CN115234944A - Swirl combined ramjet combustion chamber with stable flame - Google Patents
Swirl combined ramjet combustion chamber with stable flame Download PDFInfo
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- CN115234944A CN115234944A CN202210827881.9A CN202210827881A CN115234944A CN 115234944 A CN115234944 A CN 115234944A CN 202210827881 A CN202210827881 A CN 202210827881A CN 115234944 A CN115234944 A CN 115234944A
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 92
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 40
- 239000000446 fuel Substances 0.000 claims description 19
- 239000003921 oil Substances 0.000 claims description 12
- 239000000295 fuel oil Substances 0.000 claims description 11
- 238000002347 injection Methods 0.000 claims description 10
- 239000007924 injection Substances 0.000 claims description 10
- 230000009467 reduction Effects 0.000 claims description 5
- 239000003595 mist Substances 0.000 claims description 4
- 238000010008 shearing Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 33
- 239000000243 solution Substances 0.000 description 6
- 239000002737 fuel gas Substances 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 239000008358 core component Substances 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
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000010791 quenching Methods 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
- F23R3/42—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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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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
- F23R3/26—Controlling the air 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
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
Abstract
The invention provides a swirl combined ramjet combustion chamber with stable flame, which comprises a combustion chamber shell and a central body coaxially arranged in the combustion chamber shell, wherein an annular cavity formed between the combustion chamber shell and the central body is a combustion chamber; along the propagation direction of the air incoming flow, the combustion chamber is sequentially divided into an air inlet section, a combustion cavity and a tail nozzle; a first-stage flame stabilizing device is locally arranged in the air inlet section, and a second-stage flame stabilizing structure is arranged at the downstream of the first-stage flame stabilizing device; the first stage flame stabilizing device consists of a diffuser, a swirler and a venturi which are connected in sequence, the second stage flame stabilizing structure is a sudden expansion or concave cavity arranged behind the air inlet section, and the ignition device is arranged at the downstream of the sudden expansion or in the concave cavity. The local rotational flow and sudden expansion or concave cavity combination mode provided by the invention can obviously improve the stable flame combustion range on the basis of keeping lower total pressure loss so as to widen the working range of the ramjet.
Description
Technical Field
The invention relates to the field of ramjet engines, in particular to a swirl combined flame stabilized ramjet engine combustion chamber.
Background
The existing power systems available for supersonic flight are mainly of two main types: rocket engines and air-breathing engines, which in turn include turbojet engines and ramjet engines. The rocket engine has the defects of low specific impulse, poor economical efficiency and short action time due to the need of carrying all propellants. The turbojet technology is mainly used for aviation flight with the Mach number below 2, but due to the limitation of the temperature tolerance of the turbine, the further increase of the flight speed can cause the sharp reduction of the performance, so the flight speed and the flight altitude of the turbojet are respectively limited to Mach numbers 3 and 30km. The ramjet engine, as an air-breathing engine, can absorb oxygen from the air, and has a high specific impulse performance as a turbojet engine. In addition, the ramjet uses the flow energy to compress the trapped air, does not need rotating parts such as a gas compressor, a turbine and the like, and only comprises three parts, namely an air inlet channel, a combustion chamber and a tail nozzle. Compared with a turbojet engine, the structure of the engine is greatly simplified, and the cost of the engine is obviously reduced. The thrust generated by the ramjet depends on the air inlet speed, has good performance when the Mach number is more than 3, and is suitable for high-speed flight.
The combustion chamber is a core component of a ramjet engine and the ramjet engine combustion process includes ignition, flame propagation, and flame stabilization processes. After the mixed gas flow is ignited, the flame spreads to the whole main combustion area so as to maintain the stable combustion of the main combustion area. However, because the incoming flow speed of the ramjet is very high and far greater than the propagation speed of the flame, the flame is very easy to quench, and the flame stabilizing device plays a crucial role. The working principle of the flame stabilizing device is that a low-speed flow area is established in a high-speed flow field in a combustion chamber, so that the speed of air flow in the low-speed flow area is reduced, and flame can be always remained in the low-speed flow area to serve as a 'Changming lamp' as a stable ignition source.
The flame stabilizing device of the existing ramjet combustion chamber mainly comprises two forms of a bluff body (such as a V-shaped groove) and a backward step (such as a sudden expansion), and a rotational flow flame stabilizer widely adopted in a turbine engine is not applied to the ramjet. The reason is that the prior ramjet has single purpose and narrow working range, and can meet the requirements by adopting a sudden expansion or a V-shaped groove. However, with the ever expanding range of applications for ramjet engines, higher demands are being made on the operating stability and the overall pressure loss of the flame holder. The blockage of the bluff body is large, and the flame stabilizing range of the backward step is limited, so that the two forms are difficult to meet the working requirements of low pressure loss and wide-range flame stabilization, and the problem to be solved in the field is urgently needed.
Disclosure of Invention
Aiming at the defects of the ramjet combustion chamber technology, the invention provides a ramjet combustion chamber with stable flame and combined rotational flow. The invention combines the local distributed cyclone and the sudden expansion or the concave cavity, integrates the advantages of the two, and has the outstanding characteristics of high combustion efficiency, wide stable range and low pressure loss.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
a ramjet combustion chamber with swirl combination and stable flame comprises a combustion chamber shell and a central body coaxially arranged in the combustion chamber shell, wherein an annular cavity formed between the combustion chamber shell and the central body is a combustion chamber;
the combustion chamber is divided into an air inlet section, a combustion cavity and a tail nozzle along the air inflow direction in sequence; a first-stage flame stabilizing device is locally arranged in the air inlet section, and a second-stage flame stabilizing structure is arranged at the downstream of the first-stage flame stabilizing device;
the first stage flame stabilizing device consists of a diffuser, a swirler and a venturi which are connected in sequence, the second stage flame stabilizing structure is a sudden expansion or a concave cavity arranged behind the air inlet section, and the ignition device is arranged at the downstream of the sudden expansion or in the concave cavity;
the high-speed air entering the diffuser enters the swirler after being subjected to diffuser and speed reduction of the diffuser to form swirl air, the center of the swirler is provided with an oil injection hole for injecting fuel oil, the swirl air and the fuel oil injected by the oil injection hole are fully mixed in the outlet of the swirler and the venturi tube to form premixed gas, the premixed gas is ignited by the ignition device at the sudden expansion downstream or in the concave cavity, and the flame forms a stable ignition source in the sudden expansion downstream or in the concave cavity.
Furthermore, the two first-stage flame holders are symmetrically arranged in the annular air inlet section by taking the central axis of the central body as a symmetry axis.
Furthermore, in the first-stage flame stabilizing device, the diffuser inlet is flush with the inlet of the air inlet section.
Further, the ignition device is arranged on the central section where the two first-stage flame holders are located.
Furthermore, the second-stage flame stabilizing structure is a step-shaped sudden expansion arranged at the joint of the air inlet section and the combustion cavity, and an annular backward step is formed at the joint of the air inlet section and the combustion cavity.
Further, the distance between the ignition device and the wall surface of the sudden expansion is d-1.5 d, wherein d is the height of a flow passage of the air inlet section.
Further, the second stage flame holding structure is an annular concave cavity arranged in the combustion chamber.
Further, the ignition device is spaced from the front wall surface of the cavity by a distance of 0.75l 2 Wherein l is 2 Is the length of the cavity, /) 2 The value range of (d) is 0.5 d-1.5 d, and d is the height of the flow channel of the gas inlet section.
Furthermore, the swirler is an inner-outer two-stage swirler, the inner swirler is used for shearing and crushing oil mist to form a backflow area, and the outer swirler is used for improving axial uniformity of the outlet.
Furthermore, fuel oil/gas spray holes are uniformly distributed at the outlet of the air inlet section of the combustion chamber in the circumferential direction, and are arranged in a direction perpendicular to the air inflow direction, and main fuel oil/gas required by combustion is provided for the combustion cavity through the fuel oil/gas spray holes.
The invention has the following beneficial effects:
1. the arrangement and distribution of the swirlers are critical, and if the swirlers occupy the inlet of the whole full-ring combustion chamber, a large total pressure loss is caused, which cannot be borne by the combustion chamber of the ramjet engine. In the invention, because the swirlers are only distributed at the part of the inlet of the combustion chamber, the stable combustion range of flame can be greatly widened on the premise of controlling the total pressure loss, so that the ramjet can work in a wider range.
2. The diffuser provided by the invention can reduce the air flow rate and is easy to ignite after the swirler.
3. The swirler and the venturi tube provided by the invention can effectively enhance oil-gas mixing, further improve ignition performance and combustion efficiency, and the formed backflow zone can also improve flame stability.
4. The local rotational flow and sudden expansion or concave cavity combination mode provided by the invention can obviously improve the stable flame combustion range on the basis of keeping lower total pressure loss so as to widen the working range of the ramjet.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments or the prior art of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for the ordinary skill in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is an axial cross-sectional view of a ramjet combustion chamber with a combination swirl and flare in accordance with an embodiment of the present invention;
FIG. 2 is an axial cross-sectional view of a ramjet combustion chamber of a swirl and bowl combination in accordance with an embodiment of the present invention;
FIG. 3 is a partial axial cross-sectional view of a portion of a flame holding device with a swirl and cavity combination according to an embodiment of the invention.
The symbols in the figure represent:
1. a combustion chamber housing; 2. a central body; 3. an air inlet section; 4. a diffuser; 5. a swirler; 6. a venturi; 7. sudden expansion; 8. a concave cavity; 9. an ignition device; 10. a combustion chamber; 11. a tail nozzle.
The objects, features, and advantages of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all directional indicators (such as upper, lower, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Referring to fig. 1, an embodiment provides a swirl-combined flame-stabilized ramjet combustor, which includes a combustor casing 1 and a central body 2 coaxially disposed in the combustor casing 1, wherein an annular cavity formed between the combustor casing 1 and the central body 2 is a combustor.
Along the air inflow direction, the combustion chamber is divided into an air inlet section 3, a combustion cavity 10 and a tail nozzle 11 in sequence; a first-stage flame stabilizing device is locally arranged in the air inlet section 3, and a second-stage flame stabilizing structure is arranged at the downstream of the first-stage flame stabilizing device.
The first-stage flame stabilizing device is composed of a diffuser 4, a swirler 5 and a venturi tube 6 which are connected in sequence, the second-stage flame stabilizing structure is a sudden expansion 7 arranged behind the air inlet section 3, and an ignition device 9 is arranged at the downstream of the sudden expansion 7. Specifically, the second-stage flame stabilizing structure is a step-shaped sudden expansion arranged at the joint of the air inlet section 3 and the combustion cavity 10, and an annular backward step is formed at the joint of the air inlet section and the combustion cavity.
In the embodiment shown in FIG. 1, to reduce overall pressure losses, it is different from the integral swirl intake that is common in turbine engines. As shown in figure 1, the first-stage flame holders are two, and the two first-stage flame holders are symmetrically arranged in the annular air inlet section 3 by taking the central shaft of the central body as a symmetry axis. The inlet of the diffuser 4 in the first stage flame holder is flush with the inlet of the inlet section 3 of the combustion chamber. The ignition device 9 is arranged on the central section where the two first-stage flame-stabilizing devices are arranged, as shown in fig. 1, two ignition devices are arranged, the two ignition devices are symmetrically arranged by taking the central body central shaft as a symmetry axis, the two ignition devices and the two first-stage flame-stabilizing devices are arranged on the same central section, and the two first-stage flame-stabilizing devices respectively correspond to one ignition device. The first-stage flame stabilizing device and the ignition device 9 are arranged in the embodiment in such a way that two groups of flame stabilizing devices and ignition devices are arranged, are vertically symmetrical, have small blocking ratio and have the circulating flow not more than 2 percent of the total flow.
After the high-speed air comes into the air inlet section of the combustion chamber, a part of the high-speed air comes into the first-stage flame stabilizing device which is locally distributed in the air inlet channel. Specifically, a part of high-speed air comes to flow into the diffuser 4, and the high-speed air entering the diffuser 4 flows through the diffuser 4 to be subjected to pressure expansion and speed reduction, so that the fuel gas is easy to ignite after the swirler 5. The high-speed incoming air after being diffused and reduced in speed by the diffuser 4 enters the swirler 5 and is deflected under the flow guiding action of the swirl vanes in the swirler 5 to form swirl air. Specifically, the swirler 5 is an inner-outer two-stage swirler, and the inner swirler is used for shearing and crushing oil mist to form a backflow area; the outer swirler serves to improve outlet axial uniformity. The number of the swirl vanes of the swirler 5 is reasonably between 8 and 14. And the center of the swirler 5 is provided with an oil injection hole for injecting fuel oil, and the swirling air and the fuel oil injected by the oil injection hole are fully mixed in the outlet of the swirler and the venturi tube 6 to form premixed gas, so that the ignition performance and the combustion efficiency are improved. The premixed gas is ignited by the ignition device 9 downstream of the flare where the flame forms a stable ignition source. The venturi 6 also has the function of preventing flashback.
Fuel/gas jet holes (not shown in figure 1) are uniformly distributed in the circumferential direction at the outlet of the air inlet section 3 of the combustion chamber, the fuel/gas jet holes are arranged in the direction perpendicular to the air inflow direction, main fuel/gas required by combustion is provided for the combustion chamber through the fuel/gas jet holes, namely the main fuel/gas is jetted out from the fuel/gas jet holes in a transverse flow direct injection mode, so that the oil-gas mixing degree is improved. The flame behind the venturi 6 ignites the main fuel/gas after the flare 7, and because the flare 7 is circular, the flame spreads rapidly and forms a stable ignition source.
Preferably, the height of the flow path of the air inlet section 3 is d, and the distance from the outlet of the venturi tube 6 to the sudden expansion 7 is l 1 ，l 1 The value range of (a) is-0.5 d, and when the value is negative, the venturi 6 extends from the air inlet section 3 to the rear of the sudden expansion 7.
The position of the ignition device 9 is determined by the return flow zone formed by the first stage flame holding device. The ignition device 9 is not suitable to extend too far into the combustion chamber, otherwise the head part of the ignition device is wetted by fuel to influence ignition; it is not suitable for too shallow, and the ignition is not easy at too shallow wall surface. The ignition device 9 should be located at the edge of the recirculation zone, the combustion concentration distribution is proper, and the gas flow velocity is low. The length of the ignition device 9 projecting into the combustion chamber is therefore 10mm here. In the embodiment shown in fig. 1, when the combination of swirling flow and sudden expansion is adopted, the distance between the ignition device and the wall surface of the sudden expansion is preferably d-1.5 d, so that the ignition device can meet the requirement that the ignition device is positioned at the edge of a backflow region, the combustion concentration distribution is proper, the gas flow speed is low, successful ignition is easy, and a stable ignition source is formed.
Referring to fig. 2 and 3, another embodiment provides a swirl-combined flame-stabilized ramjet combustor, which includes a combustor casing 1 and a central body 2 coaxially disposed in the combustor casing 1, wherein an annular cavity formed between the combustor casing 1 and the central body 2 is a combustor.
Along the air inflow direction, the combustion chamber is divided into an air inlet section 3, a combustion cavity 10 and a tail nozzle 11 in sequence; a first-stage flame stabilizing device is locally arranged in the air inlet section 3, and a second-stage flame stabilizing structure is arranged at the downstream of the first-stage flame stabilizing device.
The first-stage flame stabilizing device is composed of a diffuser 4, a swirler 5 and a venturi tube 6 which are connected in sequence, the second-stage flame stabilizing structure is a concave cavity 8 arranged behind the air inlet section 3, and an ignition device 9 is arranged in the concave cavity 8. The antetheca of cavity 8 is the cavity antetheca, and the cavity antetheca is located the junction of section 3 and burning chamber 10 that admits air, and the cavity begins from the junction of section 3 and burning chamber 10 that admits air promptly, forms the echelonment at the junction of section 3 and burning chamber 10 and expands suddenly, forms annular backward step at the junction of section and burning chamber that admits air.
In the embodiment shown in FIG. 2, to reduce overall pressure losses, it is different from the integral swirl intake that is common in turbine engines. As shown in fig. 2, the first-stage flame holders are two, and the two first-stage flame holders are symmetrically arranged in the annular air inlet section 3 by taking the central axis of the central body as a symmetry axis. The inlet of the diffuser 4 in the first stage flame holder is flush with the inlet of the inlet section 3 of the combustion chamber. The ignition device 9 is arranged on the central section where the two first-stage flame-stabilizing devices are arranged, as shown in fig. 1, two ignition devices are arranged, the two ignition devices are symmetrically arranged by taking the central body central shaft as a symmetry axis, the two ignition devices and the two first-stage flame-stabilizing devices are arranged on the same central section, and the two first-stage flame-stabilizing devices respectively correspond to one ignition device. The first stage flame stabilizer and the ignition device 9 are arranged in the embodiment in such a way that two groups of flame stabilizers and ignition devices are arranged, are symmetrical up and down, have small blocking ratio and have the flow rate not exceeding 2 percent of the total flow rate.
After the high-speed air comes into the air inlet section of the combustion chamber, a part of the high-speed air comes into the first-stage flame stabilizing device which is locally distributed in the air inlet channel. Specifically, a part of high-speed air comes to flow into the diffuser 4, and the high-speed air entering the diffuser 4 flows through the diffuser 4 to be subjected to pressure expansion and speed reduction, so that the fuel gas is easy to ignite after the swirler 5. The high-speed incoming air after being diffused and reduced in speed by the diffuser 4 enters the swirler 5 and is deflected under the flow guiding action of the swirl vanes in the swirler 5 to form swirl air. Specifically, the swirler 5 is an inner-outer two-stage swirler, and the inner swirler is used for shearing and crushing oil mist to form a backflow area; the outer swirler serves to improve outlet axial uniformity. The number of the swirl vanes of the swirler 5 is reasonably between 8 and 14. And the center of the swirler 5 is provided with an oil injection hole for injecting fuel oil, and the swirling air and the fuel oil injected by the oil injection hole are fully mixed in the outlet of the swirler and the venturi tube 6 to form premixed gas, so that the ignition performance and the combustion efficiency are improved. The premixed gas is ignited by the ignition device 9 in the cavity 8, and the flame forms a stable ignition source in said cavity 8. The venturi 6 also has the function of preventing flashback.
Fuel/gas jet holes (not shown in fig. 2) are uniformly distributed in the circumferential direction at the outlet of the air inlet section 3 of the combustion chamber, the fuel/gas jet holes are arranged in the direction perpendicular to the air inflow direction, main fuel/gas required by combustion is provided for the combustion chamber through the fuel/gas jet holes, namely the main fuel/gas is jetted out from the fuel/gas jet holes in a transverse flow direct injection mode, so that the oil-gas mixing degree is improved. The flame behind the venturi 6 ignites the main fuel/gas in the cavity 8, which, because the cavity 8 is an annular cavity, propagates rapidly and forms a stable ignition source.
With reference to fig. 3, the inlet section 3 has a height d of the flow path and a distance l from the outlet of the venturi 6 to the front wall of the recess 1 ，l 1 The value range of (a) is-0.5 d, and when the value is negative, the venturi 6 extends from the air inlet section 3 to the back of the front wall of the concave cavity.
Referring to fig. 3, the cavity 8 is divided into an upper cavity and a lower cavity, the upper cavity is recessed toward the combustion chamber housing, and the lower cavity is recessed toward the center body. The length of the cavity 8 is l 2 The value range is 0.5-1.5 d, and the height of the upper concave cavity is h 2 The value is reasonably between 0.1d and 0.4 d; the height of the lower concave cavity is h 1 And the value is reasonably selected from 0.2d to 0.9 d. The flame continues to spread into the combustion chamber 9 and fully burns, forms the main combustion area, and the height of combustion chamber 9 is 2d. The combusted gases are ejected from the jet nozzle 10, causing the engine to produce thrust.
The position of the ignition device 9 is determined by the recirculation zone formed by the first stage flame holder. The ignition device 9 is not suitable to extend too far into the combustion chamber, otherwise the head part of the ignition device is wetted by fuel to influence ignition; it is not suitable for too shallow, and the ignition is not easy at too shallow wall surface. The ignition device 9 should be located at the edge of the recirculation zone, the combustion concentration distribution is proper, and the gas flow velocity is low. The length of the ignition device 9 projecting into the combustion chamber is therefore 10mm here. In the embodiment shown in fig. 2 and 3, the ignition device is located at a distance of 0.75l from the front wall of the recess when the swirl and recess combination is used 2 Wherein l is 2 Is the length of the cavity, /) 2 The value range of (d) is 0.5 d-1.5 d, and d is the height of the flow channel of the gas inlet section. The ignition device is arranged in such a way that the ignition device is positioned at the edge of the backflow area to burnThe concentration distribution is proper, the gas flow speed is low, and the ignition is easy to successfully ignite and a stable ignition source is formed.
In the above embodiments, the swirler and the venturi are used, so that oil-gas mixing can be effectively enhanced, the ignition performance and the combustion efficiency are further improved, and the formed backflow zone can also improve the flame stability.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (10)
1. The utility model provides a stable ramjet combustion chamber of whirl combination flame which characterized in that: the combustor comprises a combustor shell and a central body coaxially arranged in the combustor shell, wherein an annular cavity formed between the combustor shell and the central body is a combustor;
the combustion chamber is sequentially divided into an air inlet section, a combustion cavity and a tail nozzle along the air inflow direction; a first-stage flame stabilizing device is locally arranged in the air inlet section, and a second-stage flame stabilizing structure is arranged at the downstream of the first-stage flame stabilizing device;
the first stage flame stabilizing device consists of a diffuser, a swirler and a venturi which are connected in sequence, the second stage flame stabilizing structure is a sudden expansion or a concave cavity arranged behind the air inlet section, and the ignition device is arranged at the downstream of the sudden expansion or in the concave cavity;
the high-speed air entering the diffuser enters the swirler after being subjected to diffuser and speed reduction of the diffuser to form swirl air, the center of the swirler is provided with an oil injection hole for injecting fuel oil, the swirl air and the fuel oil injected by the oil injection hole are fully mixed in the outlet of the swirler and the venturi tube to form premixed gas, the premixed gas is ignited by the ignition device at the sudden expansion downstream or in the concave cavity, and flame forms a stable ignition source at the sudden expansion downstream or in the concave cavity.
2. The swirl-combined flame-stabilized ramjet combustion chamber of claim 1, wherein: the two first-stage flame stabilizing devices are symmetrically arranged in the annular air inlet section by taking the central shaft of the central body as a symmetry axis.
3. The swirl-combined flame-stabilized ramjet combustion chamber of claim 2, wherein: in the first-stage flame stabilizing device, the diffuser inlet is flush with the inlet of the air inlet section.
4. The swirl-combined flame-stabilized ramjet combustion chamber of claim 2, wherein: the ignition device is arranged on the central section where the two first-stage flame holders are arranged.
5. The swirl-combined flame-stabilized ramjet combustion chamber of claim 2 or 3 or 4, characterized in that: the second-stage flame stabilizing structure is a step-shaped sudden expansion arranged at the joint of the air inlet section and the combustion cavity, and an annular backward step is formed at the joint of the air inlet section and the combustion cavity.
6. The swirl-combined flame-stabilized ramjet combustion chamber of claim 5, wherein: the distance between the ignition device and the wall surface of the sudden expansion is d-1.5 d, wherein d is the height of a flow channel of the air inlet section.
7. The swirl-combined flame-stabilized ramjet combustion chamber of claim 2 or 3 or 4, characterized in that: the second-stage flame stabilizing structure is an annular concave cavity arranged in the combustion chamber.
8. The swirl-combined flame-stabilized ramjet combustion chamber of claim 7, wherein: the distance of the ignition device from the front wall surface of the concave cavity is 0.75l 2 Wherein l is 2 Is the length of the cavity, /) 2 The value range of (d) is 0.5 d-1.5 d, and d is the height of the flow channel of the gas inlet section.
9. The swirl-combined flame-stabilized ramjet engine combustor of claim 1 or 2 or 3 or 4 or 6 or 8, characterized in that: the cyclone is an inner-outer two-stage cyclone, the inner cyclone is used for shearing and crushing oil mist to form a backflow area, and the outer cyclone is used for improving the axial uniformity of the outlet.
10. The swirl-combined flame-stabilized ramjet combustion chamber of claim 9, wherein: the fuel/gas jet holes are uniformly distributed at the outlet of the air inlet section of the combustion chamber in the circumferential direction, are arranged perpendicular to the air inflow direction, and provide main fuel/gas required by combustion for the combustion cavity through the fuel/gas jet holes.
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| CN202210827881.9A CN115234944A (en) | 2022-07-14 | 2022-07-14 | Swirl combined ramjet combustion chamber with stable flame |
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| CN202210827881.9A CN115234944A (en) | 2022-07-14 | 2022-07-14 | Swirl combined ramjet combustion chamber with stable flame |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003010432A1 (en) * | 2001-07-23 | 2003-02-06 | Ramgen Power Systems, Inc. | Rotary ramjet engine with flameholder extending to running clearance at engine casing interior wall |
| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower type flame holder for rotor engine |
| CN104964310A (en) * | 2015-06-12 | 2015-10-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Ramjet combustion chamber |
| CN109113895A (en) * | 2018-09-11 | 2019-01-01 | 中国人民解放军国防科技大学 | Flame stabilizing device of ramjet engine |
| CN109668171A (en) * | 2018-12-20 | 2019-04-23 | 中国航发四川燃气涡轮研究院 | A kind of radial grading subregion high temperature rise combustor head |
| CN110017502A (en) * | 2018-01-09 | 2019-07-16 | 通用电气公司 | Jet stream rotational flow air injection fuel injector for gas-turbine unit |
| CN212319717U (en) * | 2020-04-17 | 2021-01-08 | 江联重工集团股份有限公司 | Sudden expansion type flame stabilizer for blast furnace gas burner |
-
2022
- 2022-07-14 CN CN202210827881.9A patent/CN115234944A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003010432A1 (en) * | 2001-07-23 | 2003-02-06 | Ramgen Power Systems, Inc. | Rotary ramjet engine with flameholder extending to running clearance at engine casing interior wall |
| CN101144430A (en) * | 2007-10-19 | 2008-03-19 | 北京航空航天大学 | Tower type flame holder for rotor engine |
| CN104964310A (en) * | 2015-06-12 | 2015-10-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Ramjet combustion chamber |
| CN110017502A (en) * | 2018-01-09 | 2019-07-16 | 通用电气公司 | Jet stream rotational flow air injection fuel injector for gas-turbine unit |
| CN109113895A (en) * | 2018-09-11 | 2019-01-01 | 中国人民解放军国防科技大学 | Flame stabilizing device of ramjet engine |
| CN109668171A (en) * | 2018-12-20 | 2019-04-23 | 中国航发四川燃气涡轮研究院 | A kind of radial grading subregion high temperature rise combustor head |
| CN212319717U (en) * | 2020-04-17 | 2021-01-08 | 江联重工集团股份有限公司 | Sudden expansion type flame stabilizer for blast furnace gas burner |
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