CN208763745U (en) | 2018-05-29 | 2018-05-29 | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine |
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| CN (1) | CN208763745U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108468588A (en) * | 2018-05-29 | 2018-08-31 | 重庆隆鑫发动机有限公司 | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine |
-
2018
- 2018-05-29 CN CN201820819537.4U patent/CN208763745U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108468588A (en) * | 2018-05-29 | 2018-08-31 | 重庆隆鑫发动机有限公司 | Heavy End Aviation Fuel engine cylinder head assembly and aero-engine |
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