CN114440258A - Coaxial injection device of supersonic combustion chamber - Google Patents
Coaxial injection device of supersonic combustion chamber Download PDFInfo
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- CN114440258A CN114440258A CN202210025735.4A CN202210025735A CN114440258A CN 114440258 A CN114440258 A CN 114440258A CN 202210025735 A CN202210025735 A CN 202210025735A CN 114440258 A CN114440258 A CN 114440258A
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- supersonic
- air injection
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- fuel injector
- fuel
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- 238000002347 injection Methods 0.000 title claims abstract description 43
- 239000007924 injection Substances 0.000 title claims abstract description 43
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 18
- 239000000446 fuel Substances 0.000 claims abstract description 85
- 230000008859 change Effects 0.000 claims abstract description 10
- 230000003247 decreasing effect Effects 0.000 claims abstract description 3
- 239000003638 chemical reducing agent Substances 0.000 claims description 7
- 230000006698 induction Effects 0.000 claims 1
- 238000002156 mixing Methods 0.000 description 9
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000006641 stabilisation Effects 0.000 description 5
- 238000011105 stabilization Methods 0.000 description 5
- 230000003993 interaction Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 229940090046 jet injector Drugs 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
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Classifications
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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
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N1/00—Regulating fuel supply
- F23N1/02—Regulating fuel supply conjointly with air supply
- F23N1/025—Regulating fuel supply conjointly with air supply using electrical or electromechanical 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
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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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The invention discloses a coaxial injection device of a supersonic combustion chamber, which comprises a supersonic air injection hole and an annular fuel injector, wherein the supersonic air injection hole is used for carrying out air injection, the annular fuel injector is arranged on the outer side of the supersonic air injection hole and is used for injecting fuel, the supersonic air injection hole and the annular fuel injector are coaxial, the supersonic air injection hole comprises a first straight line section with equal sectional area and a first gradual change section with sequentially increased sectional area, the annular fuel injector comprises a second straight line section with equal sectional area and a second gradual change section with sequentially decreased sectional area, the supersonic air injection hole is used for accelerating air injection from sonic velocity to supersonic velocity, and the annular fuel injector is used for accelerating fuel from subsonic velocity to sonic velocity. The invention can realize the partial premixing of fuel and air in a short distance, and further establish turbulent partial premixed flame with supersonic speed at the downstream, thereby obviously improving the flame stability boundary of the engine.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a coaxial injection device of a supersonic combustion chamber.
Background
The hypersonic aircraft has the advantages of high speed, strong maneuverability and the like, and has wide application prospect in military and civil fields. As a core power device, the air-breathing ramjet engine does not need to carry an oxidant, and generates thrust by absorbing the chemical reaction between air in the air and fuel, so that higher specific impact performance can be realized. It is worth noting that the very short residence time of the supersonic gas flow in the combustion chamber (in the order of millimeters) coupled with the strong interaction of shock waves, high turbulence intensity and chemical reactions, which under extreme conditions makes reliable ignition and stable combustion difficult, places high demands on the design and optimization of fuel injection and flame stabilization schemes.
Jet injection along the vertical direction of the wall surface is the most promising fuel supply scheme at present, and the jet injection device is simple in structure and can better realize rapid mixing of fuel and air. In order to solve the ignition and flame stabilization problems under the low mach flight condition, a low-speed backflow region is required to be arranged in a supersonic flow field, and a typical scheme comprises a backward step, a support plate, a concave cavity and the like. The backward step can generate a smaller backflow area, and the flame stabilizing capability is relatively limited; for incoming flow with relatively low total temperature, the support plate has more advantages in flame stabilizing capability and has the defect of generating a lot of total pressure loss; the cavity coupling upstream wall jet injection is the most common combustion organization mode at present, combining two aspects of flame stabilization and global performance. Despite the strong interaction of the jet with the cavity, the fuel delivered into the cavity by entrainment is generally limited. If the equivalence ratio of the upstream fuel is below a certain threshold, the jet flame will also be blown out; conversely, the global equivalence ratio is too high, so that thermal congestion of the flow field can occur, and even rich flame-out can be induced. Considering a supersonic combustor with a fixed geometry, there is a range of equivalence ratios for flame stabilization. In order to design a combustion chamber with more robust operation performance, it is necessary to widen the upper and lower boundaries of stable operation of the engine as much as possible. The depth, the size, the trailing edge angle and the like of the concave cavity are changed, so that the combustion performance of a specific state point can be improved to a certain extent, but the current problem is difficult to solve fundamentally. The air-breathing ramjet engine does not carry fuel, the fuel is not premixed with the captured air, and the working performance of the air-breathing ramjet engine is more dependent on the injection mixing scheme of the fuel, so that the overall performance of the engine is expected to be greatly improved by designing a brand-new injection device.
The prior wall fuel jet injection devices are of a very simple configuration, usually a circular orifice or array. A pressure reducing device and a control valve are arranged at the downstream of the fuel storage tank and are connected with the sonic nozzle through a thin pipeline, and fuel is directly injected vertically along the vertical direction of the wall surface and enters a combustion chamber. The cylindrical fuel jet interacts with supersonic air incoming flow to induce opposite-direction-of-rotation flow vortex pairs and windward shear vortices, entrainment causes mixing of fuel and air, and turbulence pulsation in the upstream boundary layer can further promote the mixing process.
The wall jet injector is of a very simple design and consists of a collecting chamber and a circular collecting chamber. However, fuel and air are not premixed, and the mixing of the two relies on the interaction of the jet with the supersonic air flow, so that it is very difficult to achieve adequate mixing within a limited feature size. In spite of the presence of the re-entrant flame stabilization device, turbulent jet combustion still exhibits very significant non-premixed characteristics, the chemical reaction rate is mainly dependent on the mixing rate, and the combustion intensity and efficiency are low. There is a great safety risk if the fuel is mixed well with the air in advance.
Disclosure of Invention
The invention aims to provide a coaxial injection device of a supersonic combustion chamber, which overcomes the defects in the prior art.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
the coaxial injection device of the supersonic combustion chamber comprises a supersonic air injection hole and an annular fuel injector, wherein the supersonic air injection hole is used for carrying out air injection, the annular fuel injector is arranged on the outer side of the supersonic air injection hole and used for injecting fuel, the supersonic air injection hole and the annular fuel injector are coaxial, the supersonic air injection hole comprises a first straight line section with equal sectional area and a first gradual change section with sequentially increased sectional area, the annular fuel injector comprises a second straight line section with equal sectional area and a second gradual change section with sequentially decreased sectional area, the supersonic air injection hole is used for accelerating the air injection from sonic velocity to supersonic velocity, and the annular fuel injector is used for accelerating the fuel from subsonic velocity to sonic velocity.
Furthermore, the inlet end of the supersonic air jet hole is connected with an air inlet channel of the air suction type ramjet engine through a first channel, and a flow controller is arranged on the first channel.
Furthermore, the input end of the annular fuel injector is connected with a high-pressure fuel cylinder through a second channel, and the second channel is sequentially provided with an electromagnetic valve and a pressure reducer.
Further, the device also comprises a controller connected with the flow controller, the electromagnetic valve and the pressure reducer, and a computer connected with the controller.
Further, the air jet hole inlet area of the annular fuel injector is calculated by the formula:
in the formula, T0,airIs the total pressure, p0,airFor total temperature, C is 0.04042.
Further, the calculation formula of the annular fuel injector is as follows:
in the formula, Mo,airThe exit mach number, y denotes the specific heat ratio.
Further, the calculation formula of the outlet cross-sectional area of the annular fuel injector is as follows:
in the formula, T0,fuelTotal temperature of fuel at inlet, P0,fuelIs the sum of the fuel at the inletAnd (6) pressing.
Compared with the prior art, the invention has the advantages that: the invention can realize partial premixing of fuel and air in a short distance, further establish turbulent partial premixed flame of supersonic velocity at downstream, obviously promote the flame stability boundary of the engine, the air jet in the invention is a small part of flow separated from the air inlet of the engine, will not change the global equivalence ratio of the air-breathing ramjet, further under the situation of keeping the fuel flow unchanged, the flow of controlling the air can dynamically adjust the air mixing proportion, and further control the intensity of chemical reaction.
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 described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the coaxial injector of the supersonic combustor of the present invention;
FIG. 2 is a control schematic of the coaxial injection means of the supersonic combustor of the present invention.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, and the scope of the present invention will be more clearly and clearly defined.
Referring to fig. 1 and 2, the present embodiment discloses a coaxial injection device of a supersonic combustor, which includes a supersonic air nozzle hole 1 for performing air jet and an annular fuel injector 2 disposed outside the supersonic air nozzle hole 1 and used for injecting fuel, wherein the supersonic air nozzle hole 1 and the annular fuel injector are coaxial 2, an inner profile of the supersonic air nozzle hole 1 gradually expands, an annular profile of the annular fuel injector 2 gradually contracts, the supersonic air nozzle hole 1 is used for accelerating the air jet from sonic velocity to supersonic velocity, the annular fuel injector 2 is used for accelerating the fuel from subsonic velocity to sonic velocity, and the area ratio of an inlet and an outlet of the annular fuel injector is designed to ensure that the subsonic fuel jet finally reaches sonic velocity. The ingenious jet flow of the supersonic air jet hole 1 can ensure that the jet flow speed is higher, the shearing action between the jet flow speed and the jet flow speed is very strong, and the jet flow speed has enough penetration depth.
Specifically, the supersonic air nozzle 1 comprises a first straight line segment 10 with the same sectional area and a first gradual change segment 11 with the gradually-increased sectional area, and the annular fuel injector 2 comprises a second straight line segment 20 with the same sectional area and a second gradual change segment 21 with the gradually-decreased sectional area.
In this embodiment, the inlet end of supersonic air nozzle hole 1 is connected with air inlet channel 4 of air-breathing ramjet through first channel, air is caught from the air inlet channel, the global equivalence ratio of air-breathing ramjet cannot be changed, flow controller 5 is arranged on the first channel, and flow controller 5 can dynamically adjust the air flow, so that the change of the fuel-air ratio is realized, the combustion efficiency can be adjusted under the condition that the fuel is not changed, and the real-time maneuvering capability of the system is improved.
In this embodiment, the input end of the annular fuel injector 2 is connected to the high-pressure fuel cylinder 3 through a second channel, and the second channel is sequentially provided with an electromagnetic valve 6 and a pressure reducer 7. The parameters of the fuel jet flow can be determined according to the actual design working condition, and the actual parameters can be controlled by the fuel high-pressure gas cylinder, the pressure reducer, the electromagnetic valve and the like.
In order to realize the automatic control function, the present embodiment further includes a controller 8 connected to the flow controller 5, the solenoid valve 6, and the pressure reducer 7, and a computer 9 connected to the controller 8.
This embodiment is in contrast to the arrangement employed in conventional low velocity combustors where the air jets are located at supersonic air jet orifices and fuel is injected from an external annular fuel injector. The inner molded surface of the supersonic air jet hole is gradually expanded, so that the air jet is gradually accelerated to the supersonic speed from the sound speed, the subsonic fuel jet is also finally accelerated to the sound speed state, and finally the coaxial fuel/air injection with the external sound speed and the internal supersonic speed is formed.
In order to better implement the present invention, the parameter design in the present invention is further described below.
The area and inlet parameters of the injectors are designed according to the air and fuel flow, and the air flow is known
Total temperature and total pressure are respectively p0,airAnd T0,air. When the inlet Mach number Mi,airOutlet mach number M ═ 1o,airAccording to the flow formula, the area of the inlet of the air jet hole can be calculated as follows:
where C is 0.04042, the cross-sectional area of the outlet of the air line is:
where y denotes the specific heat ratio, the cross-sectional area of the outlet of the annular fuel injector can be calculated using the same concept:
from this, the area of the inlet of the annular fuel injector, in which T is calculated0,fuelTotal temperature of fuel at inlet, P0,fuelIs the total pressure of the fuel at the inlet.
The invention mainly aims to improve the mixing efficiency of fuel and air, establish turbulent premixed flame with stable concave cavity at the downstream, and further expand the flame stable boundary of the concave cavity combustion chamber; by adjusting the proportion of fuel and air, the dynamic adjustment of chemical reaction intensity is realized, and the purpose of controlling combustion efficiency and thrust in the process of maneuvering flight is achieved.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, various changes or modifications may be made by the patentees within the scope of the appended claims, and within the scope of the invention, as long as they do not exceed the scope of the invention described in the claims.
Claims (7)
1. The coaxial injection device of the supersonic combustion chamber is characterized by comprising a supersonic air injection hole and an annular fuel injector, wherein the supersonic air injection hole is used for carrying out air injection, the annular fuel injector is arranged on the outer side of the supersonic air injection hole and used for injecting fuel, the supersonic air injection hole and the annular fuel injector are coaxial, the supersonic air injection hole comprises a first straight line section with equal sectional area and a first gradual change section with sequentially increased sectional area, the annular fuel injector comprises a second straight line section with equal sectional area and a second gradual change section with sequentially decreased sectional area, the supersonic air injection hole is used for accelerating air injection from sonic velocity to supersonic velocity, and the annular fuel injector is used for accelerating fuel from subsonic velocity to sonic velocity.
2. The coaxial injector of a supersonic combustor according to claim 1, wherein the inlet end of said supersonic air jet is connected to the intake port of an induction ramjet engine through a first channel, said first channel having a flow controller.
3. Coaxial injector for supersonic combustors according to claim 2 characterized in that the input of the annular fuel injector is connected to the fuel high pressure cylinder through a second channel, which in turn is provided with a solenoid valve and a pressure reducer.
4. The coaxial injection device of a supersonic combustor according to claim 3, further comprising a controller connected to said flow controller, solenoid valve and pressure reducer, and a computer connected to said controller.
5. The coaxial injection device of a supersonic combustor according to claim 1, wherein the air jet hole inlet area of said annular fuel injector is calculated as:
in the formula, T0,airIs the total pressure, p0,airFor total temperature, C is 0.04042.
6. Coaxial injector for supersonic combustor according to claim 1 characterized by the fact that the calculation formula of the annular fuel injector is:
in the formula, Mo,airThe exit mach number, y denotes the specific heat ratio.
7. Coaxial injector of a supersonic combustor according to claim 1, characterized in that the cross-sectional area of the outlet of said annular fuel injector is calculated as:
in the formula, T0,fuelTotal temperature of fuel at inlet, P0,fuelIs the total pressure of the fuel at the inlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210025735.4A CN114440258A (en) | 2022-01-11 | 2022-01-11 | Coaxial injection device of supersonic combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210025735.4A CN114440258A (en) | 2022-01-11 | 2022-01-11 | Coaxial injection device of supersonic combustion chamber |
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| CN114440258A true CN114440258A (en) | 2022-05-06 |
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| CN202210025735.4A Pending CN114440258A (en) | 2022-01-11 | 2022-01-11 | Coaxial injection device of supersonic combustion chamber |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115682032A (en) * | 2022-11-03 | 2023-02-03 | 西北工业大学 | Novel polycyclic fuel support plate injector |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102226533A (en) * | 2011-05-26 | 2011-10-26 | 中国人民解放军国防科学技术大学 | High-speed premixed flame furnace for supersonic burning research |
| CN108603658A (en) * | 2016-03-15 | 2018-09-28 | 杰伊·凯勒 | Non-premixed swirl burner tip and combustion strategy |
| EP3434883A2 (en) * | 2017-07-25 | 2019-01-30 | United Technologies Corporation | Low emissions combustor assembly for gas turbine engine |
| CN109931628A (en) * | 2019-03-27 | 2019-06-25 | 北京理工大学 | It is a kind of based on the ring cavity eddy flow of the combustion chamber RDE to spray structure |
-
2022
- 2022-01-11 CN CN202210025735.4A patent/CN114440258A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102226533A (en) * | 2011-05-26 | 2011-10-26 | 中国人民解放军国防科学技术大学 | High-speed premixed flame furnace for supersonic burning research |
| CN108603658A (en) * | 2016-03-15 | 2018-09-28 | 杰伊·凯勒 | Non-premixed swirl burner tip and combustion strategy |
| EP3434883A2 (en) * | 2017-07-25 | 2019-01-30 | United Technologies Corporation | Low emissions combustor assembly for gas turbine engine |
| CN109931628A (en) * | 2019-03-27 | 2019-06-25 | 北京理工大学 | It is a kind of based on the ring cavity eddy flow of the combustion chamber RDE to spray structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115682032A (en) * | 2022-11-03 | 2023-02-03 | 西北工业大学 | Novel polycyclic fuel support plate injector |
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