CN116697402A - Support plate plasma excitation integrated afterburner - Google Patents

Support plate plasma excitation integrated afterburner Download PDF

Info

Publication number
CN116697402A
CN116697402A CN202310715216.5A CN202310715216A CN116697402A CN 116697402 A CN116697402 A CN 116697402A CN 202310715216 A CN202310715216 A CN 202310715216A CN 116697402 A CN116697402 A CN 116697402A
Authority
CN
China
Prior art keywords
afterburner
flame stabilizer
casing
radial flame
plasma
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310715216.5A
Other languages
Chinese (zh)
Inventor
赵兵兵
李志远
魏国振
刘明金
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Air Force Engineering University of PLA
Original Assignee
Air Force Engineering University of PLA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Air Force Engineering University of PLA filed Critical Air Force Engineering University of PLA
Priority to CN202310715216.5A priority Critical patent/CN116697402A/en
Publication of CN116697402A publication Critical patent/CN116697402A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
    • H05H1/00—Generating plasma; Handling plasma
    • H05H1/24—Generating plasma
    • H05H1/26—Plasma torches
    • H05H1/32—Plasma torches using an arc
    • H05H1/34—Details, e.g. electrodes, nozzles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Plasma Technology (AREA)

Abstract

The invention discloses a support plate plasma excitation integrated afterburner, which comprises: the back side of the radial flame stabilizer is provided with a plasma exciter, the plasma exciter comprises a plasma exciter positive electrode and a plasma exciter negative electrode, the plasma exciter positive electrode is positioned at the back end of a first end face of the radial flame stabilizer, the first end face is a plane parallel to the direction of air flow in the duct on the radial flame stabilizer, the plasma exciter negative electrode is positioned at the back end of a second end face of the radial flame stabilizer, and the second end face is a plane opposite to the first end face on the radial flame stabilizer. When the afterburner is used for tissue combustion, plasma rich in active particles is generated through discharge of a plasma exciter, and the plasma is involved in the ignition and combustion process of fuel/air mixture, so that stable and rapid ignition and continuous combustion supporting of the afterburner are realized, and the ignition and combustion tissue mode of the afterburner is greatly optimized.

Description

Support plate plasma excitation integrated afterburner
Technical Field
The invention belongs to the technical field of aeroengines and gas turbines, and particularly relates to a support plate plasma excitation integrated afterburner.
Background
Afterburners have been an important component of fighter aircraft and can be used to re-inject fuel into the gas flowing out of the turbine for combustion under certain conditions to increase engine thrust in a short period of time for speed advantage.
Currently, there are three main ways of afterburner ignition: thermal jet ignition, catalyst ignition and spark ignition. The hot jet ignition, the flame transfer path is far, the flow is complex, especially when passing through a multi-stage turbine, the hot jet ignition is subjected to strong disturbance, and a large amount of ignition tests are correspondingly carried out when debugging the afterburner; the catalyst is ignited, the ignition device has simple structure, light weight and convenient ignition, but platinum rhodium wires have high price and are easy to be polluted and lose efficacy, and the working reliability of the ignition device is affected; the electric spark is ignited, the ignition delay time is longer, and the ignition stability is poor.
The plasma ignition combustion-supporting technology is a novel ignition and combustion strengthening technology, has high ignition energy and short delay time, and can obviously increase the chemical reaction rate, improve the combustion efficiency and enlarge the stable combustion range.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides the support plate plasma excitation integrated afterburner, which realizes stable and rapid ignition and continuous combustion supporting of the afterburner and greatly optimizes the ignition and combustion organization modes of the afterburner.
In order to solve the above problems, the present invention provides a support plate plasma excitation integrated afterburner, which is characterized by comprising: the radial flame stabilizer comprises a support plate and a radial flame stabilizer, wherein the front side of the radial flame stabilizer is connected with the rear side of the support plate, a plasma exciter is arranged at the rear side of the radial flame stabilizer and comprises a plasma exciter anode and a plasma exciter cathode, the plasma exciter anode is positioned at the rear end of a first end face of the radial flame stabilizer, the first end face is a plane parallel to the direction of airflow in a duct on the radial flame stabilizer, the plasma exciter cathode is positioned at the rear end of a second end face of the radial flame stabilizer, and the second end face is a plane opposite to the first end face on the radial flame stabilizer.
The support plate plasma excitation integrated afterburner is characterized by further comprising a casing and an inner cone, wherein the casing comprises an afterburner casing and an inner channel casing, the afterburner casing is used for separating the outside from the inside of an engine, the inner channel casing is arranged in the afterburner casing, and an annular channel enclosed between the afterburner casing and the inner channel casing is an outer channel; the inner cone is arranged in the inner duct casing, and an annular channel surrounded by the inner cone and the inner duct casing is an inner duct;
the radial flame stabilizer penetrates through the whole outer duct, the outermost side of the radial flame stabilizer is connected with the afterburner casing, and the inner side of the radial flame stabilizer is connected with the inner cone.
The support plate plasma excitation integrated afterburner is characterized by further comprising an oil conveying ring, an oil injection rod and an oil injection nozzle, wherein the oil conveying ring is arranged on the outer side of the afterburner casing; one end of the oil injection rod is communicated with an oil delivery ring at the outer side of the afterburner casing; the oil nozzle is communicated with the oil injection rod;
the radial flame stabilizer is provided with a hollow cavity, the other end of the oil injection rod penetrates through the hollow cavity of the radial flame stabilizer and then stretches into the inner cone, the rear parts and the rear end faces of the two side faces of the radial flame stabilizer are provided with oil injection nozzle through holes communicated with the hollow cavity, and the oil injection nozzle is arranged in the oil injection nozzle through holes and communicated with the oil injection rod in the hollow cavity.
The support plate plasma excitation integrated afterburner is characterized in that the radial flame stabilizer is also provided with vent holes, the vent holes are positioned on two side surfaces and the rear end surface of the radial flame stabilizer, and the vent holes are positioned on the front side and the rear side of the corresponding oil nozzle through hole.
The support plate plasma excitation integrated afterburner is characterized in that a concave cavity is formed in one end of the inner cone, which is close to the tail flame of the engine.
The support plate plasma excitation integrated afterburner is characterized in that: the support plates are integrally arranged around the cone body, and the support plates and the concave cavities are integrally designed.
The support plate plasma excitation integrated afterburner is characterized in that: the recessed cavity plasma excitation integrated afterburner further comprises a vibration isolation screen which is connected to the rear half section of the afterburner casing.
Compared with the prior art, the invention has the following advantages:
1. the invention adopts the plasma exciter for ignition, when the plasma exciter works, discharge plasma is generated between the anode and the cathode, and the discharge plasma can directly act on the combustion process of fuel/air mixture at the back flow area behind the radial flame stabilizer, on one hand, the plasma discharge can promote the atomization and cracking of the fuel, on the other hand, active particles in the plasma can enhance the combustion chemical reaction rate, expand the stable combustion range, improve the combustion efficiency, realize the stable and rapid ignition and continuous combustion supporting of the afterburner, and greatly optimize the ignition mode of the afterburner.
2. The support plate, the inner cone and the casing form an airflow flowing channel together. Creating a large recirculation zone behind the radial flame stabilizer in the direction of airflow flow; the cavity on the rear side of the inner cone is used to create a small recirculation zone.
3. The design of the large and small backflow areas adopted by the invention not only reduces the total pressure loss and improves the thrust mass ratio of the aircraft, but also improves the durability and the service life of the afterburner material; the combustion stability of the inner and outer duct gases is considered, and the structural reliability is also improved.
4. The invention adopts an integrated design, shortens the length of the engine, lightens the mass of the engine and reduces the flow loss.
The invention is described in further detail below with reference to the drawings and examples.
Drawings
The above and other features, advantages and aspects of embodiments of the present invention will become more apparent by reference to the following detailed description when taken in conjunction with the accompanying drawings. The same or similar reference numbers will be used throughout the drawings to refer to the same or like elements. It should be understood that the figures are schematic and that elements and components are not necessarily drawn to scale.
FIG. 1 is a schematic diagram showing the connection relation structure of a support plate and a radial flame stabilizer in an embodiment of the invention.
Fig. 2 shows a schematic perspective view of a radial flame stabilizer in an embodiment of the invention.
FIG. 3 illustrates a schematic cross-sectional view of a radial flame stabilizer in an embodiment of the invention.
Fig. 4 is a schematic cross-sectional view of a support plate according to an embodiment of the present invention.
FIG. 5 illustrates a cross-sectional view of a forced induction combustion chamber in an embodiment of the present invention.
Fig. 6 shows an enlarged view of a of fig. 5.
Fig. 7 shows a schematic view of the structure of the inner cone of the present invention.
FIG. 8 shows a schematic external configuration of an enhanced combustion chamber in accordance with an embodiment of the present invention.
Reference numerals illustrate:
10-supporting plates; 20-radial flame stabilizer; 21-a hollow cavity;
22-an oil nozzle through hole; 23-positive electrode of plasma exciter; 24-plasma exciter cathode;
25-vent holes; 31-afterburner casing; 32-inner channel casing;
33-an outer duct; 34-an inner duct; 40-an inner cone;
41-a cavity; 50-an oil conveying ring; 51-an oil injection rod;
52-an oil nozzle; 60-vibration isolation screen.
Detailed Description
Embodiments of the present invention will be described in more detail herein with reference to the accompanying drawings. While the invention is susceptible of embodiment in the drawings, it is to be understood that the invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but rather are provided to provide a more thorough and complete understanding of the invention. It should be understood that the drawings and embodiments of the invention are for illustration purposes only and are not intended to limit the scope of the present invention.
As shown in fig. 1 to 4, the invention discloses a support plate plasma excitation integrated afterburner, which comprises a support plate 10 and a radial flame stabilizer 20, wherein the front side of the radial flame stabilizer 20 is connected with the rear side of the support plate 10, the rear side of the radial flame stabilizer 20 is provided with a plasma exciter, a positive electrode 23 of the plasma exciter is positioned at the rear end of a first end surface of the radial flame stabilizer 20, the first end surface is a plane parallel to the direction of airflow in a duct on the radial flame stabilizer 20, a negative electrode 24 of the plasma exciter is positioned at the rear end of a second end surface of the radial flame stabilizer 20, and the second end surface is a plane opposite to the first end surface on the radial flame stabilizer 20.
In this embodiment, a plasma exciter is disposed at the rear end of the radial flame stabilizer 20, and an arc discharge is generated between the positive electrode 23 and the negative electrode 22 of the plasma exciter and plasma is generated around the plasma exciter, that is, a large amount of plasma is generated in a backflow area at the rear end of the radial flame stabilizer 20, and the fuel-air mixture is ignited by the arc plasma and forms a stable flame, which prolongs the residence time of the flame, so that the combustion is more sufficient, stable and rapid ignition and continuous combustion supporting of the afterburner are realized, and the ignition mode of the afterburner is greatly optimized.
As shown in fig. 4, the support plate plasma excitation integrated afterburner further comprises a casing and an inner cone 40, wherein the casing comprises an afterburner casing 31 and an inner culvert casing 32, the afterburner casing 31 is used for separating the outside from the inside of the engine, the inner culvert casing 32 is arranged in the afterburner casing 31, and an annular channel enclosed between the afterburner casing 31 and the inner culvert casing 32 is an outer culvert 33; the inner cone 40 is disposed inside the inner duct casing 32, and an annular channel defined by the inner cone 40 and the inner duct casing 32 is an inner duct 34; wherein the radial flame stabilizer 20 extends through the entire outer duct 33 and the outermost side of the radial flame stabilizer 20 is connected to the afterburner casing 31 and the inner side of the radial flame stabilizer 20 is connected to the inner cone 40.
As shown in fig. 5, 6 and 8, the baffle plasma excitation integrated afterburner further comprises: an oil delivery ring 50, an oil injection rod 51 and an oil injection nozzle 52, wherein the oil delivery ring 50 is arranged on the outer side of the afterburner casing 31; one end of the oil injection rod 51 is communicated with an oil delivery ring 50 outside the afterburner casing 31; the oil jet 52 communicates with the oil jet rod 51; the radial flame stabilizer 20 is provided with a hollow cavity 21, the other end of the oil injection rod 51 penetrates through the hollow cavity 21 of the radial flame stabilizer 20 and then extends into the inner cone 40, the rear parts and the rear end faces of the two side faces of the radial flame stabilizer 20 are provided with oil injection nozzle through holes 22 communicated with the hollow cavity 21, and the oil injection nozzle 52 is arranged in the oil injection nozzle through holes 22 and communicated with the oil injection rod 51 in the hollow cavity 21.
In this embodiment, a concave cavity 41 is disposed at one end of the inner cone 40 near the tail flame, and the support plate 10 and the radial flame stabilizer 20 are installed in the air flow passage between the inner cone 40 and the inner channel casing 32. The radial flame stabilizer 20 and the inner cone are integrally designed, and the oil injection rod 51 is arranged inside the radial flame stabilizer 20; the radial flame stabilizer 20 is integrally arranged around the inner cone 40; the outlet of the outer duct 33 is positioned behind the radial flame stabilizer 20, and the air flows out of the inner duct 34 to the radial flame stabilizer 20 and then are mixed; part of the nozzles are positioned in small holes formed in the radial flame stabilizer 20; fuel is sprayed out from a nozzle in a small hole on the side surface of the radial flame stabilizer 20; the radial flame stabilizer 20 is provided with a plasma exciter electrode at an end face thereof for ignition. The air flow from the external culvert is divided into two parts in the radial flame stabilizer 20, and a small part flows into the radial flame stabilizer, and then flows out from the rear end of the radial flame stabilizer 20 to be mixed with the internal fuel gas; the other major portion flows out of the rear of the radial flame stabilizer 20 to mix with the connotative air flow; the two portions of the air flow form a large recirculation zone behind the radial flame stabilizer 20 to stabilize the flame and extend the residence time of the flame to provide more complete combustion.
As shown in fig. 2 and 6, the radial flame stabilizer 20 is further provided with a vent hole 25, the vent hole 25 is located on two side surfaces and a rear end surface of the radial flame stabilizer 20, and the vent hole 25 is located at a front side position and a rear side position of the corresponding fuel injection nozzle through hole 22.
In this embodiment, the fuel injection rod 51 is inserted into the middle of the support plate 10, fuel is injected from the fuel injection nozzle 52 in the fuel injection nozzle through hole 22 on the side of the support plate 10, the vent holes 25 are opened on the support plate 10 at the front and rear positions corresponding to the fuel injection nozzle through hole 22, and the air jet injected from the vent holes 25 can improve the penetration of the fuel jet and the distribution of the fuel mass fraction. The oil spray rod 51 is closely matched with the support plate 10, so that fuel oil can be atomized on the surface of the support plate 10 to form an oil film, and the fuel oil is secondarily atomized at the tail part and the front part of the concave cavity of the support plate, thereby improving the fuel oil utilization rate.
As shown in fig. 5 and 7, the end of the inner cone 40 near the engine tail flame is provided with a cavity 41.
The inner cone 40 and the casing together form a channel for the flow of air in this embodiment. The rear side of the inner cone 40, i.e. the side close to the tail flame, is provided with a concave cavity 41 for generating a small backflow area, and the residence time of the fuel gas flowing through the concave cavity is prolonged, so that an on-duty flame is formed, the ignition of fuel gas at other parts is facilitated, the ignition efficiency is improved, the flame can be stabilized, and the full combustion of the fuel gas is promoted. The air flow forms a large recirculation zone through the inner and outer ducts at the back side of the support plate and radial flame stabilizer 20, improving combustion stability. The electrode of the plasma exciter arranged at the rear end of the radial flame stabilizer 20 ignites the fuel-air mixture in the large backflow area, and the inner cone cavity utilizes low-speed backflow at the cavity to form a flame linkage effect, so that the inner hollow tail-cutting support plate distributed in the diffuser stabilizes flame.
In this embodiment, when the plasma exciter works, discharge plasma is generated between the positive electrode and the negative electrode, and the discharge plasma can directly act on the combustion process of the fuel/air mixture in the back flow area behind the radial flame stabilizer 20, so that on one hand, the plasma discharge can promote the atomization and cracking of the fuel, on the other hand, active particles in the plasma can enhance the combustion chemical reaction rate, expand the stable combustion range and improve the combustion efficiency.
As shown in fig. 5, the support plates are integrally arranged around the cone body, and the support plates and the concave cavities are integrally designed, so that the problems of large weight and volume, large flow loss, large resistance, improvement of flame combustion stability and the like of the existing afterburner are solved.
As shown in fig. 5, the support plate plasma excitation integrated afterburner further comprises a vibration isolation screen 60, wherein the vibration isolation screen 60 is connected to the rear half of the afterburner casing 31.
On the basis of changing the original general afterburner, the invention integrally adopts an integrated design to reduce the weight and the volume and a support plate-concave cavity integrated design to reduce the flow loss and the resistance. The oil injection rod is closely matched with the radial flame stabilizer, so that fuel oil can be atomized on the surface of the support plate to form an oil film, and the tail part and the front part of the concave cavity of the radial flame stabilizer of the support plate are secondarily atomized, so that the fuel oil utilization rate is improved. The inner cone cavity utilizes the low-speed backflow flame linkage function at the cavity, and simultaneously utilizes the radial flame stabilizer to stabilize the flame.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and any simple modification, variation and equivalent structural transformation of the above embodiment according to the technical substance of the present invention still fall within the scope of the technical solution of the present invention.

Claims (7)

1. A baffle plasma excitation integrated afterburner, comprising: the flame stabilizer comprises a support plate (10) and a radial flame stabilizer (20), wherein the front side of the radial flame stabilizer (20) is connected with the rear side of the support plate (10), a plasma exciter is arranged on the rear side of the radial flame stabilizer (20), the plasma exciter comprises a plasma exciter anode (23) and a plasma exciter cathode (24), the plasma exciter anode (23) is positioned at the rear end of a first end face of the radial flame stabilizer (20), the first end face is a plane parallel to the direction of airflow in a duct on the radial flame stabilizer (20), the plasma exciter cathode (24) is positioned at the rear end of a second end face of the radial flame stabilizer (20), and the second end face is a plane opposite to the first end face on the radial flame stabilizer (20).
2. The baffle plasma excitation integrated afterburner of claim 1, further comprising:
the engine comprises a casing and a combustion engine, wherein the casing comprises an afterburner casing (31) and an inner channel casing (32), the afterburner casing (31) is used for separating the outside from the inside of the engine, the inner channel casing (32) is arranged in the afterburner casing (31), and an annular channel enclosed between the afterburner casing (31) and the inner channel casing (32) is an outer channel (33);
the inner cone (40) is arranged in the inner duct casing (32), and an annular channel surrounded by the inner cone (40) and the inner duct casing (32) is an inner duct (34);
the radial flame stabilizer (20) penetrates through the whole outer duct (33), the outermost side of the radial flame stabilizer (20) is connected with the afterburner casing (31), and the inner side of the radial flame stabilizer (20) is connected with the inner cone (40).
3. A baffle plasma excitation integrated afterburner as recited in claim 2, further comprising:
an oil delivery ring (50), wherein the oil delivery ring (50) is arranged on the outer side of the afterburner casing (31);
the oil injection rod (51), one end of the oil injection rod (51) is communicated with an oil delivery ring (50) at the outer side of the afterburner casing (31);
-an oil jet (52), said oil jet (52) being in communication with said oil jet rod (51);
the radial flame stabilizer (20) is provided with a hollow cavity (21), the other end of the oil injection rod (51) penetrates through the hollow cavity (21) of the radial flame stabilizer (20) and then stretches into the inner cone (40), the rear parts and the rear end faces of the two side faces of the radial flame stabilizer (20) are provided with oil injection nozzle through holes (22) communicated with the hollow cavity (21), and the oil injection nozzle (52) is arranged in the oil injection nozzle through holes (22) and is communicated with the oil injection rod (51) in the hollow cavity (21).
4. A supporting plate plasma excitation integrated afterburner as claimed in claim 3, wherein the radial flame stabilizer (20) is further provided with vent holes (25), the vent holes (25) are located on two side surfaces and a rear end surface of the radial flame stabilizer (20), and the vent holes (25) are located on the front side and the rear side of the corresponding oil nozzle through holes (22).
5. A baffle plasma excitation integrated afterburner as claimed in any one of claims 1 to 4, wherein the inner cone (40) is provided with a recess (41) at the end adjacent the engine tail flame.
6. A baffle plasma excitation integrated afterburner as recited in claim 5, wherein: the support plates are integrally arranged around the cone body, and the support plates and the concave cavities are integrally designed.
7. A baffle plasma excitation integrated afterburner as claimed in claim 6 or wherein: the support plate plasma excitation integrated afterburner further comprises a vibration isolation screen (60), and the vibration isolation screen (60) is connected to the rear half section of the afterburner casing (31).
CN202310715216.5A 2023-06-15 2023-06-15 Support plate plasma excitation integrated afterburner Pending CN116697402A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310715216.5A CN116697402A (en) 2023-06-15 2023-06-15 Support plate plasma excitation integrated afterburner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310715216.5A CN116697402A (en) 2023-06-15 2023-06-15 Support plate plasma excitation integrated afterburner

Publications (1)

Publication Number Publication Date
CN116697402A true CN116697402A (en) 2023-09-05

Family

ID=87823557

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310715216.5A Pending CN116697402A (en) 2023-06-15 2023-06-15 Support plate plasma excitation integrated afterburner

Country Status (1)

Country Link
CN (1) CN116697402A (en)

Similar Documents

Publication Publication Date Title
US8011188B2 (en) Augmentor with trapped vortex cavity pilot
CA2551711C (en) Augmentor radial fuel spray bar with counterswirling heat shield
JP3782822B2 (en) Fuel injection device and method of operating the fuel injection device
US8387391B2 (en) Aerodynamically enhanced fuel nozzle
US8726668B2 (en) Fuel atomization dual orifice fuel nozzle
JP4406126B2 (en) Apparatus and method for rich-quenched-lean (RQL) concept in a gas turbine engine combustor with trapped vortex cavity
CN109595590B (en) Integrated afterburner of grid structure rectification support plate flame stabilizer
CN113280366B (en) Afterburner structure based on self-excitation sweep oscillation fuel nozzle
EP2466206A2 (en) Cooling flowpath dirt deflector in fuel nozzle
CN110686275B (en) Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation
CN113606610B (en) Pneumatic auxiliary atomization direct injection type nozzle applied to afterburner
US20050262847A1 (en) Method and apparatus for gas turbine engines
US11732894B2 (en) Pulse detonation combustion system
EP2400221A2 (en) Ejector purge of cavity adjacent exhaust flowpath
CN108870441B (en) Afterburner adopting circular arc fan-shaped nozzle and concave cavity structure
CN109945233B (en) Combustion chamber, atomization device thereof and aviation gas turbine engine
CN116658937A (en) Concave cavity plasma excitation integrated afterburner
CN110131048B (en) Self-contained internal combustion wave rotor ignition device and method
CN116697402A (en) Support plate plasma excitation integrated afterburner
CN113048513B (en) Multistage oil spout hole center cone integration afterburner
CN114517920A (en) Injection device, combustion chamber head, combustion chamber and aircraft engine
CN219530928U (en) Flame tube, engine and helicopter
CN115264533B (en) Natural gas coaxial staged combustion chamber adopting central ignition and combustion method
CN112050204B (en) Low-nitrogen burner
CN115307179B (en) Curved support plate double-concave-cavity integrated afterburner

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination