CN109668169B - Aero-engine combustion chamber plasma auxiliary atomization ignition nozzle - Google Patents
Aero-engine combustion chamber plasma auxiliary atomization ignition nozzle Download PDFInfo
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- CN109668169B CN109668169B CN201811577418.3A CN201811577418A CN109668169B CN 109668169 B CN109668169 B CN 109668169B CN 201811577418 A CN201811577418 A CN 201811577418A CN 109668169 B CN109668169 B CN 109668169B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23Q—IGNITION; EXTINGUISHING-DEVICES
- F23Q7/00—Incandescent ignition; Igniters using electrically-produced heat, e.g. lighters for cigarettes; Electrically-heated glowing plugs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23Q—IGNITION; EXTINGUISHING-DEVICES
- F23Q7/00—Incandescent ignition; Igniters using electrically-produced heat, e.g. lighters for cigarettes; Electrically-heated glowing plugs
- F23Q7/22—Details
Abstract
The invention discloses a plasma-assisted atomization ignition nozzle of an aircraft engine combustion chamber, which comprises an electrode mounting seat, a swirler, a cathode atomization cone, an anode venturi and a cable, wherein the swirler is mounted in the front part of the electrode mounting seat, the swirler and the electrode mounting seat jointly form the electrode mounting seat with the swirler, the anode venturi is composed of an equal-diameter section and a convergence diffusion section, the electrode mounting seat with the swirler is mounted at the inner head part of a combustion chamber flame tube, the convergence diffusion section is positioned in the combustion chamber flame tube, the anode venturi, the electrode mounting seat with the swirler and the cathode atomization cone are coaxially arranged, the upper end of the cable is mounted on the combustion chamber flame tube, and the lower end of the cable sequentially penetrates through the combustion chamber flame tube and the electrode mounting seat and then is connected with the outer wall of the equal-diameter section. The invention can meet the requirements of the advanced aeroengine combustion chamber on short ignition delay time, wide point flameout boundary, high combustion efficiency, good outlet temperature field distribution and low pollutant emission.
Description
Technical Field
The invention relates to the technical field of aviation power plasma ignition and combustion supporting and plasma liquid fuel cracking, in particular to a plasma-assisted atomization ignition nozzle of an aircraft engine combustion chamber.
Background
The combustion chamber is used as a core component of the aircraft engine, with continuous updating and upgrading of equipment, the military and civil fields provide higher requirements for the performance of the combustion chamber of the aircraft engine, and for a conventional ignition combustion mode, the high-performance requirements of the combustion chamber cannot be met in a large range. Plasma ignition and combustion supporting technology is a new technology which has emerged in recent years, and is generally accepted by people in the related field because of its unique advantages, and the advantages of implementing plasma ignition and combustion supporting in an aeroengine are: the ignition speed is improved, the ignition delay time is reduced, the combustion efficiency is improved, the stable combustion range is widened, the outlet temperature field quality is improved, the pollutant emission is reduced, and the like. Research on plasma ignition and combustion-supporting technologies at home and abroad mainly focuses on non-equilibrium plasma, and on one hand, high-energy electrons in the generated non-equilibrium plasma collide with atoms, molecules and other particles in combustible mixed gas to generate a large amount of active particles such as oxygen atoms, ozone and ions to initiate chain oxidation reaction of fuel; on the other hand, the ionic wind generated in the discharging process of generating the non-equilibrium plasma is utilized to promote the mixing of the fuel, increase the contact area of the active particles and the rest particles, so that the chain oxidation reaction can be generated more quickly and better, and the reaction process of combustion is accelerated. At present, two ways of ignition and combustion supporting by using plasma are provided in a combustion chamber, the first way is to generate plasma outside the combustion chamber and then introduce the plasma into the combustion chamber, and the second way is to directly add a plasma generator into the combustion chamber and directly generate plasma in the combustion chamber to participate in ignition and combustion supporting. A combustion-supporting exciter of a rotary sliding arc plasma of an aircraft engine combustion chamber is developed by a Helmingtian team of the air force engineering university of the liberation military of people in 2016, the plasma combustion-supporting technology is firstly applied to the existing aircraft engine combustion chamber in China, and the combustion-supporting exciter is successful.
Plasma fuel cracking is a novel plasma ignition and combustion-supporting technology in the field of aviation power, and forms local uniform ionized gas with chemical active components through gas discharge to generate chemical and pneumatic double effects so as to strengthen the combustion state of plasma and adjacent areas thereof. The basic principle of plasma fuel cracking is as follows: plasma discharge is implemented in a fuel flowing area, and currently, the plasma discharge is in the forms of dielectric barrier discharge or sliding arc discharge, and high-energy electrons collide with fuel molecules in the discharge process to break carbon chains of fuel macromolecules into micromolecules and active particles with low carbon chains. Has great advantages and prospects in the aspects of improving combustion efficiency, widening stable combustion range, improving outlet temperature field quality, reducing pollutant emission and the like.
However, due to the characteristics of complex structure, poor working conditions and the like of the combustion chamber of the aero-engine, at present, only one fuel cracking head applied to the combustion chamber of the aero-engine is arranged at home and abroad, the fuel cracking head is invented by the He-minded team of the university of liberation of military air force engineering of China, the patent publication number of the fuel cracking head is CN108180075A, but as the conventional nozzle is adopted in one aspect of the fuel cracking head, and the discharge area is positioned between the venturi tube and the bell mouth, the action time of the formed plasma and the fuel is not long, the action range is not large, and the rotating airflow passing through the swirler only accounts for one part of the airflow at the nozzle, the promotion effect of the rotating airflow on fuel atomization is not fully exerted, so that the cracking effect of the plasma on the fuel is; on the other hand, the air inlet direction of the swirler is perpendicular to the air inlet direction of the fuel cracking head, and certain deficiency exists in air supply. The problems with these two aspects are: the fuel atomization effect is not good, the formed atomized liquid drops are not uniform, so that the generated plasma and the fuel liquid drops are not sufficiently cracked under the action, and the ignition combustion-supporting effect is deficient to a certain extent. A plasma enhanced atomizing nozzle is developed and applied for invention patent by Harbin engineering university in 2012, and the publication number is CN202757149U, the plasma generated by dielectric barrier discharge is adopted to crack a liquid fuel part and form gas micro-clusters in the liquid fuel, and the gas micro-clusters are instantaneously exploded at the nozzle outlet after passing through a swirler, so that the atomizing effect is enhanced. However, the energy of the plasma generated by the adopted dielectric barrier discharge is smaller than that of the sliding arc plasma under the same input power, the structure is complex, fuel oil vertically enters the nozzle and has certain loss, and the nozzle is inconvenient to mount on the head of the combustion chamber of the aero-engine, so that the nozzle is not suitable for the combustion chamber of the aero-engine.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a plasma-assisted atomization ignition nozzle for an aircraft engine combustion chamber, which can well meet the urgent requirements of an advanced aircraft engine combustion chamber on short ignition delay time, wide point flameout boundary, high combustion efficiency, good outlet temperature field distribution and low pollutant emission.
In order to achieve the purpose, the invention adopts the technical scheme that: the utility model provides an aeroengine combustion chamber plasma assists atomizing ignition nozzle which characterized in that: the electrode mounting seat with the swirler is arranged at the inner head of a flame tube of a combustion chamber of an aircraft engine, the convergent-divergent section is positioned in the flame tube of the combustion chamber, the combustion chamber flame tube, the anode venturi tube, the electrode mounting seat with the swirler and the cathode atomizing cone are all coaxially arranged, the upper end of the cable is mounted on the combustion chamber flame tube, and the lower end of the cable sequentially penetrates through the combustion chamber flame tube and the electrode mounting seat and then is connected with the outer wall of the equal-diameter section.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the cathode atomization cone comprises a high-temperature alloy shell cone section, a high-temperature alloy shell connecting section, an oil filter and a drainage top block, wherein the head of the high-temperature alloy shell cone section is a conical end part, the conical end part is uniformly provided with three spouts along the circumferential direction, one end of the high-temperature alloy shell connecting section stretches into one end of the high-temperature alloy shell cone section far away from the conical end part and is in threaded connection with the high-temperature alloy shell cone section, the oil filter is installed in the middle of the high-temperature alloy shell connecting section, three mounting holes are uniformly formed in the conical end part along the circumferential direction, the three mounting holes are correspondingly arranged and correspondingly communicated with the three spouts, a top block with a swirl groove and a nozzle are arranged in each mounting hole, the nozzles are arranged at positions close to the spouts and are matched with one ends of the mounting holes, and the top block with the swirl groove is arranged at the other end of the mounting holes, the one end that takes whirl groove kicking block to be close to the nozzle cooperates with the upper portion inner cone surface of nozzle, drainage kicking block threaded connection just is close to in the inside of superalloy outer shell cone section the toper tip is in order compressing tightly taking whirl groove kicking block and nozzle.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the top block with the cyclone grooves comprises a circular table head and a cylindrical tail, the large end of the circular table head is arranged at one end of the cylindrical tail, and three inclined grooves are uniformly formed in the circular table head in the circumferential direction.
The plasma-assisted atomizing ignition nozzle for the combustion chamber of the aircraft engine is characterized in that the half-cone angle of the conical end part is 30-60 degrees, and the included angle α between the central line of the inclined groove and the generatrix of the circular truncated cone head part3Said α3The angle of the angle is 60-65 degrees.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the nozzle includes big cylinder portion and little cylinder portion, the one end setting of little cylinder portion is in the other end middle part of big cylinder portion, be provided with one on the nozzle with round platform head matched with inverted cone-shaped groove, inverted cone-shaped groove's apical part stretches into in the little cylinder portion, the middle part of little cylinder portion is provided with the aperture that runs through that communicates with inverted cone-shaped groove mutually, little cylinder portion sets up and is being close to nozzle department.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the electrode mounting seat is of a hollow cylinder structure, the outer surface of the rear portion of the electrode mounting seat is a flame tube head mounting fitting surface, the inner surface of the rear portion of the electrode mounting seat is an anode venturi tube inner fitting surface, a penetrating cable mounting hole is formed in one side of the middle of the electrode mounting seat, an electrode mounting seat boss which is coaxial with the cable mounting hole is arranged on the outer side of the electrode mounting seat, and the electrode mounting seat boss is located at the outer end of the cable mounting hole.
Plasma-assisted atomization of combustion chamber of aero-engineThe ignition nozzle is characterized in that the swirler comprises an outer annular wall, an inner annular wall and swirl vanes, the inner annular wall is arranged in the outer annular wall, the swirl vanes are obliquely arranged between the outer annular wall and the inner annular wall and can enable the airflow outlet angle α of the swirl vanes2The number of the swirl vanes is 20-30 degrees, the swirl vanes are 8-12 and are uniformly distributed between the outer ring wall and the inner ring wall, the outer ring wall is arranged in the front part of the electrode mounting seat, and the cone section of the high-temperature alloy shell close to the cylindrical section of the cone end part is arranged at the center of the inner ring wall.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the cable comprises a copper bar inner layer, an insulating outer layer and an insulating boss, wherein the insulating outer layer is sleeved on the middle upper portion of the copper bar inner layer, and the insulating boss is sleeved on the upper end of the insulating outer layer.
Foretell aeroengine combustion chamber plasma assists atomizing ignition nozzle, its characterized in that: the outer layer hood of the flame tube of the combustion chamber is provided with a cable fixing hole, the inner surface of the rear end of the flame tube of the combustion chamber is a flame tube head supporting surface for fixing an electrode mounting seat, and the flame tube head supporting surface is matched with a flame tube head mounting matching surface; the cable passes through the cable fixing hole and the cable mounting hole in sequence, the lower end of the inner layer of the copper bar is connected with the outer wall of the equal-diameter section, the lower end face of the insulating outer layer is matched with the boss of the electrode mounting seat, and the insulating boss is mounted at the cable fixing hole.
The plasma-assisted atomization ignition nozzle for the combustion chamber of the aircraft engine is characterized in that the outer surface of the constant-diameter section is an outer matching surface of an anode venturi tube, the outer matching surface of the anode venturi tube is tightly attached to the inner matching surface of the anode venturi tube, and an air outlet angle α on the inner surface of the rear end port of the convergence diffusion section1Is 45-55 degrees.
Compared with the prior art, the invention has the following advantages:
1. the invention solves the problems in the ignition combustion supporting aspect in the combustion chamber of the prior aeroengine, belongs to the research accumulation of the project group in the plasma ignition and combustion supporting aspect and the application thereof in the combustion chamber of the aeroengine for a long time; the invention meets the important requirement of the state for developing advanced aero-engines, can possibly become a subversive technology for improving the combustion performance of the aero-engine combustion chamber, leads the design of the combustion chamber and pushes the military and civil aircrafts in China to develop to a higher level.
2. The plasma auxiliary atomization ignition nozzle for the combustion chamber of the aircraft engine is invented and created on the basis of the common combustion chamber of the aircraft engine, has a simple structure and strong universality, can realize an ignition function while assisting fuel atomization, can realize the ignition and combustion-supporting functions only by replacing the head of a flame tube in the combustion chamber of the original aircraft engine, and has the same structural size and flow distribution as those of the original combustion chamber.
3. The rotational flow gas for driving the three-dimensional rotating sliding arc plasma exciter to work is derived from the gas at the inlet of the combustion chamber, and the blade type axial flow cyclone at the head generates rotational flow without external air introduction.
4. The invention can make full use of the cracking effect of the plasma, so that the fuel atomization effect is obvious, the uniformity of fuel and air mixture is improved, and active particles promoting combustion chemical reaction are generated, thereby solving the problems of slow ignition speed, long ignition delay time, low combustion efficiency, lean flameout, high-altitude ignition and uneven outlet temperature field of a combustion chamber of an aircraft engine under special conditions.
The invention is described in further detail below with reference to the figures and examples.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
FIG. 2 is a schematic view of a cathode atomizing cone of the present invention.
FIG. 3 is a schematic diagram of the internal structure of the cathode atomizing cone of the present invention.
Fig. 4 is a front view of the top block with a swirl groove of the present invention.
Fig. 5 is a bottom view of the top block with a swirl groove of the present invention.
FIG. 6 is a front view of the nozzle of the present invention.
Fig. 7 is a sectional view a-a of fig. 6.
Fig. 8 is a top view of fig. 6.
Fig. 9 is a schematic structural view of an electrode mount with a swirler according to the present invention.
FIG. 10 is a schematic view of the cyclone of the present invention.
FIG. 11 is an expanded view of the cyclone of the present invention.
Fig. 12 is a schematic view of the structure of the cable of the present invention.
FIG. 13 is a schematic view of the combustor basket of the present invention.
FIG. 14 is a schematic diagram of the configuration of the anode venturi of the present invention.
Description of reference numerals:
1-cathode atomizing cone; 2-electrode mounting base; 3, a swirler;
3-1-outer annular wall; 3-2-inner annular wall; 3-swirl vanes;
4-a cable; 5, a flame tube of the combustion chamber; 6-anode venturi;
6-1-equal diameter section; 6-2-convergent-divergent section; 7-high temperature alloy shell connecting section;
8-superalloy jacket-cone section; 8-1-nozzle; 9-oil filtration;
10, draining a top block; 11-a top block with a swirl groove; 11-1-a truncated cone head;
11-2-cylindrical tail; 12-a nozzle; 12-1-a large cylindrical portion;
12-11-inverted cone groove; 12-2-a small cylindrical portion; 12-21-through small hole;
13-a chute; 14-electrode mount boss; 15-cable mounting holes;
16-flame tube head mounting matching surface; 17-inner matching surface of the anode venturi tube;
18-an insulating outer layer; 19-inner layer of copper bar; 20-insulating bosses;
21-cable fixing holes; 22-a flame tube head bearing surface; 23-outer matching surface of the anode venturi tube.
Detailed Description
For convenience of description, the present invention defines the air intake direction as front.
As shown in fig. 1, the present invention comprises an electrode mounting base 2, a swirler 3, a cathode atomizing cone 1, an anode venturi 6 and a cable 4, wherein the swirler 3 is mounted in the front portion of the electrode mounting base 2, the swirler 3 and the electrode mounting base 2 together form the electrode mounting base with the swirler, the cone end of the cathode atomizing cone 1 is mounted on the swirler 3, the cone portion of the cathode atomizing cone 1 is located in the electrode mounting base 2, the anode venturi 6 is composed of a constant diameter section 6-1 and a convergent-divergent section 6-2, the large end of the convergent-divergent section 6-2 is arranged at one end of the constant diameter section 6-1, the constant diameter section 6-1 is mounted in the rear end of the electrode mounting base 2, the inner surface of the constant diameter section 6-1 and the inner surface of the electrode mounting base 2 are both arc surfaces, the constant diameter section 6-1 is smoothly joined with the inner surface of the electrode mounting base 2, the electrode mounting seat with the swirler is mounted at the inner head of a combustion chamber flame tube 5 of an aircraft engine, the convergent-divergent section 6-2 is positioned in the combustion chamber flame tube 5, the anode venturi tube 6, the electrode mounting seat with the swirler and the cathode atomizing cone 1 are coaxially arranged, the upper end of the cable 4 is mounted on the combustion chamber flame tube 5, and the lower end of the cable 4 sequentially penetrates through the combustion chamber flame tube 5 and the electrode mounting seat 2 and then is connected with the outer wall of the equal-diameter section 6-1.
The combustion chamber flame tube 5 is a combustion chamber flame tube of an aircraft engine, and the cone part of the cathode atomizing cone 1 is positioned in the electrode mounting seat 2 (namely the bottom surface of the cone part of the cathode atomizing cone 1 is superposed with the outlet end surface of the central through hole of the electrode mounting seat with the swirler).
As shown in fig. 2 and 3, the cathode atomizing cone 1 includes a superalloy casing cone section 8, a superalloy casing cone connecting section 7, an oil filter 9 and a drainage top block 10, wherein the head of the superalloy casing cone section 8 is a tapered end, three nozzles 8-1 are uniformly arranged on the tapered end along the circumferential direction, one end of the superalloy casing cone section 7 extends into one end of the superalloy casing cone section 8 far away from the tapered end and is in threaded connection with the superalloy casing cone section 8, the oil filter 9 is installed in the middle of the superalloy casing cone connecting section 7, three installation holes are uniformly arranged in the tapered end along the circumferential direction, the three installation holes are correspondingly arranged and communicated with the three nozzles 8-1, a rotation top block 11 and a nozzle 12 are arranged in each flow groove installation hole, the nozzle 12 is arranged near the nozzle 8-1 and is matched with one end of the installation hole, the top block 11 with the swirl slots is arranged at the other end of the mounting hole, one end, close to the nozzle 12, of the top block 11 with the swirl slots is matched with the upper inner conical surface of the nozzle 12, and the drainage top block 10 is in threaded connection with the inside of the high-temperature alloy shell cone section 8 and is close to the conical end to tightly press the top block 11 with the swirl slots and the nozzle 12.
The high-temperature alloy shell cone section 8 and the high-temperature alloy shell connecting section 7 are made of GH3044 alloy, and the rest is made of tungsten-copper alloy. The mounting hole consists of two sections, the diameter of the first section of the mounting hole is 5-7 mm, the axial length of the first section of the mounting hole is 5-6 mm, and the mounting hole is mainly used for placing the swirl groove top block 11; the diameter of the second section of mounting hole is 3 mm-3.4 mm, and the second section of mounting hole penetrates through the front section conical head of the high-temperature alloy shell connecting section 7 and is used for placing the nozzle 12.
The outer diameter of the cylindrical part of the high-temperature alloy shell-cone section 8 is 22-26 mm, the axial length is 38-42 mm, the inner surface is divided into an upper thread part and a lower thread part, the length of the upper thread part is 18-22 mm, and the length of the lower thread part is 17-21 mm. The drainage ejector block 10 is a cylinder with a central through hole, the outer diameter is 18 mm-22 mm, the diameter of the central through hole is 7 mm-9 mm, and the axial length is 13 mm-17 mm. The outer surface of the drainage top block 10 is provided with external threads matched with the equal-diameter section of the high-temperature alloy shell cone section 8, and the lower end face of the drainage top block 10 is contacted with the upper end face of the swirl groove top block 11 through threads, so that the swirl groove top block 11 and the nozzle 12 are compressed.
The constant diameter section of the high-temperature alloy shell connecting section 7 is 22-26 mm in outer diameter and 38-42 mm in axial length, the lower threaded section is 18-22 mm in axial length, the inner surface is divided into three sections, the first section is 20-24 mm in inner diameter and 18-22 mm in length, the second section is 11-13 mm in inner diameter and 10-4 mm in length, the third section is 18-22 mm in inner diameter and 26-30 mm in length, and a central hole of the second section is an oil filter mounting hole and is used for mounting an oil filter 9 and filtering impurities in fuel oil to ensure the cleanliness of the oil.
As shown in fig. 4 and 5, the top block 11 with the swirl slots comprises a circular truncated cone head 11-1 and a cylindrical tail 11-2, the large end of the circular truncated cone head 11-1 is arranged at one end of the cylindrical tail 11-2, and the circular truncated cone head 11-1 is uniformly provided with three chutes 13 along the circumferential direction.
The diameter of the tail part 11-2 of the cylinder is 4 mm-6 mm, the length is 5 mm-6 mm, the height of the head part 11-1 of the circular truncated cone is 0.9 mm-1.1 mm, the diameter of the small circle is 1.10 mm-1.15 mm, and the three inclined grooves 13 are used for enabling the entering fuel to rotate.
In this embodiment, the half cone angle of the tapered end portion is 30 ° to 60 °.
As shown in fig. 5, an included angle α between the center line of the inclined groove 13 and the generatrix of the truncated cone head 11-13Said α3The angle of the angle is 60-65 degrees.
As shown in fig. 6 to 8, the nozzle 12 comprises a large cylindrical portion 12-1 and a small cylindrical portion 12-2, one end of the small cylindrical portion 12-2 is arranged in the middle of the other end of the large cylindrical portion 12-1, an inverted cone-shaped groove 12-11 matched with the truncated cone head 11-1 is arranged on the nozzle 12, the tip of the inverted cone-shaped groove 12-11 extends into the small cylindrical portion 12-2, a small through hole 12-21 communicated with the inverted cone-shaped groove 12-11 is arranged in the middle of the small cylindrical portion 12-2, and the small cylindrical portion 12-2 is arranged near the nozzle 8-1.
The nozzle 12 cooperates with the stepped configuration of the mounting bore to secure the nozzle 12. The diameter of the large cylindrical part 12-1 is 5 mm-7 mm, the height is 0.9 mm-1.1 mm, the diameter of the small cylindrical part 12-2 is 3 mm-3.4 mm, the height is 0.9 mm-1.1 mm, the diameter of the bottom circle of the inverted cone-shaped groove 12-11 is 5 mm-7 mm, the included angle between the generatrix of the cone surface and the central line is 60-65 degrees, the height of the cone surface is 1.3 mm-1.7 mm, the diameter of the small penetrating hole 12-21 is 0.18 mm-0.22 mm, and the length is 0.4 mm-0.6 mm.
As shown in fig. 9, the electrode mounting base 2 is a hollow cylinder structure, the outer surface of the rear portion of the electrode mounting base 2 is a flame tube head mounting fitting surface 16, the inner surface of the rear portion of the electrode mounting base 2 is an anode venturi inner fitting surface 17, a penetrating cable mounting hole 15 is formed in one side of the middle portion of the electrode mounting base 2, an electrode mounting base boss 14 coaxial with the cable mounting hole 15 is formed in the outer side of the electrode mounting base 2, and the electrode mounting base boss 14 is located at the outer end of the cable mounting hole 15.
The electrode mounting base 2 is a hollow revolving body, the electrode mounting base 2 is made of ceramics, the flame tube head mounting matching surface 16 is used for matching with a flame tube head supporting surface 22 at the rear end of a flame tube 5 of the combustion chamber, the anode Venturi tube inner matching surface 17 is used for matching with the outer surface of the equal-diameter section 6-1 of the anode Venturi tube 6, and the matching surface length is 18 mm-20 mm. The outer diameter of the electrode mounting seat 2 is 72 mm-76 mm, and the axial length is 35 mm-39 mm. The diameter of the electrode mounting base boss 14 is 2.8 mm-3.2 mm, the height is 0.8 mm-1.2 mm, the electrode mounting base boss 14 is used for being matched with the lower end face of the insulating outer layer 18, the length of the center of the electrode mounting base boss 14 from the rear end face of the electrode mounting base 2 is 14 mm-18 mm, and the diameter of the cable mounting hole 15 is matched with the copper bar inner layer 19.
As shown in FIG. 10, the cyclone 3 comprises an outer annular wall 3-1, an inner annular wall 3-2 and swirl vanes 3-3, the inner annular wall 3-2 is arranged in the outer annular wall 3-1, the swirl vanes 3-3 are obliquely arranged between the outer annular wall 3-1 and the inner annular wall 3-2 and can enable the air flow outlet angle α of the swirl vanes 3-32The number of the swirl vanes 3-3 is 20-30 degrees, the number of the swirl vanes 3-3 is 8-12, the swirl vanes are uniformly distributed between an outer annular wall 3-1 and an inner annular wall 3-2, the outer annular wall 3-1 is arranged in the front part of the electrode mounting seat 2, and the high-temperature alloy shell cone section 8 is arranged at the center of the inner annular wall 3-2 close to the cylindrical section of the conical end part.
The swirler 3 is a single-stage blade type axial flow swirler, and airflow passes through the swirler 3 to form rotating airflow between the cathode atomizing cone 1 and the anode venturi 6. The inner diameter of the inner annular wall 3-2 is 20 mm-26 mm, and the inner diameter of the outer annular wall 3-1 is 60mmThe thickness of the inner ring wall 3-2 is 1.8 mm-2.2 mm, the outer ring wall 3-1 is the outer wall of the electrode mounting seat 2 which is integrally formed with the outer ring wall, and the axial length of the swirler 3 is 10 mm-12 mm. The airflow passes through the swirler 3 to form a rotating airflow between the cathode atomizing cone 1 and the anode venturi 6. Inner diameter d of inner annular wall 3-21Equal to the outer diameter of the cylindrical portion of the superalloy jacket-cone segment 8.
As shown in FIG. 11, when the inlet angle of the airflow is 90, the outlet angle of the airflow α2Is 20-30 °
As shown in fig. 12, the cable 4 includes a copper rod inner layer 19, an insulating outer layer 18 and an insulating boss 20, the insulating outer layer 18 is sleeved on the middle upper portion of the copper rod inner layer 19, and the insulating boss 20 is sleeved on the upper end of the insulating outer layer 18.
The outer diameter of the outer insulating layer 18 is 4 mm-6 mm, the diameter of the inner copper rod layer 19 is 2 mm-4 mm, the outer insulating layer 18 is made of polytetrafluoroethylene, the diameter of the upper end of the insulating boss 20 is 10 mm-12 mm, the diameter of the lower end of the insulating boss is 8 mm-10 mm, and the outer insulating layer is used for installing the cable 4 in a cable fixing hole 21 of the combustor flame tube 5. The lower end of the cable 4 is provided with an exposed copper bar, the exposed length is 5 mm-6 mm, the exposed copper bar is arranged in a cable mounting hole 15 of an electrode mounting seat with a cyclone, and the inner layer 19 of the copper bar of the cable 4 is kept well in electric conduction with the anode Venturi tube 6 of the high-temperature alloy.
As shown in fig. 13, the outer layer cap of the combustor basket 5 is provided with a cable fixing hole 21, the inner surface of the rear end of the combustor basket 5 is a basket head supporting surface 22 for fixing the electrode mounting base 2, and the basket head supporting surface 22 is matched with the basket head mounting matching surface 16; the cable 4 sequentially penetrates through a cable fixing hole 21 and a cable mounting hole 15, the lower end of the copper bar inner layer 19 is connected with the outer wall of the equal-diameter section 6-1, the lower end face of the insulating outer layer 18 is matched with the boss 14 of the electrode mounting seat, and the insulating boss 20 is mounted at the cable fixing hole 21.
The combustor liner 5 is processed by adopting nickel-based high-temperature alloy GH536, and the diameter of the cable fixing hole 21 is 10-12 mm.
As shown in FIG. 14, the outer surface of the constant diameter section 6-1 is an anode Venturi outer mating surface 23, and the anodeThe outer matching surface 23 of the venturi is tightly jointed with the inner matching surface 17 of the anode venturi, and the outlet angle α of the inner surface of the rear end port of the convergent-divergent section 6-21Is 45-55 degrees.
The anode venturi 6 is a hollow revolving body, and the anode venturi 6 is made of alloy materials. The outer diameter of the constant diameter section 6-1 and the inner diameter of the inner matching surface 17 of the anode Venturi tube are both d2And d is2The value of (1) is 62-66 mm, and the length of the equal-diameter section 6-1 is equal to the length of the inner matching surface 17 of the anode Venturi and is 18-20 mm; inner diameter d of rear end port of convergent-divergent section 6-2358 mm-62 mm, the thickness of the anode Venturi tube 6 is 0.8 mm-1.2 mm.
The working principle of the invention is as follows: according to the invention, the anode venturi 6 is connected with high-voltage alternating current through the cable 4, the anode venturi 6 and the cable 4 are electrified in a direct contact mode, the inlet of the cathode atomizing cone 1 connected with the oil pipe is arranged on an outer casing of a combustion chamber of the aero-engine, and the cathode atomizing cone 1 and the outer casing of the aero-engine are grounded.
During operation, fuel oil enters from the through hole of the high-temperature alloy shell connecting section 7, impurities are filtered through the oil filter 9, the fuel oil is filled in the cavity of the cathode atomization cone 1, enters the gap between the top block 11 with the swirl groove and the high-temperature alloy shell cone section 8 through the central through hole of the drainage top block 10, then generates swirl through the chute 13 with the swirl groove top block 11 and the taper part, and is sprayed out through the small hole of the nozzle 12 to generate atomized fuel oil.
The nozzle 12 is simple in structure, fuel oil firstly passes through the chute 13 to generate rotational flow, atomization is facilitated in the next step, the fuel oil is sprayed out at a small hole of the nozzle 12 at a high speed, atomized fuel oil droplets cover a conical area, the fuel oil droplets generated by the method are good in atomization effect and uniform in droplet distribution, the three nozzles better cover a combustion area of a combustion chamber, the overlapped area of the fuel oil sprayed out of the three nozzles 12 is overlapped with a backflow area of the head of the combustion chamber, and stable combustion of flame is facilitated.
Under the action of the rotating airflow, three-dimensional rotating sliding arc discharge is formed between the anode venturi tube 6 and the cathode atomizing cone 1 to generate three-dimensional rotating sliding arc plasma, fuel oil sprayed at multiple points in short upstream passes through a discharge region after being preliminarily atomized, and the kerosene is ignited by utilizing the characteristics of high temperature, high speed and rich active particles of the three-dimensional rotating sliding arc plasma. In addition, a large amount of high-energy electrons generated in the three-dimensional rotating sliding arc discharging process and active particles generated by excitation collide with atomized fuel oil small molecules, bonds among the high-carbon fuel oil molecules are broken, and low-carbon small molecules with lower 'boiling points' are formed. On one hand, the low-carbon micromolecules can be generated in the process of fuel oil cracking by sliding arc discharge, participate in combustion in the form of gaseous fuel, accelerate the physical process of combustion and flame propagation and improve the completeness of combustion; on the other hand, active particles such as oxygen atoms, ozone, ions, active groups and the like generated in the sliding arc discharge process participate in the combustion reaction, and the chemical reaction rate of the combustion is improved. The combustion efficiency is improved, the stable combustion range and the flameout boundary are widened, the outlet temperature field quality is improved, and the pollutant emission is reduced.
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 (9)
1. The utility model provides an aeroengine combustion chamber plasma assists atomizing ignition nozzle which characterized in that: the electrode assembly comprises an electrode mounting seat (2), a swirler (3), a cathode atomizing cone (1), an anode venturi (6) and a cable (4), wherein the swirler (3) is mounted in the front part of the electrode mounting seat (2), the swirler (3) and the electrode mounting seat (2) jointly form the electrode mounting seat with the swirler, the cone end of the cathode atomizing cone (1) is mounted on the swirler (3), the cone part of the cathode atomizing cone (1) is positioned in the electrode mounting seat (2), the anode venturi (6) consists of an equal-diameter section (6-1) and a convergent-divergent section (6-2), the large end of the convergent-divergent section (6-2) is arranged at one end of the equal-diameter section (6-1), the equal-diameter section (6-1) is mounted in the rear end of the electrode mounting seat (2), the inner surface of the equal-diameter section (6-1) and the inner surface of the electrode mounting seat (2) are both arc surfaces, the inner surface of the joint of the equal-diameter section (6-1) and the electrode mounting seat (2) is smoothly connected, the electrode mounting seat with the swirler is arranged at the inner head of a flame tube (5) of a combustion chamber of an aircraft engine, the convergence diffusion section (6-2) is positioned in the flame tube (5) of the combustion chamber, the anode venturi tube (6), the electrode mounting seat with the swirler and the cathode atomization cone (1) are coaxially arranged, the upper end of the cable (4) is arranged on the flame tube (5) of the combustion chamber, and the lower end of the cable (4) sequentially penetrates through the flame tube (5) of the combustion chamber and the electrode mounting seat (2) and then is connected with the outer wall of the equal-diameter section (6-1);
the cathode atomization cone (1) comprises a high-temperature alloy shell cone section (8), a high-temperature alloy shell connecting section (7), an oil filter (9) and a drainage top block (10), the head of the high-temperature alloy shell cone section (8) is a cone end part, the cone end part is uniformly provided with three spouts (8-1) along the circumferential direction, one end of the high-temperature alloy shell connecting section (7) extends into one end of the high-temperature alloy shell cone section (8) far away from the cone end part and is in threaded connection with the high-temperature alloy shell cone section (8), the oil filter (9) is installed in the middle of the high-temperature alloy shell connecting section (7), three mounting holes are uniformly arranged along the circumferential direction in the cone end part and are correspondingly arranged and communicated with the three spouts (8-1), and each mounting hole is internally provided with a rotary flow groove (11) and a nozzle (12), nozzle (12) set up be close to spout (8-1) department and with the one end of mounting hole cooperatees, take whirl groove kicking block (11) to set up the other end of mounting hole, take whirl groove kicking block (11) to be close to the one end of nozzle (12) and the cooperation of the upper portion internal cone of nozzle (12), drainage kicking block (10) threaded connection just is close to in the inside of superalloy shell cone section (8) the toper tip is in order to compress tightly taking whirl groove kicking block (11) and nozzle (12).
2. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle as claimed in claim 1, wherein: the top block (11) with the swirl groove comprises a circular table head (11-1) and a cylindrical tail (11-2), the large end of the circular table head (11-1) is arranged at one end of the cylindrical tail (11-2), and the circular table head (11-1) is uniformly provided with three chutes (13) along the circumferential direction.
3. The plasma-assisted atomizing ignition nozzle for the combustion chamber of the aircraft engine as claimed in claim 2, wherein the half cone angle of the tapered end part is 30-60 degrees, and the included angle α between the center line of the inclined groove (13) and the generatrix of the truncated cone head part (11-1)3Said α3The angle of the angle is 60-65 degrees.
4. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle according to claim 2 or 3, characterised in that: the nozzle (12) comprises a large cylindrical part (12-1) and a small cylindrical part (12-2), one end of the small cylindrical part (12-2) is arranged in the middle of the other end of the large cylindrical part (12-1), an inverted cone-shaped groove (12-11) matched with the circular truncated cone head (11-1) is formed in the nozzle (12), the tip part of the inverted cone-shaped groove (12-11) extends into the small cylindrical part (12-2), a small through hole (12-21) communicated with the inverted cone-shaped groove (12-11) is formed in the middle of the small cylindrical part (12-2), and the small cylindrical part (12-2) is arranged close to the nozzle (8-1).
5. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle as claimed in claim 1, wherein: the electrode mounting seat (2) is of a hollow cylinder structure, the outer surface of the rear portion of the electrode mounting seat (2) is a flame tube head mounting matching surface (16), the inner surface of the rear portion of the electrode mounting seat (2) is an anode venturi inner matching surface (17), a penetrating cable mounting hole (15) is formed in one side of the middle of the electrode mounting seat (2), an electrode mounting seat boss (14) which is coaxial with the cable mounting hole (15) is arranged on the outer side of the electrode mounting seat (2), and the electrode mounting seat boss (14) is located at the outer end of the cable mounting hole (15).
6. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle as claimed in claim 5, wherein: the swirler (3) comprises an outer annular wall (3-1),The cyclone separator comprises an inner annular wall (3-2) and cyclone vanes (3-3), wherein the inner annular wall (3-2) is arranged in the outer annular wall (3-1), and the cyclone vanes (3-3) are obliquely arranged between the outer annular wall (3-1) and the inner annular wall (3-2) and can enable the air flow outlet angle α of the cyclone vanes (3-3)2The number of the swirl vanes (3-3) is 20-30 degrees, the swirl vanes (3-3) are 8-12 and are uniformly distributed between the outer annular wall (3-1) and the inner annular wall (3-2), the outer annular wall (3-1) is arranged in the front part of the electrode mounting seat (2), and the high-temperature alloy shell cone section (8) is arranged at the center of the inner annular wall (3-2) close to the cylindrical section of the conical end part.
7. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle according to claim 5 or 6, characterised in that: the cable (4) comprises a copper bar inner layer (19), an insulating outer layer (18) and an insulating boss (20), wherein the insulating outer layer (18) is sleeved on the middle upper portion of the copper bar inner layer (19), and the insulating boss (20) is sleeved on the upper end of the insulating outer layer (18).
8. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle as claimed in claim 7, wherein: the outer layer hood of the flame tube (5) of the combustion chamber is provided with a cable fixing hole (21), the inner surface of the rear end of the flame tube (5) of the combustion chamber is a flame tube head supporting surface (22) for fixing the electrode mounting seat (2), and the flame tube head supporting surface (22) is matched with the flame tube head mounting matching surface (16); the cable (4) sequentially penetrates through a cable fixing hole (21) and a cable mounting hole (15), the lower end of the copper bar inner layer (19) is connected with the outer wall of the equal-diameter section (6-1), the lower end face of the insulating outer layer (18) is matched with the electrode mounting seat boss (14), and the insulating boss (20) is mounted in the cable fixing hole (21).
9. An aircraft engine combustion chamber plasma-assisted atomisation ignition nozzle according to claim 5 or 6, characterised in that: the outer surface of the equal-diameter section (6-1) is an anode Venturi outer matching surface (23), the anode Venturi outer matching surface (23) is tightly attached to an anode Venturi inner matching surface (17), and the rear part of the convergence diffusion section (6-2)Outlet angle α of inner surface of port1Is 45-55 degrees.
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| CN201811577418.3A CN109668169B (en) | 2018-12-20 | 2018-12-20 | Aero-engine combustion chamber plasma auxiliary atomization ignition nozzle |
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| CN112413642B (en) * | 2020-11-09 | 2022-02-15 | 中国人民解放军空军工程大学 | Intelligent combustion chamber of aero-engine |
| CN113153539B (en) * | 2021-03-19 | 2023-05-12 | 中国人民解放军空军工程大学 | Single-double-circuit combined three-dimensional rotating sliding arc plasma exciter |
| CN113898974B (en) * | 2021-10-19 | 2022-10-04 | 中国人民解放军空军工程大学 | Aero-engine combustion chamber sliding arc plasma on-duty flame head |
| CN115264533B (en) * | 2022-07-24 | 2023-06-23 | 哈尔滨工程大学 | Natural gas coaxial staged combustion chamber adopting central ignition and combustion method |
| CN115342387A (en) * | 2022-08-08 | 2022-11-15 | 中国航发湖南动力机械研究所 | Combustion chamber adopting rotating sliding arc ignition structure and aero-engine |
| CN116164307B (en) * | 2023-03-09 | 2024-04-19 | 中国空气动力研究与发展中心空天技术研究所 | Gas spiral-flow type air-hydrogen torch igniter |
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| CN202835445U (en) * | 2012-08-23 | 2013-03-27 | 中国航空动力机械研究所 | Centrifuge atomizing spray nozzle |
| CN104879780B (en) * | 2014-02-28 | 2018-10-19 | 北京大学 | A kind of multichannel heating region ignition burning device |
| CN103925116B (en) * | 2014-04-28 | 2016-03-02 | 中国航天空气动力技术研究院 | Sliding arc ignition mechanism |
| US20200224877A1 (en) * | 2016-10-21 | 2020-07-16 | Fgc Plasma Solutions | Apparatus and method for using plasma to assist with the combustion of fuel |
| CN107218623B (en) * | 2017-05-25 | 2019-08-09 | 航天神洁(北京)科技发展有限公司 | A kind of sliding arc auxiliary combustion equipment generating atmospheric non-equilibrium plasma |
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