Aircraft engine
阅读说明：本技术 一种航空发动机 (Aircraft engine ) 是由 张涛 吴来军 于海静 温广武 覃春林 钟博 夏龙 王华涛 王春雨 于 2019-10-29 设计创作，主要内容包括：一种航空发动机,涉及重型载荷无人机发动机领域,设有外壳体,外壳体的内壁上设有环形燃烧槽,外壳体内设有喷出口调节筒,喷出口调节筒与环形燃烧槽围成环形燃烧腔,喷出口调节筒内设有加速喷射管,加速喷射管前端部与喷出口调节筒前端部内壁固定连接；外壳体上设有与加速喷射管前端相对的喷出口挡环,环形燃烧槽前端内壁和喷出口挡环后侧壁上设有弧形导流壁,加速喷射管前端位于弧形导流壁后侧内,二者间设有环形喷出口,外壳体上设有空气吸入口,外壳体上设有燃料入口、气体入口和点火口；喷出口调节筒后部螺纹连接有定位法兰,定位法兰经螺栓与外壳体相连。本发明具有结构简单、燃烧效率高、重量轻、维护成本低等优点。(An aircraft engine relates to the field of heavy-duty load unmanned aerial vehicle engines and is provided with an outer shell, wherein an annular combustion groove is formed in the inner wall of the outer shell, a jet port adjusting cylinder is arranged in the outer shell, an annular combustion cavity is formed by the jet port adjusting cylinder and the annular combustion groove, an accelerating jet pipe is arranged in the jet port adjusting cylinder, and the front end part of the accelerating jet pipe is fixedly connected with the inner wall of the front end part of the jet port adjusting cylinder; the outer shell is provided with a jet orifice baffle ring opposite to the front end of the accelerated jet pipe, the inner wall of the front end of the annular combustion groove and the rear side wall of the jet orifice baffle ring are provided with arc-shaped guide walls, the front end of the accelerated jet pipe is positioned in the rear side of the arc-shaped guide walls, an annular jet orifice is arranged between the arc-shaped guide walls and the annular jet orifice baffle ring, the outer shell is provided with an air suction inlet, and the outer shell is provided with a fuel inlet; the rear part of the jet port adjusting cylinder is connected with a positioning flange in a threaded manner, and the positioning flange is connected with the outer shell through a bolt. The invention has the advantages of simple structure, high combustion efficiency, light weight, low maintenance cost and the like.)
1. An aircraft engine, characterized in that: the device is provided with a sleeve-shaped outer shell, an annular combustion groove is arranged on the inner wall of the outer shell, a spraying port adjusting cylinder capable of being adjusted forwards and backwards is arranged in the outer shell, an annular combustion cavity is enclosed by the spraying port adjusting cylinder and the annular combustion groove, a Venturi-tube-shaped accelerating jet pipe is arranged in the spraying port adjusting cylinder, and the front end part of the accelerating jet pipe is fixedly connected with the inner wall of the front end part of the spraying port adjusting cylinder; an ejection port baffle ring opposite to the front end of the accelerated jet pipe is arranged on the outer shell in front of the annular combustion groove, an arc-shaped flow guide wall is arranged on the inner wall of the front end of the annular combustion groove and the rear side wall of the ejection port baffle ring, the front end of the accelerated jet pipe is positioned in the rear side of the arc-shaped flow guide wall, an annular ejection port which is positioned at the front end of the accelerated jet pipe and ejects into the accelerated jet pipe is arranged between the accelerated jet pipe and the accelerated jet pipe, an air suction port is arranged on the outer shell in front of the accelerated jet pipe, and a fuel inlet; the rear part of the jet port adjusting cylinder is connected with a positioning flange in a threaded manner, and the positioning flange is connected with the outer shell through a bolt.
2. The aircraft engine of claim 1, wherein: the jet port adjusting cylinder is connected with the inner wall of the outer shell body on the rear side of the annular combustion groove in a sealing mode through threads.
3. The aircraft engine of claim 1, wherein: the ejection port adjusting cylinder is in mirror surface sealing contact with the outer shell on the rear side of the annular combustion groove.
4. The aircraft engine of claim 1, wherein: the outer shell and the accelerated jet pipe are made of materials with low density, high temperature resistance, wear resistance, corrosion resistance, high elastic modulus and good toughness.
5. The aircraft engine of claim 1, wherein: the accelerating injection pipe consists of an inlet section at the front part, a reducing section at the middle part and a widening section at the rear part, and the contour of the inner side wall of the accelerating injection pipe meets the von Karman curve.
6. The aircraft engine of claim 1, wherein: the air suction inlet is in a horn shape with a small-caliber end positioned in the front end of the acceleration jet pipe, and the minimum inner diameter of the middle part of the acceleration jet pipe is 0.2-0.5 times, preferably 0.25-0.35 times of the minimum inner diameter of the air suction inlet; the inner diameter of the rear end of the accelerating injection pipe is 0.5 to 0.9 times, preferably 0.6 to 0.8 times of the minimum inner diameter of the air suction inlet.
7. The aircraft engine of claim 1, wherein: the sectional area of the annular ejection port is 0.03 to 0.1 times, preferably 0.06 to 0.08 times the minimum sectional area of the air suction port.
8. The aircraft engine of claim 1, wherein: the spraying direction of the annular spraying port forms an included angle of 30-60 degrees with the axis of the accelerating spraying pipe; preferably 40-50 deg..
Technical Field
The invention relates to the field of heavy-load unmanned aerial vehicle engines, in particular to an aero-engine which is simple in structure, high in combustion efficiency, light in weight and low in maintenance cost.
Background
As is known, an aircraft engine is a key power part of an aircraft, and the technical level of the aircraft engine represents the comprehensive industrial basic strength of a country. At present, the main types of the aeroengine in China are as follows: piston engines, turbofan engines, turbojet engines, and ramjet engines are technically mainly pursuing states such as russia and the united states. Among them, the turbofan engine is widely used in military aircraft and commercial aircraft because of its good stability, large thrust, good fuel economy and relatively low noise. However, this type of engine is complex to manufacture, has many and precise parts, and has extremely high maintenance cost, which limits its wide use in light aircraft (such as heavy-duty unmanned aerial vehicles). At present, two types of engines of the light aircraft are mainly used, namely an oil-driven piston engine and a motor-driven blade propulsion engine. The oil-driven piston engine has high energy density and long endurance time, but has heavy weight, which severely limits the carrying capacity of the aircraft. The motor-driven blade propulsion engine mainly comprises a lithium battery power supply and a hydrogen fuel cell power supply as energy sources, and although the weight of the engine is obviously reduced compared with that of an oil-driven piston engine, the endurance capacity of the engine is weak, and the endurance time of the engine is not more than 2 hours. The hydrogen fuel cell has high requirement on hydrogen purity, so that the flying cost per kilometer is extremely high. Therefore, a novel engine with long endurance time, light dead weight, low fuel cost and low maintenance cost is urgently needed at present, and the blank of the power of a light aircraft (such as a heavy-load unmanned aerial vehicle) is filled.
The invention content is as follows:
the invention aims to solve the defects of the prior art and provides the aero-engine which is simple in structure, high in combustion efficiency, light in weight and low in maintenance cost.
The technical scheme adopted by the invention for solving the defects of the prior art is as follows:
an aircraft engine, characterized in that: the device is provided with a sleeve-shaped outer shell, an annular combustion groove is arranged on the inner wall of the outer shell, a spraying port adjusting cylinder capable of being adjusted forwards and backwards is arranged in the outer shell, an annular combustion cavity is enclosed by the spraying port adjusting cylinder and the annular combustion groove, a Venturi-tube-shaped accelerating jet pipe is arranged in the spraying port adjusting cylinder, and the front end part of the accelerating jet pipe is fixedly connected with the inner wall of the front end part of the spraying port adjusting cylinder; an ejection port baffle ring opposite to the front end of the accelerated jet pipe is arranged on the outer shell in front of the annular combustion groove, an arc-shaped flow guide wall is arranged on the inner wall of the front end of the annular combustion groove and the rear side wall of the ejection port baffle ring, the front end of the accelerated jet pipe is positioned in the rear side of the arc-shaped flow guide wall, an annular ejection port which is positioned at the front end of the accelerated jet pipe and ejects into the accelerated jet pipe is arranged between the accelerated jet pipe and the accelerated jet pipe, an air suction port is arranged on the outer shell in front of the accelerated jet pipe, and a fuel inlet; the rear part of the jet port adjusting cylinder is connected with a positioning flange in a threaded manner, and the positioning flange is connected with the outer shell through a bolt.
The jet port adjusting cylinder is connected with the inner wall of the outer shell on the rear side of the annular combustion groove in a sealing mode through threads. The screw pitch of the screw thread on the ejection port adjusting cylinder, which is hermetically connected with the inner wall of the outer shell at the rear side of the annular combustion groove, is different from the screw pitch of the screw thread at the rear part of the ejection port adjusting cylinder, which is connected with the positioning flange, and the positioning flange can lock the ejection port adjusting cylinder in the outer shell, so that the phenomenon that the size of the annular ejection port is changed due to the uncontrolled back and forth movement of the ejection port adjusting cylinder in the outer shell by vibration is avoided, and the speed (.
The ejection port adjusting cylinder is in mirror surface sealing contact with the outer shell on the rear side of the annular combustion groove. The axial position of the jet port adjusting cylinder on the outer shell can be changed by rotating the jet port adjusting cylinder, so that the distance between the front end of the accelerating jet pipe and the arc-shaped flow guide wall (the minimum sectional area of the annular jet port is adjusted) is adjusted, and the adjustment is simple and convenient.
The shell and the accelerated jet pipe are made of materials with low density, high temperature resistance, wear resistance, corrosion resistance, high elastic modulus and good toughness. Such as carbon fiber reinforced silicon carbide composite material, carbon fiber reinforced zirconium dioxide composite material, carbon fiber reinforced hafnium dioxide composite material, etc. in the carbon fiber ceramic composite material.
The accelerating injection pipe consists of an inlet section at the front part, a reducing section at the middle part and a widening section at the rear part, and the contour of the inner side wall of the accelerating injection pipe meets the Von-Karman curve.
The air suction inlet is in a horn shape with a small caliber end positioned in the front end of the acceleration jet pipe, and the minimum inner diameter of the middle part of the acceleration jet pipe is 0.2-0.5 times, preferably 0.25-0.35 times of the minimum inner diameter of the air suction inlet; the inner diameter of the rear end of the accelerating injection pipe is 0.5 to 0.9 times, preferably 0.6 to 0.8 times of the minimum inner diameter of the air suction inlet.
The sectional area of the annular ejection port in the present invention is 0.03 to 0.1 times, preferably 0.06 to 0.08 times the minimum sectional area of the air intake port.
The spraying direction of the annular spraying port (high-pressure gas) forms an included angle of 30-60 degrees with the axis of the accelerating spraying pipe; preferably 40-50 deg..
When the invention is used, the fuel inlet is connected with the fuel supply device through the fuel control device, the gas inlet is connected with the oxygen supply device through the gas control device, and the igniter is arranged on the ignition port. The fuel control device inputs fuel in the fuel supply device into the annular combustion chamber through the fuel inlet, the gas control device inputs oxygen or oxygen-containing gas into the annular combustion chamber through the gas inlet, the igniter ignites the fuel, high-temperature expansion gas generated in the annular combustion chamber is sprayed out into the accelerating injection pipe through the annular spraying port to drive air at the inlet section of the accelerating injection pipe to enter the tapered section, and the mixed air is accelerated and sprayed out from the tapered section to generate reverse thrust on the engine main body. The unmanned aerial vehicle has no movable part and light weight, and is suitable for heavy-load and light-load unmanned aerial vehicles; the cost of the engine is far lower than that of the prior turbofan engine or aviation motor, the endurance is long, no movable part is needed, the maintenance is simple, and the fuel economy is good (the fuel adopts methanol or ethanol or gasoline). The major structure adopts carbon pottery combined material, does not have forced cooling system, has alleviateed the engine dead weight greatly, and unmanned aerial vehicle duration is short for this engine has been solved, the fuel combustion is with high costs, the big problem of dead weight.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Detailed Description
The aircraft engine shown in fig. 1 is provided with a sleeve-shaped outer shell 4, an annular combustion groove 3 is arranged on the inner wall of the front part of the outer shell 4, a spraying
The shell and the accelerated jet pipe are made of materials with low density, high temperature resistance, wear resistance, corrosion resistance, high elastic modulus and good toughness. Such as carbon fiber reinforced silicon carbide composite material, carbon fiber reinforced zirconium dioxide composite material, carbon fiber reinforced hafnium dioxide composite material, etc. in the carbon fiber ceramic composite material.
The sectional area of the annular ejection port in the present invention is 0.03 to 0.1 times, preferably 0.06 to 0.08 times the minimum sectional area of the air intake port.
When the invention is used, the fuel inlet is connected with the fuel supply device (high-pressure fuel tank or fuel tank) through the fuel control device (valve or fuel pump), the gas inlet is connected with the oxygen supply device (oxygen tank or air) through the gas control device (valve or air pump), and the igniter (spark plug) is arranged on the ignition port. The fuel control device inputs fuel in the fuel supply device into the annular combustion chamber through the fuel inlet, the gas control device inputs oxygen or oxygen-containing gas into the annular combustion chamber through the gas inlet, the igniter ignites the fuel, high-temperature expansion gas generated in the annular combustion chamber is sprayed out into the acceleration injection pipe (from front to back) through the annular spray port to drive air at the inlet section of the acceleration injection pipe to enter the tapered section, and the mixed air is accelerated and sprayed out from the tapered section to generate reverse thrust on the engine main body.
The working principle of the invention is as follows: according to the continuous equation of hydrodynamics, wherein rho is the air density and t is the time U is the flow velocity. The flow velocity and the flow of the air in the cavity of the Laval nozzle meet the continuity equation. The high-temperature gas generated in the combustion chamber 1 expands and is sprayed into the inlet section 3 from the annular slit 2, so that the air at the periphery of the inlet section 3 is driven into the tapered section 4, and the mixed air is accelerated and sprayed out from the tapered section 5 (as shown in fig. 1). The momentum of the sprayed cold and hot mixed air is M = mV according to the momentum conservation, wherein M is the mass of the sprayed air per unit time, and V is the speed of the sprayed air. The counter-thrust generated by this momentum is: . Since the subsonic momentum aircraft engine has an overall weight that is about 58% lighter than a piston engine or an electric motor driven blade engine of the same thrust, the overall thrust (where m is m) 0Is the overall mass of the engine) will be about 62% higher than a conventional engine.
After the standard methanol fuel with the purity of 85% is selected and preheated to 55 ℃, the standard methanol fuel is input from a fuel inlet at the conveying speed of 45-60ml/min, meanwhile, enough oxygen is input from a gas inlet, and after an igniter is ignited, the instant maximum thrust 670N is generated. The enthalpy of combustion of methanol is 726.55KJ/mol, producing an effective power of about 20 KW. Thermal efficiency: 35 percent, which is improved by 8 to 10 percent compared with a piston type engine. The specific thrust is 4-6.5 times of that of a piston engine.
The unmanned aerial vehicle has no movable part and light weight, and is suitable for heavy-load and light-load unmanned aerial vehicles; the cost of the engine is far lower than that of the prior turbofan engine (or aviation motor), the endurance is long, no movable part exists, the maintenance is simple, and the fuel economy is good (the fuel adopts methanol or ethanol or gasoline). The major structure adopts carbon pottery combined material, does not have forced cooling system, has alleviateed the engine dead weight greatly, and unmanned aerial vehicle duration is short for this engine has been solved, the fuel combustion is with high costs, the big problem of dead weight.
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