CN115419917A - Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber - Google Patents
Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber Download PDFInfo
- Publication number
- CN115419917A CN115419917A CN202210910202.4A CN202210910202A CN115419917A CN 115419917 A CN115419917 A CN 115419917A CN 202210910202 A CN202210910202 A CN 202210910202A CN 115419917 A CN115419917 A CN 115419917A
- Authority
- CN
- China
- Prior art keywords
- stabilizing support
- flame stabilizing
- mixer
- flame
- support plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000000087 stabilizing effect Effects 0.000 title claims abstract description 91
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 64
- 238000002156 mixing Methods 0.000 title claims abstract description 39
- 238000002347 injection Methods 0.000 claims abstract description 67
- 239000007924 injection Substances 0.000 claims abstract description 67
- 239000000446 fuel Substances 0.000 claims abstract description 44
- 239000000956 alloy Substances 0.000 claims description 4
- 238000000034 method Methods 0.000 claims 1
- 239000007800 oxidant agent Substances 0.000 abstract description 5
- 230000001590 oxidative effect Effects 0.000 abstract description 5
- 239000007788 liquid Substances 0.000 description 11
- 239000007789 gas Substances 0.000 description 10
- 239000003921 oil Substances 0.000 description 7
- 230000000694 effects Effects 0.000 description 5
- 239000000945 filler Substances 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 4
- 230000006641 stabilisation Effects 0.000 description 4
- 238000011105 stabilization Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 239000004480 active ingredient Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 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
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- 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
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, which comprise a lobe mixer; the jetting flame stabilizing support plates are internally provided with jetting cavities, jetting holes communicated with the jetting cavities are formed in the surfaces of the jetting flame stabilizing support plates, the jetting flame stabilizing support plates are multiple, one ends of the jetting flame stabilizing support plates are connected to the tail ends of the lobe flow mixers along the airflow direction, and the other ends of the jetting flame stabilizing support plates are communicated with the flow mixer flange; the mixer flange is internally provided with a fuel channel and an oil supply connecting pipe nozzle communicated with the fuel channel, the fuel channel is communicated with the injection cavity, and the mixer flange is connected with the combustion chamber shell. The problem of the engine under different working modes different medium fuel and outer air (oxidant) high-efficient mixing burning is solved.
Description
Technical Field
The application relates to the technical field of air turbine rocket combined power engines, in particular to an air-gas-liquid mixing flame stabilizing device in an engine combustion chamber.
Background
The combined power engines such as Air Turbine Rocket (ATR) engines and the like have wide working ranges (Ma = 0-4), and parameters such as flow, speed, temperature, pressure, mixing ratio and the like of inlet air of a combustion chamber and rich gas are continuously changed along with the change of the working conditions of the engines. The stable and efficient combustion of the contained rich fuel gas and the contained air in the combustion chamber is organized, the stable and efficient combustion is vital to the performance of an engine, and the improvement of the mixing uniformity of the rich fuel gas and the air is the most effective way for realizing high-efficiency combustion in the combustion chamber. The research of scholars at home and abroad finds that the scheme of the wave-lobe type mixer can effectively solve the problem of mixing air and rich fuel gas (gas-gas).
However, with the continuous improvement of the power demand of the adjacent space, the performance demand of the air turbine rocket engine is improved, the original advantages of zero-speed takeoff, 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 required. To achieve this performance characteristic, the combined engine needs to operate in different operating modes, namely an ATR mode and a ram mode. Under the ram mode, a fuel supply system is introduced, and fuel and bypass air (gas-liquid) mixing combustion are realized, so that the cruise high-performance requirement is met. The difference of working media in different modes and the great change of the inflow parameters of the combustion chamber inlet under each mode along with the working condition bring great challenges to the high-efficiency combustion organization. However, the pure lobe mixer solution cannot achieve the purpose of gas-liquid mixing combustion.
Disclosure of Invention
The technical problem to be solved by 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 stabilizer, which realizes the efficient mixing and combustion of different media of fuel and oxidant (gas-gas and gas-liquid) of a combined power engine under different working modes and solves the problem of the efficient mixing and combustion of the fuel and the oxidant of the engine under different working modes.
The technical solution of the invention is as follows:
an integrated heterogeneous multiphase flow mixing flame stabilizing device and a lobe mixer; the jet flame stabilizing support plates are internally provided with jet cavities, the surfaces of the jet cavities are provided with jet holes communicated with the jet cavities, the jet flame stabilizing support plates are multiple, one ends of the jet flame stabilizing support plates are connected to the tail ends of the lobe mixer along the airflow direction, and the other ends of the jet flame stabilizing support plates are communicated with a mixer flange; the fuel channel is communicated with the injection cavity, and the 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 jetting cavity through the fuel channel, and is jetted from the jetting hole.
The lobe mixer is a chamfered lobe mixer.
One end of the injection flame stabilizing support plate is welded at the trough of the lobed flow mixer.
Lobes of the lobe mixer and the jetting flame stabilizing support plates are distributed in a staggered mode, and the number of the lobes and the number of the jetting flame stabilizing support plates are kept the same; the number of the active ingredients is 8 to 16.
The jetting flame stabilizing support plate comprises two connecting plates, an included angle between the two connecting plates is smaller than 180 degrees, one side of the included angle between the two connecting plates, which is smaller than 180 degrees, is an opening end of the jetting flame stabilizing support plate, and the opening end of the jetting flame stabilizing support plate faces back to the direction of air flow. Namely, the structure of the two connecting plates is arranged, so that the injection flame stabilizing support plate is V-shaped, and the opening direction of the V-shaped is back to the airflow direction.
The jetting flame stabilizing support plate and the rear end face of the lobe mixer form a certain angle, and the inclination angle alpha is 5-10 degrees. Namely, the included angle between the central line of the injection flame stabilizing support plate and the vertical plane of the central axis of the lobe mixer is 5-10, and one end of the injection flame stabilizing support plate, which is far away from the lobe mixer, is inclined along the incoming flow direction.
The length, the width and other dimensions of the injection flame-stabilizing support plate are selected according to design working condition parameters of the engine.
The ratio of the total projected area of the lobe flow mixer and the jet flame stabilizing support plate on the inner circle cross section of the flow mixer flange to the inner circle cross section of the flow mixer flange is defined as a total projected blocking ratio, and the value delta = 0.3-0.5.
The jet flame stabilizing support plate is internally provided with a fuel channel, the size of the fuel channel is selected according to the design working condition parameters of the engine, the leeward side of the jet flame stabilizing support plate is provided with jet holes, and the hole diameter is 0.5-2.0 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 selected according to the design working condition parameters of the engine.
The size of a built-in fuel channel of the mixer flange is selected according to the design working condition parameters of the engine.
The lobe flow mixer, the injection flame stabilizing support plate and the flow mixer flange are all made of high-temperature alloy materials.
A combined power engine combustion chamber comprises a combustion chamber straight section, a combustion chamber expansion section, a tail nozzle and an integrated heterogeneous multiphase flow mixing flame stabilizing device which are sequentially connected, the flow mixer flange of the flame stabilizing device is connected between the straight section of the combustion chamber and the expanding section of the combustion chamber, and the lobe flow mixer and the injection flame stabilizing support plate are positioned inside the straight section of the combustion chamber and the expanding section of the combustion chamber.
In summary, the present application at least includes the following beneficial technical effects:
the integrated heterogeneous multiphase flow mixing flame stabilizing device integrates the lobe flow mixer and the jet flame stabilizing structure, simultaneously considers two engine working modes, has few parts and simple structural system, realizes efficient, stable and reliable combustion of air, fuel-rich gas and liquid fuel, and meets the latest power performance requirement of the current combined power engine.
On one hand, under the ATR working mode, the turbulence degree in a combustion chamber is improved, the mixing effect of inner and outer culvert air currents is strengthened, the air-air mixing time is shortened, the length of the combustion chamber is reduced, the range of a low-speed backflow area at the rear of the mixer can be increased, and ignition, flame stabilization and flame conduction of the combustion chamber are facilitated. On the other hand, under the stamping working mode, a low-speed backflow area is formed at the downstream of the injection flame stabilizing support plate, the retention time of fuel oil is prolonged under the entrainment action of airflow, so that the liquid fuel oil has sufficient time to absorb heat, atomize and evaporate, the formation of combustible oil-gas mixture is facilitated, and the combustion chamber realizes continuous and stable combustion.
Drawings
FIG. 1 is a schematic structural diagram of an integrated heterogeneous multiphase flow blending flame stabilizer according to an embodiment of the invention;
FIG. 2 is a cross-sectional view of the flame holder of FIG. 1 in an axial direction;
FIG. 3 is a right side view of FIG. 2;
fig. 4 is a schematic view of an installation structure of the integrated heterogeneous multiphase flow blending flame holder in the combined power engine according to the embodiment of the invention.
Description of the reference numerals: 1. a lobed 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 nozzle.
Detailed Description
The present application is described in further detail below with reference to the following figures and specific examples:
aiming at the power performance requirement of the air turbine rocket combined power engine in the background technology, the width of an engine working package is wide, and two working modes exist in a combustion chamber: ATR mode and stamping mode. The oxidant in the combustion chamber is external bypass incoming flow air, parameters such as speed, temperature and flow greatly change along with modal working conditions, and the fuel respectively changes along with the working modal into kerosene rich fuel gas (ATR modal) and liquid kerosene (stamping modal). In order to simultaneously consider two working modes, the combustion chamber works reliably, flame is stable, and efficient mixing combustion is realized, the lobe flow mixer 1 and the injection flame stabilizing device are integrated into a whole, and the injection flame stabilizing structure is arranged on the lobe flow mixer 1 on the basis, so that the multi-mode working requirements of the engine are met.
The embodiment of the application discloses an integrated heterogeneous multiphase flow mixing flame stabilizing device, as shown in fig. 1 and 2, the device comprises a lobe flow mixer 1, a jetting flame stabilizing support plate 2 for jetting fuel oil, and an oil supply device for supplying oil to the jetting flame stabilizing support plate 2. The bypass air flows from the outer side of the lobe mixer 1 and is uniformly mixed with the fuel sprayed by the spraying flame stabilizing support plate 2, so that 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 injection holes 5 communicated with the injection cavity are arranged on the surface of the injection flame stabilizing support plate 2. The plurality of injection flame stabilizing support plates 2 are arranged, one ends of the plurality of injection flame stabilizing support plates 2 are connected to the tail end of the lobe mixer 1 along the airflow direction, and the other ends of the injection flame stabilizing support plates 2 are communicated with an oil supply device. Specifically, one end of the injection flame stabilizing support plate 2 is connected to the trough of the lobe flow mixer 1, the other end of the injection flame stabilizing support plate 2 extends in the direction far away from the axis of the lobe flow mixer 1, lobes of the lobe flow mixer 1 and the injection flame stabilizing support plate 2 are distributed in a staggered mode, and the number of the lobes of the lobe flow mixer 1 is the same as the number of the injection flame stabilizing support plates 2. The oil supply device comprises a mixer flange 3, a fuel passage is arranged in the mixer flange 3, the mixer flange 3 is provided with an oil supply connecting pipe nozzle 4 communicated with the fuel passage, and the fuel passage 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 are made of high-temperature alloy materials, and all parts are welded and assembled by high-temperature alloy welding wires. The jetting flame stabilizing support plate 2 is welded at the trough of the lobe mixer 1, forms a certain angle with the rear end face of the lobe mixer 1, and has an inclination angle alpha of 5-10 degrees, and the jetting flame stabilizing support plate 2 inclines along the incoming flow direction. The fuel oil sprayed from the injection holes is favorably injected 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 size parameters of the lobe mixer 1 and the injection flame stabilizing support plate 2, the ratio of the total projected area of the inner circle cross section of the mixer flange to the inner circle cross section of the mixer flange (which is defined as the total projected blockage ratio) is ensured, and the value is delta = 0.4-0.5. The blockage ratio is too large, the air flow circulation capacity is reduced, the total pressure loss is increased, and the performance of the combustion chamber is reduced. The blockage ratio is too small, the mixing effect of fuel and oxidant is poor, the combustion distance is prolonged, the combustion is insufficient, the flame stabilizing capability is reduced, and the performance of the combustion chamber is reduced.
The injection flame stabilizing support plate 2 comprises two connecting plates, the 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, which is perpendicular to the length direction of the injection flame stabilizing support plate 2, is V-shaped, the open end of the injection flame stabilizing support plate 2 is arranged on one side of the two connecting plates, the included angle is 30-50 degrees, 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 figure 4, a combination power engine combustion chamber, including the straight section 6 of combustion chamber, combustion chamber expansion section 7 to and foretell heterogeneous flow mixture flame stabilization device, flame stabilization device's mixer flange 3 passes through bolted connection between the straight section 6 of combustion chamber and combustion chamber expansion section 7, improves flame stabilization device's stability, and fuel feeding filler neck 4 can be located the straight section 6 of combustion chamber, the outside of combustion chamber expansion section 7, be convenient for through fuel feeding filler neck 4 to input fuel in the mixer flange 3.
The application has the implementation principle that:
when the combustion chamber works in an ATR mode, outer culvert air flows from the outer side of the lobe mixer 1, inner culvert fuel-rich gas flows from the inner side of the lobe mixer 1, the lobe mixer 1 is a beveling type lobe mixer 1, and the boundary layer viscous shearing action of two streams of air flow at the tail edge of a lobe is utilized for strengthening mixing. By beveling the trailing edge of the lobe mixer 1, the radial speed of the outlet airflow can be increased, and the mixing effect is improved. According to parameters such as inlet flow under different working conditions, the velocities of the fuel-rich gas and the outer culvert air at the outlet section of the lobe mixer 1 are equal by controlling the outlet area ratio of the fuel-rich gas and the outer culvert air. The oblique-cutting type lobe mixer 1 can be in a chrysanthemum-shaped structure, and each lobe is uniformly distributed in a radial mode by taking the axial center of the lobe mixer 1 as an original point. In consideration of weight reduction, the wall thickness of the lobe mixer 1 can be 1.0 mm-1.2 mm. In addition, the size parameters such as the number of lobes, the chamfer angle, the axial length and the like can be optimally designed according to the dimension of the combustion chamber and the inlet airflow parameter, the number of the lobes of the lobe mixer 1 can be selected between 8 and 16, and the chamfer angle of the trailing edge of the lobe is selected between 20 and 45 degrees.
When the combustion chamber works in a stamping mode, bypass air flows from the outer side of the lobe mixer 1, the supply of the fuel rich in the bypass is stopped, liquid fuel enters a built-in fuel channel in the mixer flange 3 from the fuel supply connecting nozzle 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 injection holes 5 in the injection flame stabilizing support plate 2 and is mixed and sheared with the bypass air, and the fuel-air mixture is formed through crushing and atomization, 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 in a bypass, entrainment of air flow occurs, a low-speed backflow zone is formed at the downstream, residence time of fuel oil is increased, atomization mixing effect is enhanced, and flame stabilizing effect is achieved. In addition, the injection hole 5 is 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 thermal protection of the injection flame stabilizing support plate 2 is solved. Firstly, the design of 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 sections of the fuel passages 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.
No matter the combustion chamber works in the ATR mode or the stamping mode, the injection flame stabilizing support plate 2 has the functions of stabilizing flame, enhancing mixing and transmitting flame.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications without departing from the spirit and scope of the present invention.
Claims (10)
1. An integrated heterogeneous multi-phase flow mixing flame-stabilizing device, the method is characterized in that: comprising a lobed mixer (1); the jet flame stabilizing support plate (2) is internally provided with a jet cavity, the surface of the jet flame stabilizing support plate is provided with a jet hole (5) communicated with the jet cavity, the jet flame stabilizing support plate (2) is provided with a plurality of jet flame stabilizing support plates, one ends of the jet flame stabilizing support plates (2) are connected to the tail end of the lobe mixer (1) along the airflow direction, lobes of the lobe mixer (1) and the jet flame stabilizing support plates (2) are distributed in a staggered mode, and the other end of the jet flame stabilizing support plate (2) is communicated with an oil supply device used for supplying oil to the jet cavity.
2. The integrated heterogeneous multiphase flow blending flame holder according to claim 1, wherein: the fuel supply device comprises a mixer flange (3), a fuel channel is arranged inside the mixer flange (3), the mixer flange (3) is provided with a fuel supply adapter (4) communicated with the fuel channel, the fuel channel is communicated with the injection cavity, and the mixer flange (3) is used for being connected with the combustion chamber shell.
3. The integrated heterogeneous multiphase flow blending flame holder according to 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 lobes of the lobe mixer (1) and the number of the injection flame stabilizing support plates (2) are kept the same.
4. The integrated heterogeneous multiphase flow blending flame holder according to claim 1, wherein: the jetting flame stabilizing support plate (2) comprises two connecting plates, an included angle between the two connecting plates is smaller than 180 degrees, one side of the included angle between the two connecting plates, which is smaller than 180 degrees, is an open end of the jetting flame stabilizing support plate (2), and the open end of the jetting flame stabilizing support plate (2) faces back to the direction of air flow.
5. The integrated heterogeneous multiphase flow blending flame holder according to claim 4, wherein: the included angle between the two connecting plates of the injection flame stabilizing support plate (2) is 30-50 degrees.
6. The integrated heterogeneous multiphase flow blending flame holder according to claim 1, wherein: an included angle between the central line of the injection flame stabilizing support plate (2) and a 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.
7. The integrated heterogeneous multiphase flow blending flame holder according to claim 1, wherein: 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).
8. The integrated heterogeneous multiphase flow blending flame holder according to claim 2, wherein: the ratio of the total projected area of the lobe mixer (1) and the jet flame-stabilizing support plate (2) on the inner circle section of the mixer flange (3) to the inner circle section of the mixer flange (3) is the total projected blockage ratio delta, and delta = 0.3-0.5.
9. The integrated heterogeneous multiphase flow blending flame holder according to claim 2, wherein: the lobe mixer (1), the injection flame stabilizing support plate (2) and the mixer flange (3) are all made of high-temperature alloy materials.
10. A combination power engine combustion chamber, characterized by: the heterogeneous multi-phase flow mixing flame-stabilizing device comprises a combustion chamber straight section (6), a combustion chamber expanding section (7) and a tail nozzle (8) which are sequentially connected, and the heterogeneous multi-phase flow mixing flame-stabilizing device as claimed in any one of claims 1 to 9, wherein a mixer flange (3) of the flame-stabilizing device is connected between the combustion chamber straight section (6) and the combustion chamber expanding section (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910202.4A CN115419917A (en) | 2022-07-29 | 2022-07-29 | Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910202.4A CN115419917A (en) | 2022-07-29 | 2022-07-29 | Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115419917A true CN115419917A (en) | 2022-12-02 |
Family
ID=84196365
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210910202.4A Pending CN115419917A (en) | 2022-07-29 | 2022-07-29 | Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115419917A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115879396A (en) * | 2023-03-02 | 2023-03-31 | 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/CN115419917A/en active Pending
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 |
|---|
| 李文龙: "《局部进气条件下空气涡轮火箭发动机掺混燃烧研究》", 推荐技术, vol. 34, no. 9, 30 September 2013 (2013-09-30), pages 1222 - 1229 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115879396A (en) * | 2023-03-02 | 2023-03-31 | 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1965197B (en) | Premix burner with staged liquid fuel supply and also method for operating a premix burner | |
| EP2466207A2 (en) | Fuel atomization dual orifice fuel nozzle | |
| CN109654533B (en) | Trailing edge air blowing type stabilizer adaptive to incoming flow distortion | |
| CN113280366B (en) | Afterburner structure based on self-excitation sweep oscillation fuel nozzle | |
| CA2761315A1 (en) | Aerodynamically enhanced fuel nozzle | |
| CN213300149U (en) | V-shaped flame stabilizer with turbulence structure capable of being premixed | |
| CN111121090A (en) | Swirl combustion chamber structure for improving mixing | |
| CN115419917A (en) | Integrated heterogeneous multiphase flow mixing flame stabilizing device and combined power engine combustion chamber | |
| CN114413282B (en) | Stabilizer for strengthening oil-gas mixing for ramjet engine | |
| CN113776082B (en) | Air-cooled wall type support plate combined flame stabilizer and combustion chamber | |
| CN110822475B (en) | On-duty flame stabilizer using air cooling structure to match ignition position and design method | |
| CN113606609A (en) | Combined stabilizer based on center step ignition and working method thereof | |
| RU2291975C1 (en) | Mixing head of chamber of liquid rocket engine | |
| CN113551265B (en) | Fuel nozzle and gas turbine | |
| CN113719857B (en) | Fuel oil atomization device and application thereof | |
| CN114046537A (en) | Combined premixing nozzle of microminiature gas turbine | |
| CN115164232B (en) | Baffle, baffle assembly and stabilizer | |
| CN115164233B (en) | Baffle assembly and stabilizer | |
| CN114294676B (en) | Pre-combustion chamber structure with wide ignition boundary | |
| CN116771549A (en) | Thrust chamber arrangement and method for operating a thrust chamber arrangement | |
| CN113108314A (en) | On-duty fuel nozzle tip, fuel nozzle and gas turbine | |
| CN216924348U (en) | Energy-saving gas burner | |
| US8701414B2 (en) | Injection device for combustion chambers of liquid-fueled rocket engines | |
| CN216841974U (en) | Gas mixer | |
| CN211902857U (en) | Air duct pipe and combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |