CN110439691B - Plasma duty flame igniter based on afterburner of aero-engine - Google Patents

Abstract

The invention discloses a plasma duty flame igniter based on an aero-engine afterburner, comprising a flame stabilizer and an embedded cathode assembly. The embedded cathode assembly includes a connecting sleeve, a cathode casing, a transverse insulating tube, Y-shaped cathode, guide rod casing, longitudinal insulating tube and conducting rod, the connecting sleeve sleeve is threadedly connected to the cathode casing, the right end of the connecting sleeve is welded with the flame stabilizer, the left middle part of the transverse insulating tube is set in the cathode casing, Y The closed end of the cathode is arranged in the transverse insulating tube; the guide rod casing is vertically arranged on the top left side of the cathode casing, the upper and middle part of the longitudinal insulating tube is set in the guide rod casing, and the lower end of the longitudinal insulating tube passes through the cathode casing and is The end is located in the right part of the transverse insulating tube, and the upper middle part of the conducting rod is arranged in the longitudinal insulating tube. The invention solves the problems of bad working environment and complex structure of the existing aero-engine afterburner, which are not conducive to stable and rapid ignition and continuous organized combustion.

Description

Plasma duty flame igniter based on afterburner of aero-engine

technical field

The invention belongs to the technical field of aerodynamic ignition, in particular to a plasma duty flame igniter based on an afterburner of an aeroengine.

Background technique

Although the mass of the afterburner of the aero-engine only accounts for 20% of the total mass of the engine, it is an important component to improve the thrust of the engine. The turbojet engine is equipped with an afterburner, and the thrust increase ratio can reach 40% to 50%; the thrust increase ratio of the turbofan engine with an afterburner can reach 60% to 70% or even higher. The use of an afterburner can greatly increase the unit head-on thrust and thrust-to-weight ratio of the engine, comprehensively improve the maneuverability of the aircraft, expand the flight envelope, and improve the air superiority capability of the fighter. Due to the harsh working environment of the afterburner, the gas pressure is low, the flow rate is high, and the flow is extremely unstable, which is not conducive to ignition and tissue combustion. The ignited mixture needs to be in a long cylinder to complete the combustion process. Only 85% to 90% of the heat content of the fuel can be converted into useful heat energy, and the rest is either discharged from the engine because the fuel droplets are too late to burn, or lost through the cylinder to dissipate heat. Therefore, improving the afterburner efficiency is of great significance for reducing fuel consumption and increasing thrust.

At present, there are three ways to ignite the afterburner of aero-engines: nozzle ignition, flare ignition and catalytic ignition. Several existing ignition methods have shortcomings: the traditional nozzle ignition system adopts electric spark ignition, the ignition delay time is long, and the ignition stability is poor; When it is subjected to strong disturbance, a large number of ignition tests should be performed accordingly when debugging the afterburner; the ignition device of the catalytic ignition system is simple in structure, light in weight, and easy to ignite, but the platinum-rhodium wire is expensive and easily polluted and fails. affect its reliability.

In recent years, the plasma ignition technology has gradually attracted the attention and attention of researchers in the field of aerodynamics. Plasma ignition and combustion is the process of using gas discharge to form a local high temperature area and excite a large number of active particles to achieve rapid ignition of combustible gas mixture or ignition and combustion. The mechanism is mainly manifested as three effects: thermal effect, chemical effect and aerodynamic effect. The advantages brought by plasma ignition support include: widening the ignition boundary, shortening the ignition delay time, improving ignition reliability, improving combustion efficiency, and reducing fuel consumption. Therefore, plasma ignition is one of the effective technical ways to expand the ignition boundary and improve the stable combustion range.

Sliding arc discharge is a discharge method that can generate non-equilibrium plasma at atmospheric pressure. The basic principle is that a strong electric field is applied to a pair or more electrodes, and an air flow is passed between the electrodes to generate an initial discharge channel between the electrodes. These arcs slide along the direction of the channel under the action of the air flow, thereby forming Sliding discharge. Several typical forms of sliding arc discharge are two-dimensional sliding arc discharge, rotary sliding arc discharge, and multi-electrode sliding arc discharge. The gliding arc discharge can generate continuous and stable non-equilibrium low-temperature plasma, and the collision of electrons and neutral molecules in the plasma will cause the dissociation, excitation and ionization of the molecules, resulting in a large number of active particles and groups, with relatively high performance. High chemical activity. Therefore, the gliding arc discharge plasma technology has broad application prospects in the aviation field.

SUMMARY OF THE INVENTION

The purpose of the present invention is to overcome the deficiencies in the above-mentioned prior art, provide a kind of plasma duty flame igniter based on aero-engine afterburner, effectively solve the problem that the existing aero-engine afterburner has a bad working environment and a complicated structure , It is not conducive to the problem of stable and rapid ignition and continuous organized combustion. It realizes the stable and rapid ignition and continuous combustion support of the afterburner, greatly optimizes the ignition method of the afterburner, and conducts secondary combustion of the remaining gas in the main combustion chamber. Realize the clean emission of exhaust gas.

In order to achieve the above object, the technical scheme adopted in the present invention is: a kind of plasma duty flame igniter based on aero-engine afterburner, it is characterized in that: comprising a flame stabilizer and an embedded cathode combination installed on the flame stabilizer The number of the embedded cathode assembly is at least one, and the embedded cathode assembly includes a connecting sleeve, a cathode casing, a transverse insulating tube, a Y-shaped cathode, a guide rod casing, a longitudinal insulating tube, and a conducting conductor. rod, the connecting sleeve is sleeved on the outer wall of the right part of the cathode casing and the inner wall of the connecting sleeve is threadedly connected with the outer wall of the cathode casing, and the right end of the connecting sleeve is welded with the small end of the flame stabilizer, so The left middle part of the lateral insulating tube is arranged in the cathode casing, the right end of the lateral insulating tube is located outside the cathode casing, the closed end of the Y-shaped cathode is arranged in the lateral insulating tube, and the open end of the Y-shaped cathode is located in the lateral insulating tube. Outside the tube, the open end of the Y-shaped cathode is located in the flame stabilizer; the guide rod casing is vertically arranged on the top of the left side of the cathode casing, and the upper and middle part of the longitudinal insulating tube is set in the guide rod casing. The lower end of the longitudinal insulating tube passes through the cathode casing and the end is located in the right part of the horizontal insulating tube, the upper and middle part of the conducting rod is arranged in the longitudinal insulating tube, and the lower end of the conducting rod passes through the lateral insulating tube in turn. The right part and the closed end of the Y-shaped cathode; the central axis of the flame stabilizer, the connecting sleeve, the cathode casing, the transverse insulating tube and the Y-shaped cathode are the same central axis and the central axis is the first central axis. The central axis of the guide rod housing, the longitudinal insulating tube and the conduction guide rod is the same central axis, and the central axis is the second central axis.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the shape of the cathode casing is cylindrical, and the cathode casing is located on the outer wall near the open end and at the position corresponding to the connection sleeve A first external thread is provided, and the first external thread cooperates with the first internal thread thread arranged through the inner wall of the connecting sleeve; the top of the cylinder bottom of the cathode casing is 3mm to 5mm upwards with a single-sided penetration Small round holes, the diameter of the small round holes penetrating through one side is 3 mm to 5 mm.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the single-sided through-hole small circular hole is opened at the top of the cylinder bottom of the cathode casing at 4 mm upward, and the single-sided through-through small circular hole The diameter of the hole is 4mm.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the cross-sectional shape of the lateral insulating tube is circular, the outer right part of the lateral insulating tube is provided with a boss, and the lateral insulating tube is provided with a boss. The right part of the lateral insulating tube is a boss base, the outer diameter of the boss base is equal to the outer diameter of the cathode casing, and the stepped end face of the boss base is flush with the right end face of the cathode casing; the lateral insulation The tube is provided with a cylindrical hole and a small three-dimensional groove in sequence from the right side of the boss base along the axis, and the cylindrical hole and the small three-dimensional groove are connected; a circle is opened on the top of the left side of the horizontal insulating tube and corresponding to the position of the small round hole. The left side of the transverse insulating tube is provided with a side circular hole communicating with both the circular groove and the small three-dimensional groove, and the side circular hole is located between the circular groove and the small three-dimensional groove.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the Y-shaped cathode comprises a V-shaped groove body, a straight section rod and a three-dimensional head which are arranged in sequence from right to left, and the V-shaped cathode is arranged in sequence from right to left. The groove body, the straight section rod and the three-dimensional head are integrally formed, and the two groove pieces of the V-shaped groove body are arranged symmetrically up and down, and the angle formed by the two groove pieces of the V-shaped groove body is a and a is 43°～47°, the width of the slot piece is W and W is 8mm～12mm, and the three-dimensional head is provided with a head through hole that runs through the upper and lower sides; the size of the straight rod is the same as that of the cylindrical hole. The size of the straight rod is the same as that of the cylindrical hole, and the straight rod is inserted into the cylindrical hole and fits with the cylindrical hole; the size of the three-dimensional head is consistent with the size of the small three-dimensional groove, and the shape of the three-dimensional head The shape of the three-dimensional head is the same as that of the small three-dimensional groove, and the three-dimensional head is inserted into the small three-dimensional groove and is clearance-fitted with the small three-dimensional groove.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the angle formed by the two groove pieces of the V-shaped groove body is a and a is 45°, and the width of the groove piece is W and W is 10mm.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the energized guide rod comprises an energized base and an energized straight rod arranged in sequence from top to bottom, and the energized base and the energized straight rod are: One-piece molding structure, the outer shape of the energized base and the energized straight rod are cylindrical, the upper part of the energized base is provided with a connecting circular hole along the axial direction, and the inner wall of the connecting circular hole is provided with a second internal thread and is energized The base is threaded with the power cable of the engine through the second internal thread.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the longitudinal insulating tube is an insulating tube with a secondary boss on the outside and the boss located on the upper part is a primary boss. The cross-sectional shape of the longitudinal insulating tube is circular, and the longitudinal insulating tube is provided with a lower cylindrical hole, an upper cylindrical hole and a large circular hole in sequence from bottom to top in the axial direction, and the upper cylindrical hole is connected with the lower cylindrical hole and the large circular hole. , the depth of the lower cylindrical hole is the first-level boss; the diameter of the lower cylindrical hole and the energized straight rod are equal, the size of the upper cylindrical hole and the energized base are the same, and the energized guide rod is from top to bottom After being inserted into the longitudinal insulating tube in turn and closely matched with the longitudinal insulating tube, the energized base is located in the upper cylindrical hole, and the lower end of the energized straight rod passes through the lower cylindrical hole and passes through the side round hole and finally threaded with the head through hole connection, the lower end face of the energized straight rod is flush with the lower end face of the head through hole, the energized straight rod is clearance fit with the side round hole and the diameter of the energized straight rod is consistent with the side round hole, the large round hole It mates with the power cable of the engine.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the outer shape of the guide rod casing is a cylindrical boss shape, and the guide rod casing is provided with longitudinal insulation along the axial direction. The three-stage stepped hole with the same shape of the tube, the longitudinal insulating tube is inserted into the three-stage stepped hole in sequence from top to bottom and is closely matched with the guide rod housing, and the lower end of the longitudinal insulating tube passes through one side through the small hole in turn. The circular holes and circular grooves are in clearance fit with the unilateral small circular holes and circular grooves. The lower end of the rod casing is abutted against the top of the left side of the cathode casing, and the upper left side of the connecting sleeve is arranged in close proximity to the right side of the lower end of the guide rod casing.

The above-mentioned plasma duty flame igniter based on aero-engine afterburner is characterized in that: the number of the embedded cathode assemblies is three, and the three embedded cathode assemblies are evenly distributed on the flame stabilizer .

Compared with the prior art, the present invention has the following advantages:

1. The present invention is simple in structure and small in size, and cleverly uses the inner wall of the flame stabilizer as the anode of the igniter, and designs the cathode into the shape of a Y-shaped arc surface. Therefore, it is easy to form the minimum discharge distance and effectively widen the ignition time. range, greatly enhances ignition stability and improves the reliability of rapid ignition of the afterburner in harsh environments.

2. The present invention designs the breakdown area in the backflow area of the oil-gas mixture of the flame stabilizer, making full use of the small flow rate of the gas in the backflow area which is easy to ignite, and the working medium is the oil-gas mixture, which does not require an additional gas supply system.

3. The present invention relates to the plasma ignition technology and the sliding arc discharge technology in the field of aerodynamics. The oil and gas mixture flowing through the return area of the V-shaped flame stabilizer is used as the working medium, and the high pressure is passed at the minimum distance between the cathode and the anode of the igniter. The breakdown forms a gliding arc discharge, and the arc flame moves along the inner wall of the V-shaped flame stabilizer to form a plasma area, and uses the cross-flame effect to ignite the surrounding oil and gas mixture to achieve stable and rapid ignition. The invention utilizes gas discharge to form a local high temperature region and excites a large number of active particles, thereby effectively widening the ignition boundary, shortening the ignition delay time, and improving the ignition reliability.

4. The invention can be repeatedly ignited, and can be applied not only during the operation of the afterburner of the aero-engine, but also during the independent operation of the main combustion chamber of the aero-engine, realizing the secondary combustion of the remaining gas and greatly improving the combustion. efficiency, reduce fuel consumption, and achieve clean exhaust emissions.

The present invention will be further described in detail below through the accompanying drawings and embodiments.

Description of drawings

FIG. 1 is a schematic structural diagram of the present invention.

FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1 .

FIG. 3 is a schematic diagram of the connection relationship between the embedded cathode assembly and the flame stabilizer of the present invention.

FIG. 4 is a schematic structural diagram of the cathode casing of the present invention.

FIG. 5 is a schematic structural diagram of the transverse insulating tube of the present invention.

FIG. 6 is a schematic structural diagram of a Y-shaped cathode of the present invention.

FIG. 7 is a B-B cross-sectional view of FIG. 6 .

FIG. 8 is a schematic structural diagram of an energization guide rod of the present invention.

FIG. 9 is a schematic structural diagram of the longitudinal insulating tube of the present invention.

FIG. 10 is a schematic structural diagram of the guide rod housing of the present invention.

Explanation of reference numbers:

1—flame stabilizer; 2—connecting sleeve; 3—cathode casing;

3-1—Small round hole through one side; 4—Transverse insulating tube; 4-1—Cylindrical hole;

4-2—Small three-dimensional groove; 4-3—Circular groove; 4-4—Side circular hole;

4-5—Boss; 5—Y-type cathode; 5-1—V-type tank body;

5-2—straight rod; 5-3—three-dimensional head; 5-4—head through hole;

6—Guide rod housing; 6-1—Three-level stepped hole; 7—Longitudinal insulating tube;

7-1—lower cylindrical hole; 7-2—upper cylindrical hole; 7-3—large round hole;

8—Electrified guide rod; 8-1—Electrified base; 8-2—Electrified straight rod;

8-3—connecting circular hole; 9—first central axis; 10—second central axis;

11—Embedded cathode assembly.

Detailed ways

As shown in FIG. 1 to FIG. 3 , the present invention includes a flame stabilizer 1 and an embedded cathode assembly 11 installed on the flame stabilizer 1. The number of the embedded cathode assembly 11 is at least one, and the embedded cathode assembly 11 is at least one. The cathode assembly 11 includes a connecting sleeve 2, a cathode casing 3, a transverse insulating tube 4, a Y-shaped cathode 5, a guide rod casing 6, a longitudinal insulating pipe 7 and a conducting rod 8, and the connecting sleeve 2 is sleeved on the On the outer wall of the right part of the cathode casing 3 and the inner wall of the connecting sleeve 2 is screwed with the outer wall of the cathode casing 3, the right end of the connecting sleeve 2 is welded with the small end of the flame stabilizer 1, and the transverse insulating tube 4 The left middle part of the horizontal insulating tube 4 is located in the cathode casing 3, the right end of the horizontal insulating tube 4 is located outside the cathode casing 3, the closed end of the Y-shaped cathode 5 is set in the horizontal insulating tube 4, and the Y-shaped cathode 5 The open end is located outside the transverse insulating tube 4, and the open end of the Y-shaped cathode 5 is located in the flame stabilizer 1; the guide rod housing 6 is vertically arranged on the top left side of the cathode housing 3, and the longitudinal insulating tube 7 The upper middle part of the guide rod is set in the guide rod housing 6, the lower end of the longitudinal insulating tube 7 passes through the cathode housing 3 and the end is located in the right part of the transverse insulating tube 4, and the upper and middle part of the conduction guide rod 8 is set in the In the longitudinal insulating tube 7, the lower end of the conducting rod 8 passes through the right part of the transverse insulating tube 4 and the closed end of the Y-shaped cathode 5 in sequence; the flame stabilizer 1, the connecting sleeve 2, the cathode casing 3. The central axis of the transverse insulating tube 4 and the Y-type cathode 5 is the same central axis and the central axis is the first central axis 9. The central axis of the guide rod housing 6, the longitudinal insulating tube 7 and the conduction guide rod 8 are the same central axis and the central axis is the second central axis 10 .

As shown in FIG. 4 , the outer shape of the cathode casing 3 is cylindrical, and a first external thread is provided on the outer wall of the cathode casing 3 near the open end and corresponding to the position of the connecting sleeve 2 . The thread cooperates with the first internal thread thread that penetrates through the inner wall of the connection sleeve 2; the top of the cylinder bottom of the cathode casing 3 is 3mm to 5mm upwards with a single-sided through hole 3-1. The diameter of the side through hole 3-1 is 3 mm to 5 mm.

In this embodiment, the single-side through hole 3-1 is opened at the top of the cathode casing 3 at a position 4 mm upward from the bottom of the cylinder, and the single-side through hole 3-1 has a diameter of 4 mm.

As shown in FIG. 5 , the cross-sectional shape of the lateral insulating tube 4 is a circle, a boss 4-5 is provided on the outer side of the right part of the lateral insulating tube 4, and the right part of the lateral insulating tube 4 is a boss The outer diameter of the base and the boss base is equal to the outer diameter of the cathode casing 3, and the stepped end face of the boss base is flush with the right end face of the cathode casing 3; The right side is provided with a cylindrical hole 4-1 and a small three-dimensional groove 4-2 in turn along the axis, and the cylindrical hole 4-1 and the small three-dimensional groove 4-2 are connected; A circular groove 4-3 is opened at the position of the circular hole 3-1, and a side circular hole 4-4 that communicates with the circular groove 4-3 and the small three-dimensional groove 4-2 is opened on the left side of the lateral insulating tube 4, The side circular hole 4-4 is located between the circular groove 4-3 and the small three-dimensional groove 4-2.

As shown in FIG. 6 and FIG. 7 , the Y-shaped cathode 5 includes a V-shaped groove body 5-1, a straight rod 5-2 and a three-dimensional head 5-3 arranged in sequence from right to left. The body 5-1, the straight section rod 5-2 and the three-dimensional head 5-3 are integrally formed. The two groove pieces of the V-shaped groove body 5-1 are arranged symmetrically up and down. The angle formed by the two groove pieces is a and a is 43° to 47°, the width of the groove piece is W and W is 8mm to 12mm, and the three-dimensional head 5-3 is provided with upper and lower sides passing through. The head penetrates the hole 5-4; the size of the straight section rod 5-2 is consistent with the size of the cylindrical hole 4-1, and the shape of the straight section rod 5-2 is the same as the shape of the cylindrical hole 4-1. The rod 5-2 is inserted into the cylindrical hole 4-1 and is clearance fit with the cylindrical hole 4-1; the size of the three-dimensional head 5-3 is consistent with the size of the small three-dimensional groove 4-2, and the shape of the three-dimensional head 5-3 matches The shapes of the small three-dimensional grooves 4-2 are the same, and the three-dimensional head 5-3 is inserted into the small three-dimensional groove 4-2 and fits with the small three-dimensional groove 4-2 in a clearance fit.

In this embodiment, the angle formed by the two groove pieces of the V-shaped groove body 5-1 is a and a is 45°, and the width of the groove pieces is W and W is 10 mm.

As shown in FIG. 8 , the energization guide rod 8 includes an energization base 8-1 and an energization straight rod 8-2 arranged in sequence from top to bottom, and the energization base 8-1 and the energization straight rod 8-2 are integrally formed. Structure, the outer shape of the energization base 8-1 and the energization straight rod 8-2 are both cylindrical, and the upper part of the energization base 8-1 is provided with a connecting circular hole 8-3 along the axial direction, and the connecting circular hole 8 The inner wall of -3 is provided with a second internal thread, and the power-on base 8-1 is threadedly matched with the power-on cable of the engine through the second internal thread.

As shown in FIG. 9 , the longitudinal insulating tube 7 is an insulating tube with a secondary boss on the outside, and the boss located on the upper part is a primary boss. The cross-sectional shape of the longitudinal insulating tube 7 is a circle. The longitudinal insulating tube 7 is provided with a lower cylindrical hole 7-1, an upper cylindrical hole 7-2 and a large round hole 7-3 in order from bottom to top in the axial direction. The upper cylindrical hole 7-2, the lower cylindrical hole 7-1 and the large round hole The holes 7-3 are all connected, and the depth of the lower cylindrical hole 7-1 is the first-level boss; the diameter of the lower cylindrical hole 7-1 and the energized straight rod 8-2 are equal, and the upper cylindrical hole 7-1 has the same diameter. -2 The size of the energized base 8-1 is the same. The energized guide rods 8 are sequentially inserted into the longitudinal insulating tube 7 from top to bottom and are closely matched with the longitudinal insulating tube 7. The energized base 8-1 is located in the upper cylindrical hole 7. In -2, the lower end of the energized straight rod 8-2 passes through the lower cylindrical hole 7-1 and passes through the side round hole 4-4 and is finally screwed with the head through hole 5-4. The energized straight rod 8 The lower end face of -2 is flush with the lower end face of the head through hole 5-4, the energizing straight rod 8-2 is in clearance fit with the side round hole 4-4, and the diameter of the energizing straight rod 8-2 is the same as that of the side round hole 4-4 are matched, and the large round hole 7-3 is matched with the power cable of the engine.

As shown in FIG. 10 , the outer shape of the guide rod housing 6 is a cylindrical boss shape, and the guide rod housing 6 has a three-stage stepped hole 6- 1. The longitudinal insulating tube 7 is sequentially inserted into the three-stage stepped hole 6-1 from top to bottom and tightly fitted with the guide rod housing 6. The lower end of the longitudinal insulating tube 7 passes through the small round hole 3 on one side in turn. -1 and the circular groove 4-3 and clearance fit with the unilateral small circular hole 3-1 and the circular groove 4-3, the outer diameter of the lower end of the longitudinal insulating tube 7 is the same as that of the unilateral small circular hole 3-1. The diameter is consistent with the diameter of the circular groove 4-3, the lower end of the guide rod casing 6 is close to the top of the left side of the cathode casing 3, and the upper left side of the connecting sleeve 2 is connected to the guide rod casing 6. The right side of the lower end is set right next to it.

As shown in FIG. 1 , the number of the embedded cathode assemblies 11 is three, and the three embedded cathode assemblies 11 are evenly distributed on the flame stabilizer 1 .

The flame holder of the afterburner of the aero-engine is a circular flame holder with a larger diameter. During the actual installation, three holes are evenly opened at the bottom of the groove on the flame stabilizer 1, and the included angle between two adjacent holes is 120°, and the embedded cathode assembly 11 in this embodiment is fixed on the flame. on stabilizer 1. The flame stabilizer was originally a component on the afterburner of the aero-engine, but now it is only used as an anode.

At present, there are many invention patents for the plasma igniter applied to the main combustion chamber of the aero-engine, but there is still no plasma ignition system applied to the afterburner of the aero-engine. In order to solve this problem, the applicant has designed a Plasma duty flame igniter for engine afterburner. The application of the present invention originates from the problem of practical application of afterburner of aero-engine, combined with the professional advantages of its own long-term research on plasma igniter, the design scheme is determined through experimental simulation and other analysis, and it has strong originality. The invention realizes stable and rapid ignition and continuous combustion support of the afterburner of the aero-engine, greatly optimizes the ignition mode of the afterburner of the aero-engine, performs secondary combustion on the residual gas in the main combustion chamber of the aero-engine, and realizes the cleanness of the exhaust gas. Emissions, in line with the actual needs of national research on advanced engines and the development concept of green environmental protection, provide a new idea for related research, and fill the gap in the application of plasma sliding arc technology in aero-engine afterburner.

The working principle of the present invention is as follows: the energization guide rod 8 is connected with the energization cable of the engine, the Y-shaped cathode 5 is used as the cathode, and the flame stabilizer 1 is used as the anode. The breakdown occurs at the narrowest part of the distance between the two electrodes (ie, at C in Figure 3, where C is the breakdown region), and an arc is generated. A recirculation zone is formed inside the flame stabilizer 1, and the airflow will flow to the inside of the plasma duty flame igniter along the electrode spacing; at the same time, the arc is blown in the direction shown in the figure below (that is, the direction shown by the arrow in Figure 3). When the arc slides down, it ignites the oil-air mixture in the recirculation zone inside the flame stabilizer 1 .

The above are only preferred embodiments of the present invention and do not limit the present invention. Any simple modifications, changes and equivalent structural transformations made to the above embodiments according to the technical essence of the present invention still belong to the technology of the present invention. within the scope of the program.

Claims (10)

1. a kind of plasma duty flame igniter based on aero-engine afterburner, it is characterized in that: comprise flame stabilizer (1) and the embedded cathode assembly (11) that is installed on the flame stabilizer (1), The number of the embedded cathode assembly (11) is at least one, and the embedded cathode assembly (11) includes a connecting sleeve (2), a cathode casing (3), a transverse insulating tube (4), a Y-shaped A cathode (5), a guide rod casing (6), a longitudinal insulating tube (7) and a conducting rod (8), the connecting sleeve (2) is sleeved on the right outer wall of the cathode casing (3) and The inner wall of the connection sleeve (2) is threadedly connected with the outer wall of the cathode casing (3), the right end of the connection sleeve (2) is welded with the small end of the flame stabilizer (1), and the transverse insulating tube (4) The left middle part of the Y-shaped cathode (5) is arranged in the cathode casing (3), the right end of the horizontal insulating tube (4) is located outside the cathode casing (3), and the closed end of the Y-shaped cathode (5) is arranged in the horizontal insulating tube (4). ), the open end of the Y-shaped cathode (5) is located outside the transverse insulating tube (4), and the open end of the Y-shaped cathode (5) is located in the flame stabilizer (1); the guide rod housing ( 6) Vertically arranged on the top left side of the cathode casing (3), the upper middle part of the longitudinal insulating tube (7) is arranged in the guide rod casing (6), and the lower end of the longitudinal insulating tube (7) passes through The rear end of the cathode casing (3) is located in the right part of the transverse insulating tube (4), the upper middle part of the conducting rod (8) is arranged in the longitudinal insulating tube (7), and the conducting rod (8) The lower end of the flame stabilizer (1), the connecting sleeve (2), the cathode casing (3), The central axes of the transverse insulating tube (4) and the Y-shaped cathode (5) are both the first central axis (9). ) and the central axis of the three are the second central axis (10). 2. The plasma duty flame igniter based on an aero-engine afterburner according to claim 1, wherein the cathode casing (3) has a cylindrical shape, and the cathode casing (3) has a cylindrical shape. ) on the outer wall close to the open end and at the position corresponding to the connecting sleeve (2), a first external thread is provided, and the first external thread cooperates with the first internal thread that penetrates and is arranged on the inner wall of the connecting sleeve (2); so The cathode casing (3) is provided with a unilateral through-hole (3-1) at the top at 3mm to 5mm from the bottom of the cylinder, and the diameter of the unilateral through-hole (3-1) is 3mm to 5mm . 3. according to the plasma duty flame igniter based on aero-engine afterburning chamber according to claim 2, it is characterized in that: described unilateral through hole (3-1) is opened in the cathode casing (3) The top of the cylinder bottom 4mm upward, the diameter of the small circular hole (3-1) penetrating through one side is 4mm. 4. The plasma duty flame igniter based on aero-engine afterburner according to claim 2 or 3, characterized in that: the cross-sectional shape of the transverse insulating pipe (4) is circular, and the transverse insulating pipe (4) has a circular shape. A boss (4-5) is provided on the outer side of the right part of the tube (4), the right part of the transverse insulating tube (4) is a boss base, and the outer diameter of the boss base is the same as that of the cathode casing (3). The outer diameters are equal, and the stepped end face of the boss base is flush with the right end face of the cathode casing (3); the transverse insulating tube (4) is provided with cylindrical holes (4- 1) and the small three-dimensional groove (4-2), the cylindrical hole (4-1) is communicated with the small three-dimensional groove (4-2); the left top of the lateral insulating tube (4) corresponds to the small round hole A circular groove (4-3) is opened at the position (3-1), and the left side of the lateral insulating tube (4) is provided with a circular groove (4-3) and a small three-dimensional groove (4-2) which are connected to each other. The side circular hole (4-4) is located between the circular groove (4-3) and the small three-dimensional groove (4-2). 5. The plasma duty flame igniter based on aero-engine afterburner according to claim 4, characterized in that: the Y-shaped cathode (5) comprises a V-shaped groove body (5) arranged in turn from right to left -1), straight section rod (5-2) and three-dimensional head (5-3), the V-shaped groove body (5-1), straight section rod (5-2) and three-dimensional head (5-3) ) an integral molding structure, the two groove pieces of the V-shaped groove body (5-1) are arranged symmetrically up and down, and the angle formed by the two groove pieces of the V-shaped groove body (5-1) is a and a is 43°～47°, the width of the groove piece is W and W is 8mm～12mm, and the three-dimensional head (5-3) is provided with a head through hole (5-4) penetrating through the upper and lower sides; The size of the straight rod (5-2) is consistent with the size of the cylindrical hole (4-1), and the shape of the straight rod (5-2) is the same as that of the cylindrical hole (4-1). (5-2) Insert into the cylindrical hole (4-1) and clearance fit with the cylindrical hole (4-1); the size of the three-dimensional head (5-3) is consistent with the size of the small three-dimensional groove (4-2), The shape of the three-dimensional head (5-3) is the same as that of the small three-dimensional groove (4-2), and the three-dimensional head (5-3) is inserted into the small three-dimensional groove (4-2) and is connected to the small three-dimensional groove (4-2). -2) Clearance fit. 6. The plasma duty flame igniter based on an aero-engine afterburner according to claim 5, wherein the angle formed by the two groove pieces of the V-shaped groove body (5-1) is a and a is 45°, the width of the slot is W and W is 10 mm. 7. The plasma duty flame igniter based on aero-engine afterburner according to claim 5, characterized in that: the energized guide rod (8) comprises an energized base (8-1) arranged in sequence from top to bottom ) and the energized straight rod (8-2), the energized base (8-1) and the energized straight rod (8-2) are integrally formed, and the energized base (8-1) and the energized straight rod (8- 2) The shapes are all cylindrical, the upper part of the energization base (8-1) is provided with a connecting circular hole (8-3) in the axial direction, and the inner wall of the connecting circular hole (8-3) is provided with a first connecting hole (8-3). The second internal thread and the power-on base (8-1) are threadedly matched with the power-on cable of the engine through the second internal thread. 8. The plasma duty flame igniter based on aero-engine afterburner according to claim 7, characterized in that: the longitudinal insulating tube (7) is an insulating tube with a secondary boss on the outside and is located at the upper part. The boss is a first-level boss, the cross-sectional shape of the longitudinal insulating tube (7) is circular, and the longitudinal insulating tube (7) is provided with lower cylindrical holes (7-1), The upper cylindrical hole (7-2) and the large round hole (7-3) are in communication with the lower cylindrical hole (7-1) and the large round hole (7-3). The depth of the cylindrical hole (7-1) is the first-level boss; the diameter of the lower cylindrical hole (7-1) and the energized straight rod (8-2) are equal, and the upper cylindrical hole (7-2) The size of the energized base (8-1) is the same. -1) Located in the upper cylindrical hole (7-2), the lower end of the energized straight rod (8-2) passes through the lower cylindrical hole (7-1) and passes through the side circular hole (4-4) and finally connects with the The head through hole (5-4) is threaded, the lower end face of the energization straight rod (8-2) is flush with the lower end face of the head through hole (5-4), and the energization straight rod (8-2) ) is in clearance fit with the side round hole (4-4) and the diameter of the energizing straight rod (8-2) is consistent with the side round hole (4-4), and the large round hole (7-3) is connected to the power cable of the engine match. 9. The plasma duty flame igniter based on an aero-engine afterburner according to claim 8, characterized in that: the outer shape of the guide rod housing (6) is a cylindrical boss shape, and the guide rod The casing (6) is provided with a three-stage stepped hole (6-1) along the axial direction that matches the shape of the longitudinal insulating tube (7), and the longitudinal insulating tube (7) is inserted into the three-stage stepped hole in sequence from top to bottom. After (6-1) and in close fit with the guide rod housing (6), the lower end of the longitudinal insulating tube (7) passes through the small circular hole (3-1) and the circular groove (4-3) on one side in turn. And with clearance fit with the unilateral small circular hole (3-1) and the circular groove (4-3). The diameter is consistent with the diameter of the circular groove (4-3), the lower end of the guide rod casing (6) is close to the top of the left side of the cathode casing (3), and the left The upper part of the side is arranged in close proximity to the right side of the lower end of the guide rod housing (6). 10. The plasma duty flame igniter based on an aeroengine afterburner according to claim 1 or 2, characterized in that: the number of the embedded cathode assemblies (11) is three, and the three said The embedded cathode assemblies (11) are evenly distributed on the flame stabilizer (1).

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