CN110439691B - Plasma on-duty flame igniter based on aircraft engine afterburner - Google Patents
Plasma on-duty flame igniter based on aircraft engine afterburner Download PDFInfo
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- CN110439691B CN110439691B CN201910719618.6A CN201910719618A CN110439691B CN 110439691 B CN110439691 B CN 110439691B CN 201910719618 A CN201910719618 A CN 201910719618A CN 110439691 B CN110439691 B CN 110439691B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
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Abstract
The invention discloses a plasma on-duty flame igniter based on an afterburner of an aircraft engine, which comprises a flame stabilizer and an embedded cathode assembly, wherein the embedded cathode assembly comprises a connecting sleeve, a cathode shell, a transverse insulating tube, a Y-shaped cathode, a guide rod shell, a longitudinal insulating tube and an electrified guide rod; the guide rod shell is vertically arranged at the top of the left side of the cathode shell, the upper middle part of the longitudinal insulating tube is arranged in the guide rod shell, the lower end of the longitudinal insulating tube penetrates through the cathode shell and the end part of the longitudinal insulating tube is positioned in the right part of the transverse insulating tube, and the upper middle part of the electrified guide rod is arranged in the longitudinal insulating tube. The invention solves the problems that the existing afterburner of the aero-engine has severe working environment, complex structure and is not beneficial to stable and rapid ignition and continuous organization of combustion.
Description
Technical Field
The invention belongs to the technical field of aviation power ignition, and particularly relates to a plasma on-duty flame igniter based on an afterburner of an aero-engine.
Background
Although the mass of the afterburner of an aircraft engine accounts for only 20% of the total mass of the engine, it is an important component for increasing the thrust of the engine. The turbojet engine is additionally provided with an afterburner, and the thrust augmentation ratio reaches 40-50%; the thrust augmentation ratio of the turbofan engine with the afterburner can reach 60-70% or even higher. The afterburner can greatly increase the unit head-on thrust and the thrust-weight ratio of the engine, comprehensively improve the maneuverability of the airplane, enlarge the flight envelope and improve the air-braking capacity of the fighter plane. Because the afterburner has the disadvantages of severe working environment, low gas pressure, high flow rate and extremely unstable flow, and is not beneficial to ignition and tissue combustion, the ignited mixed gas can be combusted in a longer cylinder, only 85-90% of the heat content of fuel oil in the modern afterburner can be converted into useful heat energy, and the rest part of the fuel oil is discharged out of an engine due to the fact that fuel oil fog drops are not in time for combustion or is lost through heat dissipation of the cylinder. Therefore, the improvement of afterburning efficiency has important significance for reducing fuel consumption and increasing thrust.
At present, the afterburner ignition mode of an aircraft engine has three types: electric nozzle ignition, flame-tongue ignition and catalytic ignition. Several existing ignition methods have disadvantages: the traditional electric nozzle ignition system adopts electric spark ignition, the ignition delay time is longer, and the ignition stability is poor; the fire tongue transmission path of the fire tongue ignition system is long, the flow is complex, particularly when the fire tongue ignition system passes through a multi-stage turbine, the fire tongue ignition system is strongly disturbed, and a large number of ignition tests are correspondingly required when an afterburner is debugged; the ignition device of the catalytic ignition system has simple structure, light weight and convenient ignition, but the platinum-rhodium wire is expensive and is easy to be polluted and fail, thus influencing the working reliability of the ignition device.
In recent years, plasma ignition combustion-supporting technology has gradually received high attention and attention from researchers in the field of aviation power. The plasma ignition combustion-supporting is a process of forming a local high-temperature area by utilizing gas discharge and exciting a large amount of active particles to quickly ignite combustible mixed gas or ignite combustion-supporting. The mechanism is mainly represented by three effects: thermal, chemical and pneumatic effects. The plasma ignition combustion-supporting brings the advantages that: the ignition boundary is widened, the ignition delay time is shortened, the ignition reliability is improved, the combustion efficiency is improved, the fuel consumption is reduced, and the like. Therefore, plasma ignition combustion supporting is one of effective technical approaches for expanding an ignition boundary and improving a stable combustion range.
The sliding arc discharge is a discharge mode capable of generating non-equilibrium plasma under atmospheric pressure. The basic principle is that a strong electric field is applied to one or more electrodes for excitation, air flow is introduced between the electrodes, an initial discharge channel is generated between the electrodes, and the electric arcs slide along the channel direction under the action of the air flow, so that sliding discharge is formed. The sliding arc discharge has several typical forms, including two-dimensional sliding arc discharge, rotating sliding arc discharge and multi-electrode sliding arc discharge. The sliding arc discharge can generate continuous and stable non-equilibrium state low-temperature plasma, and the collision of electrons and neutral molecules in the plasma can cause the dissociation, excitation and ionization of molecules, so that a large amount of active particles and radicals are generated, and the chemical activity is higher. Therefore, the sliding arc discharge plasma technology has wide application prospect in the aviation field.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a plasma on-duty flame igniter based on an afterburner of an aircraft engine, effectively solves the problems that the afterburner of the existing aircraft engine has a severe working environment and a complex structure and is not beneficial to stable and rapid ignition and continuous tissue combustion, realizes stable and rapid ignition and continuous combustion supporting of the afterburner, greatly optimizes the ignition mode of the afterburner, performs secondary combustion on residual gas in a main combustion chamber, and realizes clean emission of tail gas.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides a plasma flame point firearm on duty based on aeroengine afterburner which characterized in that: the cathode comprises a flame stabilizer and embedded cathode assemblies arranged on the flame stabilizer, wherein the number of the embedded cathode assemblies is at least one, each embedded cathode assembly comprises a connecting sleeve, a cathode shell, a transverse insulating tube, a Y-shaped cathode, a guide rod shell, a longitudinal insulating tube and an electrifying guide rod, the connecting sleeve is sleeved on the outer wall of the right part of the cathode shell, the inner wall of the connecting sleeve is in threaded connection with the outer wall of the cathode shell, the right end of the connecting sleeve is welded with the small end of the flame stabilizer, the left middle part of the transverse insulating tube is arranged in the cathode shell, the right end of the transverse insulating tube is positioned outside the cathode shell, the closed end of the Y-shaped cathode is arranged in the transverse insulating tube, the open end of the Y-shaped cathode is positioned outside the transverse insulating tube, and the open end of the Y-shaped cathode is positioned in; the guide rod shell is vertically arranged at the top of the left side of the cathode shell, the upper middle part of the longitudinal insulating tube is arranged in the guide rod shell, the lower end of the longitudinal insulating tube penetrates through the cathode shell and the end part of the longitudinal insulating tube is positioned in the right part of the transverse insulating tube, the upper middle part of the electrified guide rod is arranged in the longitudinal insulating tube, and the lower end of the electrified guide rod sequentially penetrates through the right part of the transverse insulating tube and the closed end part of the Y-shaped cathode; the axis of flame holder, adapter sleeve, negative pole casing, horizontal insulating tube and Y type negative pole is same axis and this axis is first axis, the axis of guide arm casing, vertical insulating tube and circular telegram guide arm is same axis and this axis is the second axis.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the cathode shell is cylindrical, a first external thread is arranged on the outer wall of the cathode shell close to the opening end and corresponds to the position of the connecting sleeve, and the first external thread is in threaded fit with a first internal thread which penetrates through the inner wall of the connecting sleeve; the top of the position 3 mm-5 mm above the cylinder bottom of the cathode shell is provided with a small through round hole at one side, and the diameter of the small through round hole at one side is 3 mm-5 mm.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the single-side through small round hole is arranged at the top of the position 4mm above the cylinder bottom of the cathode shell, and the diameter of the single-side through small round hole is 4 mm.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the cross section of the transverse insulating tube is circular, a boss is arranged on the outer side of the right part of the transverse insulating tube, a boss base is arranged on the right part of the transverse insulating tube, the outer diameter of the boss base is equal to that of the cathode shell, and the step end face of the boss base is flush with the right end face of the cathode shell; the transverse insulating pipe is sequentially provided with a cylindrical hole and a small three-dimensional groove along the axis from the right side of the boss base, and the cylindrical hole is communicated with the small three-dimensional groove; the left side top of horizontal insulating tube just corresponds little round hole position department and opens there is the circular slot, the left side of horizontal insulating tube is opened there is the side round hole that communicates with circular slot and little solid groove homogeneous phase, the side round hole is located between circular slot and the little solid groove.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the Y-shaped cathode comprises a V-shaped groove body, a straight section rod and a three-dimensional head which are sequentially arranged from right to left, the V-shaped groove body, the straight section rod and the three-dimensional head are of an integrally formed structure, two groove pieces of the V-shaped groove body are symmetrically arranged up and down, the angle formed by the two groove pieces of the V-shaped groove body is a, a is 43-47 degrees, the width of each groove piece is W, W is 8-12 mm, and the three-dimensional head is provided with a head through hole which is communicated with the upper side and the lower side; the size of the straight section rod is matched with that of the cylindrical hole, the shape of the straight section rod is the same as that of the cylindrical hole, and the straight section rod is inserted into the cylindrical hole and is in clearance fit with the cylindrical hole; the size of the three-dimensional head is matched with that of the small three-dimensional groove, the appearance 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 in clearance fit with the small three-dimensional groove.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the angle formed by the two groove sheets of the V-shaped groove body is a, a is 45 degrees, the width of the groove sheet is W, and W is 10 mm.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the electrified guide rod comprises an electrified base and an electrified straight rod which are sequentially arranged from top to bottom, the electrified base and the electrified straight rod are of an integrally formed structure, the electrified base and the electrified straight rod are cylindrical, a connecting round hole is formed in the upper portion of the electrified base along the axial direction, a second internal thread is arranged on the inner wall of the connecting round hole, and the electrified base is in threaded fit with an electrified cable of the engine through the second internal thread.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the longitudinal insulating pipe is an insulating pipe with a secondary boss outside, the boss at the upper part is a primary boss, the cross section of the longitudinal insulating pipe is circular, the longitudinal insulating pipe is sequentially provided with a lower cylindrical hole, an upper cylindrical hole and a large round hole from bottom to top along the axial direction, the upper cylindrical hole is communicated with the lower cylindrical hole and the large round hole, and the depth of the lower cylindrical hole is the primary boss; the diameter of the lower cylindrical hole is equal to that of the electrified straight rod, the size of the upper cylindrical hole is equal to that of the electrified base, the electrified guide rod is sequentially inserted into the longitudinal insulating tube from top to bottom and is tightly matched with the longitudinal insulating tube, the electrified base is located in the upper cylindrical hole, the lower end of the electrified straight rod penetrates through the lower cylindrical hole, penetrates through the side circular hole and is finally in threaded connection with the head through hole, the lower end face of the electrified straight rod is flush with the lower end face of the head through hole, the electrified straight rod is in clearance fit with the side circular hole, the diameter of the electrified straight rod is matched with the side circular hole, and the large circular hole is matched with an electrified cable.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the appearance of guide arm casing is the cylindricality boss form, the guide arm casing is opened along the axial has the identical tertiary shoulder hole with the appearance of vertical insulating tube, vertical insulating tube is from last to inserting behind the tertiary shoulder hole in proper order down and closely cooperating with the guide arm casing, the lower extreme of vertical insulating tube passes in proper order the unilateral and runs through little round hole and circular slot and runs through little round hole and the equal clearance fit of circular slot with the unilateral, the lower extreme external diameter of vertical insulating tube and the unilateral diameter homogeneous phase that runs through little round hole and circular slot coincide, the lower extreme of guide arm casing is tightly leaned on the left side top of negative pole casing, connecting sleeve's left side upper portion and the lower extreme right side of guide arm casing are near setting up.
Foretell flame point firearm on duty based on aeroengine afterburner's plasma, its characterized in that: the number of the embedded cathode assemblies is three, and the three embedded cathode assemblies are uniformly distributed on the flame stabilizer.
Compared with the prior art, the invention has the following advantages:
1. the invention has simple structure and small size, skillfully takes the inner wall of the flame stabilizer as the anode of the igniter, and designs the cathode into the shape of a Y-shaped cambered surface, thereby easily forming the minimum discharge interval, effectively widening the ignition range, greatly enhancing the ignition stability and improving the reliability of quick ignition of the afterburner in severe environment.
2. The invention designs the breakdown area in the backflow area of the oil-gas mixture of the flame stabilizer, fully utilizes the characteristic that the gas flow rate in the backflow area is small and the ignition is easy, and the working medium is the oil-gas mixture without an additional gas supply system.
3. The invention relates to a plasma ignition combustion-supporting technology and a sliding arc discharge technology in the field of aviation power, wherein oil-gas mixed gas flowing through a backflow area of a V-shaped flame stabilizer is used as a working medium, sliding arc discharge is formed at the minimum distance between a cathode and an anode of an igniter through high-voltage breakdown, arc flame moves along the inner wall surface of the V-shaped flame stabilizer to form a plasma area, and the surrounding oil-gas mixed gas is ignited by using a cross-flame effect to realize stable and rapid ignition. The invention forms a local high-temperature area by utilizing gas discharge and excites a large amount of active particles, thereby effectively widening the ignition boundary, shortening the ignition delay time and improving the ignition reliability.
4. The invention can repeatedly ignite for many times, can be applied to the working period of an afterburner of an aircraft engine and the independent working period of a main combustor of the aircraft engine, realizes the secondary combustion of residual fuel gas, greatly improves the combustion efficiency, reduces the fuel consumption and realizes the clean emission of tail gas.
The invention is described in further detail below with reference to the figures and examples.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a sectional view a-a of fig. 1.
FIG. 3 is a schematic view of the connection between the embedded cathode assembly and the flame holder of the present invention.
Fig. 4 is a schematic structural view of a cathode casing according to the present invention.
FIG. 5 is a schematic structural view of the lateral insulating tube of the present invention.
FIG. 6 is a schematic structural view of a Y-type cathode according to the present invention.
Fig. 7 is a sectional view B-B of fig. 6.
FIG. 8 is a schematic view of the structure of the electrified guide bar of the present invention.
Fig. 9 is a schematic structural view of the longitudinal insulating tube of the present invention.
FIG. 10 is a schematic view of the guide bar housing of the present invention.
Description of reference numerals:
1-flame stabilizer; 2, connecting a sleeve; 3-cathode casing;
3-1, penetrating the small round hole on one side; 4-transverse insulating tube; 4-1-cylindrical hole;
4-2-small three-dimensional groove; 4-3-round groove; 4-side round hole;
4-5-boss; 5-Y-type cathode; 5-1-V groove body;
5-2-straight section bar; 5-3-a stereoscopic head; 5-4-head through hole;
6-guide rod shell; 6-1-three-stage stepped hole; 7-longitudinal insulating tube;
7-1-lower cylindrical hole; 7-2-upper cylindrical hole; 7-3-big round hole;
8, electrifying the guide rod; 8-1-a powered base; 8-2-electrifying straight rods;
8-3-connecting round holes; 9-a first central axis; 10-a second central axis;
11-embedded cathode assembly.
Detailed Description
As shown in fig. 1 to 3, the present invention comprises a flame stabilizer 1 and an embedded cathode assembly 11 mounted on the flame stabilizer 1, wherein the number of the embedded cathode assembly 11 is at least one, the embedded cathode assembly 11 comprises 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 tube 7 and an electrified guide rod 8, the connecting sleeve 2 is sleeved on the outer wall of the right portion of the cathode casing 3, the inner wall of the connecting sleeve 2 is in threaded connection 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, the left middle portion of the transverse insulating tube 4 is arranged in the cathode casing 3, the right end of the transverse insulating tube 4 is arranged outside the cathode casing 3, the closed end of the Y-shaped cathode 5 is arranged in the transverse insulating tube 4, the open end of the Y-shaped cathode 5 is arranged outside the transverse insulating tube 4, the open end of the Y-shaped cathode 5 is positioned in the flame stabilizer 1; the guide rod shell 6 is vertically arranged at the top of the left side of the cathode shell 3, the upper middle part of the longitudinal insulating tube 7 is arranged in the guide rod shell 6, the lower end of the longitudinal insulating tube 7 penetrates through the cathode shell 3 and the end part of the longitudinal insulating tube is positioned in the right part of the transverse insulating tube 4, the upper middle part of the electrified guide rod 8 is arranged in the longitudinal insulating tube 7, and the lower end of the electrified guide rod 8 sequentially penetrates through the right part of the transverse insulating tube 4 and the closed end part of the Y-shaped cathode 5; the axis of flame holder 1, adapter sleeve 2, negative pole casing 3, horizontal insulating tube 4 and Y type negative pole 5 is same axis and this axis is first axis 9, the axis of guide arm casing 6, vertical insulating tube 7 and circular telegram guide arm 8 is same axis and this axis is second axis 10.
As shown in fig. 4, the cathode casing 3 is cylindrical, and a first external thread is disposed on the outer wall of the cathode casing 3 near the open end and at a position corresponding to the connection sleeve 2, and the first external thread is in threaded fit with a first internal thread disposed on the inner wall of the connection sleeve 2; the top of the position 3 mm-5 mm above the bottom of the cathode shell 3 is provided with a small through round hole 3-1 at one side, and the diameter of the small through round hole 3-1 at one side is 3 mm-5 mm.
In this embodiment, the single-side through small circular hole 3-1 is provided at the top of the position 4mm above the cylinder bottom of the cathode housing 3, and the diameter of the single-side through small circular hole 3-1 is 4 mm.
As shown in fig. 5, the cross section of the transverse insulating tube 4 is circular, a boss 4-5 is arranged on the outer side of the right part of the transverse insulating tube 4, the right part of the transverse insulating tube 4 is a boss base, the outer diameter of the boss base is equal to that of the cathode shell 3, and the step end face of the boss base is flush with the right end face of the cathode shell 3; the transverse insulating tube 4 is provided with a cylindrical hole 4-1 and a small three-dimensional groove 4-2 along the axis in sequence from the right side of the boss base, and the cylindrical hole 4-1 is communicated with the small three-dimensional groove 4-2; the round slot 4-3 is formed in the position, corresponding to the small round hole 3-1, of the top of the left side of the transverse insulating tube 4, the side round hole 4-4 communicated with the round slot 4-3 and the small three-dimensional slot 4-2 is formed in the left side of the transverse insulating tube 4, and the side round hole 4-4 is located between the round slot 4-3 and the small three-dimensional slot 4-2.
As shown in fig. 6 and 7, the Y-shaped cathode 5 includes a V-shaped groove body 5-1, a straight-section bar 5-2 and a three-dimensional head 5-3, which are sequentially arranged from right to left, the V-shaped groove body 5-1, the straight-section bar 5-2 and the three-dimensional head 5-3 are of an integrally formed structure, two groove pieces of the V-shaped groove body 5-1 are symmetrically arranged up and down, an angle formed by the two groove pieces of the V-shaped groove body 5-1 is a and a is 43 to 47 °, a width of the groove piece is W and W is 8 to 12mm, and the three-dimensional head 5-3 is provided with a head through hole 5-4 which is through from top to bottom; the size of the straight section rod 5-2 is matched with that of the cylindrical hole 4-1, the shape of the straight section rod 5-2 is the same as that of the cylindrical hole 4-1, and the straight section rod 5-2 is inserted into the cylindrical hole 4-1 and is in clearance fit with the cylindrical hole 4-1; the size of the three-dimensional head 5-3 is matched with that 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 in clearance fit with the small three-dimensional groove 4-2.
In this embodiment, the angle formed by the two slots of the V-shaped slot body 5-1 is a, a is 45 °, and the width of the slot is W, W is 10 mm.
As shown in fig. 8, the electrified guide rod 8 comprises an electrified base 8-1 and an electrified straight rod 8-2 which are sequentially arranged from top to bottom, the electrified base 8-1 and the electrified straight rod 8-2 are of an integrally formed structure, the electrified base 8-1 and the electrified straight rod 8-2 are both cylindrical, a connecting round hole 8-3 is axially formed in the upper portion of the electrified base 8-1, second internal threads are arranged on the inner wall of the connecting round hole 8-3, and the electrified base 8-1 is in threaded fit with an electrified cable of an engine through the second internal threads.
As shown in fig. 9, the longitudinal insulating tube 7 is an insulating tube with a second-level boss at the outside and the boss at the upper part is a first-level boss, the cross section of the longitudinal insulating tube 7 is circular, the longitudinal insulating tube 7 is provided with a lower cylindrical hole 7-1, an upper cylindrical hole 7-2 and a large cylindrical hole 7-3 in sequence from bottom to top along the axial direction, the upper cylindrical hole 7-2 is communicated with the lower cylindrical hole 7-1 and the large cylindrical hole 7-3, and the depth of the lower cylindrical hole 7-1 is the first-level boss; the diameter of the lower cylindrical hole 7-1 is equal to that of the electrified straight rod 8-2, the size of the upper cylindrical hole 7-2 is equal to that of the electrified base 8-1, the electrified guide rod 8 is inserted into the longitudinal insulating tube 7 from top to bottom in sequence and then is tightly matched with the longitudinal insulating tube 7, the electrifying base 8-1 is positioned in the upper cylindrical hole 7-2, the lower end of the electrifying straight rod 8-2 penetrates through the lower cylindrical hole 7-1 and then penetrates through the side round hole 4-4 to be finally in threaded connection with the head through hole 5-4, the lower end face of the electrifying straight rod 8-2 is flush with the lower end face of the head through hole 5-4, the electrified straight rod 8-2 is in clearance fit with the side round hole 4-4, the diameter of the electrified straight rod 8-2 is matched with the side round hole 4-4, and the large round hole 7-3 is matched with an electrified cable of an engine.
As shown in fig. 10, the guide rod housing 6 is in the shape of a cylindrical boss, the guide rod housing 6 is axially provided with a three-stage stepped hole 6-1 matching with the shape of the longitudinal insulating tube 7, the longitudinal insulating tube 7 is inserted into the three-stage stepped hole 6-1 from top to bottom in sequence and then is tightly matched with the guide rod shell 6, the lower end of the longitudinal insulating tube 7 sequentially penetrates through the small round hole 3-1 and the circular groove 4-3 penetrating through the single side and is in clearance fit with the small round hole 3-1 and the circular groove 4-3 penetrating through the single side, the outer diameter of the lower end of the longitudinal insulating tube 7 is matched with the diameter of the small round hole 3-1 penetrating through one side and the diameter of the round groove 4-3, the lower end of the guide rod shell 6 is tightly against the top of the left side of the cathode shell 3, and the upper part of the left side of the connecting sleeve 2 is tightly against the right side of the lower end of the guide rod shell 6.
As shown in fig. 1, the number of the embedded cathode assemblies 11 is three, and three embedded cathode assemblies 11 are uniformly distributed on the flame stabilizer 1.
The flame stabilizer of the afterburner of the aircraft engine is a circular ring flame stabilizer with a larger diameter. In actual installation, three holes are uniformly formed in the bottom of a groove on the flame stabilizer 1, the included angle between two adjacent holes is 120 degrees, and the embedded cathode assembly 11 in the embodiment is fixed on the flame stabilizer 1. The flame stabilizer, originally a component on an afterburner of an aircraft engine, is now used only as an anode.
At present, the invention patents of the plasma igniter applied to the main combustion chamber of the aircraft engine are more, but a plasma ignition system applied to an afterburner of the aircraft engine is not available, and in order to solve the problem, the applicant designs a plasma on-duty flame igniter based on the afterburner of the aircraft engine. The invention is based on the practical application problem of the afterburner of the aircraft engine, combines the professional advantages of long-term research on the plasma igniter, determines the design scheme through analysis such as experimental simulation and the like, and has extremely strong originality. The invention realizes the stable and rapid ignition and continuous combustion supporting of the afterburner of the aircraft engine, greatly optimizes the ignition mode of the afterburner of the aircraft engine, performs secondary combustion on residual gas in a main combustion chamber of the aircraft engine, realizes the clean emission of tail gas, meets the practical requirements of national research on advanced engines and the development concept of environmental protection, provides a new idea for related research, and fills the blank of the plasma sliding arc technology in the application field of the afterburner of the aircraft engine.
The working principle of the invention is as follows: the electrified guide rod 8 is connected with an electrified cable of the engine, the Y-shaped cathode 5 is used as a cathode, and the flame stabilizer 1 is used as an anode. Breakdown occurs at the narrowest point of the two electrode spacing (i.e., at C in fig. 3, the breakdown region at C), creating an arc. A reflow region is formed in the flame stabilizer 1, and airflow can flow to the interior of the plasma on-duty flame igniter along the electrode distance; while blowing an arc in the direction shown in the following figure (i.e., in the direction of the arrow shown in fig. 3). The arc ignites the mixture of oil and gas in the recirculation zone inside the flame holder 1 while sliding downwards.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (10)
1. The utility model provides a plasma flame point firearm on duty based on aeroengine afterburner which characterized in that: comprises a flame stabilizer (1) and an embedded cathode assembly (11) arranged on the flame stabilizer (1), wherein the number of the embedded cathode assembly (11) is at least one, the embedded cathode assembly (11) comprises a connecting sleeve (2), a cathode shell (3), a transverse insulating tube (4), a Y-shaped cathode (5), a guide rod shell (6), a longitudinal insulating tube (7) and an electrified guide rod (8), the connecting sleeve (2) is sleeved on the outer wall of the right part of the cathode shell (3), the inner wall of the connecting sleeve (2) is in threaded connection with the outer wall of the cathode shell (3), the right end of the connecting sleeve (2) is welded with the small end of the flame stabilizer (1), the left middle part of the transverse insulating tube (4) is arranged in the cathode shell (3), and the right end of the transverse insulating tube (4) is arranged outside the cathode shell (3), the closed end of the Y-shaped cathode (5) is arranged in the transverse insulating tube (4), the open end of the Y-shaped cathode (5) is positioned outside the transverse insulating tube (4), and the open end of the Y-shaped cathode (5) is positioned in the flame stabilizer (1); the guide rod shell (6) is vertically arranged at the top of the left side of the cathode shell (3), the upper middle part of the longitudinal insulating tube (7) is arranged in the guide rod shell (6), the lower end of the longitudinal insulating tube (7) penetrates through the cathode shell (3) and the end part of the longitudinal insulating tube is positioned in the right part of the transverse insulating tube (4), the upper middle part of the electrifying guide rod (8) is arranged in the longitudinal insulating tube (7), and the lower end of the electrifying guide rod (8) sequentially penetrates through the right part of the transverse insulating tube (4) and the closed end part of the Y-shaped cathode (5); the central axes of the flame stabilizer (1), the connecting sleeve (2), the cathode shell (3), the transverse insulating tube (4) and the Y-shaped cathode (5) are all first central axes (9), and the central axes of the guide rod shell (6), the longitudinal insulating tube (7) and the electrified guide rod (8) are all second central axes (10).
2. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 1, wherein: the cathode shell (3) is cylindrical, a first external thread is arranged on the outer wall of the cathode shell (3) close to the opening end and at the position corresponding to the connecting sleeve (2), and the first external thread is in threaded fit with a first internal thread which penetrates through the inner wall of the connecting sleeve (2); the top of the position 3 mm-5 mm above the bottom of the cathode shell (3) is provided with a small through round hole (3-1) on one side, and the diameter of the small through round hole (3-1) on one side is 3 mm-5 mm.
3. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 2, wherein: the single-side through small round hole (3-1) is arranged at the top of the position 4mm above the cylinder bottom of the cathode shell (3), and the diameter of the single-side through small round hole (3-1) is 4 mm.
4. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 2 or 3, wherein: the cross section of the transverse insulating tube (4) is circular, a boss (4-5) is arranged on the outer side of the right part of the transverse insulating tube (4), the right part of the transverse insulating tube (4) is a boss base, the outer diameter of the boss base is equal to that of the cathode shell (3), and the step end face of the boss base is flush with the right end face of the cathode shell (3); the transverse insulating pipe (4) is sequentially provided with a cylindrical hole (4-1) and a small three-dimensional groove (4-2) along the axis from the right side of the boss base, and the cylindrical hole (4-1) is communicated with the small three-dimensional groove (4-2); the round groove (4-3) is formed in the position, corresponding to the small round hole (3-1), of the top of the left side of the transverse insulating pipe (4), the round hole (4-4) communicated with the round groove (4-3) and the small three-dimensional groove (4-2) is formed in the left side of the transverse insulating pipe (4), and the round hole (4-4) is located between the round groove (4-3) and the small three-dimensional groove (4-2).
5. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 4, wherein: the Y-shaped cathode (5) comprises a V-shaped groove body (5-1), a straight section rod (5-2) and a three-dimensional head (5-3), wherein the V-shaped groove body (5-1), the straight section rod (5-2) and the three-dimensional head (5-3) are sequentially arranged from right to left, and are of an integrally formed structure, two groove pieces of the V-shaped groove body (5-1) are vertically and symmetrically arranged, an angle formed by the two groove pieces of the V-shaped groove body (5-1) is a and is 43-47 degrees, the width of each groove piece is W and is 8-12 mm, and a head through hole (5-4) with the upper side and the lower side communicated is formed in the three-dimensional head (5-3); the size of the straight section rod (5-2) is matched with that of the cylindrical hole (4-1), the shape of the straight section rod (5-2) is the same as that of the cylindrical hole (4-1), and the straight section rod (5-2) is inserted into the cylindrical hole (4-1) and is in clearance fit with the cylindrical hole (4-1); the size of the three-dimensional head (5-3) is matched with that 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 in clearance fit with the small three-dimensional groove (4-2).
6. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 5, wherein: the angle formed by the two groove sheets of the V-shaped groove body (5-1) is a, a is 45 degrees, the width of the groove sheet is W, and W is 10 mm.
7. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 5, wherein: the power-on guide rod (8) comprises a power-on base (8-1) and a power-on straight rod (8-2) which are sequentially arranged from top to bottom, the power-on base (8-1) and the power-on straight rod (8-2) are of an integrally formed structure, the power-on base (8-1) and the power-on straight rod (8-2) are cylindrical in shape, a connecting round hole (8-3) is formed in the upper portion of the power-on base (8-1) in the axial direction, second internal threads are arranged on the inner wall of the connecting round hole (8-3), and the power-on base (8-1) is in threaded fit with a power-on cable of an engine through the second internal threads.
8. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 7, wherein: the longitudinal insulating pipe (7) is an insulating pipe with a secondary boss outside and the boss at the upper part is a primary boss, the cross section of the longitudinal insulating pipe (7) is circular, the longitudinal insulating pipe (7) is sequentially provided with a lower cylindrical hole (7-1), an upper cylindrical hole (7-2) and a large circular hole (7-3) from bottom to top along the axial direction, the upper cylindrical hole (7-2) is communicated with the lower cylindrical hole (7-1) and the large circular hole (7-3), and the depth of the lower cylindrical hole (7-1) is the primary boss; the diameter of the lower cylindrical hole (7-1) is equal to that of the electrifying straight rod (8-2), the size of the upper cylindrical hole (7-2) is equal to that of the electrifying base (8-1), the electrifying guide rod (8) is sequentially inserted into the longitudinal insulating tube (7) from top to bottom and is tightly matched with the longitudinal insulating tube (7), the electrifying base (8-1) is positioned in the upper cylindrical hole (7-2), the lower end of the electrifying straight rod (8-2) penetrates through the lower cylindrical hole (7-1) and then penetrates through the side circular hole (4-4) to be finally in threaded connection with the head through hole (5-4), the lower end face of the electrifying straight rod (8-2) is flush with the lower end face of the head through hole (5-4), the electrifying straight rod (8-2) is in clearance fit with the side circular hole (4-4), and the diameter of the electrifying straight rod (8-2) is identical to that of the side circular hole (4-4) And the large round hole (7-3) is matched with an electrified cable of the engine.
9. The aero engine afterburner based plasma on-duty flame igniter of claim 8, wherein: the guide rod shell (6) is in a cylindrical boss shape, the guide rod shell (6) is axially provided with three-stage stepped holes (6-1) matched with the appearance of a longitudinal insulating tube (7), the longitudinal insulating tube (7) is sequentially inserted into the three-stage stepped holes (6-1) from top to bottom and is tightly matched with the guide rod shell (6), the lower end of the longitudinal insulating tube (7) sequentially penetrates through a small round hole (3-1) and a circular groove (4-3) on one side and is in equal clearance fit with the small round hole (3-1) and the circular groove (4-3) on one side, the outer diameter of the lower end of the longitudinal insulating tube (7) is matched with the diameter of the small round hole (3-1) on one side and the diameter of the circular groove (4-3), the lower end of the guide rod shell (6) is tightly leaned on the top of the left side of the cathode shell (3), the upper part of the left side of the connecting sleeve (2) is closely arranged with the right side of the lower end of the guide rod shell (6).
10. The aero engine afterburner based plasma on-duty flame igniter as claimed in claim 1 or 2, wherein: the number of the embedded cathode assemblies (11) is three, and the three embedded cathode assemblies (11) are uniformly distributed on the flame stabilizer (1).
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| CN111779577B (en) * | 2020-06-30 | 2021-09-14 | 四川航天中天动力装备有限责任公司 | Afterburner ignition system |
| CN113217196B (en) * | 2021-03-03 | 2022-09-20 | 中国人民解放军空军工程大学 | Self-air-entraining sliding arc plasma jet igniter of concave cavity flame stabilizer and ignition method |
| CN115930264B (en) * | 2023-02-23 | 2024-08-02 | 中国航发沈阳发动机研究所 | Afterburner for small aeroengine |
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