CN110762555B - Pneumatic auxiliary type cavity support plate flame stabilizer - Google Patents
Pneumatic auxiliary type cavity support plate flame stabilizer Download PDFInfo
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- CN110762555B CN110762555B CN201911016174.6A CN201911016174A CN110762555B CN 110762555 B CN110762555 B CN 110762555B CN 201911016174 A CN201911016174 A CN 201911016174A CN 110762555 B CN110762555 B CN 110762555B
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- 239000003381 stabilizer Substances 0.000 title claims abstract description 117
- 238000002485 combustion reaction Methods 0.000 claims abstract description 49
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 6
- 238000007789 sealing Methods 0.000 claims description 5
- 238000005507 spraying Methods 0.000 claims description 4
- 239000003921 oil Substances 0.000 description 39
- 239000000295 fuel oil Substances 0.000 description 6
- 239000000446 fuel Substances 0.000 description 5
- 230000006641 stabilisation Effects 0.000 description 5
- 238000011105 stabilization Methods 0.000 description 5
- 230000004323 axial length Effects 0.000 description 3
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F23R3/16—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
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention discloses a pneumatic auxiliary type concave cavity support plate flame stabilizer, which comprises a front duct splitter plate, a concave cavity flame stabilizer connected with the rear end of the front duct splitter plate, a rear duct splitter plate arranged at the rear end of the concave cavity flame stabilizer and a support plate flame stabilizer, wherein the front duct splitter plate is connected with the rear end of the front duct splitter plate; the front bypass flow dividing plate comprises a first flow dividing plate which gradually extends towards the direction far away from the outer wall of the combustion chamber along the inflow direction of the air flow: the rear end of the first flow dividing plate is connected with a second flow dividing plate extending along the horizontal direction; the support plate flame stabilizer is fixed on the lower surface of the second flow dividing plate; the second flow dividing plate is provided with a plurality of first flow passages for the outer duct gas to flow into the cavity of the recessed cavity flame stabilizer. The pneumatic auxiliary type concave cavity support plate flame stabilizer improves the ignition and flame stabilizing capability of the concave cavity support plate flame stabilizer, so that the flame stabilizer has wider flameout boundary conditions than the conventional concave cavity support plate flame stabilizer.
Description
Technical Field
The invention relates to a flame stabilizer used in a turbofan engine afterburner, a sub-combustion ramjet engine combustor and a multi-mode combustor of a turbofan/ramjet combined cycle engine, in particular to a pneumatic auxiliary type concave cavity support plate flame stabilizer.
Background
The turbine-based combined cycle engine (TBCC for short) has the performance advantages of wide flight range, conventional take-off and landing, reusability and the like as an air suction engine, and is considered to be the most promising hypersonic aircraft power device at the present stage. The low incoming flow temperature and the excessive flow rate of the local flow conditions in the TBCC multi-mode combustion chamber are caused by the characteristic that the bypass ratio is changed greatly in the whole working range, so that the ignition and flame stabilization in the multi-bypass combustion chamber are difficult.
With the improvement of the airflow speed in the modern high-performance afterburner, in order to ensure the reliable ignition performance of the combustor, a duty flame stabilizer is generally adopted for soft ignition on the outer ring of the combustor, and a radial flame stabilizer is used in combination to improve the flame propagation capability, so that a cavity/support plate combined flame stabilizer is formed. But the radial flame stabilizer can block the flow passage to increase the flow speed in the on-duty flame stabilizer, and meanwhile, a low-speed backflow area formed after the radial flame stabilizer can also scratch the flow of the on-duty area and destroy the flow form of the on-duty area, so that the on-duty ignition performance and the flame stabilizing capability of the combustion chamber are further deteriorated.
Meanwhile, the combined flame stabilizer is directly applied to the multi-duct combustion chamber, and the performance of the combined flame stabilizer is necessarily limited by the severe flow conditions of the multi-duct combustion chamber. The low temperature, high velocity conditions within the multi-duct combustor require far more ignition and flame stabilization than the current afterburner and scramjet combustor technology. Therefore, the cavity/plate flame stabilizer needs to have broader lean ignition and lean extinction capabilities to meet the widely varying operating requirements of the multi-duct combustion chamber over the operating envelope.
Disclosure of Invention
The invention aims to: in order to solve the problems in the prior art, the invention provides a pneumatic auxiliary type concave cavity support plate flame stabilizer.
The technical scheme is as follows: the invention relates to a pneumatic auxiliary type concave cavity support plate flame stabilizer, which comprises a front bypass flow dividing plate, a concave cavity flame stabilizer connected with the rear end of the front bypass flow dividing plate, a rear bypass flow dividing plate arranged at the rear end of the concave cavity flame stabilizer and a support plate flame stabilizer, wherein the front bypass flow dividing plate is arranged on the front side of the front bypass flow dividing plate;
The front bypass flow dividing plate comprises a first flow dividing plate which gradually extends towards the direction far away from the outer wall of the combustion chamber along the inflow direction of the air flow: the rear end of the first flow dividing plate is connected with a second flow dividing plate extending along the horizontal direction;
The support plate flame stabilizer is fixed on the lower surface of the second flow dividing plate; the second flow dividing plate is provided with a plurality of first flow passages for the outer duct gas to flow into the cavity of the recessed cavity flame stabilizer.
The flame stabilizer comprises a support plate, a flame stabilizer and a second flow dividing plate, wherein first flow passages are distributed on two sides of the flame stabilizer, and each first flow passage comprises a guide plate extending towards the direction away from the outer wall surface of the combustion chamber and sealing plates positioned on two sides of the guide plate and used for connecting the guide plate with the second flow dividing plate.
The airflow outlet of the first flow channel is a rectangular opening.
The recessed flame stabilizer is composed of a radially extending front edge plate, a horizontally extending bottom plate and a rear edge plate extending from the rear end of the bottom plate to a direction away from the outer wall of the combustion chamber.
The support plate flame stabilizer is a hollow triangular prism with gradually increased width along the axial direction; a first air cavity, an oil storage cavity and a second air cavity are sequentially arranged in the support plate flame stabilizer along the axial direction; and a plurality of oil spraying holes which are distributed radially are distributed on two side walls of the oil storage cavity.
The rear bypass flow dividing plate expands toward the direction approaching the outer wall of the combustion chamber.
The base plate is fixedly provided with an ignition power nozzle and an on-duty oil supply device.
The on-duty oil supply device consists of a centrifugal nozzle, a pressure stabilizing cavity and a first oil supply rod.
The oil storage cavity is communicated with an outlet of the second oil supply rod.
The beneficial effects are that: (1) According to the invention, the first flow channels for the outer duct gas to flow into the concave cavities are arranged at the two sides of the support plate flame stabilizer, so that the damage of the support plate flame stabilizer to the flow field of the on-duty area of the flame stabilizer is solved, the ignition performance and flame stabilizing capability of the concave cavity support plate flame stabilizer are improved, and the working range of the conventional concave cavity support plate flame stabilizer is widened; (2) The front bypass flow dividing plate is divided into a first flow dividing plate with a certain angle with the horizontal direction and a second flow dividing plate with a certain angle with the horizontal direction, so that the air flow entering the combustion chamber is more reasonably distributed; (3) The rear duct splitter plate provided by the invention has a certain divergence angle, so that the heat congestion of the high-temperature air flow of the connotation can be prevented, and the effective combustion area is increased to improve the combustion efficiency; (4) According to the invention, the air cavities with lower heat conductivity coefficients are respectively arranged in front of and behind the oil storage cavity, so that the fuel oil in the oil storage cavity can be thermally protected; (5) According to the invention, the fuel oil fed into the oil storage cavity from the second fuel injection rod is sprayed out through the fuel injection holes arranged on the two side walls of the support plate flame stabilizer, so that the integrated oil supply of the support plate flame stabilizer is realized.
Drawings
FIG. 1 is a three-dimensional model of a flame stabilizer for a cavity plate of the present invention.
FIG. 2 is a schematic view of the assembly of a cavity plate flame holder of the present invention within a rectangular combustion chamber.
Fig. 3 is a schematic structural view of a first flow channel according to the present invention.
FIG. 4 is a schematic cross-sectional view of a flame holder of the support plate of the present invention.
FIG. 5 is a schematic diagram of the working flow of the flame stabilizer with the concave supporting plate of the invention.
FIG. 6 is a streamline distribution of a prior art cavity plate flame holder and a cavity plate flame holder of the present invention.
FIG. 7 is a lean-spot flameout gas/oil ratio of a prior art cavity plate flame holder and a cavity plate flame holder of the present invention.
Description of the embodiments
Example 1: the pneumatic auxiliary type concave cavity support plate flame stabilizer in the embodiment comprises a front duct splitter plate 1, a concave cavity flame stabilizer 2 connected with the rear end of the front duct splitter plate 1, a rear duct splitter plate 3 arranged at the rear end of the concave cavity flame stabilizer 2 and a support plate flame stabilizer 4.
The front end/side to rear end/side direction described in this embodiment is the flow direction of the air flow entering the combustion chamber, and is also the axial direction (X-axis direction in fig. 3) described in this embodiment. The radial direction described in this embodiment is the direction from the upper end/side to the lower end/side of the combustion chamber (the Y-axis direction in fig. 3).
The combustion chamber described in this embodiment is of an existing structure, and the outer wall of the combustion chamber is located above the combustion chamber, and the wall surface of the combustion chamber is provided with an oil supply device.
As shown in fig. 1, the front bypass diverter plate 1 is formed from a first diverter plate 101 and a horizontally extending second diverter plate 102 connected to the first diverter plate 101; the first splitter plate 101 gradually extends towards the direction far away from the outer wall 801 of the combustion chamber 8 along the inflow direction of the air flow, and the second splitter plate 102 extending along the horizontal direction is connected to the rear end of the first splitter plate 101, namely, two flat plates with clamping angles form the front duct splitter plate 1.
The cavity flame stabilizer 2 in this embodiment is a structure of an existing cavity flame stabilizer, and the cavity flame stabilizer 2 is composed of a radially extending front edge plate 201 perpendicular to the second splitter plate 102, a horizontally extending bottom plate 202, and a rear edge plate 203 extending from the rear end of the bottom plate 202 toward a direction away from the outer wall 801 of the combustion chamber 8, where the front edge plate 201, the bottom plate 202, and the rear edge plate 203 enclose a cavity of the cavity flame stabilizer 2. The front flange plate 201 is fixedly connected with the front duct splitter plate 1, the rear end of the rear flange plate 203 is connected with the rear duct splitter plate 3, and the rear duct splitter plate 3 extends towards the direction close to the outer wall of the combustion chamber, so that the rear duct splitter plate 3 expands towards the direction of the outer wall of the combustion chamber. The front culvert flow dividing plate 1 plays a role in distributing inner culvert flow and outer culvert flow, the rear culvert flow dividing plate 3 is provided with a certain expansion angle, so that high-temperature air flow heat congestion of an inner culvert can be prevented, and meanwhile, the effective combustion area is increased to improve the combustion efficiency.
The bottom plate 202 of the cavity flame stabilizer 2 is provided with a firing nozzle matching hole 204 for mounting the firing nozzle 6, and is also provided with a fuel nozzle matching hole 205 for mounting the on-duty oil supply device 7 for realizing the on-duty ignition function of the cavity flame stabilizer. As a preferred form of this embodiment, the ignition tip fitting hole 204 is provided on the base plate 202 at a distance of 1/4 of the axial length from the leading edge plate, and the fuel nozzle fitting hole 205 is provided at a distance of 1/2 of the axial length from the base plate. The on-duty oil supply device 7 is of an existing structure, and the on-duty oil supply device 7 consisting of a centrifugal nozzle 701, a pressure stabilizing cavity 702 and a first oil supply rod 703 is adopted in the invention.
As shown in fig. 2, the support plate flame stabilizer 4 is fixed on the lower surface of the second splitter plate 102, the support plate flame stabilizer 4 is transversely positioned in the middle of the cavity flame stabilizer 2, and the tail end surface of the support plate flame stabilizer 4 is flush with the front end surface of the cavity flame stabilizer 1. The support plate flame stabilizer 4 is a thin-wall hollow member, the transverse cross section is V-shaped, the overall shape of the support plate flame stabilizer 4 is triangular prism-shaped, the transverse cross section width of the support plate flame stabilizer 4 is gradually increased along the axial direction, the hollow cavity inside the support plate flame stabilizer 4 is sequentially divided into a first air cavity 401, an oil storage cavity 402 and a second air cavity 403 along the axial direction, a plurality of oil spraying holes 404 which are distributed radially are distributed on two side walls of the oil storage cavity 402, the oil storage cavity 402 is communicated with an outlet of a second oil supply rod 405 (the second oil supply rod 405 is of an existing structure), and in the embodiment, a row of oil spraying holes 404 which are distributed radially are arranged on the side wall of the oil storage cavity 402.
After the fuel oil enters the oil storage cavity 402 from the second oil supply rod 405, the fuel oil is sprayed out through the oil spray holes 404 arranged on the two side walls of the support plate flame stabilizer 4, so that the integrated oil supply of the support plate flame stabilizer is realized. The air with lower heat conductivity coefficient in the first air cavity 401 and the second air cavity 403 can thermally protect the fuel oil in the fuel oil storage cavity 402, and meanwhile, the second air cavity 403 can also be used for carrying out cooling hole design to thermally protect the tail end surface of the support plate flame stabilizer 4.
As shown in fig. 3, the X-axis direction is axial, the Y-axis direction is radial, and the Z-axis direction is transverse, and as shown in the drawing, the second splitter plate 102 is provided with a plurality of first flow channels 5 for the external duct gas to flow into the cavity as pneumatic auxiliary devices, the first flow channels 5 are used for sending the gas flow passing through the external duct into the cavity of the cavity flame stabilizer 1, and the pneumatic auxiliary devices are not limited to the structure of the first flow channels 5 in the embodiment, so that other devices capable of realizing the inflow of the external duct gas into the connotation are all equivalent substitutions of the pneumatic auxiliary device of the invention. In order to protect the in-cavity flow structure of the re-entrant flame holder 2, first flow passages 5 are arranged on both sides of the fulcrum flame holder 4, the first flow passages 5 being located on the second flow dividing plate 102 of the front bypass flow dividing plate 4, close to the re-entrant flame holder 2.
The first flow channel 5 is composed of a rectangular flow guide plate 501 extending obliquely downwards and triangular sealing plates 502 fixed on two sides of the flow guide plate 501, the flow guide plate 501 gradually extends towards the direction far away from the outer wall surface of the combustion chamber, rectangular holes formed in the front bypass flow guide plate 1 form two air flow channels, and meanwhile flow guide functions are achieved on inner air flow and outer air flow. Sealing plates 502 on both sides of the baffle 501 connect the baffle 501 with the second splitter plate 102; the side plates 502 are triangular plates which are vertically arranged, and have the functions of fixing and sealing to reduce flow loss; the airflow outlet 503 of the first flow passage 5 is a rectangular opening. Preferably, the axial distance S between the rear edge of the pneumatic auxiliary device and the front edge of the concave flame stabilizer 2 is 5-15 mm, the radial opening H of the air flow outlet 503 is 2-8 mm, the axial length of the rectangular hole formed by the front bypass flow dividing plate 1 of the first flow passage 5 is preferably 20-40 mm, the first flow passage 5 can be transversely (i.e. the width of the first flow passage) extended to the support plate flame stabilizer 4 and can be cut off in advance, and the preferred value is 20-35 mm.
As shown in fig. 4, the pneumatically-assisted concave supporting plate flame stabilizer in the present embodiment is assembled in a rectangular combustion chamber, and the front bypass splitter plate 1, the concave flame stabilizer 2 and the rear bypass splitter plate 3 are fixedly connected with the side wall surface of the rectangular combustion chamber 8 through two side surfaces, and the upper wall surface of the combustion chamber 8 is the outer wall surface 801 in the present embodiment; the upper end surface of the support plate flame stabilizer 4 is fixedly connected with the second flow dividing plate 102 of the front duct flow dividing plate 1, and the lower end surface is fixedly connected with the lower wall surface 802 of the combustion chamber 8. The ignition nozzle 6 is concentrically matched with the ignition nozzle matching hole 204, and the on-duty oil supply device 7 is concentrically matched with the fuel nozzle matching hole 205; the ignition nozzle 6 and the on-duty oil supply device 7 are fixed on the upper wall surface of the rectangular combustion chamber 8 in a welding or mechanical matching mode.
The working flow of the pneumatic auxiliary type concave cavity support plate flame stabilizer in the embodiment is as follows:
As shown in fig. 5, the air flowing in from the rectangular combustion chamber inlet is divided into an outer culvert air flow and an inner culvert air flow by the front culvert split plate. Part of the outer culvert airflow is converged into the inner culvert airflow from the two airflow channels at the first flow channel (the pneumatic auxiliary device), the rest part of the outer culvert airflow thermally protects the hot end part in the outer culvert channel, and the rear culvert splitter plate is converged with the inner culvert airflow and participates in combustion; and the connotation air flow flows through the concave cavity support plate flame stabilizer and forms a low-speed backflow area suitable for ignition and flame stabilization in the concave cavity flame stabilizer and behind the support plate flame stabilizer under the action of two air flows. And (3) oil supply is carried out on the cavity flame stabilizer in an on-duty area by utilizing the centrifugal nozzle, proper oil gas in the cavity is matched with the ignition electric nozzle to discharge to form on-duty flame in the cavity, and the on-duty flame gradually ignites the main flow area of the support plate stabilizer to supply oil when propagating along the support plate flame stabilizer to the center of the combustion chamber, so that stable flame is finally formed in the rectangular combustion chamber. Meanwhile, the pneumatic auxiliary mode has self-adaptability, and two air inlets before ignition enable the concave cavity support plate flame stabilizer to be internally provided with a flow field structure suitable for ignition; after successful ignition and stable combustion, the rising of the inner culvert pressure of the combustion chamber causes the outer culvert air inflow to be reduced, and more outer culvert air is used for the thermal protection of the hot end part so as to ensure the structural reliability; and when the combustion chamber approaches to the flameout limit, the drop of the inclusion pressure can increase the inclusion air inflow again so as to improve the flame stability.
Application example: fig. 6 is a streamline distribution of two kinds of cavity/support plate flame stabilizers, wherein fig. 6a and 6c are conventional cavity support plate stabilizers, and fig. 6b and 6d are pneumatic auxiliary cavity support plate stabilizers of the device. As can be seen by comparing the streamline distribution in the two stabilizers, the recirculation zone formed in the cavity is greatly affected by the strut stabilizer, the low-velocity recirculation zone in the cavity of the cross section of the strut stabilizer (shown in fig. 6 a) is completely destroyed, and the low-velocity recirculation zone in the cavity away from the cross section of the strut stabilizer (shown in fig. 6 c) is also extruded and contracted by the influence of three-dimensional flow, so that the performance of ignition and flame stabilization is reduced. The pneumatic auxiliary type concave cavity support plate flame stabilizer provided by the invention protects the low-speed backflow area in the concave cavity by utilizing two air inlets, so that the influence of the support plate flame stabilizer on the flow of the concave cavity is weakened, a continuous and complete low-speed backflow area exists in the concave cavity at a position far away from the section (shown in fig. 6 d) of the support plate stabilizer, and a certain backflow exists between the concave cavity and the support plate at the position of the section (shown in fig. 6 b) of the support plate stabilizer, so that the stay time of air flow in the concave cavity/the support plate flame stabilizer is longer, and better ignition and flame stabilization performance are facilitated.
Fig. 7 is a lean blowout oil/gas ratio of a conventional bowl/plate flame holder and a pneumatically assisted bowl/plate flame holder of the present apparatus, with an inflow temperature of 600K. The two stabilizers are different from the pneumatic auxiliary device, and other structural parameters of the concave cavity flame stabilizer and the support plate flame stabilizer are the same. As can be seen from fig. 7, the pneumatic auxiliary type cavity/support plate flame stabilizer provided by the invention has better lean oil point and flameout performance than the traditional cavity/support plate flame stabilizer under the working conditions of t=600k and ma=0.1-0.3. In general, the pneumatic auxiliary type cavity/support plate flame stabilizer adopting the device can better improve lean oil point flameout performance of a combustion chamber, widen the ignitable speed limit of the cavity/support plate flame stabilizer, and enable the lean oil point and flameout oil-gas ratio to be averagely reduced by 19.3 percent and 25.6 percent.
From the test verification results, the invention adopts a pneumatic auxiliary mode to ensure that a continuous and complete reflux zone structure exists in the concave cavity stabilizer, and has wider flammable ignition positions than the conventional concave cavity support plate stabilizer; the pneumatic auxiliary type concave cavity support plate flame stabilizer increases the residence time of air flow in the concave cavity flame stabilizer, and improves the flammability speed limit of the combustion chamber; the gas flow passage adopted by the invention is used as a pneumatic auxiliary mode, has stronger self-adaptability than a mechanical mode, and can sense the change of the combustion state in the combustion chamber to be self-adaptively adjusted.
Claims (6)
1. The pneumatic auxiliary type cavity support plate flame stabilizer is characterized by comprising a front duct splitter plate (1), a cavity flame stabilizer (2) connected with the rear end of the front duct splitter plate (1), a rear duct splitter plate (3) arranged at the rear end of the cavity flame stabilizer (2) and a support plate flame stabilizer (4); the front bypass flow dividing plate (1) comprises a first flow dividing plate (101) which gradually extends along the direction of inflow of the air flow towards the direction away from the outer wall of the combustion chamber: the rear end of the first flow dividing plate (101) is connected with a second flow dividing plate (102) extending along the horizontal direction;
The support plate flame stabilizer (4) is fixed on the lower surface of the second flow dividing plate (102); the second flow dividing plate (102) is provided with a plurality of first flow passages (5) for the outer duct gas to flow into the cavity of the cavity flame stabilizer (2);
The two sides of the support plate flame stabilizer (4) are respectively provided with a first flow passage (5), and the first flow passages (5) comprise guide plates (501) extending towards the direction far away from the outer wall surface of the combustion chamber and sealing plates (502) positioned at the two sides of the guide plates and used for connecting the guide plates with the second flow dividing plates (102);
the recessed flame stabilizer (2) consists of a radially extending front edge plate (201), a horizontally extending bottom plate (202) and a rear edge plate (203) extending from the rear end of the bottom plate (202) towards the direction away from the outer wall of the combustion chamber;
The support plate flame stabilizer (4) is a hollow triangular prism with gradually increased width along the axial direction; a first air cavity (401), an oil storage cavity (402) and a second air cavity (403) are sequentially arranged in the support plate flame stabilizer (4); and a plurality of oil spraying holes (404) which are distributed radially are distributed on two side walls of the oil storage cavity (402).
2. A pneumatically assisted recessed cavity plate flame holder according to claim 1, characterized in that the air flow outlet (503) of the first flow channel (5) is a rectangular opening.
3. The pneumatically assisted recessed pocket support flame holder of claim 1, wherein said rear bypass splitter (3) expands in a direction toward the combustion chamber outer wall.
4. The pneumatic auxiliary type concave support plate flame stabilizer according to claim 1, wherein an ignition power nozzle (6) and an on-duty oil supply device (7) are fixed on the bottom plate (202).
5. The pneumatic auxiliary type concave support plate flame stabilizer according to claim 4, wherein the on-duty oil supply device (7) consists of a centrifugal nozzle (701), a pressure stabilizing cavity (702) and a first oil supply rod (703).
6. The pneumatically assisted re-entrant strut flame stabilizer of claim 1, wherein said oil reservoir (402) communicates with an outlet of a second oil supply rod (405).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911016174.6A CN110762555B (en) | 2019-10-24 | 2019-10-24 | Pneumatic auxiliary type cavity support plate flame stabilizer |
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| CN201911016174.6A CN110762555B (en) | 2019-10-24 | 2019-10-24 | Pneumatic auxiliary type cavity support plate flame stabilizer |
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| CN110762555B true CN110762555B (en) | 2024-04-19 |
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| CN113606609B (en) * | 2021-07-19 | 2022-10-11 | 南京航空航天大学 | Combined stabilizer based on center step ignition and working method thereof |
| CN113776082B (en) * | 2021-09-09 | 2023-01-06 | 南京航空航天大学 | Air-cooled wall type support plate combined flame stabilizer and combustion chamber |
| CN114165813B (en) * | 2021-12-03 | 2022-08-30 | 北京航空航天大学 | Pneumatic auxiliary integrated support plate stabilizer with double oil way oil supply |
| CN115371080B (en) * | 2022-07-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Reinforced tissue combustion chamber |
| CN115307179B (en) * | 2022-08-15 | 2023-08-01 | 北京航空航天大学 | Curved support plate double-concave-cavity integrated afterburner |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07248116A (en) * | 1994-03-11 | 1995-09-26 | Kawasaki Heavy Ind Ltd | Reduced-environmental-pollution combustor and combustion control method for the same |
| CN101418956A (en) * | 2007-10-22 | 2009-04-29 | 周建兴 | A kind of supersonic speed combustion chamber burner scheme of novel injection structure |
| WO2013154004A1 (en) * | 2012-04-10 | 2013-10-17 | いすゞ自動車株式会社 | Combustion chamber structure for direct injection engine |
| CN103884024A (en) * | 2014-04-03 | 2014-06-25 | 北京航空航天大学 | Flame crossover device capable of achieving organization combustion and transferring flames to outer duct airflow |
| CN104019464A (en) * | 2014-05-28 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Engine, flameholder and concave cavity design method of flameholder |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
| CN109780572A (en) * | 2019-01-09 | 2019-05-21 | 南京航空航天大学 | A kind of the combination flameholder and its working method of adjustable cavity whirlpool plot structure |
| CN109780571A (en) * | 2018-12-26 | 2019-05-21 | 南京航空航天大学 | A kind of vaporation-type combination flameholder |
| CN211575177U (en) * | 2019-10-24 | 2020-09-25 | 南京航空航天大学 | Pneumatic auxiliary type flame stabilizer with concave cavity supporting plate |
-
2019
- 2019-10-24 CN CN201911016174.6A patent/CN110762555B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07248116A (en) * | 1994-03-11 | 1995-09-26 | Kawasaki Heavy Ind Ltd | Reduced-environmental-pollution combustor and combustion control method for the same |
| CN101418956A (en) * | 2007-10-22 | 2009-04-29 | 周建兴 | A kind of supersonic speed combustion chamber burner scheme of novel injection structure |
| WO2013154004A1 (en) * | 2012-04-10 | 2013-10-17 | いすゞ自動車株式会社 | Combustion chamber structure for direct injection engine |
| CN103884024A (en) * | 2014-04-03 | 2014-06-25 | 北京航空航天大学 | Flame crossover device capable of achieving organization combustion and transferring flames to outer duct airflow |
| CN104019464A (en) * | 2014-05-28 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Engine, flameholder and concave cavity design method of flameholder |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
| CN109780571A (en) * | 2018-12-26 | 2019-05-21 | 南京航空航天大学 | A kind of vaporation-type combination flameholder |
| CN109780572A (en) * | 2019-01-09 | 2019-05-21 | 南京航空航天大学 | A kind of the combination flameholder and its working method of adjustable cavity whirlpool plot structure |
| CN211575177U (en) * | 2019-10-24 | 2020-09-25 | 南京航空航天大学 | Pneumatic auxiliary type flame stabilizer with concave cavity supporting plate |
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