CN116658937A - Concave cavity plasma excitation integrated afterburner - Google Patents

Concave cavity plasma excitation integrated afterburner Download PDF

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Publication number
CN116658937A
CN116658937A CN202310714007.9A CN202310714007A CN116658937A CN 116658937 A CN116658937 A CN 116658937A CN 202310714007 A CN202310714007 A CN 202310714007A CN 116658937 A CN116658937 A CN 116658937A
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CN
China
Prior art keywords
casing
afterburner
flame stabilizer
cavity
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
CN202310714007.9A
Other languages
Chinese (zh)
Inventor
赵兵兵
刘明金
魏国振
李志远
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
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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 CN202310714007.9A priority Critical patent/CN116658937A/en
Publication of CN116658937A publication Critical patent/CN116658937A/en
Pending legal-status Critical Current

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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
    • F23R3/28—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
    • F23R3/02—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
    • 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
    • F23R3/286—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

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  • 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)
  • Hydrogen, Water And Hydrids (AREA)

Abstract

The invention discloses a recessed cavity plasma excitation integrated afterburner, which comprises a casing, a radial flame stabilizer, an inner cone and a plasma igniter, wherein the casing comprises an afterburner casing and an inner channel casing, and an annular channel enclosed between the afterburner casing and the inner channel casing is an outer channel; the radial flame stabilizer penetrates through the whole outer duct; the annular channel surrounded by the inner cone and the inner channel casing is an inner channel, one end of the inner cone, which is close to the tail flame of the engine, is provided with a concave cavity, and the plasma igniter is positioned at the concave cavity of the root of the radial flame stabilizer, which is close to the inner cone. The inner cone and the casing together form an airflow channel. The cavity on the rear side of the inner cone is used to create a small recirculation zone. The plasma igniters are arranged on the two sides of the concave cavity, and can directly act on the combustion process of the fuel/air mixture at the concave cavity to form flame coupling, so that the combustion stability is improved.

Description

Concave cavity plasma excitation integrated afterburner
Technical Field
The invention belongs to the technical field of aeroengines and gas turbines, and particularly relates to a recessed cavity plasma excitation integrated afterburner.
Background
The afterburner can inject fuel into the fuel gas flowing out after the turbine for re-combustion under specific conditions, so that the thrust of the engine is increased in a short time, the speed advantage of the aircraft is obtained, and the afterburner is widely applied and developed in the field of aeroengines.
The existing afterburner of the aeroengine has the practical problems of large size, high weight, high fuel consumption, difficult ignition, easy oscillation combustion and the like, and the integrated afterburner has obvious advantages in the aspects of improving the ignition capacity of the aeroengine, reducing the fluid resistance, improving the combustion efficiency and the like. Because the integrated afterburner has great advantages and prospects, research work on related aspects has been carried out at home and abroad. The F120 and F110 engines developed by the GE company preliminarily realize the integrated design of the support plate, the mixer, the stabilizer and the oil injection rod, wherein the integrated design mainly comprises the integration of the support plate and the oil injection rod and the integration of the mixer and the radial/annular stabilizer. In addition, the general company adopts the design scheme of integrating the rear frame of the turbine, and is the afterburning scheme with the highest integration degree at present.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a concave cavity plasma excitation integrated afterburner, wherein an inner cone and a casing form an airflow flowing channel together. The cavity on the rear side of the inner cone is used to create a small recirculation zone. The plasma igniters are arranged on the two sides of the concave cavity, and can directly act on the combustion process of the fuel/air mixture at the concave cavity, so that the ignition and combustion process are accelerated by using the plasmas rich in active particles, and the combustion stability is improved.
In order to solve the problems, the invention provides a recessed cavity plasma excitation integrated afterburner. The invention is realized by the following technical scheme: the cavity plasma excitation integrated afterburner is characterized by comprising a casing, a radial flame stabilizer, an inner cone and a plasma igniter;
the engine comprises an engine, a combustion chamber and a combustion chamber, wherein the engine comprises a combustion chamber engine casing and an inner channel engine casing, the combustion chamber engine casing is used for separating the outside from the inside of the engine, the inner channel engine casing is arranged in the combustion chamber engine casing, and an annular channel enclosed between the combustion chamber engine casing and the inner channel engine casing is an outer channel;
the radial flame stabilizer penetrates through the whole outer duct, and the outermost side of the radial flame stabilizer is connected with the afterburner casing;
the inner cone body is arranged in the inner duct casing, an annular channel surrounded by the inner cone body and the inner duct casing is an inner duct, the inner side of the radial flame stabilizer is connected with the inner cone body, and a concave cavity is formed in one end, close to engine tail flame, of the inner cone body;
the plasma igniter is positioned at the root of the radial flame stabilizer near the concave cavity of the inner cone.
The cavity plasma excitation integrated afterburner is characterized in that: the positive electrode of the plasma igniter is positioned at one side of the concave cavity close to the root of the radial flame stabilizer, and the negative electrode of the plasma igniter is positioned at one side of the concave cavity far away from the root of the radial flame stabilizer.
The cavity plasma excitation integrated afterburner is characterized in that: the recessed cavity plasma excitation integrated afterburner further comprises a support plate, wherein the support plate is arranged on the outer side of the inner cone and connected with the front side of the radial flame stabilizer.
The cavity plasma excitation integrated afterburner is characterized in that: the recessed cavity plasma excitation integrated afterburner further comprises 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 of the two side surfaces and the rear end surface 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 cavity plasma excitation integrated afterburner is characterized in that: the radial flame stabilizer is also provided with vent holes, the vent holes are positioned on the two side surfaces and the rear end surface of the radial flame stabilizer, and the vent holes are positioned on the positions of the front side and the rear side of the corresponding oil nozzle through hole.
The cavity 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 cavity 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 and is positioned on the inner side of the afterburner casing.
Compared with the prior art, the invention has the following advantages:
1. the inner cone and the casing form an airflow flowing channel together. The cavity on the rear side of the inner cone is used to create a small recirculation zone. The plasma igniters are arranged on the two sides of the concave cavity, plasma excitation generated by the discharge of the plasma igniters can directly act on the combustion process of fuel oil/air mixture at the concave cavity, and the ignition and combustion process is accelerated by using the plasmas rich in active particles, so that the combustion stability is improved.
2. 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.
3. The invention adopts an integrated design, shortens the length of the engine, lightens the mass of the engine and reduces the flow loss.
4. The invention adopts the plasma igniter to ignite, when the plasma igniter works, discharge plasma is generated between the anode and the cathode, and the discharge plasma can directly act on the combustion process of fuel oil/air mixture at the concave cavity, so that on one hand, the plasma discharge can promote the atomization and cracking of the fuel oil, and 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.
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 shows a schematic external configuration of an enhanced combustion chamber in accordance with an embodiment of the present invention.
FIG. 2 illustrates a cross-sectional view of a forced induction combustion chamber in an embodiment of the present invention.
Fig. 3 shows an enlarged view of a of fig. 2.
Fig. 4 shows a schematic view of the structure of the inner cone of the present invention.
Fig. 5 shows a schematic perspective view of the support plate according to the present invention.
Reference numerals illustrate:
11-afterburner casing; 12-an inner channel casing; 13-an outer duct;
20-radial flame stabilizer; 30-an inner cone; 31-an internal channel;
32-a cavity; 41-positive electrode of plasma igniter;
42-a plasma igniter cathode; 50-supporting plates;
51-hollow cavity; 52-an oil nozzle through hole; 53-vent holes;
60-an oil conveying ring; 61-an oil injection rod; 62-oil nozzle;
70-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.
Referring to FIG. 1, an exemplary system architecture diagram to which embodiments of the present invention may be applied is shown.
As shown in fig. 2 and 4, the present invention discloses a re-entrant plasma excitation integrated afterburner comprising a casing, a radial flame stabilizer 20, an inner cone 30 and a plasma igniter 40.
The engine comprises an afterburner engine casing 11 and an inner culvert casing 12, wherein the afterburner engine casing 11 is used for separating the outside from the inside of the engine, the inner culvert casing 12 is arranged in the afterburner engine casing 11, and an annular channel enclosed between the afterburner engine casing 11 and the inner culvert casing 12 is an outer culvert 13; the radial flame stabilizer 20 penetrates through the whole outer duct 13, and the outermost side of the radial flame stabilizer 20 is connected with the afterburner casing 11; the inner cone 30 is arranged inside the inner duct casing 12, an annular channel surrounded by the inner cone 30 and the inner duct casing 12 is an inner duct 31, the inner side of the radial flame stabilizer 20 is connected with the inner cone 30, a concave cavity 32 is formed at one end, close to the engine tail flame, of the inner cone 30, and the plasma igniter 40 is located at the concave cavity 32, close to the inner cone 30, of the root of the radial flame stabilizer 20.
The inner cone 30 and the casing together form a channel for airflow. The rear side of the inner cone 30, i.e. the side close to the tail flame, is provided with a recess 32 for creating a small recirculation zone. The plasma igniters 40 are arranged on two sides of the concave cavity 32, and the plasma igniters 40 can directly act on the combustion process of the fuel/air mixture at the concave cavity 32, so that the ignition and combustion process is accelerated by using the plasmas rich in active particles, and the combustion stability is improved.
As shown in fig. 2 and 4, the positive plasma igniter electrode 41 is located on the side of the cavity 32 near the root of the radial flame holder 20, and the negative plasma igniter electrode 42 is located on the side of the cavity 32 away from the root of the radial flame holder 20.
In this embodiment, when the plasma igniter 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 at the concave cavity 32, so that on one hand, the plasma discharge can promote the atomization and cracking of the fuel, and 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. 2, the re-entrant plasma excitation integrated afterburner further comprises a support plate 50, the support plate 50 being disposed outside the inner cone 30 and connected to the front side of the radial flame stabilizer 20.
As shown in fig. 1 to 4, the recessed plasma excitation integrated afterburner further comprises an oil delivery ring 60, an oil injection rod 61 and an oil injection nozzle 62, wherein the oil delivery ring 60 is arranged on the outer side of the afterburner casing 11; one end of the oil injection rod 61 is communicated with an oil delivery ring 60 on the outer side of the afterburner casing 11; the oil jet 62 communicates with the oil jet rod 61. The radial flame stabilizer 20 is provided with a hollow cavity 51, the other end of the oil injection rod 61 penetrates through the hollow cavity 51 of the radial flame stabilizer 20 and then extends into the inner cone 30, 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 52 communicated with the hollow cavity 51, and the oil injection nozzle 62 is arranged in the oil injection nozzle through holes 52 and communicated with the oil injection rod 61 in the hollow cavity 51.
In this embodiment, a concave cavity 32 is disposed at one end of the inner cone 30 near the tail flame, and a support plate 50 is installed in the air flow channel between the inner cone 30 and the inner channel casing 12. The radial flame stabilizer 20 and the inner cone are integrally designed, and the oil injection rod 61 is arranged inside the radial flame stabilizer 20; the radial flame stabilizer 20 is integrally arranged around the inner cone 30; the igniter is positioned at the root of the radial flame stabilizer 20 near the cavity 32 of the inner cone 30; the outlet of the outer culvert 13 is positioned behind the radial flame stabilizer 20, and the air flows out from the inner culvert 31 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 ejected from nozzles in small holes in the side of the radial flame holder 20. 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. The inner cone is also provided with a small backflow area, and the residence time of the gas flowing through the small backflow area is prolonged, so that a duty flame is formed, the ignition of the gas at other parts is facilitated, the ignition efficiency is improved, the flame can be stabilized, and the full combustion of the gas is promoted.
In this embodiment, the air flow forms a large backflow area at the back side of the support plate and the radial flame stabilizer 20 through the inner and outer ducts, so that the combustion stability is improved, the inner cone cavity utilizes the combined flame effect of low-speed backflow at the cavity, and simultaneously, the radial flame stabilizer is utilized to stabilize the flame.
As shown in fig. 3 and 5, the radial flame stabilizer 20 is further provided with a vent hole 53, the vent hole 53 is located on two side surfaces and a rear end surface of the radial flame stabilizer 20, and the vent hole 53 is located at a position corresponding to a front side and a rear side of the oil nozzle through hole 52.
In this embodiment, the fuel injection rod 61 is inserted into the middle of the support plate 50, fuel is injected from the fuel injection nozzle 62 in the fuel injection nozzle through hole 52 at the side of the support plate 50, and the air holes 53 are opened on the radial flame stabilizer 20 at the front and rear positions corresponding to the fuel injection nozzle through hole 52, so that the air jet injected from the air holes 53 can improve the penetration of the fuel jet and the distribution of the fuel mass fraction. The oil injection rod 61 is closely matched with the support plate 50 and the radial flame stabilizer 20, so that fuel oil can be atomized on the surfaces of the support plate 50 and the radial flame stabilizer 20 to form an oil film, and the fuel oil can be secondarily atomized at the tail part and the front part of the concave cavity of the radial flame stabilizer 20, thereby improving the fuel oil utilization rate.
In the embodiment, 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. 2, the re-entrant plasma excitation integrated afterburner further comprises a vibration isolation screen 70, the vibration isolation screen 70 being attached to the rear half of the casing.
On the basis of changing the original general combustion chamber, 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 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 re-entrant plasma excitation integrated afterburner, comprising:
the engine comprises a casing and a combustion chamber casing, wherein the casing comprises an afterburner casing (11) and an inner channel casing (12), the afterburner casing (11) is used for separating the outside from the inside of an engine, the inner channel casing (12) is arranged in the afterburner casing (11), and an annular channel enclosed between the afterburner casing (11) and the inner channel casing (12) is an outer channel (13);
a radial flame stabilizer (20), the radial flame stabilizer (20) extending through the entire outer duct (13) and the outermost side of the radial flame stabilizer (20) being connected with the afterburner casing (11);
the inner cone (30), the inner cone (30) is arranged in the inner duct casing (12), an annular channel enclosed by the inner cone (30) and the inner duct casing (12) is an inner duct (31), the inner side of the radial flame stabilizer (20) is connected with the inner cone (30), and a concave cavity (32) is formed in one end, close to engine tail flame, of the inner cone (30);
a plasma igniter (40), the plasma igniter (40) being located at the root of the radial flame stabilizer (20) near the cavity (32) of the inner cone (30).
2. A re-entrant plasma excitation integrated afterburner as claimed in claim 1, wherein: the plasma igniter (40) comprises a plasma igniter positive electrode (41) and a plasma igniter negative electrode (42), the plasma igniter positive electrode (41) is located on one side of the concave cavity (32) close to the root of the radial flame stabilizer (20), and the plasma igniter negative electrode (42) is located on one side of the concave cavity (32) far away from the root of the radial flame stabilizer (20).
3. A re-entrant plasma excitation integrated afterburner as claimed in claim 2, wherein: the cavity plasma excitation integrated afterburner further comprises a support plate (50), wherein the support plate (50) is arranged on the outer side of the inner cone (30) and is connected with the front side of the radial flame stabilizer (20).
4. A re-entrant plasma excitation integrated afterburner as claimed in claim 3, wherein: the cavity plasma excitation integrated afterburner further comprises:
an oil delivery ring (60), wherein the oil delivery ring (60) is arranged on the outer side of the afterburner casing (11);
the oil injection rod (61), one end of the oil injection rod (61) is communicated with an oil delivery ring (60) at the outer side of the afterburner casing (11);
-an oil jet (62), said oil jet (62) being in communication with said oil jet rod (61);
the radial flame stabilizer (20) is provided with a hollow cavity (51), the other end of the oil injection rod (61) penetrates through the hollow cavity (51) of the radial flame stabilizer (20) and then stretches into the inner cone (30), 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 (52) communicated with the hollow cavity (51), and the oil injection nozzle (62) is arranged in the oil injection nozzle through holes (52) and is communicated with the oil injection rod (61) in the hollow cavity (51).
5. A re-entrant plasma excitation integrated afterburner as claimed in claim 4, wherein: the radial flame stabilizer (20) is also provided with vent holes (53), the vent holes (53) are positioned on two side surfaces and the rear end surface of the radial flame stabilizer (20), and the vent holes (53) are positioned on the front side and the rear side of the corresponding oil nozzle through hole (52).
6. A re-entrant plasma excitation integrated afterburner as claimed in claim 1, wherein: the support plates are integrally arranged around the cone body, and the support plates and the concave cavities are integrally designed.
7. A re-entrant plasma excitation integrated afterburner as claimed in claim 5, wherein: the recessed cavity plasma excitation integrated afterburner further comprises a vibration isolation screen (70), and the vibration isolation screen (70) is connected to the rear half section of the afterburner casing (11).
CN202310714007.9A 2023-06-15 2023-06-15 Concave cavity plasma excitation integrated afterburner Pending CN116658937A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310714007.9A CN116658937A (en) 2023-06-15 2023-06-15 Concave cavity plasma excitation integrated afterburner

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Application Number Priority Date Filing Date Title
CN202310714007.9A CN116658937A (en) 2023-06-15 2023-06-15 Concave cavity plasma excitation integrated afterburner

Publications (1)

Publication Number Publication Date
CN116658937A true CN116658937A (en) 2023-08-29

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117212836A (en) * 2023-10-26 2023-12-12 融通航空发动机科技有限公司 Supersonic aircraft and independent oil supply combined flame stabilizer

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117212836A (en) * 2023-10-26 2023-12-12 融通航空发动机科技有限公司 Supersonic aircraft and independent oil supply combined flame stabilizer
CN117212836B (en) * 2023-10-26 2024-06-07 融通航空发动机科技有限公司 Supersonic aircraft and independent oil supply combined flame stabilizer

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