CN115419917B - Heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber - Google Patents
Heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber Download PDFInfo
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- CN115419917B CN115419917B CN202210910202.4A CN202210910202A CN115419917B CN 115419917 B CN115419917 B CN 115419917B CN 202210910202 A CN202210910202 A CN 202210910202A CN 115419917 B CN115419917 B CN 115419917B
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- 230000000087 stabilizing effect Effects 0.000 title claims abstract description 96
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 64
- 238000002156 mixing Methods 0.000 title claims abstract description 33
- 238000002347 injection Methods 0.000 claims abstract description 113
- 239000007924 injection Substances 0.000 claims abstract description 113
- 239000000446 fuel Substances 0.000 claims abstract description 43
- 239000000945 filler Substances 0.000 claims abstract description 11
- 239000003921 oil Substances 0.000 claims description 14
- 239000000295 fuel oil Substances 0.000 claims description 12
- 239000007788 liquid Substances 0.000 claims description 12
- 239000002737 fuel gas Substances 0.000 claims description 7
- 239000000956 alloy Substances 0.000 claims description 4
- 230000000903 blocking effect Effects 0.000 claims description 4
- 230000009471 action Effects 0.000 claims description 2
- 238000010008 shearing Methods 0.000 claims description 2
- 239000007800 oxidant agent Substances 0.000 abstract description 5
- 230000001590 oxidative effect Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 10
- 238000013461 design Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 238000005507 spraying Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 3
- 238000000889 atomisation Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 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
- F23R3/28—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
-
- 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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The application relates to the field of combined power engines, and particularly discloses an integrated heterogeneous multiphase flow mixing flame stabilizing device and a combined power engine combustion chamber, wherein the integrated heterogeneous multiphase flow mixing flame stabilizing device comprises a lobe mixer; the injection flame stabilizing support plates are internally provided with injection cavities, the surfaces of the injection cavities are provided with injection holes communicated with the injection cavities, the injection flame stabilizing support plates are provided with a plurality of injection flame stabilizing support plates, one ends of the injection flame stabilizing support plates are connected to the tail ends of the lobe flow mixers along the air flow direction, and the other ends of the injection flame stabilizing support plates are communicated with the flow mixer flange; the fuel mixer flange is internally provided with a fuel channel, an oil supply filler neck communicated with the fuel channel is arranged, the fuel channel is communicated with the injection cavity, and the mixer flange is connected with the combustion chamber shell. Solves the problem of high-efficiency mixing combustion of different medium fuels and external air (oxidant) of the engine in different working modes.
Description
Technical Field
The application relates to the technical field of air turbine rocket combined power engines, in particular to a gas-liquid mixing flame stabilizing device in an engine combustion chamber.
Background
The working range of the combined power engine such as an Air Turbine Rocket (ATR) engine is wide (Ma=0-4), and parameters such as flow, speed, temperature, pressure, mixing ratio and the like of inlet air and rich gas of a combustion chamber are continuously changed along with the change of the working condition of the engine. The stable and efficient combustion of the internal combustion gas and the external air in the combustion chamber is of great importance to the performance of the engine, and the improvement of the mixing uniformity of the internal combustion gas and the air is the most effective way for realizing the efficient combustion in the combustion chamber. The research of students at home and abroad shows that the adoption of the scheme of the lobe-type mixer can effectively solve the mixing problem of air and rich fuel gas (gas-gas).
However, with the continuous improvement of the power demand in the near space, the performance demand of the air turbine rocket engine is improved, so that the original advantages of zero-speed take-off, wide working range and good acceleration of the engine are ensured, and the performance characteristics of long high-speed cruising time, large thrust and high specific impulse are also required. To achieve this performance characteristic, the combined engine needs to operate in different modes of operation, namely ATR mode and ram mode. Under the stamping mode, a fuel supply system is introduced, and the fuel and the external air (gas-liquid) are mixed for combustion, so that the cruise high-performance requirement is met. The difference of working media in different modes and the great change of the inlet inflow parameters of the combustion chamber in each mode along with the working condition bring great challenges to efficient combustion organization. However, the mere lobed mixer approach does not achieve the goal of gas-liquid mixing combustion.
Disclosure of Invention
The technical solution of the invention is as follows: in order to solve the problems in the background art, the invention provides an integrated heterogeneous multiphase flow mixing flame stabilizing device, which realizes the efficient mixing combustion of different medium fuels and oxidants (gas-gas and gas-liquid) under different working modes of a combined power engine and solves the problem of the efficient mixing combustion of the fuels and the oxidants under different working modes of the engine.
The technical scheme of the invention is as follows:
An integrated heterogeneous multiphase flow mixing flame stabilizing device and a lobe mixer; the injection flame stabilizing support plates are internally provided with injection cavities, the surfaces of the injection cavities are provided with injection holes communicated with the injection cavities, the injection flame stabilizing support plates are provided with a plurality of injection flame stabilizing support plates, one ends of the injection flame stabilizing support plates are connected to the tail ends of the lobe flow mixers along the air flow direction, and the other ends of the injection flame stabilizing support plates are communicated with the flow mixer flange; the fuel mixer flange is internally provided with a fuel channel, the fuel mixer flange is provided with a fuel supply filler neck communicated with the fuel channel, the fuel channel is communicated with the injection cavity, and the fuel mixer flange is connected with the combustion chamber shell.
Through the technical scheme, when liquid fuel is needed in the combustion chamber, the liquid fuel is injected into the fuel channel of the mixer flange from the fuel supply filler neck, then enters the injection cavity through the fuel channel, and then is sprayed out from the injection hole.
The lobe mixers are chamfer lobe mixers.
One end of the injection flame stabilizing support plate is welded at the trough of the lobe mixer.
The lobes of the lobe mixer are staggered with the injection flame stabilizing support plates, and the number of the lobes is the same as that of the injection flame stabilizing support plates; the number is 8 to 16.
The injection flame stabilizing support plate comprises two connecting plates, an included angle between the two connecting plates is smaller than 180 degrees, one side, smaller than 180 degrees, of the two connecting plates is an opening end of the injection flame stabilizing support plate, and the opening end of the injection flame stabilizing support plate faces away from the air flow direction. Namely, the two connecting plates are structurally arranged, so that the injection flame stabilizing support plate is V-shaped, and the opening direction of the V-shape is opposite to the air flow direction.
The injection flame stabilizing support plate forms a certain angle with the rear end face of the lobe mixer, and the inclination angle alpha is 5-10 degrees. The included angle between the central line of the jetting flame stabilizing support plate and the vertical plane of the central axis of the lobe flow mixer is 5-10, and one end of the jetting flame stabilizing support plate, which is far away from the lobe flow mixer, is inclined along the incoming flow direction.
The length, the V-shaped groove width and other dimensions of the injection flame stabilizing support plate are selected according to the design working condition parameters of the engine.
The ratio of the projection total area of the lobe mixer and the injection flame stabilizing support plate on the inner circular cross section of the mixer flange to the inner circular cross section of the mixer flange is defined as the total projection blocking ratio, and the value delta=0.3-0.5.
The fuel oil channel is arranged in the injection flame stabilizing support plate, the size of the fuel oil channel is selected according to the design working condition parameters of the engine, the back wind surface of the injection flame stabilizing support plate is provided with injection holes, and the aperture is 0.5 mm-2.0 mm.
The injection holes on the injection flame stabilizing support plate are distributed equidistantly, the number of the injection holes is 5-15, and the injection holes are specifically selected according to the design working condition parameters of the engine.
The size of the built-in fuel channel of the mixer flange is selected according to the design working condition parameters of the engine.
The lobe mixer, the injection flame stabilizing support plate and the mixer flange are all made of high-temperature alloy materials.
The utility model provides a combination power engine combustion chamber, includes straight section of combustion chamber, combustion chamber expansion section, the tail pipe that connects gradually to and a heterogeneous multiphase flow of an integral type mixes steady flame device, steady flame device's mixed flow ware flange joint is between the straight section of combustion chamber and combustion chamber expansion section, and lobe mixed flow ware, the steady flame extension board of injection are located the inside of the straight section of combustion chamber and combustion chamber expansion section.
In summary, the application at least comprises the following beneficial technical effects:
The integrated heterogeneous multiphase flow mixing flame stabilizing device integrates the lobe flow mixer and the injection flame stabilizing structure, simultaneously gives consideration to two engine working modes, has small number of parts and simple structural system, realizes efficient, stable and reliable combustion of air, rich fuel gas and liquid fuel oil, and meets the latest power performance requirement of the current combined power engine.
On the one hand, under the ATR working mode, the turbulence in the combustion chamber is improved, the mixing effect of inner and outer culvert air flows is enhanced, the gas-gas mixing time is shortened, the length of the combustion chamber is reduced, the range of a low-speed backflow area behind the flow mixer can be increased, and the ignition and flame stabilization and flame transfer of the combustion chamber are facilitated. On the other hand, in the stamping working mode, a low-speed backflow area is formed at the downstream of the injection flame stabilizing support plate, the entrainment effect of air flow increases the residence time of fuel oil, so that the liquid fuel oil has sufficient time for heat absorption, atomization and evaporation, the formation of a fuel-gas mixture is facilitated, and the continuous and stable combustion of the combustion chamber is realized.
Drawings
FIG. 1 is a schematic diagram of an integrated heterogeneous multiphase flow blending flame stabilizing device according to an embodiment of the present invention;
FIG. 2 is an axial cross-sectional view of the flame stabilizing device of FIG. 1;
FIG. 3 is a right side view of FIG. 2;
fig. 4 is a schematic diagram of an installation structure of an integrated heterogeneous multiphase flow blending flame stabilizing device in a combined power engine according to an embodiment of the invention.
Reference numerals illustrate: 1. a lobe mixer; 2. injecting a flame stabilizing support plate; 3. a mixer flange; 4. an oil supply filler neck; 5. a jet hole; 6. a combustion chamber straight section; 7. a combustion chamber expansion section; 8. a tail pipe.
Detailed Description
The application is described in further detail below with reference to the attached drawings and to specific embodiments:
Aiming at the power performance requirement of the air turbine rocket combined power engine in the background art, the engine working package width is as follows, and two working modes exist in a combustion chamber: ATR mode and ram mode. The oxidant in the combustion chamber is external air, the parameters of speed, temperature, flow and the like are greatly changed along with the mode working condition, and the fuel is respectively kerosene fuel rich gas (ATR mode) and liquid kerosene (stamping mode) along with the change of the working mode. In order to realize reliable operation, stable flame and efficient blending combustion of the combustion chamber under two working modes simultaneously, the invention integrates the lobe mixer 1 and the injection flame stabilizing device, and the injection flame stabilizing structure is arranged on the lobe mixer 1 as a basis, thereby meeting the multi-mode working requirements of the engine.
The embodiment of the application discloses an integrated heterogeneous multiphase flow mixing flame stabilizing device, which comprises a lobe mixer 1, an injection flame stabilizing support plate 2 for injecting fuel oil and an oil supply device for supplying oil to the injection flame stabilizing support plate 2, as shown in fig. 1 and 2. The external air flows from the outer side of the lobe mixer 1 and is uniformly mixed with the fuel oil sprayed by the spraying flame stabilizing support plate 2, so that the gas-liquid mixing is realized.
As shown in fig. 1 and 3, an injection cavity is arranged in the injection flame stabilizing support plate 2, and an injection hole 5 communicated with the injection cavity is arranged on the surface of the injection flame stabilizing support plate 2. The spraying flame stabilizing support plates 2 are arranged in a plurality, one ends of the spraying flame stabilizing support plates 2 are connected to the tail ends of the lobe mixer 1 along the air flow direction, and the other ends of the spraying flame stabilizing support plates 2 are communicated with the oil supply device. Specifically, one end of the injection stable flame support plate 2 is connected to the trough of the lobe mixer 1, the other end extends in a direction away from the axis of the lobe mixer 1, the lobes of the lobe mixer 1 are staggered with the injection stable flame support plate 2, and the number of the lobes of the lobe mixer 1 and the number of the injection stable flame support plate 2 are kept the same. The oil supply device comprises a mixer flange 3, a fuel channel is arranged in the mixer flange 3, the mixer flange 3 is provided with an oil supply filler neck 4 communicated with the fuel channel, and the fuel channel is communicated with the injection cavity. The mixer flange 3 is provided with a plurality of flange holes, and the mixer flange 3 is connected with the combustion chamber shell through the flange holes.
The device comprises a lobe mixer 1, an injection flame stabilizing support plate 2, a mixer flange 3 and an oil supply filler neck 4. All the components are made of high-temperature alloy materials, and all the components are assembled by welding high-temperature alloy welding wires. The injection flame stabilizing support plate 2 is welded at the trough of the lobe mixer 1 and forms a certain angle with the rear end face of the lobe mixer 1, the inclined angle alpha is 5-10 degrees, and the injection flame stabilizing support plate 2 is inclined along the incoming flow direction. The fuel oil sprayed from the spraying holes is favorably sprayed to the edge area (far away from the central area) of the combustion chamber, the fresh air in the edge area is fully utilized, the oil gas distribution is more reasonable, and the combustion performance is improved.
In the design of the dimension parameters of the lobe mixer 1 and the injection flame stabilizing support plate 2, the ratio of the total projected area of the inner circular cross section of the mixer flange to the inner circular cross section of the mixer flange (which is defined as the total projected blocking ratio) is ensured to be delta=0.4-0.5. The excessively large blockage ratio reduces airflow capacity, increases total pressure loss, and reduces combustion chamber performance. Too small a blocking ratio, poor mixing effect of fuel and oxidant, lengthened combustion distance, insufficient combustion, reduced flame holding capability, and reduced combustion chamber performance.
The injection flame stabilizing support plate 2 comprises two connecting plates, an included angle between the two connecting plates is smaller than 180 degrees, specifically, the included angle between the two connecting plates of the injection flame stabilizing support plate 2 is 30-50 degrees, the cross section of the injection flame stabilizing support plate 2 perpendicular to the length direction of the injection flame stabilizing support plate is V-shaped, one side of the included angle between the two connecting plates is 30-50 degrees, which is the open end of the injection flame stabilizing support plate 2, and the open end of the injection flame stabilizing support plate 2 faces away from the air flow direction. The injection hole 5 is positioned on the leeward side of the injection flame stabilizing support plate 2; the injection holes 5 are uniformly distributed on the surface of the injection flame stabilizing support plate 2.
As shown in fig. 4, the combustion chamber of the combined power engine comprises a combustion chamber straight section 6, a combustion chamber expansion section 7 and the integrated heterogeneous multiphase flow mixing flame stabilizing device, wherein the flow mixer flange 3 of the flame stabilizing device is connected between the combustion chamber straight section 6 and the combustion chamber expansion section 7 through bolts, the stability of the flame stabilizing device is improved, and the oil supply filler neck 4 can be positioned on the outer sides of the combustion chamber straight section 6 and the combustion chamber expansion section 7, so that fuel is conveniently input into the flow mixer flange 3 through the oil supply filler neck 4.
The implementation principle of the application is as follows:
When the combustion chamber works in the ATR mode, external air flows from the outer side of the lobe mixer 1, internal fuel gas flows from the inner side of the lobe mixer 1, the lobe mixer 1 is a chamfer type lobe mixer 1, and the two airflow boundary layers at the tail edge of the lobe are intensively mixed by using the viscous shearing action of the boundary layers. By beveling the trailing edge of the lobe mixer 1, the radial velocity of the outlet airflow can be increased, improving the mixing effect. According to parameters such as inlet flow of different working conditions, the speed of the fuel-rich gas and the external air at the outlet section of the lobe mixer 1 is equal by controlling the outlet area ratio of the fuel-rich gas and the external air. The chamfer-type lobe mixer 1 may be specifically in a chrysanthemum-shaped structure, and each lobe is uniformly distributed radially by taking the axial center of the lobe mixer 1 as an origin. In view of weight reduction, the wall thickness of the lobe mixer 1 can be 1.0 mm-1.2 mm. In addition, the number of the lobes, the chamfer angle, the axial length and other dimensional parameters can be optimally designed according to the dimensions of the combustion chamber and the inlet airflow parameters, the number of the lobes of the lobe mixer 1 can be selected from 8-16, and the chamfer angle of the tail edge of the lobes is selected from 20-45 degrees.
When the combustion chamber works in a stamping mode, outer culvert air flows from the outer side of the lobe mixer 1, the inner culvert fuel gas stops supplying, liquid fuel enters a built-in fuel channel in the mixer flange 3 from the fuel supply filler neck 4, then the fuel enters an injection cavity in the injection flame stabilizing support plate 2 along the built-in fuel channel in the mixer flange 3, finally the fuel is sprayed out from the injection hole 5 on the injection flame stabilizing support plate 2, and is mixed and sheared with the outer culvert air, and crushed and atomized to form an oil-gas mixture, so that combustion is realized. The injection flame stabilizing support plate 2 is designed to be V-shaped, air flows through the injection flame stabilizing support plate 2, the air flow is entrained, a low-speed backflow area is formed at the downstream, the fuel oil residence time is prolonged, the atomization mixing effect is enhanced, and the flame stabilizing effect is achieved. In addition, the injection holes 5 are arranged on the leeward side of the injection flame stabilizing support plate 2, so that the injection flame stabilizing support plate 2 avoids a high-temperature gas area, and the problem of heat protection of the injection flame stabilizing support plate 2 is solved. Firstly, the aperture and the number of the injection holes 5 are selected according to the inlet parameters of the design working condition of the combustion chamber, wherein the aperture is 0.5 mm-1.0 mm, and the number is 5-15. Secondly, the total area of the cross section of the fuel passage arranged in the mixer flange 3 and the injection flame stabilizing support plate 2 is larger than the total area of the injection holes 5.
The injection flame stabilizing support plate 2 plays a role in stabilizing flame, enhancing blending and delivering flame no matter the combustion chamber works in an ATR mode or a stamping mode.
While the invention has been described in terms of the preferred embodiment, it is not intended to limit the invention, but it will be apparent to those skilled in the art that variations and modifications can be made without departing from the spirit and scope of the invention, and therefore the scope of the invention is defined in the appended claims.
Claims (5)
1. An integrated heterogeneous multiphase flow blending flame stabilizing device is characterized in that: comprises a lobe mixer (1);
The device comprises an injection stable flame support plate (2), wherein an injection cavity is formed in the injection stable flame support plate, injection holes (5) communicated with the injection cavity are formed in the surface of the injection stable flame support plate (2), a plurality of injection stable flame support plates (2) are arranged, one ends of the injection stable flame support plates (2) are connected to the tail ends of the lobe mixer (1) along the air flow direction, the lobes of the lobe mixer (1) are distributed with the injection stable flame support plates (2) in a staggered mode, the leeward surfaces of the lobe mixer (1) and the injection stable flame support plates (2) are located on the same plane, and the other ends of the injection stable flame support plates (2) are communicated with an oil supply device for supplying oil to the injection cavity;
the injection flame stabilizing support plate (2) comprises two connecting plates, an included angle between the two connecting plates is 30-50 degrees, one side of the included angle between the two connecting plates, which is 30-50 degrees, is an opening end of the injection flame stabilizing support plate (2), and the opening end of the injection flame stabilizing support plate (2) faces away from the air flow direction;
The included angle between the central line of the injection flame stabilizing support plate (2) and the vertical plane of the central axis of the lobe mixer (1) is 5-10 degrees, and one end of the injection flame stabilizing support plate (2) far away from the lobe mixer (1) is inclined along the incoming flow direction; the injection hole (5) is positioned on the lee surface of the injection flame stabilizing support plate (2);
The oil supply device comprises a mixer flange (3), a fuel oil channel is arranged in the mixer flange (3), an oil supply filler neck (4) communicated with the fuel oil channel is arranged, the fuel oil channel is communicated with the injection cavity, and the mixer flange (3) is used for being connected with the combustion chamber shell;
In the ATR mode, the external air flows from the outer side of the lobe mixer (1), the internal fuel gas flows from the inner side of the lobe mixer (1), and the reinforced mixing is carried out by utilizing the viscous shearing action of the boundary layers of two airflow at the tail edges of the lobes;
In a stamping mode, external air flows from the outer side of the lobe mixer (1), internal fuel gas is stopped from being supplied, liquid fuel enters a built-in fuel channel in the mixer flange (3) from the fuel supply filler neck (4), then fuel enters an injection cavity in the injection flame stabilizing support plate (2) along the built-in fuel channel in the mixer flange (3), and finally is sprayed out from an injection hole (5) in the injection flame stabilizing support plate (2);
The ratio of the total projection area of the inner circular cross section of the lobe mixer (1) and the injection flame stabilizing support plate (2) on the mixer flange (3) to the inner circular cross section of the mixer flange (3) is the total projection blocking ratio delta, delta=0.3-0.5.
2. The integrated heterogeneous multiphase flow blending flame stabilizing device of claim 1, wherein: one end of the injection flame stabilizing support plate (2) is connected to the trough of the lobe mixer (1); the number of the lobes of the lobe mixer (1) and the number of the jetting flame stabilizing support plates (2) are kept the same.
3. The integrated heterogeneous multiphase flow blending flame stabilizing device of claim 1, wherein: the injection holes (5) are uniformly distributed on the surface of the injection flame stabilizing support plate (2).
4. The integrated heterogeneous multiphase flow blending flame stabilizing device of claim 1, wherein: the lobe mixer (1), the injection flame stabilizing support plate (2) and the mixer flange (3) are made of high-temperature alloy materials.
5. A combined power engine combustion chamber, characterized in that: the device comprises a combustion chamber straight section (6), a combustion chamber expansion section (7) and a tail nozzle (8) which are sequentially connected, and the integrated heterogeneous multiphase flow mixing flame stabilizing device according to any one of claims 1-4, wherein a mixer flange (3) of the flame stabilizing device is connected between the combustion chamber straight section (6) and the combustion chamber expansion section (7).
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| CN202210910202.4A CN115419917B (en) | 2022-07-29 | 2022-07-29 | Heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber |
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| CN115879396B (en) * | 2023-03-02 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Flow one-dimensional pneumatic design method for air inlet front chamber of high-altitude simulation test bed |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB836058A (en) * | 1956-07-13 | 1960-06-01 | Snecma | Improvements in flame spreading devices for combustion systems |
| 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 |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN104654362A (en) * | 2015-02-13 | 2015-05-27 | 中国人民解放军国防科学技术大学 | Large-scale hyshot scramjet engine and three-dimensional petal-shaped section combustor |
| CN104776448A (en) * | 2015-03-11 | 2015-07-15 | 北京航空航天大学 | Multifunctional mode adjustable flame stabilizing supporting plate |
| CN109654533A (en) * | 2018-12-04 | 2019-04-19 | 厦门大学 | A kind of trailing edge blowing formula stabilizer adapting to incoming flow distortion |
| CN110131074A (en) * | 2019-05-24 | 2019-08-16 | 西安航天动力研究所 | A kind of double elements air turbo rocket propulsion system |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
| CN110939530A (en) * | 2019-11-14 | 2020-03-31 | 西安航天动力研究所 | Mixed flame stabilizing device |
| CN113137628A (en) * | 2021-04-14 | 2021-07-20 | 西安航天动力研究所 | Combustion chamber of scramjet engine |
| CN216924353U (en) * | 2021-11-09 | 2022-07-08 | 天津宇澄久华节能环保技术有限公司 | Flame stabilizing device for burner flame in furnace |
| CN114738795A (en) * | 2022-04-14 | 2022-07-12 | 西北工业大学 | Support plate stabilizer with gas mixing function and integrated afterburner |
-
2022
- 2022-07-29 CN CN202210910202.4A patent/CN115419917B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB836058A (en) * | 1956-07-13 | 1960-06-01 | Snecma | Improvements in flame spreading devices for combustion systems |
| 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 |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN104654362A (en) * | 2015-02-13 | 2015-05-27 | 中国人民解放军国防科学技术大学 | Large-scale hyshot scramjet engine and three-dimensional petal-shaped section combustor |
| CN104776448A (en) * | 2015-03-11 | 2015-07-15 | 北京航空航天大学 | Multifunctional mode adjustable flame stabilizing supporting plate |
| CN109654533A (en) * | 2018-12-04 | 2019-04-19 | 厦门大学 | A kind of trailing edge blowing formula stabilizer adapting to incoming flow distortion |
| CN110131074A (en) * | 2019-05-24 | 2019-08-16 | 西安航天动力研究所 | A kind of double elements air turbo rocket propulsion system |
| CN110160083A (en) * | 2019-05-24 | 2019-08-23 | 西安航天动力研究所 | The steady flame device of gas-air mixer |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
| CN110939530A (en) * | 2019-11-14 | 2020-03-31 | 西安航天动力研究所 | Mixed flame stabilizing device |
| CN113137628A (en) * | 2021-04-14 | 2021-07-20 | 西安航天动力研究所 | Combustion chamber of scramjet engine |
| CN216924353U (en) * | 2021-11-09 | 2022-07-08 | 天津宇澄久华节能环保技术有限公司 | Flame stabilizing device for burner flame in furnace |
| CN114738795A (en) * | 2022-04-14 | 2022-07-12 | 西北工业大学 | Support plate stabilizer with gas mixing function and integrated afterburner |
Non-Patent Citations (1)
| Title |
|---|
| 《局部进气条件下空气涡轮火箭发动机掺混燃烧研究》;李文龙;推荐技术;20130930;第34卷(第9期);1222-1229 * |
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