A plasma ignition and combustion exciter for an aeroengine triple-swirl combustor

Abstract

An aero-engine three-swirl combustion chamber plasma ignition combustion exciter includes a three-stage swirl device, a ceramic insulation section and a swirl fuel nozzle in an integrated structure; the two-stage swirl device is arranged on the outer wall surface of the inner ring of the one-stage swirl device, the three-stage swirl device is arranged on the outer wall surface of the isolation ring of the two-stage swirl device, and the one-stage swirl device is arranged on the outer wall surface of the ceramic insulation section; the inner wall surface of the ceramic insulation section is inserted into the swirl fuel nozzle; the three-stage swirl device design has the advantages of forming strong turbulence, a stable backflow area and uniform mixed gas, which helps to improve the combustion chamber ignition and extinction performance and improve the working stability and reliability of the engine; the small volume insulation structure realizes high-density small-area discharge, and overcomes the problems of poor working effect due to the non-ideal discharge area, extinction under specific working conditions and weak working performance due to insufficient strength of the ceramic material in the prior art.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine combustion chamber, and particularly relates to a plasma ignition combustion exciter of a three-swirl combustion chamber of an aero-engine. BACKGROUND

[0002] Three-swirl combustion as a key combustion organization form of a new generation of aero-engine combustion chamber has the characteristics of high temperature rise performance, low pollutant emission, reasonable oil mist distribution and wide stable working range under the premise of ensuring high efficient combustion of the combustion chamber. Three-swirl combustion utilizes three-stage swirler to realize greater head intake to ensure greater oil-gas ratio combustion.

[0003] The sliding arc plasma combustion supporting technology is a new technology for improving the combustion performance of the combustion chamber by ionizing air, fuel and air / fuel mixture to generate plasma for combustion supporting excitation under the driving of fluid medium through high-voltage alternating current applied between electrodes. This technology has great potential in expanding the combustion chamber's point-extinction boundary, improving combustion efficiency, reducing pollutant emission and improving the quality of the combustion chamber outlet temperature field. A large number of basic researches on the plasma ignition combustion supporting technology have been carried out at home and abroad, and the technology is still in the stage of technical research. The sliding arc plasma discharge form is one of the feasible schemes of the plasma ignition combustion supporting technology due to its simple discharge structure, stable working performance and good ignition combustion excitation effect.

[0004] The patent application with publication number CN111765032A discloses a fuel atomizing nozzle with a sliding arc plasma-high disturbance cross structure. The center is connected to the high-voltage electrode by placing a tungsten rod into the discharge area, and then the high-voltage electrode discharges with the nozzle as a whole to achieve ignition. However, this method requires separate gas supply to the nozzle and the discharge may cause ablation at the nozzle outlet, thus having certain limitations. The patent application with publication number CN111734532A discloses a filamentous arc plasma exciter with a swirl hole. The filamentous arc plasma is combined with the head of the combustion chamber, but the ceramic insulation structure of this method requires a large modification of the swirl device of the combustion chamber head, which reduces the number of swirl holes on one hand and makes the fuel spray unable to fully contact the arc on the other hand, resulting in that this plasma exciter has a large impact on the flow field of the combustion chamber itself, which is not conducive to ignition and limits further application. The invention patent application with publication number CN113623685A shows a vortex device structure for rotating sliding arc ignition, which installs an insulation cone on the vortex device structure by additionally installing a support structure, and the electrode is arranged on the cone for discharge ignition. Similarly, this invention requires a large change in the structure of the vortex device, which affects the flow field structure of the combustion chamber and cannot meet the design requirements of the combustion chamber. The patent application with publication number CN113898974A introduces an aviation engine combustion chamber sliding arc plasma duty flame head. This structure sleeves the high-voltage electrode on the primary swirl device to realize discharge with the nozzle. The insulation material of this structure is a ceramic-based printed swirl device with a thin wall, which is prone to rupture and cannot meet the long-term discharge ignition requirements. The patent application with publication number CN113153539A introduces a single and double path combined three-dimensional rotating sliding arc plasma exciter. This structure has two high-voltage electrodes, which can realize discharge of the high-voltage electrode with the fuel nozzle and discharge of the high-voltage electrode on the outer swirl structure. However, this structure also faces the problem of large volume and thin wall ceramic-based insulation configuration. In addition, double discharge increases the control of the circuit in principle, which greatly increases the complexity, thus making it difficult to further develop. The patent application with publication number CN102162644B discloses a dielectric barrier discharge plasma swirl device structure. The electrodes are arranged in pairs on the expansion section of the burner to form a form of multiple pairs of surface dielectric barrier discharge for ignition and combustion. However, the dielectric barrier discharge has low energy and the fuel is prone to pollute the discharge electrode, thus limiting the excitation effect. The US invention patent with patent number US10648672B2 discloses a plasma fuel nozzle with a typical three-swirl structure. However, this structure requires a long electrode structure at the center position, which requires further modification of the electrode to be baked in the high-temperature combustion area.Japanese patent No. P2009-162478A discloses a premixed type rotational flow arc discharge plasma combustion supporting device, which is combined with an igniter structure, and generates a pre-combustion flame by rotational flow arc discharge, but the structure is complex, and fuel oil needs to be additionally introduced to the igniter.

[0005] Since the three-rotational flow combustion enters too much air in the slow vehicle state (a state in which the air flow temperature and pressure at the inlet of the combustion chamber are relatively low), the fuel and air mixing ratio of the combustion is reduced, and further, the flameout caused by too low fuel flow is caused, in addition, the problems of flameout and secondary ignition under extremely low temperature, low pressure and the like are faced. SUMMARY

[0006] In order to overcome the defects of the prior art, the purpose of the present application is to provide a three-rotational flow combustion chamber plasma ignition combustion exciter for an aero-engine, which adopts a three-stage rotational flow device design, has the advantages of forming strong turbulence, stable backflow area and uniform mixed gas, adopts a small volume insulation structure design, realizes high-density small-area discharge, and overcomes the problems of poor working effect due to non-ideal discharge area, flameout under certain working conditions, and weak working performance due to insufficient strength of ceramic material.

[0007] To achieve the above purpose, the technical scheme adopted by the present application is:

[0008] A three-rotational flow combustion chamber plasma ignition combustion exciter for an aero-engine, comprising a first-stage rotational flow device, a second-stage rotational flow device, a third-stage rotational flow device, a high-voltage electrode, a ceramic insulation section and a rotational flow fuel nozzle.

[0009] The first-stage rotational flow device, the second-stage rotational flow device and the third-stage rotational flow device are integrated structures, the second-stage rotational flow device is arranged on the outer wall surface of the first-stage rotational flow device inner ring of the first-stage rotational flow device, and the third-stage rotational flow device is arranged on the outer wall surface of the second-stage rotational flow device isolation ring of the second-stage rotational flow device, and the first-stage rotational flow device is fixedly sleeved on the outer wall surface of the ceramic insulation section.

[0010] The ceramic insulation section and the high-voltage electrode are fixedly connected, and the wire passage axes of the two coincide.

[0011] The rotational flow fuel nozzle is inserted and fixed to the inner wall surface of the ceramic insulation section, and the upper surface of the rotational flow fuel nozzle is flush with the upper surface of the ceramic insulation section.

[0012] The upper surfaces of the first-stage rotational flow device, the second-stage rotational flow device, the third-stage rotational flow device and the ceramic insulation section are kept at the same horizontal plane height.

[0013] The first-stage cyclone separator includes an inner ring, on the inner wall of which are machined first-stage cyclone blades. These blades are evenly distributed circumferentially along the central axis of the fuel nozzle. The inner ring is a rotating structure, and its upper outlet is a conical surface. The angle between the conical surface and the central axis is... θ 10-3 =45°~75°, outer diameter D of the lower surface of the inner ring of the first-stage hydrocyclone 10-10 =30mm~38mm, inner diameter D of the lower surface of the inner ring of the first-stage hydrocyclone. 10-1 =18mm~26mm, wall thickness of the lower surface of the inner ring of the first-stage hydrocyclone d 10-2 =2mm~10mm, height of the inner ring of the first-stage hydrocyclone h 10-4 =24mm~32mm; the type of the first-stage swirl blade is an axial swirl blade, and the installation angle of the first-stage swirl blade with respect to the horizontal direction is... θ 10-8 =40°~70°, thickness of the first-stage swirl blade δ 10-6 =0.8mm~3.6mm, axial installation height of the first-stage swirl blade h 10-7 =5mm~10mm, the vertical distance between the lower surface of the first-stage cyclone blade and the lower surface of the inner ring of the first-stage cyclone separator. h 10-9 =2mm~6mm, number of first-stage swirl blades m 1=8~14, first-stage swirl blade 12 center diameter D 10-11 =11mm~13mm.

[0014] The secondary cyclone separator includes a secondary cyclone separator isolation ring, on the inner wall of which are machined secondary cyclone blades. These blades are evenly distributed circumferentially along the central axis of the fuel nozzle. A blunt body is installed above the secondary cyclone separator isolation ring along the airflow direction. Both the secondary cyclone separator isolation ring and the blunt body are rotating structures. The outer diameter D of the lower surface of the secondary cyclone separator isolation ring... 20-14 =52mm~60mm, inner diameter D of the lower surface of the isolation ring of the secondary hydrocyclone 20-13 =45mm~51mm, thickness of the isolation ring for the secondary cyclone separator d 20-12 =(D 20-14 - D 20-13 ) / 2, Height of the isolation ring of the secondary cyclone separator h 20-9 =20mm~28mm; Blunt body thickness h 10-8 =3mm~5mm, maximum outer diameter D of the outlet on the upper surface of the blunt body 20-1= 63mm~73mm, the blunt body upper surface outlet inner diameter D 20-2 = 32mm~40mm, the blunt body upper surface width d 20-4 = (D 20-1 - D 20-2 ) / 2, the blunt body upper surface and the side wall surface angle θ 20-3 = 15°~45°, the blunt body side wall surface and the axial angle θ 20-5 = 105°~135°; the secondary cyclone vane type is axial cyclone vane, the secondary cyclone vane and the horizontal direction installation angle θ 20-10 = 50°~70°, the secondary cyclone vane thickness δ 20-7 = 0.8mm~3mm, the secondary cyclone vane installation height h 20-15 = 10mm~18mm, the secondary cyclone vane and the secondary cyclone separator ring lower surface vertical distance h 20-11 = 5mm~9mm, the number of secondary cyclone vanes m 2= 12~20, the center diameter D of secondary cyclone vane 20-16 = 30mm~40mm; the secondary cyclone 20 overall height h 20-6 = h 10-8 + h 20-9 .

[0015] The tertiary cyclone includes a tertiary cyclone outer ring, and a tertiary cyclone vane is processed on the inner wall surface of the tertiary cyclone outer ring, and the tertiary cyclone vane is circumferentially and equally distributed along the fuel nozzle center axis; the tertiary cyclone outer ring is a revolution body structure, and the outer diameter D 30-12 = 80mm~85mm of the lower surface of the tertiary cyclone outer ring, the inner diameter D 30-11 = 74mm~78mm of the lower surface of the tertiary cyclone outer ring, the wall thickness of the lower surface of the tertiary cyclone outer ring d 30-4 = (D 30-12 - D 30-11 ) / 2; the tertiary cyclone outer ring outlet position is an expansion structure, and the expansion structure height h 30-5 = 2.5mm~4.5mm, the outlet outer ring inner diameter D 30-3 = 78mm~82mm, the outlet outer ring thickness d 30-2 =(D 30-12 - D 30-3The angle between the inner wall of the expansion structure and the axis direction θ 30-1 = 20°~40°; the type of the third-stage cyclone vane is an axial cyclone vane, and the installation angle of the third-stage cyclone vane with the horizontal direction θ 30-9 = 30°~60°, the thickness of the third-stage cyclone vane δ 30-6 = 0.8mm~3mm, the installation height of the third-stage cyclone vane h 30-7 = 10mm~18mm, the vertical distance between the third-stage cyclone vane and the lower surface of the outer ring of the third-stage cyclone h 30-10 = 4mm~8mm, the number of the third-stage cyclone vanes m 3 = 16~24, the central diameter D of the cyclone vane 30-13 = 50mm~62mm.

[0016] The high-voltage electrode comprises a high-voltage electrode ring and a high-voltage wire, the high-voltage electrode ring is provided with an electrode hole, and the high-voltage wire passes through the electrode hole and is fixed with the high-voltage electrode ring; the high-voltage electrode ring is made of a metal material or a conductive metal foil with ductility, and the metal material comprises tungsten-copper alloy, red copper, brass or stainless steel; the outer diameter D 40-1 = 11mm~14mm, the inner diameter D 40-1 = 8mm~11mm, the thickness of the high-voltage electrode ring δ 40-3 = 0.4mm~0.8mm; the high-voltage wire is made of silver wire, copper wire or stainless steel wire metal material, and the diameter of the high-voltage wire is δ 40-5 = 0.4mm~0.8mm.

[0017] The ceramic insulation section comprises a ceramic insulation tube and a wire channel; the ceramic insulation tube is a rotary body structure, and the wire channel is arranged on the outer wall surface of the ceramic insulation tube, and the wire channel is a through-hole cylindrical hole, and the inner diameter of the wire channel is d 50-9 = 0.4mm~0.8mm, the distance from the center of the wire channel to the outer wall surface of the ceramic insulation tube d 50-3 = 0.8mm~1.1mm; the upper end of the ceramic insulation tube is a stepped structure for matching the high-voltage electrode ring of the high-voltage electrode; the stepped surface D 50-1 = 8mm~11mm, the outlet diameter D 50-2 = 4mm~6mm, the stepped height of the ceramic insulation tube h 50-5 = 0.4mm~0.8mm, the stepped width of the ceramic insulation tubed 50-4 =1mm~2mm, the outer diameter D of the lower surface of the ceramic insulation tube 50-11 =10mm~15mm, the inner diameter D of the lower surface of the ceramic insulation tube 50-10 =7mm~10mm, the height of the ceramic insulation tube h 50-7 =25mm~35mm; the outlet above the inner surface of the ceramic insulation tube is a tapered surface, and the included angle between the tapered surface and the inner surface is θ 50-6 =135°~155°, the distance from the tapered surface to the lower surface of the ceramic insulation tube h 50-8 =23mm~26mm.

[0018] The upper end of the ceramic insulation tube is a stepped structure for matching the high-voltage electrode ring of the high-voltage electrode, specifically: the high-voltage electrode ring is inserted into the step of the ceramic insulation section and fixed therewith, the axis of the electrode hole on the high-voltage electrode ring coincides with the axis of the wire channel; the high-voltage wire penetrates through the wire channel of the ceramic insulation section.

[0019] The swirled fuel nozzle comprises a nozzle, a nozzle swirled vane and an oil supply rod which are sequentially communicated; the overall height of the swirled fuel nozzle h 60-5 =35mm~50mm; the height of the nozzle h 60-3 =8.5mm~10.5mm, the diameter D of the nozzle 60-2 =6.5mm~7.5mm, the outlet of the nozzle is a tapered surface, and the included angle between the tapered surface and the horizontal direction is θ 60-1 =135°~155°, the diameter D of the nozzle outlet 60-9 =1.5mm~2.5mm; the type of the nozzle swirled vane is an axial swirled vane, and the installation height of the nozzle swirled vane h 60-4 =6mm~9mm, the installation angle of the nozzle swirled vane with the horizontal direction θ 60-7 =40°~70°, the thickness of the nozzle swirled vane δ 60-6 =0.6mm~1mm, the center diameter D of the nozzle swirled vane 60-10 =7mm~10mm, the number of the nozzle swirled vanes m 4=6~12; the diameter D of the oil supply rod 60-8 =2mm~6mm.

[0020] The swirl vane directions of the primary cyclone, the secondary cyclone and the tertiary cyclone are clockwise or counterclockwise when viewed from top to bottom, and there are eight combinations of the swirl vanes of the three cyclones, namely, clockwise-clockwise-clockwise, clockwise-clockwise-counterclockwise, clockwise-counterclockwise-clockwise, clockwise-counterclockwise-counterclockwise, counterclockwise-clockwise-clockwise, counterclockwise-clockwise-counterclockwise, counterclockwise-counterclockwise-clockwise and counterclockwise-counterclockwise-counterclockwise.

[0021] The primary cyclone, the secondary cyclone and the tertiary cyclone are made of high-temperature alloy material or stainless steel material by machining welding technology or 3D metal printing technology, and are integrally designed.

[0022] The ceramic insulation section is integrally formed by DLP light curing 3D ceramic printing technology or is made by machining or mold casting, and the insulation medium is made of alumina ceramic, quartz glass, polytetrafluoroethylene, NE glass or K9 glass during machining.

[0023] Compared with the prior art, the application has the following advantages:

[0024] 1. Since the primary cyclone, the secondary cyclone and the tertiary cyclone are designed in an integrated structure and precisely cooperate with the ceramic insulation section, the application has the advantages of high overall structural strength, good stability and long service life, and fundamentally overcomes the problem of weakened working performance caused by separate support, loose connection or insufficient strength of ceramic parts in traditional design.

[0025] 2. Since the high-voltage electrode ring of the high-voltage electrode is embedded in the stepped structure at the upper end of the ceramic insulation section and is accurately aligned with the wire channel, a small area discharge is formed near the fuel nozzle outlet, so the application has the advantages of concentrated discharge energy, high plasma generation efficiency and significant ignition combustion assisting effect, and effectively solves the problem of poor working effect caused by an unsuitable discharge area position or dispersed energy.

[0026] 3. Since the three-cyclone combination design of the primary cyclone, the secondary cyclone and the tertiary cyclone provides multiple swirl direction combination modes, the application has the advantages of forming strong turbulent flow, stable backflow area and uniform mixed gas, which helps to improve the combustion chamber ignition and extinction performance and improve the working stability and reliability of the engine.

[0027] In summary, the application solves the core problem of poor discharge effect in the prior art by the organic combination of integrated structure design, high-efficiency space discharge and multi-stage swirl technology, and has the advantages of compact structure, high temperature resistance, high reliability and easy manufacturing, etc., significantly improving the ignition and extinction performance, combustion efficiency and working stability of the aero-engine combustion chamber. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is a front sectional view of the present application.

[0029] Figure 2a is a front sectional view of the primary swirler, Figure 2b is a top view of the primary swirler.

[0030] Figure 3a is a front sectional view of the secondary swirler, Figure 3b is a top view of the secondary swirler.

[0031] Figure 4a is a front sectional view of the tertiary swirler, Figure 4b is a top view of the tertiary swirler.

[0032] Figure 5a is a front sectional view of the high voltage electrode, Figure 5b is a top view of the high voltage electrode.

[0033] Figure 6a is a front sectional view of the ceramic insulation section, Figure 6b is a top view of the ceramic insulation section.

[0034] Figure 7a is a front sectional view of the swirled fuel nozzle, Figure 7b is a top view of the swirled fuel nozzle.

[0035] Figure 8 is a schematic view of the air flow distribution into the combustion chamber in the direction of the air flow of the present application.

[0036] Figure 9 is a discharge power curve of the present application at different air flow rates.

[0037] Figure 10a is the flame structure with the plasma pilot ignition combustion support exciter turned off, Figure 10b is the flame structure with the plasma pilot ignition combustion support exciter turned on.

[0038] Fig. 10 - primary swirler; 11 - primary swirler inner ring; 12 - primary swirler vane;

[0039] 20 - secondary swirler; 21 - secondary swirler isolation ring; 22 - secondary swirler vane; 23 - bluff body;

[0040] 30 - tertiary swirler; 31 - tertiary swirler outer ring; 32 - tertiary swirler vane;

[0041] 40 - high voltage electrode; 41 - high voltage electrode ring; 42 - high voltage wire; 43 - electrode hole;

[0042] 50 - ceramic insulation section; 51 - ceramic insulation tube; 52 - wire passage;

[0043] 60 - swirl fuel nozzle; 61 - nozzle; 62 - swirl vane of nozzle; 63 - oil supply rod;

[0044] 70 - sliding arc. DETAILED DESCRIPTION

[0045] The application will be described in detail below with reference to the accompanying drawings.

[0046] Reference Figure 1 The aero-engine three-swirl combustion chamber plasma ignition combustion-supporting exciter comprises a first swirl generator 10, a second swirl generator 20, a third swirl generator 30, a high-voltage electrode 40, a ceramic insulation section 50, and a swirl fuel nozzle 60. For the convenience of description, the direction of the airflow of the application is defined as downward, and the arrow direction of the airflow is defined as upward, as shown in FIG. 1.

[0047] The first swirl generator 10, the second swirl generator 20, and the third swirl generator 30 are integrated structures. The second swirl generator 20 is arranged on the outer wall surface of the first-swirl-generator inner ring 11 of the first swirl generator 10. The third swirl generator 30 is arranged on the outer wall surface of the second-swirl-generator isolation ring 21 of the second swirl generator 20. The first swirl generator 10 is sleeved on the outer wall surface of the ceramic insulation section 50 and is fixed by high-temperature ceramic adhesive.

[0048] The ceramic insulation section 50 is fixedly connected with the high-voltage electrode 40, and the axes of the wire channels of the two coincide.

[0049] The swirl fuel nozzle 60 is inserted into the inner wall surface of the ceramic insulation section 50 and is fixed by high-temperature ceramic adhesive. After assembly, the upper surface of the swirl fuel nozzle 60 is flush with the upper surface of the ceramic insulation section 50.

[0050] The upper surfaces of the first swirl generator 10, the second swirl generator 20, the third swirl generator 30, and the ceramic insulation section 50 are kept at the same horizontal height after assembly. Since the upper surface of the swirl fuel nozzle 60 is flush with the upper surface of the ceramic insulation section 50, the upper surface of the swirl fuel nozzle 60 is also located at the same horizontal height, that is, the axes of the five components coincide.

[0051] As shown in FIG. 2a and Figure 2b The first swirl generator 10 comprises a first-swirl-generator inner ring 11 and a first-swirl vane 12. The first-swirl-generator inner ring 11 is a body of revolution structure. The upper outlet of the first-swirl-generator inner ring 11 is a conical surface, which helps to converge the distributed swirl A to the center to improve the atomization of the fuel. The included angle between the conical surface and the central axis is θ 10-3 = 45° ~ 75°, the outer diameter D 10-10= 30mm~38mm, the inner diameter D of the lower surface of the inner ring 11 of the primary cyclone 10-1 = 18mm~26mm, the wall thickness of the lower surface of the inner ring 11 of the primary cyclone d 10-2 = 2mm~10mm, the height of the inner ring 11 of the primary cyclone h 10-4 = 24mm~32mm; the inner wall surface of the inner ring 11 of the primary cyclone is machined with primary cyclone blades 12, which are evenly distributed along the central axis of the fuel nozzle 60; the primary cyclone blades 12 are axial cyclone blades, and the installation angle of the primary cyclone blades 12 with the horizontal direction θ 10-8 = 40°~70°, the thickness of the primary cyclone blades 12 δ 10-6 = 0.8mm~3.6mm, the axial installation height of the primary cyclone blades 12 h 10-7 = 5mm~10mm, the vertical distance between the lower surface of the primary cyclone blades 12 and the lower surface of the inner ring 11 of the primary cyclone h 10-9 = 2mm~6mm, the number of primary cyclone blades 12 m 1 = 8~14, the central diameter D of the primary cyclone blades 12 10-11 = 11mm~13mm.

[0052] In this embodiment, the included angle between the conical surface and the central axis θ 10-3 = 60°, the outer diameter D of the lower surface of the inner ring 11 of the primary cyclone 10-10 = 34 mm, the inner diameter D of the lower surface 10-1 = 22mm, the wall thickness of the lower surface d 10-2 = 6mm, the height h 10-4 = 28.5mm; the primary cyclone blades 12 are evenly distributed along the axial direction on the inner wall surface of the inner ring 11 of the primary cyclone, and the cyclone blade type is an axial cyclone blade, and the number m 1 = 10, the installation angle of the primary cyclone blades 12 with the horizontal direction θ 10-8 = 55°, the thickness of the primary cyclone blades 12 δ 10-6 = 1.2mm, the axial installation height h 10-7 = 7.6mm, the vertical distance between the lower surface and the lower surface of the inner ring 11 of the primary cyclone h 10-9 = 2.87mm, the central diameter D of the primary cyclone blades 12 10-11= 12.7 mm.

[0053] As shown in FIG. 3a and Figure 3b FIG. 3b, the secondary swirler 20 includes a secondary swirler isolation ring 21, secondary swirler vanes 22, and a bluff body 23. The secondary swirler vanes 22 are equally distributed circumferentially along the central axis of the fuel nozzle 60, and the bluff body 23 is installed above the secondary swirler isolation ring 21 in the direction of the airflow. The secondary swirler isolation ring 21 and the bluff body 23 are hollow bodies of revolution, the outer diameter D 20-14 = 52 mm ~ 60 mm of the lower surface of the secondary swirler isolation ring 21, the inner diameter D 20-13 = 45 mm ~ 51 mm of the lower surface of the secondary swirler isolation ring 21, the thickness of the secondary swirler isolation ring 21 d 20-12 = (D 20-14 - D 20-13 ) / 2, the height of the secondary swirler isolation ring 21 h 20-9 = 20 mm ~ 28 mm, the thickness of the bluff body 23 h 10-8 = 3 mm ~ 5 mm, the maximum outer diameter D 20-1 = 63 mm ~ 73 mm of the upper surface outlet of the bluff body 23, the inner diameter D 20-2 = 32 mm ~ 40 mm of the upper surface of the bluff body 23, the width of the upper surface of the bluff body 23 d 20-4 = (D 20-1 - D 20-2 ) / 2, the angle between the upper surface of the bluff body 23 and the side wall surface θ 20-3 = 15° ~ 45°, the angle between the side wall surface of the bluff body 23 and the axial direction θ 20-5 = 105° ~ 135°; the secondary swirler vanes 22 are machined on the inner wall surface of the secondary swirler isolation ring 21, the secondary swirler vanes 22 are axial swirler vanes, and the installation angle of the secondary swirler vanes 22 with the horizontal direction θ 20-10 = 50° ~ 70°, the thickness of the vanes δ 20-7 = 0.8 mm ~ 3 mm, the installation height of the secondary swirler vanes 22 h 20-15 = 10 mm ~ 18 mm, the vertical distance between the secondary swirler vanes 22 and the lower surface of the secondary swirler isolation ring 21 h 20-11 = 5 mm ~ 9 mm, the number of secondary swirler vanes 22 m 2 = 12 ~ 20, the central diameter D 20-16 = 30 mm ~ 40 mm of the secondary swirler vanes 22; the overall height of the secondary swirler 20h 20-6 = h 10-8 + h 20-9 The secondary swirl blades 22 are evenly distributed circumferentially along the axis.

[0054] In this embodiment, the outer diameter D of the lower surface of the secondary cyclone separator isolation ring 21 is as follows: 20-14 =56mm, inner diameter D of the lower surface 20-13 =48mm, thickness d 20-12 =4mm, height h 20-9 =24.7mm; Blunt body thickness 23 h 10-8 =3.7mm, maximum outer diameter D of the outlet on the upper surface of blunt body 23 20-1 =67.9mm, the inner diameter D of the outlet on the upper surface of blunt body 23 20-2 =36.1mm, width of the upper surface of blunt body 23 d 20-4 = 15.9mm, the angle between the upper surface of blunt body 23 and the side wall surface θ 20-3 =30°, the angle between the 23rd side wall of the blunt body and the axial direction. θ 20-5 =120°; the secondary swirling blades 22 are evenly distributed along the axial direction on the inner wall surface of the secondary swirling separator isolation ring 21, and their type is axial swirling blades, the number of which is... m 2=16, the installation angle of the second-stage swirl blade 22 with the horizontal direction. θ 20-10 =60°, blade thickness δ 20-7 =1mm, Installation height of secondary swirl blade 22 h 20-15 =14mm, the vertical distance between the secondary cyclone blade 22 and the lower surface of the secondary cyclone separator isolation ring 21. h 20-11 =7.2mm, center diameter D of the second-stage swirl blade 22 20-16 =34mm; Overall height of the secondary hydrocyclone h 20-6 =28.4mm.

[0055] As shown in Figure 4a and Figure 4b As shown, the three-stage hydrocyclone 30 includes a three-stage hydrocyclone outer ring 31 and three-stage hydrocyclone blades 32. The three-stage hydrocyclone outer ring 31 is a hollow rotating body structure, and the outer diameter D of the lower surface of the three-stage hydrocyclone outer ring 31 is... 30-12 =80mm~85mm, inner diameter D of the lower surface of the outer ring 31 of the three-stage hydrocyclone 30-11= 74mm~78mm, wall thickness of lower surface of outer ring 31 of tertiary cyclone d 30-4 = (D 30-12 - D 30-11 ) / 2; the outlet position of the outer ring 31 of the tertiary cyclone is an expansion structure, the height of the expansion structure h 30-5 =2.5mm~4.5mm, inner diameter D 30-3 =78mm~82mm, thickness of the outlet outer ring d 30-2 =(D 30-12 - D 30-3 ) / 2, the angle between the inner wall surface of the expansion structure and the axial direction θ 30-1 =20°~40°; the inner wall surface of the outer ring 31 of the tertiary cyclone is machined with tertiary cyclone vanes 32, the type of the cyclone vanes is axial cyclone vanes, the installation angle of the tertiary cyclone vanes 32 with the horizontal direction θ 30-9 =30°~60°, thickness of the tertiary cyclone vanes 32 δ 30-6 =0.8mm~3mm, installation height of the tertiary cyclone vanes 32 h 30-7 =10mm~18mm, the vertical distance between the tertiary cyclone vanes 32 and the lower surface of the outer ring 31 of the tertiary cyclone h 30-10 =4mm~8mm, number of the tertiary cyclone vanes 32 m 3=16~24, central diameter D 30-13 =50mm~62mm of the tertiary cyclone vanes 32; the tertiary cyclone vanes 32 are evenly distributed along the central axis of the fuel nozzle 60.

[0056] In this embodiment, the outer diameter D 30-12 =82mm of the lower surface of the outer ring 31 of the tertiary cyclone, the inner diameter D 30-11 =76mm of the lower surface of the outer ring 31 of the tertiary cyclone, the wall thickness of the lower surface of the outer ring 31 of the tertiary cyclone d 30-4 =3mm; the outlet position of the outer ring 31 of the tertiary cyclone is an expansion structure, the height of the expansion structure h 30-5 =3.5mm, inner diameter D 30-3 =80mm of the outlet outer ring, thickness of the outlet outer ring d 30-2 =1mm, the angle between the inner wall surface of the expansion structure and the axial direction θ 30-1= 30°; the outer wall of the tertiary cyclone ring 31 is provided with tertiary cyclone vanes 32, which are evenly distributed on the outer wall of the tertiary cyclone ring 31 along the axis of the fuel nozzle 60, the tertiary cyclone vanes 32 are axial cyclone vanes, and the number of the tertiary cyclone vanes 32 is m 3 = 20, the thickness of the tertiary cyclone vanes 32 is δ 30-6 = 1mm, the installation height of the tertiary cyclone vanes 32 is h 30-7 = 14mm, the vertical distance between the tertiary cyclone vanes 32 and the lower surface of the tertiary cyclone ring is h 30-10 = 5.8mm, the central diameter D of the tertiary cyclone vanes 32 is 30-13 = 56mm.

[0057] As shown in FIGS. 5a and Figure 5b The high-voltage electrode 40 includes a high-voltage electrode ring 41, a high-voltage wire 42, and an electrode hole 43, the electrode hole 43 is formed on the high-voltage electrode ring 41, the high-voltage wire 42 is welded with the high-voltage electrode ring through the electrode hole to ensure close cooperation between the two; the high-voltage electrode ring 41 is made of tungsten-copper alloy or red copper or brass or stainless steel or other metal materials with good conductivity, or made of conductive metal foil with ductility. The outer diameter D 40-1 = 11mm~14mm, the inner diameter D 40-1 = 8mm~11mm, the thickness of the high-voltage electrode ring 41 is δ 40-3 = 0.4mm~0.8mm; the high-voltage wire 42 is made of silver wire, copper wire or stainless steel wire or other metal materials with good conductivity, and the diameter of the high-voltage wire 42 is δ 40-5 = 0.4mm~0.8mm.

[0058] In this embodiment, the high-voltage electrode ring 41 is made of brass metal and has a ring structure, the outer diameter D 40-1 = 12.7mm, the inner diameter D 40-1 = 9.42mm, the thickness of the high-voltage electrode ring 41 is δ 40-3 = 0.6mm, the high-voltage wire 42 is made of copper wire, and the diameter of the high-voltage wire 42 is δ 40-5 = 0.6mm.

[0059] As shown in FIGS. 6a and Figure 6bAs shown, the ceramic insulation section 50 includes a ceramic insulation tube 51 and a wire passage 52; the ceramic insulation tube 51 is a hollow rotary body structure, the upper end of which contains a stepped structure for matching with the high-voltage electrode ring 41, specifically, the high-voltage electrode ring 41 is inserted into the step of the ceramic insulation section 50, and the electrode hole 43 axis on the high-voltage electrode ring 41 is ensured to coincide with the axis of the wire passage 52 of the ceramic insulation tube; the high-voltage electrode ring 41 and the step of the ceramic insulation section 50 are fixedly connected in a glued manner by using high-temperature glue, and the high-voltage wire 42 penetrates through the wire passage 52 of the ceramic insulation section 50, which is beneficial to the insulation between the three-rotational-flow plasma ignition combustion exciter and other metal structures.

[0060] The stepped surface D of the ceramic insulation tube 51 50-1 =8mm~11mm, the outlet diameter D of the upper surface of the ceramic insulation tube 51 50-2 =4mm~6mm, the stepped height of the ceramic insulation tube 51 h 50-5 =0.4mm~0.8mm, the stepped width of the ceramic insulation tube 51 d 50-4 =1mm~2mm, the outer diameter D of the lower surface of the ceramic insulation tube 51 50-11 =10mm~15mm, the inner diameter D of the lower surface of the ceramic insulation tube 51 50-10 =7mm~10mm, the height of the ceramic insulation tube 51 h 50-7 =25mm~35mm; the outlet on the inner surface of the ceramic insulation tube 51 is a tapered surface, and the included angle between the tapered surface and the inner surface θ 50-6 =135°~155°, the distance from the tapered contraction to the lower surface of the ceramic insulation tube 51 h 50-8 =23mm~26mm; the wire passage 52 is a cylindrical through hole, and the inner diameter d 50-9 =0.4mm~0.8mm, the distance from the center of the wire passage 52 to the outer wall surface of the ceramic insulation tube 51 d 50-3 =0.8mm~1.1mm,

[0061] In this embodiment, the stepped surface D of the ceramic insulation tube 51 50-1 =9.4mm, the outlet diameter D of the upper surface thereof 50-2 =4.65mm, the stepped height thereof h 50-5 =0.6mm, the stepped width thereof d 50-4 =1.5mm, the outer diameter D of the lower surface of the ceramic insulation tube 51 50-11= 12.7mm, inner diameter D of lower surface of ceramic insulation tube 51 50-10 = 8.7mm, height of ceramic insulation tube 51 h 50-7 = 28.5mm, angle between outlet shrinkage cone surface and inner surface θ 50-6 = 140°, distance between shrinkage cone and lower surface of ceramic insulation tube h 50-8 = 25.7mm; the wire channel 52 is a cylindrical through hole, inner diameter d 50-9 = 0.6mm, distance between center of wire channel 52 and outer wall surface of ceramic insulation tube 51 d 50-3 = 1.08mm,

[0062] As shown in FIG. 7a and Figure 7b the swirl fuel nozzle 60 includes a nozzle 61, a nozzle swirl vane 62 and a fuel supply rod 63 in sequence. The overall height of the swirl fuel nozzle 60 is h 60-5 = 35mm~50mm, height of the nozzle 61 h 60-3 = 8.5mm~10.5mm, diameter D of the nozzle 61 60-2 = 6.5mm~7.5mm, the outlet of the nozzle 61 is a cone surface, the angle between the cone surface and the horizontal direction θ 60-1 = 135°~155°, diameter D of the outlet of the nozzle 61 60-9 = 1.5mm~2.5mm; the nozzle swirl vane 62 is an axial swirl vane, the installation height of the nozzle swirl vane 62 is h 60-4 = 6mm~9mm, the installation angle of the nozzle swirl vane 62 with the horizontal direction θ 60-7 = 40°~70°, thickness of the nozzle swirl vane 62 δ 60-6 = 0.6mm~1mm, center diameter D of the nozzle swirl vane 62 60-10 = 7mm~10mm, number of the nozzle swirl vanes 62 m 4= 6~12, diameter D of the fuel supply rod 63 60-8 = 2mm~6mm, the swirl direction of the nozzle swirl vane 62 is clockwise or counterclockwise when viewed from top to bottom.

[0063] In this embodiment, the overall height of the swirl fuel nozzle 60 is h 60-5 = 40mm, height of the nozzle 61 h 60-3= 9.7mm, nozzle 61 diameter D 60-2 = 7mm, nozzle 61 outlet is a conical surface, the conical surface and the horizontal direction angle θ 60-1 = 140°, nozzle 61 outlet diameter D 60-9 = 2mm, nozzle swirl vane 62 type is an axial swirl vane equally distributed in the circumferential direction, the swirl direction is clockwise, the number of nozzle swirl vanes 62 m 4 = 8, nozzle swirl vane 62 installation height h 60-4 = 7mm, nozzle swirl vane 62 installation angle with the horizontal direction θ 60-7 = 60°, nozzle swirl vane 62 thickness δ 60-6 = 0.8mm, nozzle swirl vane 62 center diameter D 60-10 = 8.7mm, oil supply rod diameter D 60-8 = 4mm.

[0064] The swirl vane direction of the primary cyclone 10, the secondary cyclone 20 and the tertiary cyclone 30 is clockwise or counterclockwise when viewed from top to bottom, and there are eight combinations of the swirl vane groups of the three cyclones, which are: clockwise-clockwise-clockwise, clockwise-clockwise-counterclockwise, clockwise-counterclockwise-clockwise, clockwise-counterclockwise-counterclockwise, counterclockwise-clockwise-clockwise, counterclockwise-clockwise-counterclockwise, counterclockwise-counterclockwise-clockwise and counterclockwise-counterclockwise-counterclockwise. Specifically, in the embodiment, the swirl vane combination of the three-layer cyclone is clockwise-clockwise-clockwise.

[0065] The primary cyclone 10, the secondary cyclone 20 and the tertiary cyclone 30 are made of high-temperature alloy material or stainless steel metal material, and are made by mechanical processing welding technology or 3D metal printing technology to realize integrated design. Specifically, in the embodiment, the integrated three-layer cyclone is processed by 3D stainless steel metal printing technology.

[0066] The ceramic insulation section 50 is integrally formed by DLP photocuring 3D ceramic printing technology, or is mechanically processed or die cast, and the insulation medium is made of alumina ceramic or quartz glass or polytetrafluoroethylene or NE glass or K9 glass. Specifically, in the embodiment, the ceramic insulation section 50 is integrally formed by DLP photocuring 3D ceramic printing technology, and the insulation medium is made of AL2O3 alumina.

[0067] The working principle of the application is as follows:

[0068] The three cyclones of the primary cyclone 10, the secondary cyclone 20 and the tertiary cyclone 30 are connected with the center cyclone fuel nozzle 60 in common ground, and together form the ground low voltage port of the whole exciter; the high voltage electrode ring 41 and the high voltage wire 42 form a whole in communication, and are connected to the input port of the high voltage plasma power supply as the high voltage port of the exciter; the ceramic insulation section 50 insulates the ground low voltage port and the high voltage port of the exciter from the physical layer, prevents the two parts from breakdown discharge in the non-design area and destroys the working performance of the exciter; after the high voltage plasma power supply is turned on, a discharge loop is formed between the high voltage end and the low voltage end of the three cyclone plasma ignition and combustion assisting exciter, and an air breakdown arc discharge is formed between the high voltage electrode ring 41 on the upper surface of the exciter and the nozzle 61; as shown in Figure 8 The air flow entering the combustion chamber forms three main cyclones and a small cyclone D after passing through the three cyclone plasma ignition and combustion assisting exciter, the three main cyclones are cyclone A, cyclone B and cyclone C, and the three main cyclones mainly function to form an air backflow area in the combustion chamber for establishing a stable combustion process in the combustion chamber, the air flow distributed by the cyclone D is very small and has negligible influence on the flow field of the whole combustion chamber, the cyclone D is used to drive the arc to rotate and form a rotating sliding arc 70, cool the discharge electrode and prevent metal structure from ablation, and the cyclone A can also be used to constrain the sliding arc in the nozzle outlet area to make the arc energy more concentrated. In an actual combustion chamber, most of the air flow from the high pressure compressor passes through the diffuser to slow down and increase the pressure, and then enters the combustion chamber through the three cyclones, the three main cyclones (cyclone A, cyclone B and cyclone C) generated by the tertiary cyclone can not only organize a reasonable flow field to stabilize the flame, but also promote the atomization of the fuel and the mixing with air. The discharge area of the sliding arc 70 is located at the outlet position of the nozzle 61, which is close to the main combustion area of the combustion chamber, and the fuel injected by the nozzle 61 can all contact with the sliding arc 70 before entering the combustion chamber. The sliding arc plasma ignition and combustion at the outlet position of the nozzle 61 is beneficial to form a high-density arc discharge area, which not only serves as a continuous high-temperature heat source to ignite the fuel, but also serves as a strong ionization source to continuously perform high-energy electron collision and dissociation and excitation of high-energy state substances on the air and fuel at the outlet position of the nozzle. Therefore, after the action of the three cyclone plasma ignition and combustion assisting exciter, the air-fuel mixture can be ignited, the chemical combustion reaction process can be promoted, the combustion chemical reaction rate can be improved, the ignition difficulty and combustion instability of the three cyclone combustion chamber can be solved, and the three cyclone plasma ignition and combustion assisting exciter has high application value.

[0069] Figure 9 The power curve of the arc discharge under different air flow rates after the three cyclone plasma ignition and combustion assisting exciter is connected to the high voltage plasma power supply, and the figure shows that the power during the sliding arc plasma excitation process can be stabilized within the range of 95W; Figure 10a and Figure 10bis the flame distribution characteristics of the three-swirl plasma ignition and combustion exciter in the combustion chamber without excitation and with excitation. The test parameters are air flow of 1000 L / min, fuel mass and air mass flow ratio parameter of 0.7, and under this working condition, air accounts for more than fuel, so the flame is easy to extinguish. Without the application of sliding arc plasma excitation (as shown in Figure 10a ), the flame intensity is weak, and from the right side of the brightness value, most of them are distributed in the range of 600-900; after the application of sliding arc plasma excitation, as shown in Figure 10b , the flame intensity is obviously enhanced, and the brightness value is distributed in the range of 700-1300, compared with Figure 10a , the sliding arc plasma excitation induces new flame area in the central region, and the flame height is reduced, attached to the exciter outlet plasma discharge area and the bluff body area. Therefore, the flame with sliding arc plasma excitation is more stable.

Claims

1. An aeroengine triple-swirl combustor plasma pilot-assisted ignition energizer characterized by, The application relates to a high-voltage rotating flow fuel nozzle, which comprises a primary rotating flow device (10), a secondary rotating flow device (20), a tertiary rotating flow device (30), a high-voltage electrode (40), a ceramic insulation section (50) and a rotating flow fuel nozzle (60). The primary rotating flow device (10), the secondary rotating flow device (20) and the tertiary rotating flow device (30) are integrated structures, the secondary rotating flow device (20) is arranged on the outer wall surface of a primary rotating flow device inner ring (11) of the primary rotating flow device (10), the tertiary rotating flow device (30) is arranged on the outer wall surface of a secondary rotating flow device isolation ring (21) of the secondary rotating flow device (20), and the primary rotating flow device (10) is fixedly sleeved on the outer wall surface of the ceramic insulation section (50). The ceramic insulation section (50) is fixedly connected with the high-voltage electrode (40), and the axes of wire channels of the two coincide. The rotating flow fuel nozzle (60) is inserted and fixed into the inner wall surface of the ceramic insulation section (50) and is fixed through ceramic glue, and the upper surface of the rotating flow fuel nozzle (60) is flush with the upper surface of the ceramic insulation section (50). The upper surfaces of the primary rotating flow device (10), the secondary rotating flow device (20), the tertiary rotating flow device (30) and the ceramic insulation section (50) are kept at the same horizontal plane height.

2. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 1, wherein, The first-stage cyclone separator (10) includes a first-stage cyclone separator inner ring (11), and first-stage cyclone blades (12) are machined on the inner wall surface of the first-stage cyclone separator inner ring (11). The first-stage cyclone blades (12) are evenly distributed circumferentially along the central axis of the fuel nozzle (60). The first-stage cyclone separator inner ring (11) is a rotating body structure, and the upper outlet of the first-stage cyclone separator inner ring (11) is a conical surface. The angle between the conical surface and the central axis is... The upper end of the ceramic insulation pipe (51) is a stepped structure for matching the high-voltage electrode ring (41) of the high-voltage electrode (40), specifically, the high-voltage electrode ring (41) is inserted into the step of the ceramic insulation section (50) and is fixed thereto, the axis of the electrode hole (43) on the high-voltage electrode ring (41) coincides with the axis of the wire channel (52), and the high-voltage wire (42) penetrates through the wire channel (52) of the ceramic insulation section (50). 10-3 =45°~75°, outer diameter D of the lower surface of the inner ring (11) of the first-stage hydrocyclone 10-10 =30mm~38mm, inner diameter D of the lower surface of the inner ring (11) of the first-stage hydrocyclone 10-1 =18mm~26mm, wall thickness of the lower surface of the inner ring (11) of the first-stage hydrocyclone d 10-2 =2mm~10mm, height of the inner ring (11) of the first-stage hydrocyclone h 10-4 =24mm~32mm; the type of the first-stage swirl blade (12) is an axial swirl blade, and the installation angle of the first-stage swirl blade (12) with the horizontal direction is... The rotating flow blade directions of the primary rotating flow device (10), the secondary rotating flow device (20) and the tertiary rotating flow device (30) are clockwise or counterclockwise when viewed from top to bottom, and there are eight combinations of rotating flow blades of the three rotating flow devices, namely, clockwise-clockwise-clockwise, clockwise-clockwise-counterclockwise, clockwise-counterclockwise-clockwise, clockwise-counterclockwise-counterclockwise, counterclockwise-clockwise-clockwise, counterclockwise-clockwise-counterclockwise, counterclockwise-counterclockwise-clockwise and counterclockwise-counterclockwise-counterclockwise. 10-8 =40°~70°, thickness of the first-stage swirl blade (12) The primary rotating flow device (10), the secondary rotating flow device (20) and the tertiary rotating flow device (30) are made of high-temperature alloy material or stainless steel metal material and are manufactured by using mechanical processing welding technology or 3D metal printing technology, so that integration is realized. 10-6 =0.8mm~3.6mm, axial installation height of the first-stage swirl blade (12) h 10-7 =5mm~10mm, the vertical distance between the lower surface of the first-stage cyclone blade (12) and the lower surface of the inner ring (11) of the first-stage cyclone separator. h 10-9 =2mm~6mm, number of first-stage swirl blades (12) m 1=8~14, center diameter D of first-stage swirl blade (12) 10-11 =11mm~13mm.

3. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 1, wherein, The secondary cyclone separator (20) includes a secondary cyclone separator isolation ring (21). Secondary cyclone blades (22) are machined on the inner wall of the secondary cyclone separator isolation ring (21). The secondary cyclone blades (22) are evenly distributed circumferentially along the central axis of the fuel nozzle (60). A blunt body (23) is installed above the secondary cyclone separator isolation ring (21) along the airflow direction. The secondary cyclone separator isolation ring (21) and the blunt body (23) are rotating structures. The outer diameter D of the lower surface of the secondary cyclone separator isolation ring (21) is... 20-14 =52mm~60mm, the inner diameter D of the lower surface of the isolation ring (21) of the secondary cyclone separator 20-13 =45mm~51mm, thickness of the secondary hydrocyclone isolation ring (21) d 20-12 =(D 20-14 -D 20-13 ) / 2, Height of the secondary cyclone separator isolation ring (21) h 20-9 =20mm~28mm; thickness of blunt body (23) h 10-8 =3mm~5mm, the maximum outer diameter D of the outlet on the upper surface of the blunt body (23) 20-1 =63mm~73mm, blunt body (23) upper surface outlet inner diameter D 20-2 =32mm~40mm, width of the upper surface of the blunt body (23) d 20-4 = (D 20-1 - D 20-2 ) / 2, the angle between the upper surface of the blunt body (23) and the side wall. The ceramic insulation section (50) is integrally formed by DLP light-cured 3D ceramic printing technology, is manufactured by mechanical processing or mold casting, and is made of alumina ceramic, quartz glass, polytetrafluoroethylene, NE glass or K9 glass during processing. 20-3 =15°~45°, the angle between the sidewall of the blunt body (23) and the axial direction. ​ 20-5 =105°~135°; the secondary swirl blade (22) is an axial swirl blade, and the installation angle of the secondary swirl blade (22) with the horizontal direction is 105°~135°; ​ 20-10 =50°~70°, thickness of secondary swirl blade (22) ​ 20-7 =0.8mm~3mm, Installation height of the secondary swirl blade (22) h 20-15 =10mm~18mm, the vertical distance between the secondary cyclone blade (22) and the lower surface of the secondary cyclone separator isolation ring (21) is 10mm~18mm. h 20-11 =5mm~9mm, number of secondary swirl blades (22) m 2=12~20, the center diameter D of the second-stage swirl blade (22) 20-16 =30mm~40mm; Overall height of the secondary hydrocyclone (20) h 20-6 = h 10-8 + h 20-9 。 4. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 1, wherein, The three-stage cyclone separator (30) includes a three-stage cyclone separator outer ring (31), and three-stage cyclone blades (32) are machined on the inner wall surface of the three-stage cyclone separator outer ring (31). The three-stage cyclone blades (32) are evenly distributed circumferentially along the central axis of the fuel nozzle (60). The three-stage cyclone separator outer ring (31) is a rotating body structure, and the outer diameter D of the lower surface of the three-stage cyclone separator outer ring (31) is... 30-12 =80mm~85mm, the inner diameter D of the lower surface of the outer ring (31) of the third-stage hydrocyclone is 80mm~85mm. 30-11 =74mm~78mm, wall thickness of the lower surface of the outer ring (31) of the third-stage hydrocyclone d 30-4 = (D 30-12 - D 30-11 ) / 2; The outlet position of the outer ring (31) of the three-stage hydrocyclone is an expansion structure, and the height of the expansion structure is... h 30-5 =2.5mm~4.5mm, outlet outer ring inner diameter D 30-3 =78mm~82mm, thickness of the outer ring at the outlet d 30-2 =(D 30-12 - D 30-3 ) / 2, the angle between the inner wall surface of the expansion structure and the axial direction. ​ 30-1 =20°~40°; the type of the three-stage swirl blade (32) is an axial swirl blade, and the installation angle of the three-stage swirl blade (32) with the horizontal direction is 20°~40°; ​ 30-9 =30°~60°, thickness of three-stage swirl blades (32) ​ 30-6 =0.8mm~3mm, Installation height of the third-stage swirl blade (32) h 30-7 =10mm~18mm, the vertical distance between the third-stage cyclone blade (32) and the lower surface of the outer ring (31) of the third-stage cyclone separator. h 30-10 =4mm~8mm, Number of three-stage swirl blades (32) m 3=16~24, swirl blade (32) center diameter D 30-13 =50mm~62mm.

5. An aeroengine triple-swirl combustor plasma ignition-assisted energizer according to claim 1, characterized in that, The high-voltage electrode (40) includes a high-voltage electrode ring (41) and a high-voltage wire (42). An electrode hole (43) is provided on the high-voltage electrode ring (41), and the high-voltage wire (42) passes through the electrode hole (43) and is fixed to the high-voltage electrode ring (41). The high-voltage electrode ring (41) is made of metal or a ductile conductive metal foil. The metal material includes tungsten-copper alloy, copper, brass, or stainless steel. The outer diameter D of the high-voltage electrode ring (41) is... 40-1 =11mm~14mm, inner diameter D of high voltage electrode ring (41) 40-1 =8mm~11mm, thickness of high voltage electrode ring (41) ​ 40-3 =0.4mm~0.8mm; the high-voltage conductor (42) is made of silver wire, copper wire or stainless steel wire, and the diameter of the high-voltage conductor (42) is 0.4mm~0.8mm; ​ 40-5 =0.4mm~0.8mm.

6. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 5, wherein, The ceramic insulation section (50) includes a ceramic insulation tube (51) and a conductor channel (52); the ceramic insulation tube (51) is a rotating structure, and the conductor channel (52) is provided on the outer wall of the ceramic insulation tube (51). The conductor channel (52) is a cylindrical through hole, and the inner diameter of the conductor channel (52) is... d 50-9 =0.4mm~0.8mm, the distance from the center of the conductor channel (52) to the outer wall of the ceramic insulating tube (51) d 50-3 =0.8mm~1.1mm; the upper end of the ceramic insulating tube (51) has a stepped structure for matching with the high voltage electrode ring (41) of the high voltage electrode (40); the stepped surface D of the ceramic insulating tube (51) 50-1 =8mm~11mm, ceramic insulating tube (51) upper surface outlet diameter D 50-2 =4mm~6mm, ceramic insulating tube (51) step height h 50-5 =0.4mm~0.8mm, ceramic insulating tube (51) step width d 50-4 =1mm~2mm, outer diameter D of the lower surface of ceramic insulating tube (51) 50-11 =10mm~15mm, inner diameter D of the lower surface of ceramic insulating tube (51) 50-10 =7mm~10mm, height of ceramic insulating tube (51) h 50-7 =25mm~35mm; the outlet above the inner surface of the ceramic insulating tube (51) is a contracting conical surface, and the angle between the contracting conical surface and the inner surface is 25mm~35mm. ​ 50-6 =135°~155°, the distance from the contraction point of the contraction cone to the lower surface of the ceramic insulating tube (51) is... h 50-8 =23mm~26mm.

7. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 6, wherein, ​ 8. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 1, wherein, The swirled fuel nozzle (60) comprises a nozzle (61), a nozzle swirled vane (62) and a fuel supply rod (63) in sequence; the overall height of the swirled fuel nozzle (60) h 60-5 =35mm~50mm; the height of the nozzle (61) h 60-3 =8.5mm~10.5mm, the diameter D of the nozzle (61) 60-2 =6.5mm~7.5mm, the outlet of the nozzle (61) is a conical surface, the included angle between the conical surface and the horizontal direction ​ 60-1 =135°~155°, the outlet diameter D of the nozzle (61) 60-9 =1.5mm~2.5mm; the type of the nozzle swirled vane (62) is an axial swirled vane, the installation height of the nozzle swirled vane (62) h 60-4 =6mm~9mm, the installation angle of the nozzle swirled vane (62) with the horizontal direction ​ 60-7 =40°~70°, the thickness of the nozzle swirled vane (62) ​ 60-6 =0.6mm~1mm, the center diameter D of the nozzle swirled vane (62) 60-10 =7mm~10mm, the number of the nozzle swirled vane (62) m 4=6~12; the diameter D of the fuel supply rod (63) 60-8 =2mm~6mm.

9. A plasma pilot burner igniter for a gas turbine engine triple swirl combustor according to claim 1, wherein, ​ 10. An aeroengine triple-swirl combustor plasma ignition-assisted energizer according to claim 1, characterized in that, ​ ​

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