CN114893324A - Double-component fuel injector for realizing two-phase rotary detonation initiation - Google Patents
Double-component fuel injector for realizing two-phase rotary detonation initiation Download PDFInfo
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- CN114893324A CN114893324A CN202210642713.2A CN202210642713A CN114893324A CN 114893324 A CN114893324 A CN 114893324A CN 202210642713 A CN202210642713 A CN 202210642713A CN 114893324 A CN114893324 A CN 114893324A
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- Prior art keywords
- fuel
- detonation
- injection
- air
- outer ring
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- 239000000446 fuel Substances 0.000 title claims abstract description 115
- 238000005474 detonation Methods 0.000 title claims abstract description 68
- 230000000977 initiatory effect Effects 0.000 title claims abstract description 17
- 238000002347 injection Methods 0.000 claims abstract description 41
- 239000007924 injection Substances 0.000 claims abstract description 41
- 239000007788 liquid Substances 0.000 claims abstract description 34
- 239000007800 oxidant agent Substances 0.000 claims abstract description 12
- 230000001590 oxidative effect Effects 0.000 claims abstract description 9
- 239000000203 mixture Substances 0.000 claims abstract description 8
- 238000000889 atomisation Methods 0.000 claims abstract description 3
- 238000002485 combustion reaction Methods 0.000 claims description 24
- 238000002474 experimental method Methods 0.000 claims description 10
- 239000007921 spray Substances 0.000 claims description 8
- 238000013461 design Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 6
- 238000002156 mixing Methods 0.000 description 6
- 238000011160 research Methods 0.000 description 4
- 239000000376 reactant Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000000644 propagated effect Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
-
- 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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
-
- 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
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention provides a double-component fuel injector for realizing two-phase rotary detonation initiation, which comprises an injection panel, an inner column, an outer ring, a centrifugal nozzle and a initiation device. The invention adopts a two-component fuel injection design, air is axially injected through an oxidant runner of an injection panel, gaseous fuel in a fuel cavity is mixed with the air at an annular seam expansion section through a fuel cavity injection hole, and liquid fuel is radially sprayed out from a centrifugal nozzle uniformly arranged on an outer ring and then mixed with a mixture of the gaseous fuel and the air; the injection locations of the gaseous and liquid fuels may be interchanged. Gaseous fuel and air are detonated to form a detonation wave, a high-temperature environment is created, good conditions are provided for atomization of liquid fuel, and successful detonation of the liquid fuel and the air is finally achieved. The invention can be used in the field of detonation propulsion.
Description
Technical Field
The invention relates to the technical field of detonation propulsion, in particular to a double-component fuel injector for realizing two-phase rotation detonation initiation.
Background
The prior aerospace power device generally adopts isobaric combustion, the technical level of the prior aerospace power device is mature, and the heat efficiency is difficult to further improve. Compared with isobaric combustion, combustible mixed gas in detonation combustion is compressed by leading shock waves to quickly reach a chemical reaction state, the flame propagation speed is up to thousands of meters per second and is close to constant volume combustion, and therefore the high-temperature detonation combustion has higher thermal cycle efficiency. The Rotary Detonation Engine (RDE) can better adapt to the flight requirements of large airspace and wide speed range, and has the advantage of continuous work by one-time ignition compared with a Pulse Detonation Engine (PDE). In recent years, rotary detonation engines have received high attention from various military and strong countries.
The research on the rotary detonation experiment based on the gaseous fuel is quite common, but in practical engineering application, liquid fuel which is convenient to store and carry is preferred. At present, the research focus of rotating detonation around liquid fuel mainly comprises efficient injection and mixing, detonation triggering, detonation modes and the like. Among other things, rotational knock triggering is directly related to the reliability of RDE operation. In addition, compared with gas phase rotary detonation, liquid fuel has poor activity and is difficult to be mixed with an oxidant quickly and well, and stable and reliable triggering of detonation waves faces a great challenge. Therefore, the realization of the detonation based on the two-phase rotating detonation wave is one of the difficult problems needing to be solved in the application of the RDE engineering.
In conclusion, aiming at the difficult problem of stable triggering of the two-phase rotary detonation wave, it is very important to design a device capable of realizing the two-phase rotary detonation initiation. The invention provides a double-component fuel injector for realizing two-phase rotary detonation initiation, which can just solve the problems.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide a double-component fuel injector for realizing two-phase rotary detonation initiation, which solves the problems of low activity of liquid fuel, difficult combustion organization of liquid fuel and air rotary detonation and the like by injecting a certain amount of gaseous fuel, and finally realizes the successful detonation of liquid fuel detonation waves. The invention can be used in the field of rotary detonation propulsion.
In order to achieve the purpose, the invention adopts the technical scheme that:
a double-component fuel injector for realizing two-phase rotary detonation initiation comprises an injection panel, an inner column, an outer ring, a centrifugal nozzle and a initiation device, and is characterized in that: the injection panel, the inner column and the outer ring are all circular shell bodies. The front end face of the injection panel, the outer wall surface of the inner column and the inner wall surface of the outer ring form an annular combustion chamber, the inner column is removed to form a hollow-cylinder combustion chamber, and the external dimension of the hollow-cylinder combustion chamber can be specifically designed according to the use environment.
Gaseous fuel and air are axially ejected through the injection panel into the front end of the combustion chamber. The liquid fuel is atomized by the centrifugal nozzles uniformly arranged on the periphery of the outer ring, and is mixed with the mixture of the gaseous fuel and the air after being radially sprayed.
The injection panel includes an oxidizer annulus flow channel and a fuel cavity. The oxidant runner is located outside the fuel cavity, and the circular seam adopts a convergent-divergent profile. The oxidant is accelerated continuously in the circular seam and reaches supersonic speed state before the circular seam outlet, and meanwhile, the pressure of the combustion chamber can be prevented from being transmitted forward. Gaseous fuel flows in through a fuel cavity positioned in the center of the injection panel and is sprayed out through fuel cavity spray holes with the hole center distance of 2-5 mm, the hole diameter of the fuel cavity spray holes is 150-250 of the outer diameter ratio of the combustion chamber, and each fuel cavity spray hole is communicated with the annular seam expansion section.
The outer ring is connected to an injection panel, and fuel is injected radially through a centrifugal nozzle. In the embodiment, the injection holes with the center distance of 15-35 mm are uniformly distributed in the circumferential direction of the outer ring, and a centrifugal nozzle is arranged in the injection holes. Because the circular seam expanding section has sudden expansion to the head part of the combustion chamber, a backflow area can be formed after the mixture of the gaseous fuel and the air enters the combustion chamber, and the mixing effect of the mixture and the liquid fuel is enhanced. The initiation device is arranged on the downstream side of the injection hole of the outer ring and can be in the form of a spark plug, a pre-detonation tube and the like.
The detonation of two-phase rotary detonation can be realized by exchanging the injection positions of the gaseous fuel and the liquid fuel. The liquid fuel is sprayed out from the spray holes of the fuel cavity and mixed with air in the annular seam expansion section. The gaseous fuel is injected radially from a centrifugal nozzle located at the outer ring and is blended with a mixture of liquid fuel and air at the exit of the annular gap. Under different mixing forms of the two-component fuel and the air, the influence of the two-component fuel and the air on the detonation triggering is explored.
Has the advantages that:
the invention provides a double-component fuel injector capable of realizing two-phase rotary detonation initiation, which can realize better mixing when injecting one or two fuels through a double-component fuel injection design. By blending a certain amount of gaseous fuel in the liquid fuel, the activity of the reactants is improved, which is beneficial to realizing the rotary detonation of the liquid fuel and air. By adopting the injection device, injection of a single fuel can be carried out so as to research the rotary detonation of the single-component fuel; the injection of the two-component fuel can be carried out to research the promotion mechanism of the gas fuel to the liquid fuel air rotary detonation initiation; the injection positions of the two-component fuel can be interchanged, and the influence of different mixing modes on the rotation detonation of the two-component fuel can be researched.
Drawings
FIG. 1 is a schematic diagram of a two-phase rotary detonation combustor injector for a two-component fuel;
FIG. 2 is a schematic view of an annular two-phase rotary detonation combustor injector for a two-component fuel;
FIG. 3 is a schematic view of a dual component fuel hollow barrel two phase rotary detonation combustor injector;
FIG. 4 is a cross-sectional view taken along line A-A of FIG. 3;
FIG. 5 is a partial enlarged view of the annular slot orifice structure of FIG. 3;
wherein, 1 is an injection panel, 2 is an oxidant flow channel, 3 is a fuel cavity, 4 is a fuel cavity spray hole, 5 is a circumferential weld, 6 is an inner column, 7 is an outer ring, 8 is a centrifugal nozzle, and 9 is a detonating device.
Detailed Description
The invention is further described with reference to the accompanying drawings and the specific implementation process.
Referring to fig. 1, the injector consists of an injection panel 1, an outer ring 7, a centrifugal nozzle 8 and an inner column 6. In operation, oxidant flows in from the oxidant flow channel 2 of the injection panel 1 and mixes with gaseous fuel sprayed from the fuel cavity 3 at the expanding section of the annular seam 5. The liquid fuel is sprayed out radially from a centrifugal nozzle 8 uniformly arranged on the outer ring 7 and is collided and mixed with the mixture sprayed out axially from the outlet of the annular gap 5.
In the present invention, the inner column 6 is installed or removed, and the annular combustion chamber or the empty can combustion chamber experiment can be performed, as shown in fig. 2 and 3, respectively. When the inner column 6 is installed, the experiment of liquid fuel and air in the annular rotary detonation combustor can be carried out; when the inner column 6 is removed, experiments of liquid fuel and air in the empty-barrel rotary detonation combustor can be performed. The annular combustion chamber is restrained by the inner column 6 and the outer ring 7, so that the shock wave reflection is enhanced, and the intensity of the rotary detonation wave is maintained and the rotary detonation wave is stably propagated. The hollow-cylinder combustion chamber is not restricted by the inner column 6, so that the heat load of the combustion chamber structure is reduced.
In the experiment, there were two embodiments according to different injection timing of the two-component fuel.
In the working scheme 1, gaseous fuel and oxidizer are injected from the injection panel 1, and liquid fuel is injected from the outer ring 7 after stable detonation is formed by detonation. After the gas fuel is injected to form the detonation wave, a high-temperature environment is created, good atomization conditions are provided for the liquid fuel, the activity of reactants is improved, and the detonation of the liquid fuel is promoted. After the gaseous fuel and the liquid fuel are supplied simultaneously, if the detonation wave is stably propagated in the combustion chamber, the flow of the gaseous fuel is gradually reduced to zero, and the supply of the liquid fuel is maintained until the experiment is finished.
In the working scheme 2, the gaseous fuel and the oxidizer are injected from the injection panel 1, the liquid fuel is injected from the outer ring 7 after the detonation forms a stable detonation wave, and the two fuels are continuously supplied until the experiment is finished. Compared with single-component fuel and air rotating detonation, the double-component fuel simultaneously participates in detonation combustion, enhances the activity of reactants and improves the intensity of detonation waves.
While the present invention has been described in detail and with reference to the drawings and the detailed description thereof, it is not intended to limit the invention to the embodiment, but it is possible for those skilled in the art to make various changes and modifications without departing from the spirit of the invention.
Claims (4)
1. A double-component fuel injector for realizing two-phase rotary detonation initiation comprises an injection panel, an inner column, an outer ring, a centrifugal nozzle and a detonation device, and is characterized in that gaseous fuel and air are injected firstly, a high-temperature environment is created after detonation is formed, good conditions are provided for liquid fuel atomization, and finally two-phase rotary detonation is successfully initiated; the air is axially injected through an oxidant flow channel of the injection panel, the gaseous fuel in the fuel cavity is mixed with the air at the annular seam expansion section through a fuel cavity injection hole, and the liquid fuel is radially injected from a centrifugal nozzle uniformly arranged on the outer ring and then is mixed with the mixture of the gaseous fuel and the air; the gas fuel and the liquid fuel can be exchanged at the injection position, namely, the liquid fuel is sprayed out from the spray hole of the fuel cavity and mixed with air at the circumferential seam expansion section; the gaseous fuel is radially injected from a centrifugal nozzle positioned at the outer ring and is mixed with a mixture of liquid fuel and air at an annular seam outlet; the fuel injection time sequence can also be changed, namely, gaseous fuel and air are injected firstly, the liquid fuel is injected after detonation, and the flow of the gaseous fuel is gradually reduced to zero after the detonation wave is stabilized; or firstly injecting gaseous fuel and air, and after detonation, keeping liquid fuel supply until the experiment is finished; the gas fuel injection time is controlled to be 0-1.1 s.
2. A two-component fuel injector for performing two-phase rotary detonation initiation according to claim 1 and further comprising: the injection panel, the outer ring and the inner column are coaxially arranged and are all a revolving body, and the outer ring and the inner column are respectively fixed on the injection panel; the fuel cavity is positioned in the center of the injection panel, and the injection holes of the fuel cavity are uniformly arranged at the positions close to the end part in the circumferential direction; the oxidant flow channel is positioned outside the fuel cavity and is an equal straight section and a circular seam section; the annular seam adopts a convergent-divergent profile, and an annular seam divergent section is connected with the fuel cavity through a jet hole; the outer ring is connected with the injection panel, and the detonating device is arranged on the downstream side of the injection hole of the outer ring.
3. A two-component fuel injector for performing two-phase rotary detonation initiation according to claim 2, characterised in that: fuel cavity spray holes are uniformly distributed in the circumferential direction of the fuel cavity, the center distance of the fuel cavity spray holes is 2-5 mm, and the diameter ratio of the hole diameter to the combustion chamber is 150-250; the center distance of the circumferentially uniformly distributed holes of the outer ring is 15-35 mm, and centrifugal nozzles are arranged inside the injection holes.
4. A two-component fuel injector for performing two-phase rotary detonation initiation according to claim 1 and further comprising: when the inner column is installed, a two-phase rotary detonation experiment of the annular combustion chamber can be carried out; when the inner column is taken down, a two-phase rotation detonation experiment of the empty barrel combustion chamber can be carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210642713.2A CN114893324A (en) | 2022-06-08 | 2022-06-08 | Double-component fuel injector for realizing two-phase rotary detonation initiation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210642713.2A CN114893324A (en) | 2022-06-08 | 2022-06-08 | Double-component fuel injector for realizing two-phase rotary detonation initiation |
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| CN114893324A true CN114893324A (en) | 2022-08-12 |
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| CN202210642713.2A Pending CN114893324A (en) | 2022-06-08 | 2022-06-08 | Double-component fuel injector for realizing two-phase rotary detonation initiation |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115478958A (en) * | 2022-08-26 | 2022-12-16 | 北京大学 | Continuous detonation engine based on liquid kerosene fuel |
| CN116697405A (en) * | 2023-05-31 | 2023-09-05 | 中国航发燃气轮机有限公司 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
| CN117738815A (en) * | 2024-02-19 | 2024-03-22 | 北京大学 | Multi-acute angle blending structure-based gas-liquid-solid multiphase hollow cylinder type continuous detonation engine |
| CN117759452A (en) * | 2024-02-21 | 2024-03-26 | 北京大学 | array type gas-liquid two-phase injection structure of continuous detonation engine |
| CN118445952A (en) * | 2024-07-03 | 2024-08-06 | 中国人民解放军空军工程大学 | Fuel injection device design method and rotary detonation engine |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115478958A (en) * | 2022-08-26 | 2022-12-16 | 北京大学 | Continuous detonation engine based on liquid kerosene fuel |
| CN116697405A (en) * | 2023-05-31 | 2023-09-05 | 中国航发燃气轮机有限公司 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
| CN116697405B (en) * | 2023-05-31 | 2024-01-19 | 中国航发燃气轮机有限公司 | Premixing rotational flow micro-mixing nozzle and combustion chamber |
| CN117738815A (en) * | 2024-02-19 | 2024-03-22 | 北京大学 | Multi-acute angle blending structure-based gas-liquid-solid multiphase hollow cylinder type continuous detonation engine |
| CN117738815B (en) * | 2024-02-19 | 2024-04-23 | 北京大学 | Multi-acute angle blending structure-based gas-liquid-solid multiphase hollow cylinder type continuous detonation engine |
| CN117759452A (en) * | 2024-02-21 | 2024-03-26 | 北京大学 | array type gas-liquid two-phase injection structure of continuous detonation engine |
| CN117759452B (en) * | 2024-02-21 | 2024-04-26 | 北京大学 | Array type gas-liquid two-phase injection structure of continuous detonation engine |
| CN118445952A (en) * | 2024-07-03 | 2024-08-06 | 中国人民解放军空军工程大学 | Fuel injection device design method and rotary detonation engine |
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Application publication date: 20220812 |