CN115217701B - Porous fuel atomization mixing structure and method for air suction type pulse detonation engine - Google Patents
Porous fuel atomization mixing structure and method for air suction type pulse detonation engine Download PDFInfo
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- CN115217701B CN115217701B CN202210971440.6A CN202210971440A CN115217701B CN 115217701 B CN115217701 B CN 115217701B CN 202210971440 A CN202210971440 A CN 202210971440A CN 115217701 B CN115217701 B CN 115217701B
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- 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
- F02M61/00—Fuel-injectors not provided for in groups F02M39/00 - F02M57/00 or F02M67/00
- F02M61/16—Details not provided for in, or of interest apart from, the apparatus of groups F02M61/02 - F02M61/14
- F02M61/18—Injection nozzles, e.g. having valve seats; Details of valve member seated ends, not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
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Abstract
The invention provides a porous medium-based fuel atomization mixing structure of an air suction type pulse detonation engine, which adopts a mode that a porous medium is provided with fuel porous nozzles with the pore diameter of micron order and is made of an inner deep laser drilling metal material, so that the injection depth can be deepened, the problem of insufficient fuel penetration depth is solved, and the utilization rate of incoming air is improved. The oil gas is uniformly distributed due to large-area oil supply, and the quality of premixed gas is better. The invention can solve the defect of insufficient atomization performance caused by the existing fuel nozzle, and remarkably improves the fuel atomization performance of the pulse detonation engine, so that the pulse detonation engine can stably and continuously detonate based on liquid fuel.
Description
Technical Field
The invention relates to the field of pulse detonation engines, in particular to a fuel atomization mixing structure of an air suction type pulse detonation engine.
Background
In the propulsion system of an advanced aerospace vehicle, an air in the atmosphere is used as an oxidant, liquid fuel with high energy density, easy storage, good cooling performance and high safety is used as a propellant, and the liquid fuel is matched with the injection of fuel in a combustion chamber to realize the conversion of heat power through combustion so as to generate propulsion. But the PDE of the liquid fuel is used, the fuel must be atomized, evaporated and mixed before the combustion, so that a uniform and explosive mixed gas with a certain evaporation degree is formed.
The fuel atomization is the key for realizing good detonation performance of the pulse detonation engine, and compared with the conventional aeroengine, the pulse detonation engine has high requirements on the quality of mixed gas, (1) the ideal condition requires that SMD is less than or equal to 10 mu m, the fuel evaporation degree is more than 70%, and the oil-gas ratio is uniformly distributed; (2) Not only intermittent oil supply at a given frequency but also synchronization of oil supply and intake air are required.
At present, the air suction type pulse detonation engine adopts more atomizing nozzles, including a direct atomizing nozzle and a centrifugal nozzle, and the direct atomizing nozzle has a simple structure, can provide fuel with enough mass flow under the condition of lower pressure, but has poor atomizing effect; the centrifugal nozzle has better atomization quality, but requires higher fuel oil supply pressure, so that the atomization device is more complicated.
Disclosure of Invention
The invention aims to provide a porous medium-based fuel atomization mixing structure of an air-breathing pulse detonation engine, which can effectively improve the atomization performance of liquid fuel and improve the mixing quality of fuel and air.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the fuel atomization mixing structure of the air suction type pulse detonation engine based on the porous medium comprises a hollow mixing pipe which is arranged at the rear of an air inlet section of the engine, communicated with an air inlet cover and coaxially arranged, wherein a fuel inlet channel is arranged on the circumferential surface of the hollow mixing pipe in the normal direction, and a fuel porous nozzle is arranged at a fuel outlet of the fuel inlet channel in the cavity of the hollow mixing pipe;
the fuel oil porous nozzle is a tubular nozzle with two closed ends and a fuel oil cavity, the axis of the fuel oil cavity is parallel to the axis of the hollow mixing pipe, and the fuel oil inlet channel is communicated with the fuel oil cavity;
the end part of the fuel oil porous nozzle facing one side of the air inflow direction is a front edge end surface of the fuel oil porous nozzle, the front edge end surface is composed of a pair of inclined side wall surfaces with gradually increased angles along the air flow direction, so that the front edge end surface forms a wedge-shaped front edge end surface, and the inclined side wall surfaces are arranged in an extending manner along the radial direction of the hollow mixing pipe; one end of the fuel oil porous nozzle, which is opposite to the air inflow direction, is a vertical rear wall surface extending along the radial direction of the hollow mixing pipe; a connecting side wall surface is arranged between the pair of inclined side wall surfaces and the vertical rear wall surface, and the connecting side wall surface is matched with the pair of inclined side wall surfaces and the vertical rear wall surface to form a sealed fuel cavity; the section of the wedge-shaped front edge end surface can be in an isosceles or non-isosceles triangle shape, namely an inclined transition zone of high-speed wind flow is formed on the windward end surface of the fuel oil porous nozzle;
a plurality of normally arranged injection holes are uniformly distributed on the pair of inclined side wall surfaces, the vertical rear wall surface and the connecting side wall surface respectively;
the fuel oil porous nozzle is used for breaking the fuel oil impacting on the porous inner wall surface and having tangential velocity to rush out the fuel oil flowing through the porous outer wall surface along the axial direction, and then the fuel oil is further sheared and broken by the high-speed air flowing through the air inlet section, so that the fuel oil is torn into tiny oil drops, a fuel oil air mixing section is formed in a hollow mixing pipe at the rear end of the fuel oil porous nozzle, and the fuel oil air mixing section finally enters the knocking section to participate in combustion reaction.
Further, a mounting hole is formed in the normal direction of the peripheral surface of the hollow blending pipe, a fuel pipe is connected in the mounting hole through threads, a fuel outlet of the fuel pipe is communicated with a fuel cavity of the fuel porous nozzle, a closed fuel cavity is formed by the fuel pipe and the fuel cavity, and a fuel pipe channel of the fuel pipe is the fuel inlet channel.
Further, the fuel oil porous nozzle is a tubular nozzle in a cylinder, a cuboid or a cube, and the ratio of the radial extension depth of the fuel oil porous nozzle in the inner cavity of the hollow mixing pipe to the diameter of the hollow mixing pipe is 0.1-0.2.
Further, the aperture size of the injection hole is 0.001mm-0.003mm.
Further, the fuel oil porous nozzle is a cuboid tubular nozzle, a fuel oil cavity of the fuel oil porous nozzle is a closed cavity formed by matching and enclosing a pair of inclined side wall surfaces, a vertical rear wall surface, a connecting side wall surface, an upper wall surface and a lower wall surface, the upper wall surface is fixedly connected to the inner wall of a hollow blending pipe at the outlet of a fuel oil inlet channel, and the inlet of the fuel oil cavity is arranged on the upper wall surface and is communicated with the outlet of the fuel oil inlet channel;
the plurality of normally arranged injection holes are respectively and uniformly distributed on the pair of inclined side wall surfaces, the vertical rear wall surface, the connecting side wall surface, the upper wall surface and the lower wall surface.
Further, the inclined angle α of the pair of inclined side wall surfaces constituting the leading edge end surface is 15 to 20 degrees, the inside included angle β of the connecting end portion of the pair of inclined side wall surfaces is 30 to 50 degrees, and the outside included angle γ is 30 to 35 degrees.
Further, the air inlet section is an air channel surrounded by a conical air inlet cover with a gradually-reduced caliber, a central cone is arranged in the center of the air inlet cover, a plurality of air inlet channel baffles are arranged between the central cone and the air inlet cover in an extending manner in the axial direction, a plurality of air inlet channel baffles are arranged between the central cone and the air inlet cover in the circumferential direction, and every two air inlet channel baffles divide a cavity between the central cone and the air inlet cover into a plurality of air inlet channels;
the at least two fuel inlet channels are arranged on the same horizontal section of the circumference of the hollow mixing pipe at equal intervals, and are alternately arranged with the air inlet channel partition plates, so that the air flow resistance is reduced while large-area oil supply is ensured.
Further, the fuel inlet channels comprise four fuel inlet channels which are evenly distributed on the same plane of the hollow mixing pipe in the circumferential direction, the angle difference between every two fuel inlet channels is 90 degrees, and the angle difference between each fuel inlet channel and each air inlet channel partition board is 45 degrees, so that the incoming air in each two air inlet channel partition boards can fully utilize the fuel of one fuel inlet channel.
Further, the fuel oil porous nozzle is made of a metal material, and the injection hole is formed by laser drilling on the metal material.
The invention also provides an atomization blending method of the fuel atomization blending structure of the air suction type pulse detonation engine based on the porous medium, which comprises the following steps:
the method comprises the steps that liquid fuel enters a fuel cavity of a fuel porous nozzle through a fuel inlet channel by pressurizing a high-pressure gas cylinder, the injection pressure of the fuel porous nozzle is gradually increased, the fuel fills the whole fuel cavity through a fuel cavity inlet, the inner wall surface of the fuel porous nozzle is broken by impact under the action of oil pressure, and then the fuel is sprayed out through injection holes uniformly distributed on a pair of inclined side wall surfaces, a vertical rear wall surface, a connecting side wall surface, an upper wall surface and a lower wall surface of the fuel porous nozzle;
further, the injection pressure of the fuel oil porous nozzle is increased to 2-4Mpa, at this time, the fuel oil sprayed out of the porous nozzle 3 has circumferential speed and tangential speed at the outlet of the injection hole to form an atomized spray zone, the fuel oil is dispersed to the periphery in the atomized spray zone, and under the action of increasing injection speed, an atomized cone angle theta is formed on the wall surface of the outlet of the injection hole in the atomized spray zone, and the theta is 40-90 degrees;
simultaneously, large-area fuel injection is formed by injecting a plurality of injection holes, and under the shearing and crushing effects of high-speed air flowing axially, the fuel injected by the plurality of injection holes forms a plurality of mixing eddies in a gas-oil mixing flow field and a protective film on the outer wall surface of a porous nozzle on the outlet wall surface of the injection hole, wherein the protective film is a gaseous oil film attached to the outer wall surface of the porous nozzle after the fuel is sprayed and atomized from the injection hole;
the fuel injection device further comprises a flow guide of high-speed air axially flowing through the front edge end face of the fuel porous nozzle, and a mixing vortex formed on the outlet wall face of the injection hole is promoted and increased, so that the mixing vortex forms omni-directional fuel injection approximate to a hemispherical space, and a blending zone is formed on the rear side wall of the fuel porous nozzle, and full blending of fuel and air is realized.
The beneficial effects of the invention are as follows: the invention adopts the structure of the inner deep porous nozzle to atomize the liquid fuel, thereby enhancing the mixing of the fuel and the air. The purpose of fuel atomization is to increase the specific surface area of fuel so as to accelerate the evaporation of fuel and facilitate the mixing of fuel and air, thereby ensuring the normal operation of combustion. Therefore, in the structure, a porous medium material with large porosity and large specific surface area is adopted as an atomization nozzle, the effective injection depth of the nozzle is extended by a physical method, the injection depth can be deepened by using the arrangement of inner deep nozzles, the injection depth of the fuel is low due to high air inflow speed and large momentum, and the fuel is smaller in momentum, so that the shearing atomization effect is weaker, the problem of insufficient penetration depth of the fuel is solved, the utilization rate of inflow air is improved, and the problem that the inflow air cannot be fully utilized due to the fact that fuel injection is concentrated near a wall surface is avoided.
On the other hand, as the nozzle is of a wedge-shaped front edge structure, the generation of vortex in a flow field can be promoted, and the mixing of fuel oil and air is enhanced;
meanwhile, the fuel is injected into the nozzle holes along the air flow direction and the radial direction, the mixture of the fuel and the air is improved by large-area pore injection, the omni-directional fuel injection similar to a hemispherical space is realized in a short distance, the atomizing cone angle of the nozzle is large, and the fuel atomizing performance is good;
when the flying situation of high Mach number, the nozzle is exposed to supersonic air flow, the front edge of the nozzle is subjected to severe pneumatic heating due to the fact that the total temperature of incoming flow is high, and the heat flux density is high, so that the inner deep nozzle is adopted to serve as an atomizing nozzle to atomize fuel on the one hand, on the other hand, a porous medium is used as a sweating cooling matrix, the porous medium is used as the atomizing nozzle, the sprayed fuel flows backwards along the wall surface under the action of the incoming flow, a protective film with lower temperature is formed on the surface of the nozzle, and the problem of overhigh temperature caused by high heat flux near the standing point of the front edge is solved.
Drawings
FIG. 1 is an axial cross-sectional view of an atomizing structure of an aspirated pulse detonation engine of the present invention;
FIG. 2 is a semi-sectional isometric view of an atomizing structure of an aspirated pulse detonation engine of the present invention;
FIG. 3 is a schematic view of a fuel porous nozzle according to the present invention;
FIG. 4 is a schematic cross-sectional view of a fuel multi-orifice nozzle of the present invention;
FIG. 5 is a schematic rear view of an atomizing structure of an aspirated pulse detonation engine in accordance with the present invention;
FIG. 6 is a schematic view of omni-directional fuel injection in the hemispherical space of the fuel porous nozzle of the present invention;
FIG. 7 is a schematic view of the rear cross-sectional omnidirectional fuel injection of the fuel multi-orifice nozzle of the present invention;
FIG. 8 is a schematic view of the wedge structure of the fuel porous nozzle of the present invention.
In the figure, 1-hollow mixing pipe, 11-air inlet hood, 12-central cone, 13-air inlet partition, 14-air inlet, 2-fuel inlet channel, 21-mounting hole, 22-fuel pipe, 3-fuel porous nozzle, 31-fuel cavity, 32-inclined side wall, 33-vertical back wall, 34-connecting side wall, 35-upper wall, 36-lower wall, 37-fuel cavity inlet, 38-front edge end, 4-fuel air mixing section and 5-injection hole.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
The invention provides a structure utilizing a porous medium as an atomization device, and aims at solving the problem that the atomization performance of an atomization nozzle in the existing air-breathing pulse detonation engine is poor, so that the mixing effect of fuel and oxidant is poor.
The invention aims to effectively improve the atomization performance of liquid fuel and improve the mixing quality of fuel and air. Specifically, the atomizing structure is required to meet the following requirements:
1) Compared with the traditional atomizing nozzle, the atomizing nozzle with the structure has a large atomizing cone angle, and can realize hemispherical space omnidirectional injection in a short distance;
2) The atomizing nozzle with the structure has the advantage of flexible control of the size of the porous pores.
In order to achieve the above object, the present invention provides the following embodiments:
example 1: as shown in fig. 1-5, the fuel atomization mixing structure of the air suction type pulse detonation engine based on the porous medium comprises a hollow mixing pipe 1 which is communicated with an air inlet cover 11 and coaxially arranged at the rear part of an air inlet section of the engine, wherein a fuel inlet channel 2 is arranged on the circumferential surface of the hollow mixing pipe 1 in the normal direction, and a fuel outlet of the fuel inlet channel 2 is provided with a fuel porous nozzle 3 in the cavity of the hollow mixing pipe 1; the circumference of the hollow mixing pipe 1 is provided with a mounting hole 21 in the normal direction, a fuel pipe 22 is connected in the mounting hole 21 through threads, a fuel outlet of the fuel pipe 22 is communicated with a fuel cavity 31 of the fuel porous nozzle 3, the fuel pipe 22 and the fuel cavity 31 form a closed fuel cavity, and a fuel pipe channel of the fuel pipe 22 is the fuel inlet channel 2;
the fuel oil porous nozzle 3 is a tubular nozzle with two closed ends and provided with a fuel oil cavity 31, the axis of the fuel oil cavity 31 is parallel to the axis of the hollow mixing pipe 1, and the fuel oil inlet channel 2 is communicated with the fuel oil cavity 31; the fuel oil porous nozzle 3 is a tubular nozzle with a cuboid shape, the fuel oil cavity 31 of the fuel oil porous nozzle 3 is a closed cavity formed by matching a pair of inclined side wall surfaces 32, a vertical rear wall surface 33, a connecting side wall surface 34, an upper wall surface 35 and a lower wall surface 36, the upper wall surface 35 is fixedly connected to the inner wall of the hollow mixing pipe 1 at the outlet of the fuel oil inlet channel 2, and the fuel oil cavity inlet 37 is arranged on the upper wall surface 35 and is communicated with the outlet of the fuel oil inlet channel 2; the inclined angle α of the pair of inclined side wall surfaces 32 constituting the leading edge end surface 38 is 15 to 20 degrees, the inside included angle β of the connecting end portion of the pair of inclined side wall surfaces 32 is 30 to 50 degrees, and the outside included angle γ is 30 to 35 degrees; the ratio of the radial extension depth of the fuel oil porous nozzle 3 in the inner cavity of the hollow mixing pipe 1 to the diameter of the hollow mixing pipe 1 is 0.1-0.2.
The end of the fuel oil porous nozzle 3 facing the air inflow direction is a front edge end surface 38 of the fuel oil porous nozzle 3, the front edge end surface is composed of a pair of inclined side wall surfaces 32 with gradually increased angles along the air flow direction, the front edge end surface 38 forms a wedge-shaped front edge end surface, and the inclined side wall surfaces 32 are arranged in an extending manner along the radial direction of the hollow mixing pipe 1; one end of the fuel oil porous nozzle 3 facing away from the air inflow direction is a vertical rear wall surface 33 extending along the radial direction of the hollow mixing pipe 1; a connecting side wall surface 34 is arranged between the pair of inclined side wall surfaces 32 and the vertical rear wall surface 33, and the connecting side wall surface 34 is matched with the pair of inclined side wall surfaces 32 and the vertical rear wall surface 33 to enclose a sealed fuel cavity 31;
a plurality of injection holes 5 which are arranged in a normal direction are uniformly distributed on the pair of inclined side wall surfaces 32, the vertical rear wall surface 33 and the connecting side wall surface 34 respectively; the aperture size of the injection hole 5 is 0.001mm-0.003mm.
The fuel oil porous nozzle 3 is used for breaking the fuel oil impacting on the porous inner wall surface and rushing out to the porous outer wall surface with tangential velocity, and then the fuel oil is further sheared and broken by the high-speed air which enters by the air inlet section and flows through the air inlet section along the axial direction, so that the fuel oil is torn into tiny oil drops, a fuel oil air mixing section is formed in the hollow mixing tube 1 at the rear end of the fuel oil porous nozzle 3, passes through the fuel oil air mixing section, and finally enters the knocking section to participate in combustion reaction.
The plurality of injection holes 5 are uniformly distributed on the pair of inclined side wall surfaces 32, the vertical rear wall surface 33, the connecting side wall surface 34, the upper wall surface 35 and the lower wall surface 36. The fuel oil porous nozzle is made of a metal material, and the injection hole 5 is formed by laser drilling on the metal material.
The air inlet section is an air channel surrounded by a conical air inlet cover 11 with a gradually-reduced caliber, a central cone 12 is arranged in the center of the air inlet cover 11, a plurality of air inlet partition plates 13 extend upwards in the axial direction between the central cone 12 and the air inlet cover 11, a plurality of air inlet partition plates 13 are arranged in the circumferential direction between the central cone 12 and the air inlet cover 11, and the air inlet partition plates 13 divide a cavity between the central cone 12 and the air inlet cover 11 into a plurality of air inlet channels 14; the at least two fuel inlet channels 2 are arranged on the same horizontal section of the circumference of the hollow mixing pipe 1 at equal intervals, and are alternately arranged with the air inlet channel partition plates 13 at the same time, so that the air flow resistance is reduced while the large-area oil supply is ensured. The fuel inlet channels 2 comprise four fuel inlet channels and are evenly distributed on the same plane of the hollow mixing pipe 1, 90 degrees are arranged between every two fuel inlet channels 2, and the angle difference between the fuel inlet channels and the air inlet channel partition plates is 45 degrees, so that the incoming air in every two air inlet channel partition plates can fully utilize the fuel of one fuel inlet channel.
The fuel oil and air mixing pipe 1 is a place where fuel oil and air are atomized and mixed, the head of the mixing section is welded with the rear end face of the air inlet section in a sealing way, and the tail of the mixing section can be connected with the detonation pipe.
Example 2: as shown in fig. 6-8, the invention also provides an atomization blending method of the fuel atomization blending structure of the air suction type pulse detonation engine based on the porous medium, which comprises the following steps:
the liquid fuel enters the fuel cavity 31 of the fuel porous nozzle 3 from the fuel inlet channel 2 through the pressurization of the high-pressure gas cylinder, the injection pressure of the fuel porous nozzle 3 is gradually increased, the fuel fills the whole fuel cavity 31 through the fuel cavity inlet 37, the inner wall surface of the fuel porous nozzle 3 is broken by impact under the action of oil pressure, and then the fuel is sprayed out through the injection holes 5 uniformly distributed on the pair of inclined side wall surfaces 32, the vertical rear wall surface 33, the connecting side wall surface 34, the upper wall surface 35 and the lower wall surface 36 of the fuel porous nozzle 3;
the injection pressure of the fuel oil porous nozzle 3 is increased to 2-4Mpa, at the moment, the fuel oil sprayed by the porous nozzle 3 has circumferential speed and tangential speed at the outlet of the injection hole 5 to form an atomization spray zone, the fuel oil is spread out to the periphery in the atomization spray zone, and under the action of increasing injection speed, an atomization cone angle theta is formed on the wall surface of the outlet of the injection hole 5 in the atomization spray zone, and the theta is 40-90 degrees;
meanwhile, as shown in fig. 7, the injection of the plurality of injection holes 5 forms large-area fuel injection, the fuel injected from the plurality of injection holes 5 forms a plurality of mixing eddies in a gas and oil mixing flow field and a protective film on the outer wall surface of the porous nozzle 3 on the outlet wall surface of the injection hole 5 under the shearing and crushing action of high-speed air flowing through the axial direction, and the protective film is a gaseous oil film attached to the outer wall surface of the fuel porous nozzle 3 after the fuel is atomized from the injection holes 5;
also, as shown in fig. 8, the leading edge end surface 38 of the fuel porous nozzle 3 guides the high-speed air flowing axially, and promotes and increases the mixing vortex formed on the outlet wall surface of the injection hole 5, so that the multiple mixing vortices form omni-directional fuel injection with approximately hemispherical space, and a blending zone is formed on the rear side wall of the fuel porous nozzle 3, thereby realizing the full blending of the fuel and the air.
Example 3 is the same as example 1, except that the fuel porous nozzle (3) is a tubular nozzle in the shape of a cylinder or a rectangular parallelepiped or a square, and these two structures are structures that are easily conceived and used by those skilled in the art and are not shown.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The fuel atomization mixing structure of the air suction type pulse detonation engine based on the porous medium is characterized by comprising a hollow mixing pipe (1) which is communicated with an air inlet cover (11) and coaxially arranged at the rear part of an air inlet section of the engine, wherein a fuel inlet channel (2) is arranged on the circumferential surface of the hollow mixing pipe (1) in the normal direction, and a fuel porous nozzle (3) is arranged at a fuel outlet of the fuel inlet channel (2) in a pipe cavity of the hollow mixing pipe (1);
the fuel oil porous nozzle (3) is a tubular nozzle with two closed ends and provided with a fuel oil cavity (31), the axis of the fuel oil cavity (31) is parallel to the axis of the hollow mixing pipe (1), and the fuel oil inlet channel (2) is communicated with the fuel oil cavity (31);
the end part of the fuel oil porous nozzle (3) facing one side of the air inflow direction is a front edge end surface (38) of the fuel oil porous nozzle (3), the front edge end surface is composed of a pair of inclined side wall surfaces (32) with gradually increased angles along the air flow direction, the front edge end surface (38) forms a wedge-shaped front edge end surface, and the inclined side wall surfaces (32) are arranged in an extending manner along the radial direction of the hollow mixing pipe (1); one end of the fuel oil porous nozzle (3) facing away from the air inflow direction is a vertical rear wall surface (33) extending along the radial direction of the hollow mixing pipe (1); a connecting side wall surface (34) is arranged between the pair of inclined side wall surfaces (32) and the vertical rear wall surface (33), and the connecting side wall surface (34) is matched with the pair of inclined side wall surfaces (32) and the vertical rear wall surface (33) to form a sealed fuel cavity (31);
a plurality of normally arranged injection holes (5) are uniformly distributed on the pair of inclined side wall surfaces (32), the vertical rear wall surface (33) and the connecting side wall surface (34) respectively;
the fuel oil porous nozzle (3) is used for breaking the fuel oil impacting on the porous inner wall surface and having tangential velocity to rush out the fuel oil flowing through the porous outer wall surface along the axial direction, and then the fuel oil is further sheared and broken by the high-speed air flowing through the air inlet section, so that the fuel oil is torn into tiny oil drops, a fuel oil air blending section is formed in the hollow blending tube (1) at the rear end of the fuel oil porous nozzle (3), and the fuel oil air blending section finally enters the knocking section to participate in combustion reaction.
2. The porous medium-based fuel atomization mixing structure of the air suction type pulse detonation engine, as set forth in claim 1, is characterized in that a mounting hole (21) is provided on the circumferential surface of the hollow mixing pipe (1) in the normal direction, a fuel pipe (22) is connected in the mounting hole (21) through threads, a fuel outlet of the fuel pipe (22) is communicated with a fuel cavity (31) of the fuel porous nozzle (3), the fuel pipe (22) and the fuel cavity (31) form a closed fuel cavity, and a fuel pipe channel of the fuel pipe (22) is the fuel inlet channel (2).
3. The porous medium-based fuel atomization mixing structure of the air suction type pulse detonation engine, as claimed in claim 1, wherein the fuel porous nozzle (3) is a cylindrical or cuboid or square tubular nozzle, and the ratio of the radial extension depth of the fuel porous nozzle (3) in the inner cavity of the hollow mixing pipe (1) to the diameter of the hollow mixing pipe (1) is 0.1-0.2.
4. The porous-medium-based fuel atomization blending structure of an air-breathing pulse detonation engine, as claimed in claim 1, wherein the aperture size of the injection hole (5) is 0.001mm-0.003mm.
5. A porous medium-based fuel atomization mixing structure of an air suction type pulse detonation engine, as claimed in claim 3, wherein the fuel porous nozzle (3) is a cuboid tubular nozzle, the fuel cavity (31) of the fuel porous nozzle (3) is a closed cavity surrounded by a pair of inclined side wall surfaces (32), a vertical rear wall surface (33), a connecting side wall surface (34), an upper wall surface (35) and a lower wall surface (36) in a matched manner, the upper wall surface (35) is fixedly connected to the inner wall of a hollow mixing pipe (1) at the outlet of a fuel inlet channel (2), and the fuel cavity inlet (37) is arranged on the upper wall surface (35) and is communicated with the outlet of the fuel inlet channel (2);
the plurality of normally arranged injection holes (5) are uniformly distributed on the pair of inclined side wall surfaces (32), the vertical rear wall surface (33), the connecting side wall surface (34), the upper wall surface (35) and the lower wall surface (36).
6. The porous-medium-based fuel atomizing and blending structure for an air-breathing pulse detonation engine, as set forth in claim 1, characterized in that an inclination angle α of a pair of inclined side wall surfaces (32) constituting the leading edge end surface (38) is 15 to 20 degrees, and an inside included angle β of a connecting end portion of the pair of inclined side wall surfaces (32) is 30 to 50 degrees, and an outside included angle γ is 30 to 35 degrees.
7. The porous medium-based fuel atomization mixing structure of the air-breathing pulse detonation engine, as claimed in claim 1, characterized in that the air inlet section is an air passage surrounded by a conical air inlet cover (11) with a tapered caliber, a central cone (12) is arranged in the center of the air inlet cover (11), a plurality of air inlet partition plates (13) are arranged between the central cone (12) and the air inlet cover (11) in an extending manner in the axial direction, the plurality of air inlet partition plates (13) are arranged between the central cone (12) and the air inlet cover (11) in the circumferential direction, and the air inlet partition plates (13) divide a cavity between the central cone (12) and the air inlet cover (11) into a plurality of air inlet channels (14);
at least two fuel inlet channels (2) are arranged on the same horizontal section of the circumference of the hollow mixing pipe (1) at equal intervals, and the fuel inlet channels (2) and the air inlet channel partition plates (13) are alternately arranged at the same time so as to ensure large-area oil supply and reduce air flow resistance.
8. The porous medium-based fuel atomization mixing structure of the air suction type pulse detonation engine, as claimed in claim 7, wherein the fuel inlet channels (2) comprise four fuel inlet channels which are evenly distributed on the same plane of the hollow mixing pipe (1), 90 degrees are arranged between every two fuel inlet channels (2), and the angle difference between the fuel inlet channels and the air inlet channel partition plates is 45 degrees, so that the fuel of one fuel inlet channel can be fully utilized by the inflow air in every two air inlet channel partition plates.
9. A porous media based fuel atomizing and blending structure for an air-breathing pulse detonation engine as claimed in any one of claims 1 to 8 wherein said fuel porous nozzle is made of a metallic material and said injection holes (5) are formed in the metallic material by laser drilling.
10. A method of atomizing and blending a porous medium-based fuel atomizing and blending structure for an air-breathing pulse detonation engine as claimed in any one of claims 1 to 9, comprising the steps of:
the liquid fuel enters a fuel cavity (31) of a fuel porous nozzle (3) from a fuel inlet channel (2) through pressurization of a high-pressure gas cylinder, injection pressure of the fuel porous nozzle (3) is gradually increased, the whole fuel cavity (31) is filled with the fuel through a fuel cavity inlet (37), the inner wall surface of the fuel porous nozzle (3) is broken due to impact under the action of oil pressure, and then the fuel is sprayed out through injection holes (5) uniformly distributed on a pair of inclined side wall surfaces (32), a vertical rear wall surface (33), a connecting side wall surface (34), an upper wall surface (35) and a lower wall surface (36) of the fuel porous nozzle (3);
the injection pressure of the fuel oil porous nozzle (3) is increased to 2-4Mpa, at the moment, the fuel oil sprayed by the porous nozzle (3) has circumferential speed and tangential speed at the outlet of the injection hole (5) to form an atomization spray zone, the fuel oil is dispersed to the periphery in the atomization spray zone, and under the action of increasing injection speed, an atomization cone angle theta is formed on the wall surface of the outlet of the injection hole (5) in the atomization spray zone, and the theta is 40-90 degrees;
simultaneously, large-area fuel injection is formed by injecting a plurality of injection holes (5), and under the shearing and crushing effects of high-speed air flowing through the injection holes (5), fuel oil injected by the injection holes (5) forms a plurality of mixing eddies in a gas-oil mixing flow field and a protective film on the outer wall surface of a porous nozzle (3) on the wall surface of an outlet of the injection hole (5), wherein the protective film is a gaseous oil film attached to the outer wall surface of the fuel oil porous nozzle (3) after the fuel oil is sprayed and atomized from the injection holes (5);
the front edge end surface (38) of the fuel oil porous nozzle (3) guides high-speed air axially flowing through, promotes and increases the mixing vortex formed on the outlet wall surface of the injection hole (5), so that the plurality of mixing vortices form omni-directional fuel injection approximate to hemispherical space, and a blending zone is formed on the rear side wall of the fuel oil porous nozzle (3), and the full blending of fuel oil and air is realized.
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| CN111305972A (en) * | 2020-03-28 | 2020-06-19 | 西北工业大学 | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation |
| CN114001374A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber |
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| JP4456528B2 (en) * | 2005-05-24 | 2010-04-28 | ヤンマー株式会社 | Premixed compression self-ignition internal combustion engine |
| CN101776026B (en) * | 2010-02-04 | 2011-11-02 | 西北工业大学 | Air inlet of air-breathing pulse detonation engine |
| CN102174913A (en) * | 2011-03-03 | 2011-09-07 | 西北工业大学 | Pulse detonation engine with ejector and method for processing main detonation tube |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111305972A (en) * | 2020-03-28 | 2020-06-19 | 西北工业大学 | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation |
| CN114001374A (en) * | 2021-11-12 | 2022-02-01 | 西安热工研究院有限公司 | Gas-liquid two-phase dual-fuel rotary detonation combustion chamber |
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