CN107091152A - A kind of twin cylinder bimodal aviation piston engine - Google Patents
A kind of twin cylinder bimodal aviation piston engine Download PDFInfo
- Publication number
- CN107091152A CN107091152A CN201710332206.8A CN201710332206A CN107091152A CN 107091152 A CN107091152 A CN 107091152A CN 201710332206 A CN201710332206 A CN 201710332206A CN 107091152 A CN107091152 A CN 107091152A
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- Prior art keywords
- piston
- operating room
- cylinder
- engine
- work
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The present invention discloses a kind of twin cylinder bimodal aviation piston engine, with two cylinders being symmetrical set；Power is exported by the bent axle of engine, drives a piston rod to drive the motion of two pistons simultaneously by connecting rod；Two cylinder upper and lower ends are provided with valve mechanism, fuel system and ignition system.Above-mentioned each cylinder has double work room, has one or two supply to do work by controlling valve mechanism to realize in double work room, therefore engine has two kinds of operation modes：High power work mode and small-power operation mode, and under two kinds of operation modes, engine is respectively provided with higher fuel efficiency.
Description
Technical field
The invention belongs to engine art, it is related to a kind of aviation piston engine for possessing twin cylinder double work mode.
Background technology
In recent years, vertically taking off and landing flyer is obtained in military domain and civil area and is widely applied.It is solid with tradition
Determine wing aircraft to compare, vertically taking off and landing flyer is not limited by landing condition, with 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 to VTOL
Row device proposes higher requirement：Meet VTOL and at a high speed it is flat fly on the basis of, aircraft can realize long endurance flight.
Aero-engine is described as the heart of aircraft, for vertically taking off and landing flyer, and its 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 also regard piston-mode motor as power set more.Therefore in order to realize
The long endurance of vertically taking off and landing flyer is flown, it is necessary to which a can provide sufficient power, and the high piston engine of fuel efficiency
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-weight ratio meets or exceeds 1, and this also requires engine to provide what is conducted oneself with dignity more than aircraft
Thrust.In horizontal flight, the lift of aircraft is mainly provided by wing, therefore only needs engine to provide to overcome resistance
Thrust.Because the lift-drag ratio of aircraft is larger, therefore in VTOL and at a high speed under flat winged two states, it is necessary to which engine is carried
The watt level very different of confession.
High-power aviation piston engine being used existing vertically taking off and landing flyer, can meet VTOL flight power will more
Ask, but under flat winged state, engine is in low power state, and fuel efficiency is relatively low, it is difficult to realize long endurance flight.Piston is sent out
Motivation is difficult to export widely different power on the premise of high fuel efficiency.Therefore complete different using same engine
During the task of power, otherwise power is too low can not to meet high power mission requirements, or in a low-power state, engine fuel
Efficiency is very low.
The content 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, it is adaptable to the specific demand such as vertically taking off and landing flyer.
Twin cylinder bimodal aviation piston engine of the present invention, with two cylinders being symmetrical set, above and below cylinder
Two ends are provided with valve mechanism, fuel system and ignition system.Above-mentioned two piston both sides are available for gas acting, in hair
When motivation works, two cylinders synchronous working is done work with the fuel combustion in lower operating room by the upper operating room of two cylinders and promoted
Piston up-down, the piston of left and right two is moved up and down in the case where being driven by knuckle-joint band piston bar, and piston rod is by power
Bent axle is passed to, band dynamic crankshaft rotates, so as to realize the output of engine power.With conventional pistonic engine phase
Than bent axle, which often revolves to take two turns, expansion work stroke twice so that engine promotes the power of bent axle rotation to be more uniformly distributed, engine
Work it is also more stable.
By controlling valve mechanism to realize in double work room there is one or two supply acting, therefore engine has two
Plant operation mode：High power work mode and small-power operation mode, and under two kinds of operation modes, engine is respectively provided with higher
Fuel efficiency.
The advantage of the invention is that：
1st, twin cylinder bimodal aviation piston engine of the present invention has bimodal, and same engine can provide two kinds high
The high or low power pattern of efficiency, applicability is wide, can save fuel oil.
2nd, twin cylinder bimodal aviation piston engine of the present invention uses twin cylinder, and each piston both sides are available for gas
Acting, compared with conventional pistonic engine, bent axle, which often revolves to take two turns, expansion work stroke twice so that engine promotes bent
The power of axle rotation is more uniformly distributed, and the work of engine is also more stable.
3rd, under Same Efficieney of the present invention, piston both sides are available for gas acting, and it is simpler compact that engine can be designed,
Reduce engine weight and taken up space.
Brief description of the drawings
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 schematic flow sheet 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 rods
4- valve mechanism 5- fuel system 6- ignition systems
7- bent axle 8- open slot 101- cylinder bodies
Operating room under 102- piston 103- operating room 104-
Exhaust gear on 401- upper airs mechanism of operating room 402- under 105-
Ventilating mechanism under exhaust gear 405- under admission gear 404- under 403-
Embodiment
The present invention is described in further details below in conjunction with the accompanying drawings.
Twin cylinder bimodal aviation piston engine of the present invention, with 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 into；Two-part end is provided 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 discharge waste gas；Ignition system 6 is used for according to gas
The job order of cylinder periodically produces the electric spark of enough energy between the electrode of spark plug two.Along cylinder in the middle part of the outer wall of cylinder body 101
The axial design of body 101 has stripe shape open slot 8.Piston 102 is coaxially installed on inside cylinder body 101, the cylinder body of piston both sides about 102
As upper operating room 103 and lower operating room 104 inside 101, acting can be supplied；Ze Shang operating rooms 104 and lower operating room 105
It is respectively provided with valve mechanism 4, fuel system 7 and ignition system 6；And the valve mechanism 4 in upper operating room 104 includes enterprising mechanism of qi
Structure 401 and upper exhaust gear 402；Valve mechanism 4 in lower operating room 105 includes lower admission gear 403, lower exhaust gear 404
With lower ventilating mechanism 405.Wherein, upper air mechanism 401 is respectively intended to control operating room 103 with lower admission gear 403
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
Room 103 and the exclusion of the waste gas in lower operating room 104；Lower ventilating mechanism 405 is used for controlling whether lower operating room participates in acting.
Piston rod 2 is located at outside cylinder body 101, and is set perpendicular to the axis of cylinder body 101, and the two ends of piston rod 103 are respectively mounted
There is hinge, by hinge through the open slot 8 on two cylinders 1, be hinged with the internal piston 102 of cylinder body 101.Connecting rod 4 and cylinder body
101 diameter parallels are set, and one end is articulated with the middle part of piston rod 103, and the other end is articulated with the bent axle 7 that power is exported in engine.
Sealing device is housed on above-mentioned piston 102, the sealing between piston 102 and cylinder body 101 is realized, and when piston 102 is moved, sealing
The position of device will not reach the position of open slot 8, and then realize the sealing of the internal work environment of cylinder body 101.Thus in engine
During work, two cylinders 1 work asynchronously, and are done work by the upper operating room 104 and the fuel combustion in lower operating room 105 of two cylinders 1
Piston 102 is promoted to move up and down, the piston 102 of left and right two is moved up and down in the case where being driven by knuckle-joint band piston bar 2,
Piston rod 2 imparts power to bent axle 7, and band dynamic crankshaft 7 rotates, so as to realize the output of engine power.
The twin cylinder bimodal aviation piston engine of said 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 3 a, the lower ventilating mechanism 405 of two cylinders 1 is closed
Close；Now, upper operating room 104 is in working condition with lower operating room 105.It is enterprising when upper operating room 104 is in compression stroke
Device of air and upper exhaust apparatus are closed, and lower operating room 105 is in induction stroke, and lower inlet duct is opened, and lower exhaust apparatus is closed
Close.As shown in Figure 3 b, when the row of piston 102 to top dead centre, the upper compression of operating room 104 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 105, into compression stroke, lower air inlet dress
Put and lower exhaust apparatus is closed.As shown in Figure 3 c when the row of piston 102 to lower dead center, the upper work by combustion of operating room 104 terminates,
Into exhaust stroke, enterprising device of air closure, upper exhaust apparatus is opened, and lower operating room 105, which then compresses, to be terminated, and is started burning and is done
Work(, into expansion stroke, lower inlet duct and lower exhaust apparatus are closed.As shown in Figure 3 d, when piston 102 is up, upper work
Make the exhaust of room 104 to terminate, into suction stroke, enterprising device of air is opened, upper exhaust apparatus closure, lower operating room 105 then burns
Acting terminates, into instroke, and lower inlet duct closure, lower exhaust apparatus is opened.Engine is repeated according to this circulation.
2) when engine be in small-power operation mode when, as shown in fig. 4 a, the lower ventilating mechanism 405 of two cylinders 1, under
Exhaust gear 404 and lower admission gear 403 are opened, and lower operating room 105 is connected with outside air, are not involved in compression with doing
Work(, the fuel system 5 and ignition system 6 of lower operating room 105 are closed.Each Nei Jinshang operating rooms 104 of cylinder 1 are according to " air inlet is rushed
The circulation of journey-compression stroke-expansion stroke-exhaust stroke " is operated.When upper operating room 104 is in compression stroke, upper air
Device and upper exhaust apparatus are closed；As shown in Figure 4 b when the row of piston 102 to top dead centre, the upper compression of operating room 104 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 the row of piston 102 extremely
During lower dead center, the upper work by combustion of operating room 104 terminates, into exhaust stroke, and enterprising device of air closure, upper exhaust apparatus is opened；
As shown in figure 4d, when piston 102 is up, the upper exhaust of operating room 104 terminates, and into suction stroke, enterprising device of air is opened, on
Exhaust apparatus is closed.Engine is repeated according to this circulation.
Whether open, come while by the lower ventilating mechanism 405 of control, lower exhaust gear 404 and lower admission gear 403
Whether is the work of the lower operating room 105 of control, and engine can be caused to possess high or low power both modalities which.Lower ventilating mechanism 405,
Lower exhaust gear 404 and lower admission gear 403 open simultaneously after, engine is in small-power state, only upper ventilating mechanism, on
Exhaust gear 402 participates in engine work according to the description of above-mentioned small-power state；In lower ventilating mechanism 405, lower exhaust gear
404 and lower admission gear 403 not simultaneously open when, upper exhaust gear 402 is with lower exhaust gear 404 according to above-mentioned high-power
The description of state participates in engine work.Under two kinds of operation modes, optimal ginseng can be used in the parameter such as distributive value of engine
Number so that engine possesses higher fuel efficiency under both modalities which, all, under the premise of firm power output is ensured, can subtract
The use of small fuel oil.
Claims (5)
1. a kind of twin cylinder bimodal aviation piston engine, it is characterised in that：With two cylinders being symmetrical set；Two
Individual cylinder upper and lower ends are provided with valve mechanism, fuel system and ignition system.Two cylinders work asynchronously, by living in two cylinders
The fuel combustion acting filled in the operating room of both sides promotes piston up-down, and the piston of left and right two is in the case where being driven, common band
A piston rod movement is moved, power bent axle is passed into by connecting rod by piston rod, band dynamic crankshaft is rotated, and realization is started
The output of acc power.
2. a kind of twin cylinder bimodal aviation piston engine as claimed in claim 1, it is characterised in that：The cylinder body of two cylinders
On, axially it is designed with open slot along cylinder body；Piston rod is located at outside cylinder body, and two ends pass through open slot and piston by hinge respectively
Between be hinged.
3. a kind of twin cylinder bimodal aviation piston engine as claimed 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 claimed 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 movement, the position of sealing device will not reach open slot position,
Realize the sealing of cylinder interior working environment.
5. a kind of twin cylinder bimodal aviation piston engine as described in Claims 1 to 4, it is characterised in that：With size work(
Two kinds of operation modes of rate：
The cylinder interior of cylinder is made, piston superjacent air space is upper operating room, and piston underlying space is lower operating room, then：
1) when engine is in high power work mode, the lower ventilating mechanism closure of two cylinders；Now, upper operating room is with
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, 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
Burn acting to terminate, 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, upper exhaust apparatus closure, then work by combustion terminates for lower operating room, into row
Gas stroke, lower inlet duct closure, lower exhaust apparatus is 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 with outside air, is not involved in compression and acting, and the fuel system of lower operating room and igniting are
System is closed；Each cylinder Nei Jinshang operating rooms are entered according to the circulation of " induction stroke-compression stroke-expansion stroke-exhaust stroke "
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
During piston row to lower dead center, upper operating room's work by combustion terminates, into exhaust stroke, enterprising device of air closure, upper exhaust apparatus
Open；When piston stroking upward, upper operating room's exhaust terminates, and into suction stroke, enterprising device of air is opened, and upper exhaust apparatus is closed
Close.
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107091152A true CN107091152A (en) | 2017-08-25 |
| CN107091152B CN107091152B (en) | 2019-05-14 |
Family
ID=59637309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710332206.8A Active CN107091152B (en) | 2017-05-12 | 2017-05-12 | A kind of twin cylinder bimodal aviation piston engine |
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Citations (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 |
| CN1258337A (en) * | 1997-04-24 | 2000-06-28 | 威廉·R·米切尔 | Internal combustion engine |
| CN101149003A (en) * | 2006-09-21 | 2008-03-26 | 本田技研工业株式会社 | Multicylinder internal combustion engine |
| CN101153550A (en) * | 2006-09-29 | 2008-04-02 | 本田技研工业株式会社 | 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 |
-
2017
- 2017-05-12 CN CN201710332206.8A patent/CN107091152B/en active Active
Patent Citations (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 |
| CN1258337A (en) * | 1997-04-24 | 2000-06-28 | 威廉·R·米切尔 | Internal combustion engine |
| CN101149003A (en) * | 2006-09-21 | 2008-03-26 | 本田技研工业株式会社 | Multicylinder internal combustion engine |
| CN101153550A (en) * | 2006-09-29 | 2008-04-02 | 本田技研工业株式会社 | 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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| Publication number | Publication date |
|---|---|
| CN107091152B (en) | 2019-05-14 |
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