CN111535921A - Supercharging system and method of two-stroke aviation piston engine - Google Patents

Supercharging system and method of two-stroke aviation piston engine Download PDF

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Publication number
CN111535921A
CN111535921A CN202010382820.7A CN202010382820A CN111535921A CN 111535921 A CN111535921 A CN 111535921A CN 202010382820 A CN202010382820 A CN 202010382820A CN 111535921 A CN111535921 A CN 111535921A
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China
Prior art keywords
exhaust
pipe
air
engine
pipeline
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CN202010382820.7A
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Chinese (zh)
Inventor
赵振峰
俞春存
张付军
韩恺
冯熠硕
王蕾
郭栋
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Beijing Institute of Technology BIT
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Beijing Institute of Technology BIT
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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
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
    • F01N13/08—Other arrangements or adaptations of exhaust conduits
    • 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
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/12—Control of the pumps
    • F02B37/18—Control of the pumps by bypassing exhaust from the inlet to the outlet of turbine or to the atmosphere
    • F02B37/183—Arrangements of bypass valves or actuators therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
    • F02M35/02—Air cleaners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
    • F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
    • F02M35/10—Air intakes; Induction systems
    • 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 invention discloses a supercharging system and method of a two-stroke aviation piston engine, and relates to the technical field of medium and low altitude unmanned aerial vehicle power systems, wherein the supercharging system comprises an air inlet pipeline, an exhaust pipeline and a waste gas bypass pipeline; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet main pipe, a turbocharger and a silencer. Because the inner diameter of the gradually expanding pipe in the exhaust main pipe is gradually increased, the exhaust gas generated after combustion is favorably and quickly exhausted; when the exhaust gas enters the reducer through the straight pipe, the reducer can form a positive pressure wave which is reflected back to the exhaust port, so that the fresh air which enters the cylinder is prevented from flowing out. The scavenging process of the two-stroke aviation piston engine is reasonably matched, the adverse effect of backpressure rising caused by the turbine is weakened, waste gas can be smoothly discharged in the supercharging process of the two-stroke aviation piston engine, and the performance of the engine is improved.

Description

Supercharging system and method of two-stroke aviation piston engine
Technical Field
The invention relates to the technical field of power systems of middle and low altitude unmanned aerial vehicles, in particular to a pressurization system and method of a two-stroke aviation piston pressurization engine.
Background
The naturally aspirated two-stroke aviation piston engine is widely applied to small aviation aircrafts such as medium and low altitude unmanned aerial vehicles.
However, as the flying height increases, the atmospheric pressure decreases, the air density and the oxygen content in the air in unit volume decrease, which leads to the decrease of the air intake amount of the naturally aspirated two-stroke engine, the decrease of the engine power, the increase of the oil consumption, and the rapid deterioration of the engine performance with the increase of the altitude, which severely limits the flying height of the unmanned aerial vehicle using the naturally aspirated two-stroke engine as a power source.
In the prior art, turbocharging technology is an important way for achieving engine power recovery. The turbocharging utilizes the inertia impulse force of the exhaust gas discharged by the engine to drive the turbine to rotate, further drives the coaxially connected air compressor, so that the impeller of the air compressor rotates at the same rotating speed to compress the fresh air entering the shell of the air compressor, and the air enters the engine through the air inlet system after being compressed and supercharged, thereby completing the whole working cycle.
However, the presence of a turbine in the above method causes the exhaust back pressure to rise as compared to when the turbine is absent. At this time, if the supercharging pressure is insufficient, the problems of poor scavenging and gas backflow of the naturally aspirated two-stroke piston engine occur.
Disclosure of Invention
In view of the above, the invention provides a supercharging system and method for a two-stroke aviation piston engine, which can reasonably match the scavenging process of the supercharged engine, reduce the negative influence of backpressure rise caused by a turbine, and enable the engine to smoothly discharge exhaust gas in the supercharging process.
In a first aspect, the present application provides a supercharging system for a two-stroke aviation piston engine, characterized in that the supercharging system comprises an air inlet line, an exhaust line and a waste gas bypass line; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet header pipe, a turbocharger and a silencer;
the air inlet pipeline and the exhaust pipeline are connected with the main body of the engine; an air outlet of the air filter is connected with an air inlet of an air compressor in the turbocharger, and an air outlet of the air compressor is connected with the pressure stabilizing cavity through the air inlet pipe; the intake manifold is connected with the intake side of the cylinder in the engine body, and the exhaust manifold is connected with the exhaust side of the cylinder in the engine body; one end of each exhaust manifold is connected with an exhaust port of a cylinder in the engine, the other end of each exhaust manifold is connected with the exhaust manifold, an outlet of the exhaust manifold is connected with an inlet of a turbine of the turbocharger, and an outlet of the turbine is connected with the silencer; one end of the waste gas bypass pipeline is connected with the outlet of the exhaust main pipe, and the other end of the waste gas bypass pipeline is connected with the inlet of the silencer;
the exhaust manifold comprises a reducing pipe, a reducing pipe and a straight pipe positioned between the reducing pipe and the reducing pipe; two ends of the straight pipe are respectively connected with the outlet of the reducing pipe and the inlet of the reducing pipe; and the inlet of the reducing pipe is used as the inlet of the exhaust main pipe and is connected with each exhaust manifold, and the outlet of the reducing pipe is used as the outlet of the exhaust main pipe and is connected with the inlet of a turbine of the turbocharger.
Optionally, a waste gate valve is arranged in the waste gate pipeline;
the wastegate valve includes a fully open state, a closed state, and a partially open state between the fully open state and the closed state.
Optionally, when the waste gate valve is in a fully open state, the exhaust bypass pipeline is conducted, and all waste gas is exhausted to the atmosphere through the muffler;
when the waste gas bypass valve is in a partially opened state, the exhaust bypass pipeline is conducted, one part of waste gas is directly exhausted to the atmosphere through the silencer, and the other part of waste gas drives the turbine of the turbocharger to do work and then is exhausted to the atmosphere through the silencer;
when the waste gas bypass valve is in a closed state, the exhaust bypass pipeline is disconnected, and all waste gas drives the turbine of the turbocharger to do work and is exhausted to the atmosphere through the silencer.
Optionally, the inlet inner diameter of the divergent tube is D1The inner diameter of the outlet is D2Length is L1(ii) a Wherein D is1＝k1D0，D2＝3·D1；L1The formula is adopted to calculate and obtain:
Figure BDA0002482672470000031
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresents the opening time theta of the exhaust manifold of the enginepRepresenting the delay angle of the appearance moment of the positive pressure wave crest of the exhaust manifold relative to the opening moment of the exhaust manifold, n represents the rotating speed of the engine, k1The value range of (A) is 1.05-1.125.
Optionally, said reducer has an entrance inside diameter D2The inner diameter of the outlet is D3Length is L2(ii) a Wherein D is1＝k1D0，D3＝0.5·D1；L2The formula is adopted to calculate and obtain:
Figure BDA0002482672470000032
L2＝0.24·LT；
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresenting the opening time of an exhaust manifold of the engine, n representing the rotational speed of the engine, k1The value range of (1.05-1.125), LTIs the length of the exhaust manifold.
Optionally, the inner diameter of the straight pipe is D2Length is L3(ii) a Wherein L is3＝LT-L1-L2；
In the formula, LTIs the length of the exhaust manifold, L1Is the length of said divergent tube, L2Is the length of said reducer.
Optionally, the intake circuit includes four intake manifolds therein and the exhaust circuit includes four exhaust manifolds therein.
In a second aspect, the present application provides a method of supercharging a two-stroke aviation piston engine, characterised in that the body of the engine is connected to an inlet line and an exhaust line in a supercharging system; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet header pipe, a turbocharger and a silencer; the exhaust main pipe comprises a tapered pipe, a tapered pipe and a straight pipe positioned between the tapered pipe and the tapered pipe; the method comprises the following steps:
after gravel and dust in the air are filtered by the air filter, the air flows into a compressor in the turbocharger, the compressor compresses the air, the compressed air enters the pressure stabilizing cavity through the air inlet pipe, is subjected to pressure stabilizing treatment by the pressure stabilizing cavity and enters the cylinders of the engine through the plurality of air inlet manifolds;
and waste gas generated by combustion is converged into an exhaust main pipe through the exhaust manifolds, sequentially flows into the turbocharger after passing through a divergent pipe, a straight pipe and a convergent pipe in the exhaust main pipe, drives a turbine of the turbocharger to do work, and is exhausted to the atmosphere through the silencer.
Compared with the prior art, the supercharging system and method of the two-stroke aviation piston engine provided by the invention at least realize the following beneficial effects:
the application provides a supercharging system and a method of a two-stroke aviation piston engine, wherein the system comprises an air inlet pipeline, an exhaust pipeline and a waste gas bypass pipeline; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet main pipe, a turbocharger and a silencer; the air inlet pipeline and the exhaust pipeline are connected with a main body of the engine; the air outlet of the air filter is connected with the air inlet of an air compressor in the turbocharger, and the air outlet of the air compressor flows out through fresh air entering the air cylinder. This application carries out reasonable matching through the scavenging process to two-stroke aviation piston engine, has weakened the adverse effect that the backpressure risees that the turbine brought, has guaranteed that two-stroke aviation piston engine can unobstructed exhaust gas at the pressure boost in-process.
Of course, it is not necessary for any product in which the present invention is practiced to achieve all of the above-described technical effects simultaneously.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic diagram of a supercharging system for a two-stroke aviation piston engine according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a two-stroke aviation piston engine provided in the embodiment of FIG. 1;
FIG. 3 is a schematic diagram of a configuration of an exhaust manifold provided in the embodiment of FIG. 1;
FIG. 4 is a schematic diagram of a pressure stabilizing cavity in the two-stroke aviation piston engine provided in the embodiment of FIG. 1;
fig. 5 is a flow chart illustrating a method of supercharging a two-stroke aviation piston engine according to an embodiment of the present application.
Detailed Description
Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that: the relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise.
The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.
In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the prior art, in order to increase the working height of a naturally aspirated two-stroke aviation piston engine, a turbocharging system is generally used for increasing the intake pressure of a cylinder so as to compress more fresh air into the cylinder and realize the power recovery of the engine. However, for the two-stroke engine, the turbine is additionally arranged behind the exhaust manifold, so that the exhaust back pressure of the exhaust manifold is increased, and at the moment, if the pressure difference of the inlet and the exhaust, namely the scavenging pressure difference is not large enough, the phenomenon of poor scavenging of the engine can occur, and the performance of the engine is seriously influenced.
In view of the above, the invention provides a supercharging system and method for a two-stroke aviation piston engine, which can effectively weaken the negative influence of backpressure rising caused by a turbine and ensure that the engine smoothly discharges waste gas in the supercharging process by optimizing the scavenging process of the supercharged engine.
The following detailed description is to be read in connection with the drawings and the detailed description.
Fig. 1 is a schematic structural diagram of a supercharging system of a two-stroke aviation piston engine provided by an embodiment of the application, fig. 2 is a schematic structural diagram of the two-stroke aviation piston engine provided by the embodiment of fig. 1, and fig. 3 is a schematic structural diagram of an exhaust manifold provided by the embodiment of fig. 1. Referring to fig. 1, 2 and 3, the present application provides a supercharging system for a two-stroke aviation piston engine, which includes an intake duct 10, an exhaust duct 20 and an exhaust gas bypass duct 30; the intake line 10 includes an air cleaner 110, a surge chamber 120, an intake pipe 130, and a plurality of intake manifolds 140, and the exhaust line 20 includes a plurality of exhaust manifolds 150, an exhaust manifold 160, a turbocharger 170, and a muffler 180;
the intake line 10 and the exhaust line 20 are connected to the main body 210 of the engine; the air outlet of the air filter 110 is connected with the air inlet of a compressor in the turbocharger 170, and the air outlet of the compressor is connected with the pressure stabilizing cavity 120 through an air inlet pipe 130; intake manifold 140 is connected to the intake side of cylinder 220 in the engine block, and exhaust manifold 150 is connected to the exhaust side of cylinder 220 in the engine block; one end of each exhaust manifold 150 in the plurality of exhaust manifolds 150 is connected with an exhaust port of a cylinder 220 in the engine, the other end of each exhaust manifold 150 is connected with an exhaust manifold 160, an outlet of the exhaust manifold 160 is connected with an inlet of a turbine of a turbocharger 170, and an outlet of the turbine is connected with a silencer 180; one end of the waste gas bypass pipeline is connected with the outlet of the exhaust manifold 160, and the other end of the waste gas bypass pipeline is connected with the inlet of the silencer 180;
wherein exhaust manifold 20 comprises a diverging pipe 161, a diverging pipe 162, and a straight pipe 163 between diverging pipe 161 and diverging pipe 162; two ends of straight pipe 163 are connected to the outlet of reducer 161 and the inlet of reducer 162, respectively; the inlet of the reducer 161 is connected to each exhaust manifold 150 as the inlet of the exhaust manifold 20, and the outlet of the reducer 162 is connected to the inlet of the turbine of the turbocharger as the outlet of the exhaust manifold 20.
The turbocharging technology is realized by a turbocharger which mainly comprises a turbine and a compressor. Specifically, during the supercharging process of the turbocharger 170, exhaust gas discharged by the engine is collected into the exhaust manifold 160 through the exhaust manifold 150, introduced into the turbine through the exhaust manifold 160, and expands in the turbine to work to push the turbine to rotate, so that energy in the exhaust gas is converted into mechanical energy of the turbine to drive the compressor to rotate, and work is applied to air passing through the duct of the air cleaner 110, and the compressed air enters the pressure stabilizing cavity 120 through the air inlet pipe 130, is subjected to pressure stabilizing treatment by the pressure stabilizing cavity 120, and then flows through the air inlet manifold 140 to enter the cylinder of the engine. It will be appreciated that the air pressure and density entering the cylinder increases, while the cylinder volume does not change, so the oxygen density also increases, resulting in more complete combustion in the cylinder.
When the combusted waste gas is converged into the inlet of the exhaust manifold 160 through the exhaust manifold 150, the combusted waste gas firstly passes through the divergent pipe 161, and because the inner diameter of the divergent pipe 161 is gradually increased, a negative pressure wave returning to the inlet of the exhaust manifold 160 can be formed, so that the waste gas can be rapidly discharged; then, when the exhaust gas passes through straight pipe 163 and enters reducer 162, the exhaust process is substantially completed, and the gradually decreasing inner diameter of reducer 162 forms a positive pressure wave that is reflected back to the inlet of exhaust manifold 160, blocking the outlet of exhaust manifold 160, thereby preventing the outflow of fresh gas that has entered the cylinder. Therefore, the design of the exhaust manifold is optimized, the scavenging process of the supercharged engine is improved, the negative influence of backpressure rising caused by a turbine can be effectively weakened, the smooth exhaust of the engine in the supercharging process is ensured, and the loss of fresh air can be prevented.
Optionally, with continued reference to fig. 1, a wastegate valve 190 is disposed in the wastegate line, the wastegate valve 190 including a fully open state, a closed state, and a partially open state between the fully open state and the closed state.
Specifically, the magnitude of turbocharger boost may be controlled by the opening of wastegate valve 190. The smaller the opening degree of the waste gate valve 190 is, the less the waste gas is discharged through the muffler 180, and the more the waste gas flows into the turbine side, the higher the boost pressure is; conversely, the larger the opening degree of the wastegate valve 190, the more the exhaust gas is discharged through the muffler 180, and the less the exhaust gas flows into the turbine side, the smaller the boost pressure becomes.
Obviously, the size of the boost pressure of the turbocharger can be conveniently controlled by controlling the opening of the waste gas bypass valve, and the air inlet requirement of the two-stroke engine under various working conditions can be met, so that the air pressure required by the engine running at various speeds is ensured, and the performance of the engine is further improved.
Alternatively, when the wastegate valve 190 is in the fully open state, the exhaust bypass line is turned on and all of the exhaust gas is exhausted to the atmosphere through the muffler 180;
when the waste gate valve 190 is in a partially opened state, the exhaust bypass pipeline is conducted, a part of waste gas is directly exhausted to the atmosphere through the muffler 180, and the other part of waste gas drives the turbine of the turbocharger 170 to do work and then is exhausted to the atmosphere through the muffler 180;
when the waste gate valve 190 is in a closed state, the exhaust bypass line is disconnected, and all the exhaust gas drives the turbine of the turbocharger 170 to work and is discharged to the atmosphere through the muffler 180.
Specifically, when the engine runs at a high speed, the waste gas bypass valve 190 of the turbocharger can be opened, and part of waste gas is directly discharged by the muffler 180, so that after part of waste gas is discharged, the rotating speed of the turbine is reduced, and the supercharging pressure is reduced; on the contrary, when the engine is running at a low speed or under a high altitude condition, the waste gas bypass valve 190 of the turbocharger can be closed, at the moment, because the passage for discharging the waste gas is closed, the waste gas can only flow to one side of the turbine to drive the turbine to do work, the compressor is driven to rotate, and the supercharging pressure is increased along with the waste gas bypass valve. The opening degree of the waste gate valve can be controlled by an electronic control system.
It can be understood that the boost pressure of the turbocharger is increased, the air input of the engine can be increased, and stronger power is provided for the engine, so that the working height of the engine is improved; on the other hand, in order to avoid overload operation of the engine under a high-speed working condition, the pressure cannot be infinitely increased, and at the moment, the service life of the engine can be prolonged by properly reducing the boost pressure of the turbocharger.
It can be seen that the wastegate valve is arranged to vary the flow of exhaust gas through the turbocharger, maximising the use of the limited gas; meanwhile, the boost pressure can be timely adjusted by utilizing different opening degrees of the waste gas bypass valve according to whether the engine is in a high-load or high-altitude state.
Optionally, the inlet inner diameter of the divergent tube 161 is D1The inner diameter of the outlet is D2Length is L1Wherein D is1＝k1D0，D2＝3·D1；L1The formula is adopted to calculate and obtain:
Figure BDA0002482672470000081
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresenting the opening time, theta, of the exhaust manifold of the enginepRepresenting the angle of delay of the occurrence of the exhaust manifold positive pressure wave peak relative to the exhaust manifold opening time, n representing the engine speed, k1The value range of (A) is 1.05-1.125.
Optionally, reducer 162 has an entrance inner diameter D2The inner diameter of the outlet is D3Length is L2(ii) a Wherein D is1＝k1D0，D3＝0.5·D1；L2The formula is adopted to calculate and obtain:
Figure BDA0002482672470000082
L2＝0.24·LT；
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresenting the opening time of the exhaust manifold of the engine, n representing the engine speed, k1The value range of (1.05-1.125), LTThe length of the exhaust manifold 160.
Optionally, the straight tube 163 has an inner diameter D2Length is L3(ii) a Wherein L is3＝LT-L1-L2；
In the formula, LTIs the length, L, of the exhaust manifold 1601Is the length of the diverging tube 161, L2The length of reducer 162.
This application is through the design to each part internal diameter and length in the exhaust manifold for the pressure wave that the gas flow in-process produced reaches higher or lower value through stack or reflection in reasonable time. Specifically, when the piston reaches the position near the bottom dead center, the pressure at the outlet of the exhaust manifold is low, so that the exhaust in the cylinder is fully performed; before the exhaust port is closed, the pressure at the exhaust port is higher to block the outflow of fresh air, so that the capture rate and the inflation efficiency in the cylinder are ensured, and the occurrence of a short circuit phenomenon is avoided.
Optionally, the intake circuit 10 includes four intake manifolds 140 therein and the exhaust circuit 20 includes four exhaust manifolds 150 therein.
It will be appreciated that the number of intake and exhaust manifolds is the same and may be specifically configured depending on the number of cylinders in the engine. Specifically, with continued reference to fig. 2, since the two-stroke piston engine of the present embodiment includes four cylinders 220, each cylinder 220 having an intake port and an exhaust port, each intake port being connected to one intake manifold 140 and each exhaust port being connected to one exhaust manifold 150, four intake manifolds and four exhaust manifolds are provided.
Fig. 4 is a schematic structural diagram of a pressure stabilizing cavity in the two-stroke aviation piston engine provided by the embodiment of fig. 1. Referring to fig. 2 and 4, two ends of each of the four intake manifolds 140 are respectively connected to the surge chamber 120 and the intake side of the cylinder 220. When the turbocharger works, the additionally-installed pressure stabilizing cavity can stabilize the air entering the cavity, so that the air flow is more stable, the phenomenon that the pressure fluctuation is too large after pressurization to cause safety accidents such as explosion and the like is avoided, and the stable work of the engine is ensured.
Based on the same inventive concept, the application also provides a supercharging method of the two-stroke piston engine, and fig. 5 is a flow chart of the supercharging method of the two-stroke aviation piston engine provided by the embodiment of the application. Referring to fig. 5, a two-stroke piston engine is connected to an intake line and an exhaust line in a supercharging system; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet main pipe, a turbocharger and a silencer; the exhaust main pipe comprises a reducing pipe, a reducing pipe and a straight pipe positioned between the reducing pipe and the reducing pipe; the method comprises the following steps:
step 501, filtering gravel and dust in air by using an air filter;
step 502, air flows into an air compressor in a turbocharger, and the air is compressed by the air compressor;
step 503, the compressed air enters a pressure stabilizing cavity through an air inlet pipe, is subjected to pressure stabilizing treatment by the pressure stabilizing cavity, and then enters a cylinder of the engine through a plurality of air inlet manifolds;
step 504, collecting the waste gas generated by combustion into an exhaust manifold through a plurality of exhaust manifolds, and allowing the waste gas to flow into a turbocharger after sequentially passing through a divergent pipe, a straight pipe and a convergent pipe in the exhaust manifold;
and 505, after the exhaust gas drives a turbine of the turbocharger to do work, exhausting the exhaust gas to the atmosphere through a silencer.
In the two-stroke piston engine's that this application provided pressure boost method, because in the exhaust manifold, the internal diameter of divergent pipe is crescent, consequently is favorable to making the waste gas that produces after the burning discharge fast, when waste gas through the straight tube, when getting into the convergent pipe, the convergent pipe can form the positive pressure wave of reflection return exhaust port department to prevent to have got into the fresh air outflow of cylinder. This application has weakened the adverse effect that the backpressure that the turbine brought risees through rationally matching two-stroke aviation piston engine's scavenging process, has guaranteed that two-stroke aviation piston engine can unobstructed exhaust waste gas at the pressure boost in-process to improve the performance of engine.
In conclusion, the supercharging system and method of the two-stroke aviation piston engine provided by the invention at least realize the following beneficial effects:
the application provides a supercharging system and a method of a two-stroke aviation piston engine, wherein the supercharging system comprises an air inlet pipeline, an exhaust pipeline and a waste gas bypass pipeline; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet main pipe, a turbocharger and a silencer; the air inlet pipeline and the exhaust pipeline are connected with a main body of the engine; the air outlet of the air filter is connected with the air inlet of an air compressor in the turbocharger, and the air outlet of the air compressor is connected with the pressure stabilizing cavity through an air inlet pipe; the intake manifold is connected with the intake side of the cylinder in the engine body, and the exhaust manifold is connected with the exhaust side of the cylinder in the engine body; one end of each exhaust manifold is connected with an exhaust port of a cylinder in the engine, the other end of each exhaust manifold is connected with an exhaust manifold, an outlet of the exhaust manifold is connected with an inlet of a turbine of the turbocharger, and an outlet of the turbine is connected with the silencer; one end of the waste gas bypass pipeline is connected with the outlet of the exhaust main pipe, and the other end of the waste gas bypass pipeline is connected with the inlet of the silencer; the exhaust manifold comprises a reducing pipe, a reducing pipe and a straight pipe positioned between the reducing pipe and the reducing pipe; two ends of the straight pipe are respectively connected with the outlet of the reducing pipe and the inlet of the reducing pipe; the inlet of the reducing pipe is used as the inlet of an exhaust manifold and is connected with each exhaust manifold, and the outlet of the reducing pipe is used as the outlet of the exhaust manifold and is connected with the inlet of a turbine of the turbocharger. Because the divergent pipe in the exhaust manifold is favorable for discharging the waste gas generated after combustion quickly, when the waste gas passes through the straight pipe and enters the convergent pipe, the convergent pipe can form a positive pressure wave which is reflected to the exhaust port, thereby preventing the fresh air which enters the cylinder from flowing out. This application carries out reasonable matching through the scavenging process to two-stroke aviation piston engine, has weakened the adverse effect that the backpressure risees that the turbine brought, has guaranteed that two-stroke aviation piston engine can unobstructed exhaust waste gas at the pressure boost in-process, and then improves the performance of engine.
Although some specific embodiments of the present invention have been described in detail by way of examples, it should be understood by those skilled in the art that the above examples are for illustrative purposes only and are not intended to limit the scope of the present invention. It will be appreciated by those skilled in the art that modifications may be made to the above embodiments without departing from the scope and spirit of the invention. The scope of the invention is defined by the appended claims.

Claims (8)

1. A supercharging system of a two-stroke aviation piston engine is characterized by comprising an air inlet pipeline, an exhaust pipeline and an exhaust gas bypass pipeline; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet header pipe, a turbocharger and a silencer;
the air inlet pipeline and the exhaust pipeline are connected with the main body of the engine; an air outlet of the air filter is connected with an air inlet of an air compressor in the turbocharger, and an air outlet of the air compressor is connected with the pressure stabilizing cavity through the air inlet pipe; the intake manifold is connected with the intake side of the cylinder in the engine body, and the exhaust manifold is connected with the exhaust side of the cylinder in the engine body; one end of each exhaust manifold is connected with an exhaust port of a cylinder in the engine, the other end of each exhaust manifold is connected with the exhaust manifold, an outlet of the exhaust manifold is connected with an inlet of a turbine of the turbocharger, and an outlet of the turbine is connected with the silencer; one end of the waste gas bypass pipeline is connected with the outlet of the exhaust main pipe, and the other end of the waste gas bypass pipeline is connected with the inlet of the silencer;
the exhaust manifold comprises a reducing pipe, a reducing pipe and a straight pipe positioned between the reducing pipe and the reducing pipe; two ends of the straight pipe are respectively connected with the outlet of the reducing pipe and the inlet of the reducing pipe; and the inlet of the reducing pipe is used as the inlet of the exhaust main pipe and is connected with each exhaust manifold, and the outlet of the reducing pipe is used as the outlet of the exhaust main pipe and is connected with the inlet of a turbine of the turbocharger.
2. A supercharging system according to claim 1, wherein a wastegate valve is provided in the wastegate line;
the wastegate valve includes a fully open state, a closed state, and a partially open state between the fully open state and the closed state.
3. The supercharging system of a two-stroke aviation piston engine according to claim 2,
when the waste gas bypass valve is in a fully opened state, the exhaust bypass pipeline is conducted, and all waste gas is exhausted to the atmosphere through the silencer;
when the waste gas bypass valve is in a partially opened state, the exhaust bypass pipeline is conducted, one part of waste gas is directly exhausted to the atmosphere through the silencer, and the other part of waste gas drives the turbine of the turbocharger to do work and then is exhausted to the atmosphere through the silencer;
when the waste gas bypass valve is in a closed state, the exhaust bypass pipeline is disconnected, and all waste gas drives the turbine of the turbocharger to do work and is exhausted to the atmosphere through the silencer.
4. A supercharging system according to claim 1, wherein the inlet internal diameter of the divergent conduit is D1The inner diameter of the outlet is D2Length is L1(ii) a Wherein D is1＝k1D0，D2＝3·D1；L1The formula is adopted to calculate and obtain:
Figure FDA0002482672460000021
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresents the opening time theta of the exhaust manifold of the enginepRepresenting the delay angle of the appearance moment of the positive pressure wave crest of the exhaust manifold relative to the opening moment of the exhaust manifold, n represents the rotating speed of the engine, k1The value range of (A) is 1.05-1.125.
5. A supercharging system according to claim 4, wherein the inlet of the reducer has an internal diameter D2The inner diameter of the outlet is D3Length is L2(ii) a Wherein D is1＝k1D0，D3＝0.5·D1；L2The formula is adopted to calculate and obtain:
Figure FDA0002482672460000022
L2＝0.24·LT；
in the formula, D0α represents the velocity of the forward pressure wave at the sonic velocity of the environment in which the engine is located, θeRepresenting the opening time of an exhaust manifold of the engine, n representing the rotational speed of the engine, k1The value range of (1.05-1.125), LTIs the length of the exhaust manifold.
6. A supercharging system according to claim 5, wherein the internal diameter of the straight tube is D2Length is L3(ii) a Wherein L is3＝LT-L1-L2；
In the formula, LTIs the length of the exhaust manifold, L1Is the length of said divergent tube, L2Is the length of said reducer.
7. A supercharging system according to claim 1, wherein the inlet line includes four inlet manifolds therein and the exhaust line includes four exhaust manifolds therein.
8. A supercharging method of a two-stroke aviation piston engine is characterized in that a main body of the engine is connected with an air inlet pipeline and an exhaust pipeline in a supercharging system; the air inlet pipeline comprises an air filter, a pressure stabilizing cavity, an air inlet pipe and a plurality of air inlet manifolds, and the air outlet pipeline comprises a plurality of air outlet manifolds, an air outlet header pipe, a turbocharger and a silencer; the exhaust main pipe comprises a tapered pipe, a tapered pipe and a straight pipe positioned between the tapered pipe and the tapered pipe; the method comprises the following steps:
after gravel and dust in the air are filtered by the air filter, the air flows into a compressor in the turbocharger, the compressor compresses the air, the compressed air enters the pressure stabilizing cavity through the air inlet pipe, is subjected to pressure stabilizing treatment by the pressure stabilizing cavity and enters the cylinders of the engine through the plurality of air inlet manifolds;
and waste gas generated by combustion is converged into an exhaust main pipe through the exhaust manifolds, sequentially flows into the turbocharger after passing through a divergent pipe, a straight pipe and a convergent pipe in the exhaust main pipe, drives a turbine of the turbocharger to do work, and is exhausted to the atmosphere through the silencer.
CN202010382820.7A 2020-05-08 2020-05-08 Supercharging system and method of two-stroke aviation piston engine Pending CN111535921A (en)

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