CN107091152B - A kind of twin cylinder bimodal aviation piston engine - Google Patents
A kind of twin cylinder bimodal aviation piston engine Download PDFInfo
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- CN107091152B CN107091152B CN201710332206.8A CN201710332206A CN107091152B CN 107091152 B CN107091152 B CN 107091152B CN 201710332206 A CN201710332206 A CN 201710332206A CN 107091152 B CN107091152 B CN 107091152B
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- piston
- operating room
- cylinder
- engine
- stroke
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Classifications
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- 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
- F02B75/00—Other engines
- F02B75/12—Other methods of operation
-
- 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
- F02B75/00—Other engines
- F02B75/16—Engines characterised by number of cylinders, e.g. single-cylinder engines
- F02B75/18—Multi-cylinder engines
-
- 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
- F02B75/00—Other engines
- F02B75/16—Engines characterised by number of cylinders, e.g. single-cylinder engines
- F02B75/18—Multi-cylinder engines
- F02B2075/1804—Number of cylinders
- F02B2075/1808—Number of cylinders two
Abstract
The present invention discloses a kind of twin cylinder bimodal aviation piston engine, has two cylinders being symmetrical set；By the crankshaft output power of engine, a piston rod is driven to drive the movement of two pistons simultaneously by connecting rod；Two cylinder upper and lower ends are equipped with valve mechanism, fuel system and ignition system.Above-mentioned each cylinder has double work room, realize in double work room there is one or two gas supply acting by control valve mechanism, therefore there are two types of operation modes for engine tool: high power work mode and small-power operation mode, and under two kinds of operation modes, engine all has higher fuel efficiency.
Description
Technical field
The invention belongs to engine arts, are related to a kind of aviation piston engine for having twin cylinder double work mode.
Background technique
In recent years, vertically taking off and landing flyer is all widely used in military domain and civil field.It is solid with tradition
Determine wing aircraft to compare, vertically taking off and landing flyer is not limited by landing condition, has the advantage that can be hovered；With conventional helicopters phase
Than vertically taking off and landing flyer horizontal flight speed is faster.And the increase of vertically taking off and landing flyer use demand flies VTOL
More stringent requirements are proposed for row device: on the basis of meeting VTOL and high speed is flat winged, aircraft can realize long endurance flight.
Aero-engine is known as the heart of aircraft, and for vertically taking off and landing flyer, engine is to determine flight
The key factor of device takeoff and landing performance and cruising ability.In addition to fighter plane, most vertically taking off and landing flyer are under cruising condition
With subsonic flight, therefore vertically taking off and landing flyer is also mostly using piston-mode motor as power device.Therefore in order to realize
The long endurance of vertically taking off and landing flyer is flown, and needs a to be capable of providing sufficient power, and the piston engine that fuel efficiency is high
Machine.
Vertically taking off and landing flyer is also different to the power requirement of engine under different flight state.In VTOL and
In the case of hovering, aircraft thrust ratio meets or exceeds 1, this also requires engine to be capable of providing more than aircraft self weight
Thrust.In horizontal flight, the lift of aircraft is mainly provided by wing, therefore engine is only needed to provide to overcome resistance
Thrust.Since the lift resistance ratio of aircraft is larger, under the flat winged two states of VTOL and high speed, engine is needed to mention
The watt level very different of confession.
Existing vertically taking off and landing flyer mostly uses high-power aviation piston engine, can meet VTOL flight power and want
It asks, but under flat winged state, engine is in low power state, and fuel efficiency is lower, it is difficult to realize long endurance flight.Piston hair
Motivation is difficult to export widely different power under the premise of high fuel efficiency.Therefore difference is completed using same engine
When the task of power or power is too low is unable to satisfy high power mission requirements or in a low-power state, engine fuel
Efficiency is very low.
Summary of the invention
In view of the above-mentioned problems, the present invention proposes a kind of twin cylinder bimodal aviation piston engine, same can be used
Engine high-efficiency completes different power tasks, is suitable for the specific demands such as vertically taking off and landing flyer.
Twin cylinder bimodal aviation piston engine of the present invention, has two cylinders being symmetrical set, above and below cylinder
Both ends are equipped with valve mechanism, fuel system and ignition system.Above-mentioned two piston two sides are available for gas acting, are sending out
When motivation works, two cylinders synchronous working is pushed by the upper operating room of two cylinders and the indoor fuel combustion acting of lower work
Piston up-down, two pistons in left and right are moved up and down in the case where being driven by knuckle-joint band piston bar, and piston rod is by power
Crankshaft is passed to, band dynamic crankshaft makes rotating motion, to realize the output of engine power.With conventional pistonic engine phase
Than, the every rotation of crankshaft takes two turns and has expansion work stroke twice, so that engine pushes the power of crankshaft rotation more uniform, engine
Work it is also more stable.
Realize in double work room there is one or two gas supply acting by control valve mechanism, therefore engine has two
Kind operation mode: high power work mode and small-power operation mode, and under two kinds of operation modes, engine all has higher
Fuel efficiency.
The present invention has the advantages that
1, twin cylinder bimodal aviation piston engine of the present invention has bimodal, and same engine can provide two kinds of height
The high or low power mode of efficiency, applicability is wide, can save fuel oil.
2, twin cylinder bimodal aviation piston engine of the present invention uses twin cylinder, and each piston two sides are available for gas
Acting, compared with conventional pistonic engine, the every rotation of crankshaft takes two turns and has expansion work stroke twice, so that engine pushes song
The power of axis rotation is more uniform, and the work of engine is also more stable.
3, under Same Efficieney of the present invention, piston two sides are available for gas acting, and engine can design simpler compact,
Reduce engine weight and is taken up space.
Detailed description of the invention
Fig. 1 is twin cylinder bimodal aviation piston engine overall structure diagram of the present invention；
Fig. 2 is structural representation of air cylinder in twin cylinder bimodal aviation piston engine of the present invention；
Fig. 3 is aviation piston engine high power work Modality work flow diagram of the present invention；
Fig. 4 is aviation piston engine small-power operation mode workflow schematic diagram of the present invention；
In figure:
1- cylinder 2- piston rod 3- connecting rod
4- valve mechanism 5- fuel system 6- ignition system
7- crankshaft 8- open slot 101- cylinder body
Operating room under operating room 104- on 102- piston 103-
Admission gear under exhaust gear 403- on 401- upper air mechanism 402-
Ventilating mechanism under exhaust gear 405- under 404-
Specific embodiment
The present invention is described in further details with reference to the accompanying drawing.
Twin cylinder bimodal aviation piston engine of the present invention, has two cylinders 1 being symmetrical set, piston rod 2,
Connecting rod 3, valve mechanism 4, fuel system 5 and ignition system 6, as shown in Figure 1.
The cylinder 1 includes cylinder body 101 and piston 102, as shown in Figure 2.Wherein, cylinder body 101 is by symmetrical above and below two
It is grouped as；Two-part end is equipped with valve mechanism 4, fuel system 5 and ignition system 6.Valve mechanism 4 and fuel system
5 cooperate, and are specifically used to be responsible for input fuel and air into engine and exhaust gas is discharged；Ignition system 6 is used to according to gas
The job order of cylinder periodically generates the electric spark of enough energy between two electrode of spark plug.Along cylinder in the middle part of the outer wall of cylinder body 101
101 axial design of body has stripe shape open slot 8.Piston 102 is coaxially installed on inside cylinder body 101, the cylinder body of about 102 two sides of piston
101 inside are used as upper operating room 103 and lower operating room 104, can supply acting；The operating room Ze Shang 103 and lower operating room 104
All have valve mechanism 4, fuel system 7 and ignition system 6；And the valve mechanism 4 in upper operating room 103 includes enterprising mechanism of qi
Structure 401 and upper exhaust gear 402；Valve mechanism 4 in lower operating room 104 includes lower admission gear 403, lower exhaust gear 404
With lower ventilating mechanism 405.Wherein, upper air mechanism 401 and lower admission gear 403 are respectively intended to control operating room 103 under
The input of fuel and air in operating room 104；Upper exhaust gear 402 is respectively intended to control work with lower exhaust gear 404
The exclusion of exhaust gas in room 103 and lower operating room 104；Lower ventilating mechanism 405 is used to control whether lower operating room participates in doing work.
Piston rod 2 is located at outside cylinder body 101, and is arranged perpendicular to 101 axis of cylinder body, and 2 both ends of piston rod are separately installed with
Hinge passes through the open slot 8 on two cylinders 1 by hinge, hinged with 101 internal piston 102 of cylinder body.Connecting rod 3 and cylinder body 101
Axis is arranged in parallel, and one end is articulated with 2 middle part of piston rod, and the other end is articulated with the crankshaft 7 of output power in engine.Above-mentioned work
Sealing device is housed on plug 102, realizes the sealing between piston 102 and cylinder body 101, and when piston 102 moves, sealing device
Position will not reach 8 position of open slot, and then realize the sealing of 101 internal work environment of cylinder body.Thus when the engine is working,
Two cylinders 1 synchronous working pushes piston by the fuel combustion acting in the upper operating room 103 and lower operating room 104 of two cylinders 1
102 move up and down, and two pistons 102 in left and right are moved up and down in the case where being driven by knuckle-joint band piston bar 2, and piston rod 2 will
Power passes to crankshaft 7, and band dynamic crankshaft 7 makes rotating motion, to realize the output of engine power.
The twin cylinder bimodal aviation piston engine of above structure has two kinds of operation modes of high or low power:
1) when engine is in high power work mode, as shown in Figure 3a, the lower ventilating mechanism 405 of two cylinders 1 is closed
It closes；At this point, upper operating room 103 is in working condition with lower operating room 104.It is enterprising when upper operating room 103 is in compression stroke
Device of air and upper exhaust apparatus are closed, and lower operating room 104 is in induction stroke, and lower inlet duct is opened, and lower exhaust apparatus closes
It closes.As shown in Figure 3b, when 102 row of piston to top dead centre, the upper compression of operating room 103 terminates, and starts work by combustion, into expansion
Stroke, enterprising device of air and upper exhaust apparatus are closed, and then air inlet terminates for lower operating room 104, into compression stroke, lower air inlet dress
It sets and lower exhaust apparatus is closed.As shown in Figure 3c when 102 row of piston to lower dead center, upper 103 work by combustion of operating room terminates,
Into exhaust stroke, enterprising device of air closure, upper exhaust apparatus is opened, and lower operating room 104, which then compresses, to be terminated, and is started burning and is done
Function, into expansion stroke, lower inlet duct and lower exhaust apparatus are closed.As shown in Figure 3d, when 102 uplink of piston, upper work
Making the exhaust of room 103 terminates, and into suction stroke, enterprising device of air is opened, and upper exhaust apparatus closure, lower operating room 104 then burns
Acting terminates, and into instroke, lower inlet duct closure, lower exhaust apparatus is opened.Engine is repeated according to this circulation.
2) when engine is in small-power operation mode, as shown in fig. 4 a, the lower ventilating mechanism 405 of two cylinders 1, under
Exhaust gear 404 and lower admission gear 403 open, and lower operating room 104 is connected to outside air, are not involved in compression and do
Function, the fuel system 5 and ignition system 6 of lower operating room 104 are closed.Each 1 operating room Nei Jinshang 103 of cylinder is according to " air inlet is rushed
The circulation of journey-compression stroke-expansion stroke-exhaust stroke " works.When upper operating room 103 is in compression stroke, upper air
Device and upper exhaust apparatus are closed；As shown in Figure 4 b when 102 row of piston to top dead centre, the upper compression of operating room 103 terminates, and opens
Beginning work by combustion, into expansion stroke, enterprising device of air and upper exhaust apparatus are closed；As illustrated in fig. 4 c, when 102 row of piston extremely
When lower dead center, upper 103 work by combustion of operating room terminates, and into exhaust stroke, enterprising device of air closure, upper exhaust apparatus is opened；
As shown in figure 4d, when 102 uplink of piston, the upper exhaust of operating room 103 terminates, and into suction stroke, enterprising device of air is opened, on
Exhaust apparatus closure.Engine is repeated according to this circulation.
Whether opening while by controlling lower ventilating mechanism 405, lower exhaust gear 404 and lower admission gear 403, come
Whether controlling the work of lower operating room 104, engine can be made to have high or low power both modalities which.Lower ventilating mechanism 405,
After lower exhaust gear 404 and lower admission gear 403 open simultaneously, engine is in small-power state, only upper ventilating mechanism, on
Exhaust gear 402 participates in engine operation according to the description of above-mentioned small-power state；In lower ventilating mechanism 405, lower exhaust gear
404 and lower admission gear 403 when not opening simultaneously, upper exhaust gear 402 is with lower exhaust gear 404 according to above-mentioned high-power
The description of state participates in engine operation.Under two kinds of operation modes, optimal ginseng is can be used in the parameters such as distributive value of engine
Number under the premise of guaranteeing firm power output, can subtract so that engine under both modalities which, all has higher fuel efficiency
The use of small fuel oil.
Claims (4)
1. a kind of twin cylinder bimodal aviation piston engine, it is characterised in that: have two cylinders being symmetrical set；Two
A cylinder upper and lower ends are equipped with valve mechanism, fuel system and ignition system；Two cylinders synchronous working, by living in two cylinders
It fills in the indoor fuel combustion acting of two sides work and pushes piston up-down, two pistons in left and right are in the case where being driven, common band
A piston rod movement is moved, power is passed into crankshaft by connecting rod by piston rod, band dynamic crankshaft makes rotating motion, and realization is started
The output of machine power；
The cylinder interior of cylinder is enabled, piston upper space is upper operating room, and piston lower space is lower operating room, then:
1) when engine is in high power work mode, the lower ventilating mechanism closure of two cylinders；At this point, upper operating room is under
Operating room is in working condition；When upper operating room is in compression stroke, enterprising device of air and upper exhaust apparatus are closed, lower work
Make room and be in induction stroke, lower inlet duct is opened, lower exhaust apparatus closure；When piston row to top dead centre, upper work chamber pressure
Sheepshank beam starts work by combustion, and into expansion stroke, enterprising device of air and upper exhaust apparatus are closed, lower operating room's then air inlet
Terminate, into compression stroke, lower inlet duct and lower exhaust apparatus are closed；When piston row to lower dead center, upper operating room's combustion
Burning acting terminates, and into exhaust stroke, enterprising device of air closure, upper exhaust apparatus is opened, and lower operating room, which then compresses, to be terminated, and is started
Work by combustion, into expansion stroke, lower inlet duct and lower exhaust apparatus are closed；When piston stroking upward, upper operating room's exhaust
Terminate, into suction stroke, enterprising device of air is opened, and upper exhaust apparatus closure, then work by combustion terminates for lower operating room, into row
Gas stroke, lower inlet duct closure, lower exhaust apparatus are opened；
2) when engine is in small-power operation mode, lower ventilating mechanism, lower exhaust gear and the lower air inlet of two cylinders
Mechanism is opened, and lower operating room is connected to outside air, is not involved in compression and acting, the fuel system of lower operating room and igniting system
System is closed；The operating room each cylinder Nei Jinshang according to " induction stroke-compression stroke-expansion stroke-exhaust stroke " circulation into
Row work；When upper operating room is in compression stroke, enterprising device of air and upper exhaust apparatus are closed；When piston row to top dead centre
When, upper operating room's compression terminates, and starts work by combustion, into expansion stroke, enterprising device of air and upper exhaust apparatus are closed；When
When piston row to lower dead center, upper operating room's work by combustion terminates, into exhaust stroke, enterprising device of air closure, and upper exhaust apparatus
It opens；When piston stroking upward, upper operating room's exhaust terminates, and into suction stroke, enterprising device of air is opened, and upper exhaust apparatus closes
It closes.
2. a kind of twin cylinder bimodal aviation piston engine as described in claim 1, it is characterised in that: the cylinder body of two cylinders
On, design has open slot along the axial cylinder；Piston rod is located at outside cylinder body, and both ends pass through hinge across open slot and piston respectively
Between it is hinged.
3. a kind of twin cylinder bimodal aviation piston engine as described in claim 1, it is characterised in that: the valve of cylinder upper end
Mechanism includes upper air mechanism and upper exhaust gear；The valve mechanism of cylinder lower end include lower admission gear, lower exhaust gear with
Lower ventilating mechanism.
4. a kind of twin cylinder bimodal aviation piston engine as described in claim 1, it is characterised in that: equipped with sealing on piston
Device realizes the sealing between piston and cylinder body, and in piston motion, the position of sealing device will not reach open slot position,
Realize the sealing of cylinder interior working environment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710332206.8A CN107091152B (en) | 2017-05-12 | 2017-05-12 | A kind of twin cylinder bimodal aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710332206.8A CN107091152B (en) | 2017-05-12 | 2017-05-12 | A kind of twin cylinder bimodal aviation piston engine |
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| CN107091152A CN107091152A (en) | 2017-08-25 |
| CN107091152B true CN107091152B (en) | 2019-05-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710332206.8A Active CN107091152B (en) | 2017-05-12 | 2017-05-12 | A kind of twin cylinder bimodal aviation piston engine |
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Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2746203A1 (en) * | 1977-10-14 | 1979-04-19 | Bernhard Karl Dipl Ing | Opposing paired cylinders of iC engine - are connected by common piston rod, with independent connecting rods providing swivel connection to crankshaft |
| CN1045289A (en) * | 1989-03-02 | 1990-09-12 | 朱云峰 | Two-direction four stroke engine |
| AUPO641097A0 (en) * | 1997-04-24 | 1997-05-22 | Mitchell, William Richard | Compact internal combustion engine |
| JP2008075561A (en) * | 2006-09-21 | 2008-04-03 | Honda Motor Co Ltd | Multiple cylinder internal combustion engine |
| JP4616229B2 (en) * | 2006-09-29 | 2011-01-19 | 本田技研工業株式会社 | Multi-cylinder internal combustion engine |
| CN203050887U (en) * | 2013-01-07 | 2013-07-10 | 常博宇 | Cylinder opposed type internal combustion engine |
| CN103195567A (en) * | 2013-03-08 | 2013-07-10 | 王庆 | Improvement method and structure of piston engine |
| CN203098048U (en) * | 2013-03-08 | 2013-07-31 | 王庆 | Double-combustor reciprocating engine structure |
| CN103498724A (en) * | 2013-10-18 | 2014-01-08 | 葛宪琪 | Power multiplication internal combustion engine combustion mechanism |
| CN103925075A (en) * | 2014-05-06 | 2014-07-16 | 韩鑫岗 | Multi-cycle internal combustion engine |
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2017
- 2017-05-12 CN CN201710332206.8A patent/CN107091152B/en active Active
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| CN107091152A (en) | 2017-08-25 |
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