CN115467760A - Rotary detonation engine based on non-equilibrium plasma detonation and gas supply - Google Patents
Rotary detonation engine based on non-equilibrium plasma detonation and gas supply Download PDFInfo
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- CN115467760A CN115467760A CN202211115266.1A CN202211115266A CN115467760A CN 115467760 A CN115467760 A CN 115467760A CN 202211115266 A CN202211115266 A CN 202211115266A CN 115467760 A CN115467760 A CN 115467760A
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- detonation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/08—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being continuous
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
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- 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
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- 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
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- 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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00008—Combustion techniques using plasma gas
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention provides a rotary detonation engine based on non-equilibrium plasma detonation and gas supply, which comprises a nozzle, a pre-detonation tube and an engine body, wherein the nozzle is arranged on the engine body; a combustion chamber is formed between the combustion chamber outer ring and the combustion chamber inner ring, the pre-explosion tube is arranged on the combustion chamber outer ring, and one end of the pre-explosion tube is communicated with the combustion chamber; the inlet of the pre-explosion pipe is provided with one nozzle; a spark plug is arranged in the pre-explosion tube; the plurality of nozzles are arranged in the combustion chamber and are positioned between the joint of one end of the predetonation pipe and the combustion chamber and the engine cover plate; a fuel flow passage and an oxidant flow passage which are not communicated with each other are arranged in the nozzle; and electrodes are arranged in the wall surface of the fuel flow channel, voltage is applied to two sides of the electrodes, and the electrodes are used for generating non-equilibrium plasma by ionizing the fuel medium in the flow channel. The invention can strengthen the combustion process, promote the fuel to burn out, reduce the heat loss of chemical incomplete combustion and reduce the emission of pollution gas.
Description
Technical Field
The invention relates to the field of rotary detonation engines, in particular to a rotary detonation engine based on detonation and gas supply of a non-equilibrium plasma technology.
Background
A rotary detonation engine is a new concept propulsion system based on detonation combustion. Compared with the conventional gas turbine or the ramjet, the rotary detonation engine has the advantages of high thermal efficiency, simple structure, low maintenance cost, high working frequency and the like, and is one of ideal power of future advanced propulsion systems. Various countries around the world are developing research work related to rotary detonation engines, and the manpower and material resources invested are increasing.
At present, the experimental research of the rotary detonation engine mainly takes gaseous hydrocarbon fuel as main material, but the gaseous fuel generally has higher storage requirement and small volume energy density. The liquid hydrocarbon fuel is easy to store and transport, has higher volume energy density, and is more suitable to be used as the fuel of an engine. In a rotary detonation engine, fuel and oxidant are typically injected separately in order to prevent flashback from occurring. When the fuel is in a liquid state, the mixing of the fuel and the oxidant is more uneven, which is not favorable for the stable operation of the rotary detonation engine. Before the fuel and the oxidant are combusted, the liquid fuel is subjected to an atomization and vaporization process, which is not favorable for rapid mixing of the fuel and the oxidant, and causes insufficient combustion, thereby affecting the performance of the rotary detonation engine. Further, with respect to liquid hydrocarbon fuels, it is difficult to trigger a detonation wave in a short time with a conventional spark plug.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a rotary detonation engine based on initiation and gas supply of a non-equilibrium plasma technology, wherein an initiation device is a pre-detonation tube, a stably propagated detonation wave is formed in the pre-detonation tube in a mode of transition from slow combustion to detonation, and then the detonation wave enters a combustion chamber of the rotary detonation engine through the pre-detonation tube to detonate a fuel and oxidant mixture in the combustion chamber. Contain plasma generator in the nozzle, fuel passes through the ionization before getting into engine combustion chamber and mixing for macromolecule becomes the micro molecule in the fuel, and this has changed combustion system's chemical balance, promotes the gas mixture, and then accelerates flame propagation, further improves combustion efficiency. Meanwhile, the mode can strengthen the combustion process, promote the fuel to burn out, reduce the heat loss of chemical incomplete combustion and reduce the emission of polluted gas.
The present invention achieves the above-described object by the following means.
A rotary detonation engine based on non-equilibrium plasma detonation and gas supply comprises a nozzle, a pre-detonation tube and an engine body;
the engine body comprises a combustion chamber outer ring, a combustion chamber inner ring, a center cone and an engine cover plate; a combustion chamber is formed between the combustion chamber outer ring and the combustion chamber inner ring, an engine cover plate is arranged at one end of the combustion chamber, and an outlet is formed at the other end of the combustion chamber; the central cone is coaxially connected with the inner ring of the combustion chamber;
the pre-explosion pipe is arranged on the outer ring of the combustion chamber, and one end of the pre-explosion pipe is communicated with the combustion chamber; the nozzle is arranged at the inlet of the pre-explosion tube; a spark plug is arranged in the pre-explosion tube; the nozzles are arranged in the combustion chamber and positioned between the joint of one end of the pre-explosion tube and the combustion chamber and the engine cover plate; a fuel flow passage and an oxidant flow passage which are not communicated with each other are arranged in the nozzle; and electrodes are arranged in the wall surface of the fuel flow channel, voltage is applied to two sides of the electrodes, and the electrodes are used for generating non-equilibrium plasma by ionizing the fuel medium in the flow channel.
Further, the nozzle includes a fuel flow passage, an oxidant flow passage, a high voltage electrode, and a ground electrode; the fuel flow channel and the oxidant flow channel are coaxially arranged; one end of the fuel flow passage arranged on the outer ring is a fuel inlet; one end of the oxidant flow channel arranged in the inner ring is an oxidant inlet; the wall surface of the fuel flow channel is respectively provided with a high-voltage electrode and a grounding electrode to form a discharge cavity; and the high-voltage electrode and the grounding electrode are respectively connected with an alternating current power supply.
Further, a first insulating shell is arranged on the inner wall surface of the fuel flow channel, a second insulating shell is arranged on the outer wall surface of the oxidant flow channel, the annular high-voltage electrode is installed in the first insulating shell, and the annular grounding electrode is installed in the second insulating shell.
Further, the fuel runner outlet and the oxidant runner outlet are both tapered in the flow direction.
Further, the pre-explosion tube comprises a gas detector, a pre-explosion chamber and a spiral barrier; the utility model discloses a preliminary knock combustion chamber, including preliminary knock chamber, preliminary knock chamber one end and combustion chamber intercommunication, the spark plug is installed to the preliminary knock chamber other end, be equipped with the spiral barrier in the preliminary knock chamber, be equipped with gas detector in the preliminary knock chamber for detect with the combustible mixture concentration in the preliminary knock chamber one end of combustion chamber intercommunication.
Further, the spiral obstacle blocking ratio is 0.4-0.5.
Furthermore, one end of the predetonation pipe is vertically arranged outside an outer ring of the engine combustion chamber, and the predetonation chamber is parallel to the outer ring of the engine combustion chamber.
Furthermore, a step which is gradually reduced along the flow direction is arranged on the pre-explosion tube.
Further, the fuel runner and the oxidant runner are distributed in an annular shape at equal intervals; the first insulating shell, the second insulating shell, the high-voltage electrode and the grounding electrode are coaxially arranged; and electromagnetic valves are respectively arranged at the inlets of the fuel flow passage and the oxidant flow passage.
Further, the first insulating shell and the second insulating shell are made of ceramic materials.
The invention has the beneficial effects that:
1. the rotary detonation engine based on the non-equilibrium plasma technology detonation and gas supply controls the gas inlet time and the ignition time of the spark plug through the electromagnetic valve, and further accurately controls the ignition time of the engine. Meanwhile, the ignition intensity of the engine can be controlled by controlling the air intake flow. The pre-explosion tube is horizontally installed, so that the size of the engine can be reduced.
2. According to the rotary detonation engine based on the initiation and gas supply of the non-equilibrium plasma technology, the non-equilibrium plasma is obtained by applying the alternating current with certain frequency and voltage between the two electrodes, so that the combustion is more sufficient, the combustion efficiency is improved, and the emission of harmful gas caused by incomplete combustion is reduced.
3. According to the rotary detonation engine based on the non-equilibrium plasma technology detonation and gas supply, the spiral barrier is arranged in the pre-detonation chamber, so that the distance and time for transition from slow combustion to detonation can be effectively shortened, the length of the pre-detonation tube is shortened, and the weight of the engine is reduced.
4. The rotary detonation engine based on the initiation and the gas supply of the non-equilibrium plasma technology strengthens detonation combustion through the tapered passageway at the rear half part of the pre-detonation chamber.
5. The rotary detonation engine based on the initiation and the gas supply of the non-equilibrium plasma technology is beneficial to improving the performance of the engine by installing the center cone at the tail part of the engine.
6. The rotary detonation engine based on non-equilibrium plasma technology detonation and gas supply promotes the mixing of fuel and oxidant through the tapered fuel chamber and oxidant chamber outlet channels.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained from the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a rotary detonation engine based on initiation and gas supply of a non-equilibrium plasma technology.
Fig. 2 isbase:Sub>A sectional viewbase:Sub>A-base:Sub>A of fig. 1.
Fig. 3 is an enlarged view of the nozzle of fig. 2.
Fig. 4 is a sectional view B-B of fig. 1.
In the figure:
1-a combustion chamber outer ring; 2-a fuel inlet; 3-engine cover plate; 4-an oxidant inlet; 5-inner ring of combustion chamber; 6-a central cone; 7-a first nozzle; 8-pre-explosion of the tube; 9-a combustion chamber; 10-an electromagnetic valve; 11-a second nozzle; 12-a first insulating shell; 13-a high voltage electrode; 14-a second insulating shell; 15-ground electrode; 16-a fuel flow channel; 17-an oxidant flow channel; 18-a gas detector; 19-a pre-detonation chamber; 20-helical obstacles; 21-spark plug.
Detailed Description
The invention will be further described with reference to the following figures and specific examples, but the scope of the invention is not limited thereto.
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "axial," "radial," "vertical," "horizontal," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
As shown in fig. 1 and 2, the rotary detonation engine based on non-equilibrium plasma initiation and gas supply comprises a nozzle, a pre-detonation tube 8 and an engine body;
the engine body comprises a combustion chamber outer ring 1, a combustion chamber inner ring 5, a center cone 6 and an engine cover plate 3; a combustion chamber 9 is formed between the combustion chamber outer ring 1 and the combustion chamber inner ring 5, an engine cover plate 3 is arranged at one end of the combustion chamber 9, and an outlet is formed at the other end of the combustion chamber 9; the central cone 6 is coaxially connected with the combustion chamber inner ring 5;
the pre-explosion tube 8 is arranged on the outer ring 1 of the combustion chamber, and one end of the pre-explosion tube 8 is communicated with the combustion chamber 9; a first nozzle 7 is arranged at the inlet of the pre-explosion tube 8; a spark plug 21 is arranged in the pre-explosion tube 8; the plurality of second nozzles 11 are uniformly distributed in the combustion chamber 9, and the plurality of second nozzles 11 are positioned between the joint of one end of the pre-explosion pipe 8 and the combustion chamber 9 and the engine cover plate 3; a fuel flow passage 16 and an oxidant flow passage 17 which are not communicated with each other are arranged in the nozzle; and electrodes are arranged in the wall surface of the fuel flow channel, voltage is applied to two sides of the electrodes, and the electrodes are used for generating non-equilibrium plasma by ionizing the fuel medium in the flow channel.
The first nozzle 7 and the second nozzle 11 have the same structure, and the second nozzle 11 is taken as an example, as shown in fig. 3. The second nozzle 11 includes a fuel flow passage 16, an oxidant flow passage 17, a high voltage electrode 13, and a ground electrode 15; the fuel flow channel 16 and the oxidant flow channel 17 are arranged coaxially; the fuel flow channel 16 and the oxidant flow channel 17 are distributed in an annular shape at equal intervals; the first insulating shell 12, the second insulating shell 14, the high-voltage electrode 13 and the grounding electrode 15 are coaxially arranged; the inlets of the fuel flow passage 16 and the oxidant flow passage 17 are respectively provided with an electromagnetic valve 10. One end of the fuel flow passage 16 arranged in the outer ring is a fuel inlet 2; one end of the oxidant flow channel 17 arranged in the inner ring is an oxidant inlet 4; the oxidant inlets 4 are positioned on the engine cover plate 3 and are distributed in an annular shape at equal intervals; the fuel inlets 2 are positioned on the outer wall surface of the combustion chamber outer ring 1 and the inner wall surface of the combustion chamber inner ring 5 and are distributed in an annular shape at equal intervals. The wall surface of the fuel flow channel 16 is respectively provided with a high-voltage electrode 13 and a grounding electrode 15 to form a discharge cavity; the high-voltage electrode 13 and the grounding electrode 15 are respectively connected with an alternating current power supply. A first insulating shell 12 is arranged on the inner wall surface of the fuel flow passage 16, a second insulating shell 14 is arranged on the outer wall surface of the oxidant flow passage 17, the annular high-voltage electrode 13 is installed in the first insulating shell 12, and the annular grounding electrode 15 is installed in the second insulating shell 14. The fuel channel 16 outlet and the oxidant channel 17 outlet are both tapered in the flow direction. The material of the first insulating shell 12 and the second insulating shell 14 is ceramic material. The working principle of the second nozzle 11 is as follows: combustible gas enters the fuel channels 16 through the two fuel inlets 2 and oxidant enters the oxidant channels 17 through the oxidant inlet 4. When a high-voltage ac voltage is applied to the annular high-voltage electrode 13 and the annular ground electrode 15, the fuel in the fuel flow passage 16 is ionized to form a non-equilibrium plasma. The fuel flow channel 16 outlet and the oxidant flow channel 17 outlet are both tapered in the flow direction to promote mixing of the fuel and oxidant.
As shown in fig. 4, the pre-detonation tube 8 comprises a gas detector 18, a pre-detonation chamber 19 and a spiral barrier 20; 19 one end of pre-detonation chamber and combustion chamber 9 intercommunication, spark plug 21 is installed to 19 other ends of pre-detonation chamber, be equipped with spiral barrier 20 in the pre-detonation chamber 19, be equipped with gas detector 18 in the pre-detonation chamber 19 for detect with the 19 one end of pre-detonation chamber of combustion chamber 9 intercommunication in combustible mixture concentration. The helical obstruction 20 blockage ratio is 0.4-0.5. One end of the predetonation pipe 8 is vertically arranged outside the outer ring 1 of the engine combustion chamber, and the predetonation chamber 19 is parallel to the outer ring 1 of the engine combustion chamber. The pre-detonation tube 8 is provided with a step which is gradually reduced along the flow direction, and the detonation combustion is enhanced by contracting a channel at the rear half part of the pre-detonation chamber 19.
The working process is as follows: first the fuel and oxidant enter the engine combustion chamber 9 and the pre-detonation chamber 19 through the first nozzle 7 and the second nozzle 11, respectively. When the gas detector 18 detects a combustible mixture at the rear of the pre-detonation chamber 19, the solenoid valve 10 on the first nozzle 7 is closed and the spark plug 21 is opened. The helical barrier 20 enhances the turbulence of the flame and shortens the time and distance that the retarded combustion transitions to knock. The detonation wave is intensified as it passes through the constricted passage of the pre-detonation chamber 19. The detonation wave then enters the engine combustion chamber 9, detonating the combustible mixture in the combustion chamber 9, eventually forming a rotating detonation wave in the combustion chamber 9.
It should be understood that although the specification has been described in terms of various embodiments, not every embodiment includes every single embodiment, and such description is for clarity purposes only, and it will be appreciated by those skilled in the art that the specification as a whole can be combined as appropriate to form additional embodiments as will be apparent to those skilled in the art.
The above-listed detailed description is only a specific description of a possible embodiment of the present invention, and they are not intended to limit the scope of the present invention, and equivalent embodiments or modifications made without departing from the technical spirit of the present invention should be included in the scope of the present invention.
Claims (10)
1. A rotary detonation engine based on non-equilibrium plasma detonation and gas supply is characterized by comprising a nozzle, a pre-detonation tube (8) and an engine body;
the engine body comprises a combustion chamber outer ring (1), a combustion chamber inner ring (5), a central cone (6) and an engine cover plate (3); a combustion chamber (9) is formed between the combustion chamber outer ring (1) and the combustion chamber inner ring (5), an engine cover plate (3) is arranged at one end of the combustion chamber (9), and an outlet is formed at the other end of the combustion chamber (9); the central cone (6) is coaxially connected with the combustion chamber inner ring (5);
the pre-explosion tube (8) is arranged on the outer ring (1) of the combustion chamber, and one end of the pre-explosion tube (8) is communicated with the combustion chamber (9); the inlet of the pre-explosion tube (8) is provided with one nozzle; a spark plug (21) is arranged in the pre-explosion tube (8); the nozzles are arranged in the combustion chamber (9) and are positioned between the joint of one end of the predetonation pipe (8) and the combustion chamber (9) and the engine cover plate (3); a fuel flow passage (16) and an oxidant flow passage (17) which are not communicated with each other are arranged in the nozzle; and electrodes are arranged in the wall surface of the fuel flow channel, voltage is applied to two sides of the electrodes, and the electrodes are used for generating non-equilibrium plasma by ionizing the fuel medium in the flow channel.
2. The rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 1, characterised in that the nozzle comprises a fuel flow channel (16), an oxidant flow channel (17), a high voltage electrode (13) and a ground electrode (15); the fuel flow channel (16) and the oxidant flow channel (17) are arranged coaxially; one end of the fuel flow channel (16) of the outer ring arrangement is a fuel inlet (2); one end of the oxidant flow channel (17) arranged in the inner ring is an oxidant inlet (4); the wall surface of the fuel flow channel (16) is respectively provided with a high-voltage electrode (13) and a grounding electrode (15) to form a discharge cavity; the high-voltage electrode (13) and the grounding electrode (15) are respectively connected with an alternating current power supply.
3. The rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 2, characterized in that a first insulating shell (12) is provided on the inner wall surface of the fuel flow passage (16), a second insulating shell (14) is provided on the outer wall surface of the oxidizer flow passage (17), the annular high voltage electrode (13) is mounted in the first insulating shell (12), and an annular ground electrode (15) is mounted in the second insulating shell (14).
4. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply in accordance with claim 2 characterised in that the fuel flow channel (16) outlet and oxidant flow channel (17) outlet are both tapered in the flow direction.
5. A rotary detonation engine based on non-equilibrium plasma detonation and gas supply according to claim 1 characterised in that the pre-detonation tube (8) includes a gas detector (18), a pre-detonation chamber (19) and a helical barrier (20); the device is characterized in that one end of the pre-detonation chamber (19) is communicated with the combustion chamber (9), a spark plug (21) is installed at the other end of the pre-detonation chamber (19), a spiral barrier (20) is arranged in the pre-detonation chamber (19), and a gas detector (18) is arranged in the pre-detonation chamber (19) and used for detecting the concentration of a combustible mixture in one end of the pre-detonation chamber (19) communicated with the combustion chamber (9).
6. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 5, characterised in that the helical barrier (20) blockage ratio is 0.4-0.5.
7. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 5 characterised in that the pre-detonation tube (8) is mounted with one end perpendicular to the outer engine combustor ring (1) and the pre-detonation chamber (19) is parallel to the outer engine combustor ring (1).
8. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 5, characterised in that the pre-detonation tube (8) is provided with a step tapering in the flow direction.
9. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 2 characterised in that the fuel flow channels (16) are equally spaced from the oxidant flow channels (17) in an annular arrangement; the first insulating shell (12), the second insulating shell (14), the high-voltage electrode (13) and the grounding electrode (15) are coaxially arranged; and the inlets of the fuel flow passage (16) and the oxidant flow passage (17) are respectively provided with an electromagnetic valve (10).
10. A rotary detonation engine based on non-equilibrium plasma initiation and gas supply according to claim 2 characterised in that the material of the first and second insulating shells (12, 14) is a ceramic material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211115266.1A CN115467760A (en) | 2022-09-14 | 2022-09-14 | Rotary detonation engine based on non-equilibrium plasma detonation and gas supply |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211115266.1A CN115467760A (en) | 2022-09-14 | 2022-09-14 | Rotary detonation engine based on non-equilibrium plasma detonation and gas supply |
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| CN115467760A true CN115467760A (en) | 2022-12-13 |
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| CN202211115266.1A Pending CN115467760A (en) | 2022-09-14 | 2022-09-14 | Rotary detonation engine based on non-equilibrium plasma detonation and gas supply |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116395132A (en) * | 2023-06-07 | 2023-07-07 | 中国空气动力研究与发展中心计算空气动力研究所 | Control structure is twisted to supersonic speed boundary layer |
-
2022
- 2022-09-14 CN CN202211115266.1A patent/CN115467760A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116395132A (en) * | 2023-06-07 | 2023-07-07 | 中国空气动力研究与发展中心计算空气动力研究所 | Control structure is twisted to supersonic speed boundary layer |
| CN116395132B (en) * | 2023-06-07 | 2023-10-03 | 中国空气动力研究与发展中心计算空气动力研究所 | Control structure is twisted to supersonic speed boundary layer |
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