CN112145285B - Low-oil-consumption long-endurance aircraft engine - Google Patents
Low-oil-consumption long-endurance aircraft engine Download PDFInfo
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- CN112145285B CN112145285B CN202010817563.5A CN202010817563A CN112145285B CN 112145285 B CN112145285 B CN 112145285B CN 202010817563 A CN202010817563 A CN 202010817563A CN 112145285 B CN112145285 B CN 112145285B
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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
- F02B61/00—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing
- F02B61/04—Adaptations of engines for driving vehicles or for driving propellers; Combinations of engines with gearing for driving propellers
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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
- F02B33/00—Engines characterised by provision of pumps for charging or scavenging
- F02B33/32—Engines with pumps other than of reciprocating-piston type
- F02B33/34—Engines with pumps other than of reciprocating-piston type with rotary pumps
- F02B33/40—Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0021—Construction
- F02F7/0024—Casings for larger engines
- F02F7/0026—Casings for horizontal engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02F—CYLINDERS, PISTONS OR CASINGS, FOR COMBUSTION ENGINES; ARRANGEMENTS OF SEALINGS IN COMBUSTION ENGINES
- F02F7/00—Casings, e.g. crankcases or frames
- F02F7/0065—Shape of casings for other machine parts and purposes, e.g. utilisation purposes, safety
- F02F7/0068—Adaptations for other accessories
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M5/00—Engine beds, i.e. means for supporting engines or machines on foundations
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Transmission Devices (AREA)
Abstract
The application discloses an aeroengine with low oil consumption and long endurance, which comprises an engine main body, an installation mechanism, a protection mechanism and a transmission mechanism, wherein the engine main body is positioned at the top of a base; the mounting mechanism comprises a bottom plate, a limiting plate, a fixing plate and a reinforcing plate; the protection mechanism comprises a protection shell, a fixed bearing, a shell, an air inlet pipe and a cover; the transmission mechanism comprises a bearing seat, a transmission shaft, a fixed shaft, a vertical plate, a guide rod and a knob. The engine is conveniently installed and fixed through the matching of the bottom plate and the base, the reinforcing plate is arranged to realize the stable fixation of the engine, and meanwhile, the installation and fixation are facilitated through the matching of the fixed shaft and the guide rod, so that the stability of the engine during installation is improved; the shell is arranged to facilitate air delivery, so that fuel oil can be fully combusted in the piston cylinder, and fuel oil consumption is reduced; the bearing seat is favorable for stable rotation of the propeller, and meanwhile, the air discharged by combustion plays a role in auxiliary pushing, so that the time of flight of the space shuttle is improved.
Description
Technical Field
The application relates to an aircraft engine, in particular to an aircraft engine with low oil consumption and long endurance.
Background
The piston type aircraft engine is a gasoline engine with 4 strokes and electric nozzle ignition, a crankshaft rotates for 2 circles, each piston reciprocates for 4 times in a cylinder, each time refers to 1 stroke, 4 strokes sequentially comprise air suction, compression, expansion and exhaust, 1 constant volume heating cycle is formed together, the compression ratio of the engine thermal efficiency, the compression ratio and the temperature of a working medium after combustion are too high, fuel oil can automatically combust before being ignited by the electric nozzle and form detonation waves to cause local overheating of the cylinder and increase part load, the reliability of the engine is reduced, the octane number of gasoline is an effective measure for improving the compression ratio and preventing detonation, the octane number of the aviation gasoline is generally more than 100, the power that each cylinder can deliver is limited by the temperature of the working fluid.
Piston aeroengine utilizes piston reciprocating motion to promote screw pivoted engine, through the power that aviation fuel regarded as the energy in order to realize the aircraft and take off, piston aeroengine is difficult when assembling to be installed fast, long-time use appears not hard up problem with the base easily, the difficult entering engine of air when the engine work inside, transmission part department also receives the damage easily, and when installing, it is difficult to carry on spacingly to the engine, carry out during operation engine and rock the life-span problem because of taking place easily. Therefore, the aircraft engine with low oil consumption and long endurance is provided for solving the problems.
Disclosure of Invention
An aircraft engine with low oil consumption and long endurance comprises an engine main body positioned at the top of a base, an installation mechanism, a protection mechanism and a transmission mechanism;
the mounting mechanism comprises a bottom plate, a limiting plate, a fixing plate and a reinforcing plate, the bottom plate is fixedly connected with the bottom of the engine main body, the reinforcing plate is located inside the limiting plate, the limiting plate and the fixing plate are fixedly connected with the top surface of the base, the inside of the limiting plate is movably inserted into the reinforcing plate, the reinforcing plate is fixedly connected with the limiting plate through a second bolt, and the bottom plate is fixedly connected with the base through a first bolt;
the protection mechanism comprises a protection shell, a fixed bearing, a shell, an air inlet pipe and a cover, wherein the protection shell is fixedly installed on the side wall of the main body of the engine through screws, the side wall of the main body of the engine is fixedly connected with the fixed bearing and the shell respectively, the shell is communicated with the air inlet pipe, the cover is fixedly installed at the top of the main body of the engine, and the side wall of the main body of the engine is communicated with the air outlet pipe;
the transmission mechanism comprises a bearing seat, a transmission shaft, a fixed shaft, a vertical plate, a guide rod and a knob, the bearing seat is fixedly connected with the side wall of the engine body, the inside of the bearing seat is rotatably connected with the transmission shaft, the end part of the transmission shaft is fixedly connected with the propeller, the fixed shaft is fixedly connected with the outer wall of the engine body, the vertical plate is fixedly connected with the top surface of the limiting plate, the top of the vertical plate is fixedly connected with the guide rod, and the guide rod is in threaded sleeve joint with the knob.
Further, the base top surface is equipped with the limiting plate of two symmetries, two the limiting plate all is L shape structure, and two the limiting plate all with bottom plate sliding connection.
Further, limiting plate side and fixed plate fixed connection, limiting plate top and two second bolt threaded connection, two the second bolt runs through the limiting plate and extends to inside the reinforcing plate, just the reinforcing plate is T shape structure and is connected with the laminating of fixed plate lateral wall.
Further, the cross section of the bottom plate is of a T-shaped structure, the bottom plate is connected with the surface of the base in a sliding mode, six first bolts are arranged on two sides of the bottom plate respectively, and each first bolt extends into the base.
Further, the limiting plate top is equipped with two risers, and two riser top lateral walls all are equipped with the guide bar, the guide bar is cup jointed with the inside running through of fixed axle, just the fixed axle both ends contact respectively has riser and knob.
Furthermore, the air outlet pipe is positioned on one side of the engine main body and is provided with four pipelines communicated with the engine main body, and each pipeline is communicated with an air outlet pipe of the piston cylinder.
Further, the shell is communicated with the engine main body, the shell is communicated with the air inlet pipes of the four piston cylinders, and a centrifugal fan is arranged inside the shell.
Furthermore, the bearing seat is located one side of the propeller, and a transmission shaft inside the bearing seat is connected with the crankshaft.
Furthermore, a speed reducer is arranged inside the protective shell and is in transmission connection with the centrifugal fan, and the protective shell and the bearing seat are respectively located on two sides of the engine main body.
Furthermore, two fixed shafts are arranged on two sides of the engine main body respectively, and the fixed shafts are of circular ring structures.
The beneficial effect of this application is: the application provides an aeroengine who assembles convenience and install stable low oil consumption and long duration of navigating.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.
FIG. 1 is a schematic overall perspective view of an embodiment of the present application;
FIG. 2 is a schematic diagram of an elevated view of a base plate according to an embodiment of the present application;
fig. 3 is a schematic front view of a limiting plate according to an embodiment of the present application.
In the figure: 1. the base, 2, engine body, 3, bottom plate, 4, limiting plate, 5, fixed plate, 6, reinforcing plate, 7, first bolt, 8, protective housing, 9, fixing bearing, 10, casing, 11, air-supply line, 12, cover, 13, play tuber pipe, 14, bearing frame, 15, transmission shaft, 16, screw, 17, fixed axle, 18, riser, 19, guide bar, 20, knob, 21, second bolt.
Detailed Description
In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It should be understood that the data so used may be interchanged under appropriate circumstances such that embodiments of the application described herein may be used. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings. These terms are used primarily to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to a particular orientation or to be constructed and operated in a particular orientation.
Moreover, some of the above terms may be used to indicate other meanings besides the orientation or positional relationship, for example, the term "on" may also be used to indicate some kind of attachment or connection relationship in some cases. The specific meaning of these terms in this application will be understood by those of ordinary skill in the art as appropriate.
Furthermore, the terms "mounted," "disposed," "provided," "connected," and "sleeved" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; can be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1-3, an aero-engine with low fuel consumption and long endurance includes an engine main body 2 located on the top of a base 1, a mounting mechanism, a protection mechanism and a transmission mechanism;
the mounting mechanism comprises a bottom plate 3, a limiting plate 4, a fixing plate 5 and a reinforcing plate 6, wherein the bottom plate 3 is fixedly connected with the bottom of an engine main body 2, the reinforcing plate 6 is positioned inside the limiting plate 4, the limiting plate 4 and the fixing plate 5 are fixedly connected with the top surface of a base 1, the inside of the limiting plate 4 is movably inserted into the reinforcing plate 6, the reinforcing plate 6 is fixedly connected with the limiting plate 4 through a second bolt 21, and the bottom plate 3 is fixedly connected with the base 1 through a first bolt 7;
the protection mechanism comprises a protection shell 8, a fixed bearing 9, a shell 10, an air inlet pipe 11 and a cover 12, wherein the protection shell 8 is fixedly installed on the side wall of the engine main body 2 through screws, the side wall of the engine main body 2 is fixedly connected with the fixed bearing 9 and the shell 10 respectively, the shell 10 is communicated with the air inlet pipe 11, the cover 12 is fixedly installed on the top of the engine main body 2, and the side wall of the engine main body 2 is communicated with an air outlet pipe 13;
the transmission mechanism comprises a bearing seat 14, a transmission shaft 15, a fixed shaft 17, a vertical plate 18, a guide rod 19 and a knob 20, the bearing seat 14 is fixedly connected with the side wall of the engine main body 2, the inside of the bearing seat 14 is rotatably connected with the transmission shaft 15, the end part of the transmission shaft 15 is fixedly connected with a propeller 16, the fixed shaft 17 is fixedly connected with the outer wall of the engine main body 2, the vertical plate 18 is fixedly connected with the top surface of the limiting plate 4, the top part of the vertical plate 18 is fixedly connected with the guide rod 19, and the guide rod 19 is in threaded sleeve connection with the knob 20.
The top surface of the base 1 is provided with two symmetrical limiting plates 4, the two limiting plates 4 are both in an L-shaped structure, and the two limiting plates 4 are both connected with the bottom plate 3 in a sliding manner and used for limiting the bottom plate 3, so that the installation is convenient; the side end of the limiting plate 4 is fixedly connected with the fixing plate 5, the top of the limiting plate 4 is in threaded connection with two second bolts 21, the two second bolts 21 penetrate through the limiting plate 4 and extend into the reinforcing plate 6, the reinforcing plate 6 is in a T-shaped structure and is attached and connected with the side wall of the fixing plate 5, and the strength of the fixing plate 5 is improved through the reinforcing plate 6 when an engine generates thrust; the cross section of the bottom plate 3 is of a T-shaped structure, the bottom plate 3 is connected with the surface of the base 1 in a sliding mode, six first bolts 7 are arranged on two sides of the bottom plate 3 respectively, and each first bolt 7 extends into the base 1 and is used for installing the bottom plate 3, so that the engine main body 2 can be fixed conveniently; the top of the limiting plate 4 is provided with two vertical plates 18, the side walls of the tops of the two vertical plates 18 are provided with guide rods 19, the guide rods 19 are in through sleeve joint with the inside of the fixed shaft 17, and two ends of the fixed shaft 17 are respectively in contact with the vertical plates 18 and the knobs 20 to limit two sides of the engine main body 2, so that the stability during installation is improved; the air outlet pipe 13 is positioned on one side of the engine main body 2, the air outlet pipe 13 is provided with four pipelines communicated with the engine main body 2, and each pipeline is communicated with an air outlet pipe of the piston cylinder and used for discharging combusted air; the shell 10 is communicated with the engine main body 2, the shell 10 is communicated with air inlet pipes of four piston cylinders, and a centrifugal fan is arranged in the shell 10 and used for allowing outside air to enter the engine main body 2 to achieve sufficient combustion of fuel oil; the bearing seat 14 is positioned at one side of the propeller 16, and a transmission shaft 15 inside the bearing seat 14 is connected with a crankshaft and used for transmitting the propeller 16; a speed reducer is arranged in the protective shell 8 and is in transmission connection with the centrifugal fan, and the protective shell 8 and the bearing seat 14 are respectively positioned on two sides of the engine main body 2 and used for allowing outside air to enter; two fixed shafts 17 are respectively arranged on two sides of the engine main body 2, and the fixed shafts 17 are of circular ring structures and used for limiting the guide rods 19, so that the stability of the engine main body 2 is improved.
When the fixing device is used, the base 1 is arranged on an airplane, the reinforcing plate 6 is placed inside the limiting plate 4, the limiting plate 4 is attached to the fixing plate 5, the second bolt 21 penetrates through the limiting plate 4 and is screwed down, the reinforcing plate 6 is fixed through the second bolt 21, the engine main body 2 and the bottom plate 3 are moved to the base 1, the bottom plate 3 is moved to the inside of the limit plate 4 after sliding between the limit plates 4, the bottom plate 3 is fixed on the base 1 through the first bolt 7, when the bottom plate 3 is moved, the engine main body 2 drives the fixed shaft 17 to move to the guide rod 19, at the moment, the limit of the engine main body 2 is realized through the matching of the guide rod 19 and the fixed shaft 17, the knob 20 is screwed down, so that the guide rod 19 on the vertical plate 18 realizes the further stability of the engine main body 2, the stable work of the engine is ensured, and the service life of the engine main body 2 is prolonged;
when the engine main body 2 works, fuel oil is supplemented into the piston cylinder and combusted, the transmission shaft 15 is driven to rotate in the bearing seat 14 through the crankshaft when the piston is pushed to reciprocate, then the propeller 16 is driven to rotate at a high speed to generate thrust, meanwhile, the centrifugal fan blades in the shell 10 are driven to rotate through the speed reducer in the protective shell 8, external air enters through the air inlet pipe 11 and is conveyed to the piston cylinder to be fully combusted, the combustion efficiency is ensured to reduce the fuel oil consumption, the combusted air is discharged through the air outlet pipe 13, the generated thrust is matched with the thrust of the propeller 16 to serve as a power source of an aviation aircraft, and the flight time of the aviation aircraft is prolonged.
The application has the advantages that:
1. the engine is conveniently installed and fixed through the matching of the bottom plate and the base, the reinforcing plate is arranged to realize the stable fixation of the engine, and meanwhile, the installation and fixation are facilitated through the matching of the fixed shaft and the guide rod, so that the stability of the engine during installation is improved, and the service life of the engine is prolonged;
2. the shell facilitates air to enter, fuel oil in the engine is favorably and fully combusted in the piston cylinder, fuel oil consumption is reduced, and the protective shell is favorable for protecting a transmission part and avoiding the problem of damage;
3. this application is favorable to the stable rotation of screw through being provided with the bearing frame, plays supplementary promotion effect through combustion exhaust air simultaneously, improves space plane's time of navigating.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
1. The utility model provides an aeroengine of low oil consumption and long endurance which characterized in that: comprises an engine main body (2) positioned at the top of a base (1), an installation mechanism, a protection mechanism and a transmission mechanism;
the mounting mechanism comprises a bottom plate (3), a limiting plate (4), a fixing plate (5) and a reinforcing plate (6), the bottom plate (3) is fixedly connected with the bottom of the engine main body (2), the reinforcing plate (6) is located inside the limiting plate (4), the limiting plate (4) and the fixing plate (5) are fixedly connected with the top surface of the base (1), the inside of the limiting plate (4) is movably inserted into the reinforcing plate (6), the reinforcing plate (6) is fixedly connected with the limiting plate (4) through a second bolt (21), and the bottom plate (3) is fixedly connected with the base (1) through a first bolt (7);
the protection mechanism comprises a protection shell (8), a fixed bearing (9), a shell (10), an air inlet pipe (11) and a cover (12), wherein the protection shell (8) is fixedly installed on the side wall of the engine main body (2) through screws, the side wall of the engine main body (2) is fixedly connected with the fixed bearing (9) and the shell (10) respectively, the shell (10) is communicated with the air inlet pipe (11), the cover (12) is fixedly installed at the top of the engine main body (2), and the side wall of the engine main body (2) is communicated with an air outlet pipe (13);
the transmission mechanism comprises a bearing seat (14), a transmission shaft (15), a fixed shaft (17), vertical plates (18), guide rods (19) and a knob (20), the bearing seat (14) is fixedly connected with the side wall of the engine main body (2), the inside of the bearing seat (14) is rotatably connected with the transmission shaft (15), the end part of the transmission shaft (15) is fixedly connected with a propeller (16), the fixed shaft (17) is fixedly connected with the outer wall of the engine main body (2), the vertical plates (18) are fixedly connected with the top surface of the limiting plate (4), the tops of the vertical plates (18) are fixedly connected with the guide rods (19), the guide rods (19) are in threaded sleeve joint with the knob (20), the tops of the limiting plate (4) are provided with the two vertical plates (18), the side walls of the tops of the two vertical plates (18) are provided with the guide rods (19), and the guide rods (19) are in through sleeve joint with the inside of the fixed shaft (17), and both ends of the fixed shaft (17) are respectively contacted with a vertical plate (18) and a knob (20).
2. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: the top surface of the base (1) is provided with two symmetrical limiting plates (4), the two limiting plates (4) are of L-shaped structures, and the two limiting plates (4) are connected with the bottom plate (3) in a sliding mode.
3. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: limiting plate (4) side and fixed plate (5) fixed connection, limiting plate (4) top and two second bolt (21) threaded connection, two second bolt (21) run through limiting plate (4) and extend to reinforcing plate (6) inside, just reinforcing plate (6) are T shape structure and are connected with fixed plate (5) lateral wall laminating.
4. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: the cross section of the bottom plate (3) is of a T-shaped structure, the bottom plate (3) is connected with the surface of the base (1) in a sliding mode, six first bolts (7) are arranged on two sides of the bottom plate (3) respectively, and each first bolt (7) extends to the interior of the base (1).
5. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: the air outlet pipe (13) is positioned on one side of the engine main body (2), the air outlet pipe (13) is provided with four pipelines communicated with the engine main body (2), and each pipeline is communicated with an air outlet pipe of the piston cylinder.
6. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: the engine is characterized in that the shell (10) is communicated with the engine main body (2), the shell (10) is communicated with air inlet pipes of four piston cylinders, and a centrifugal fan is arranged inside the shell (10).
7. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: the bearing seat (14) is located on one side of the propeller (16), and a transmission shaft (15) inside the bearing seat (14) is connected with the crankshaft.
8. The aircraft engine of claim 6, wherein the engine is configured to operate at low fuel consumption and long endurance: the centrifugal fan is characterized in that a speed reducer is arranged inside the protective shell (8) and is in transmission connection with the centrifugal fan, and the protective shell (8) and the bearing seat (14) are located on two sides of the engine main body (2) respectively.
9. A low fuel consumption and long endurance aircraft engine according to claim 1, further comprising: two fixed shafts (17) are respectively arranged on two sides of the engine main body (2), and the fixed shafts (17) are of circular ring structures.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010817563.5A CN112145285B (en) | 2020-08-14 | 2020-08-14 | Low-oil-consumption long-endurance aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010817563.5A CN112145285B (en) | 2020-08-14 | 2020-08-14 | Low-oil-consumption long-endurance aircraft engine |
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| CN112145285A CN112145285A (en) | 2020-12-29 |
| CN112145285B true CN112145285B (en) | 2021-09-24 |
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