CN115076722B - Fuel pre-evaporation type concave cavity vortex flame stabilizer and working method thereof - Google Patents
Fuel pre-evaporation type concave cavity vortex flame stabilizer and working method thereof Download PDFInfo
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- CN115076722B CN115076722B CN202210616629.3A CN202210616629A CN115076722B CN 115076722 B CN115076722 B CN 115076722B CN 202210616629 A CN202210616629 A CN 202210616629A CN 115076722 B CN115076722 B CN 115076722B
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- air flow
- vortex flame
- flame stabilizer
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
Abstract
The invention discloses a fuel oil pre-evaporation type concave cavity vortex flame stabilizer and a working method thereof. The invention discloses an evaporative cavity trapped vortex flame stabilizer, which comprises a cavity trapped vortex flame stabilizer, an evaporation cavity arranged at the front end of the cavity trapped vortex flame stabilizer and an connotation bleed air flow passage arranged at the front end of the evaporation cavity, wherein the evaporation cavity is communicated with the cavity trapped vortex flame stabilizer through the cavity bleed air flow passage. According to the invention, the high-temperature fuel gas is introduced, the low-speed backflow area is formed in the evaporation cavity to realize premixing of the gaseous fuel oil and the content air flow, so that the uniformity of premixed gas in the concave cavity resident vortex area is ensured, and the ignition and flame stability performance of the combustion chamber are improved.
Description
Technical Field
The invention relates to an afterburner of a turbofan engine, a combustion chamber of a sub-combustion ramjet engine and a super combustion chamber of a turbofan/ramjet combined cycle engine, in particular to a fuel pre-evaporation type concave cavity trapped vortex flame stabilizer and a working method thereof.
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 local flow velocity flow conditions in the TBCC super combustor cause difficulties in ignition and flame stabilization in the multi-mode combustor due to the characteristic of large change of bypass ratio in the whole working range.
With the increase of the airflow speed and the decrease of the incoming flow temperature in the modern high-performance combustion chamber, in order to ensure the reliable ignition performance of the combustion chamber and reduce the flow loss caused by the flame stabilizer, the outer ring of the combustion chamber is usually subjected to soft ignition by adopting an on-duty flame stabilizer. The concave cavity vortex flame stabilizer has the advantages of low resistance loss, good flame stabilizing performance and the like, and becomes a flame stabilizer with great potential under a wide range of inflow conditions.
The concave cavity trapped vortex flame stabilizer is directly applied to a multi-mode combustion chamber, the performance of the flame stabilizer is necessarily limited by the severe flow conditions of the multi-mode combustion chamber, and the requirements of low-temperature and high-speed conditions in the multi-mode combustion chamber on ignition and flame stabilization far exceed the technical level of the existing afterburner and sub-combustion ram combustion chamber. In addition, the existing concave cavity standing vortex flame stabilizer is mainly provided with an oil supply mode by directly injecting the oil on the wall surface, and the fuel is easy to directly spray from a duty area and has low gas-phase fuel concentration in the area and fails to ignite due to poor atomization performance of the fuel under high-speed and low-temperature incoming flow. Therefore, the oil supply mode of the concave cavity trapped vortex flame stabilizer needs to be redesigned, so that the concave cavity trapped vortex flame stabilizer has wider lean oil ignition performance and flame stabilizing performance to meet the use requirement of large variation of incoming flow conditions in the whole working envelope of the multi-mode combustion chamber.
The inlet inflow working condition range of the multi-mode combustion chamber is wide, the inflow temperature is lower and the speed is higher when the air is high, so that liquid fuel is not easy to evaporate, and the residence time of the fuel in the duty area is short due to the mode that the fuel is directly injected into the duty area. The existing cavity trapped vortex flame stabilizer has the problems of lean oil ignition and insufficient stable combustion performance under low-temperature and high-speed air flow.
Disclosure of Invention
The invention aims to: in order to solve the problems in the prior art, the invention provides the fuel oil pre-evaporation type concave cavity trapped vortex flame stabilizer, which improves the ignition performance and flame stabilizing capability of the concave cavity trapped vortex flame stabilizer. The invention also provides a working method of the flame stabilizer.
The technical scheme is as follows: the invention discloses a fuel pre-evaporation type concave cavity trapped vortex flame stabilizer, which comprises a concave cavity trapped vortex flame stabilizer, an evaporation cavity arranged at the front end of the concave cavity trapped vortex flame stabilizer and an connotation bleed air flow passage arranged at the front end of the evaporation cavity, wherein the evaporation cavity is communicated with the concave cavity trapped vortex flame stabilizer through the concave cavity bleed air flow passage.
As a preferable structure of the invention, a fuel injection device is arranged above the inclusion bleed air flow passage or the evaporation cavity.
As a preferable structure of the invention, the evaporating cavity is a cavity with a triangular cross section.
As a preferable structure of the present invention, the inclusion bleed air flow channel is a long and narrow air flow channel arranged at the front end of the evaporation cavity.
As a preferable structure of the invention, the cavity bleed air flow channel is an air flow channel arranged above the cavity standing vortex flame stabilizer; and/or the cavity bleed air flow passage is rectangular.
As a preferred structure of the invention, the ratio of the width of the concave cavity bleed air flow channel 4 to the width of the inclusion bleed air flow channel 3 is 0.2-0.8.
As a preferable structure of the invention, the front end of the evaporation cavity is provided with a first flow dividing plate.
As a preferable structure of the invention, the rear end of the concave cavity trapped vortex flame stabilizer is provided with a second flow dividing plate.
As a preferable structure of the invention, the cavity standing vortex flame stabilizer comprises a main board which extends horizontally, a front wall which is arranged at the front end of the main board and is vertical to the main board, and a rear wall which is arranged at the rear end of the main board and is vertical to the main board; and/or the height of the front wall is greater than the height of the rear wall. As a preferable structure of the present invention, the ratio of the front wall height to the rear wall height is 0.5 to 0.8.
As a preferable structure of the invention, the evaporation chamber comprises an evaporation chamber front wall which is arranged at the front end of the main board and extends downwards in an inclined way, and an evaporation chamber lower wall which is arranged at the lower end of the front wall and extends horizontally.
The invention relates to a working method of a fuel oil pre-evaporation type concave cavity standing vortex flame stabilizer, which comprises the following steps:
(a) Before the combustion chamber ignites, the internal air flow and the external air flow respectively flow into the combustion chamber from the inner side and the outer side of the first flow dividing plate, wherein the internal air flow passes through the internal air flow dividing channel and forms a low-speed backflow area in the evaporation cavity;
(b) The oil injection device starts to supply oil to the evaporation cavity, and the liquid fuel is preheated and aerodynamic force by the high-temperature air flow of the connotation in the evaporation cavity and evaporated into a gaseous state to form premixed gas;
(c) Premixed gas in the evaporation cavity flows into the cavity standing vortex flame stabilizer through the cavity bleed air flow channel, and a stable low-speed vortex structure is formed in the cavity;
(d) The high-energy spark discharge ignites mixed gas in the cavity resident vortex area to form duty flame.
The beneficial effects are that: (1) According to the invention, the fuel oil pre-evaporation and the cavity standing vortex flame stabilizer are combined into a whole, the liquid fuel oil is preheated by utilizing the connotation high-temperature fuel gas, the atomization and evaporation of the fuel oil are accelerated, and the pre-mixing of the evaporated fuel oil and air is realized through a reflux zone in an evaporation cavity, so that the equivalent ratio of the cavity standing vortex area is improved, the ignition performance and flame stabilizing capability of the cavity standing vortex flame stabilizer are improved, and the problems of poor ignition and stable combustion performance of lean oil of the existing cavity standing vortex flame stabilizer under low-temperature and high-speed gas flow are solved; (2) According to the fuel pre-evaporation type concave cavity standing vortex flame stabilizer, atomization and evaporation of liquid fuel are accelerated by introducing high-temperature fuel gas, and lean oil point flameout limit of a combustion chamber flowing down at high speed and low temperature is widened; (3) According to the invention, the premixing of the gaseous fuel oil and the connotation air flow is realized through the low-speed backflow area in the evaporation cavity, the uniformity of premixed air in the concave cavity resident vortex area is ensured, and the ignition and flame stability performance of the combustion chamber are improved; (4) The pre-evaporation type oil supply mechanism is arranged close to the concave cavity vortex-resident stabilizer, so that the complexity of the stabilizer structure is reduced.
Drawings
FIG. 1 is a three-dimensional model of a fuel pre-evaporation type cavity trapped vortex flame holder;
FIG. 2 is a three-dimensional model of another embodiment of a fuel pre-evaporative recessed cavity trapped vortex flame holder;
FIG. 3 is a three-dimensional model diagram of a pre-evaporation type oil supply mechanism;
FIG. 4 is a three-dimensional model view of another embodiment of a pre-evaporative oil supply mechanism;
FIG. 5 is a schematic flow diagram of a fuel pre-evaporative type cavity trapped vortex flame holder;
FIG. 6 shows the streamline distribution in the fuel pre-evaporation type cavity trapped vortex flame holder calculated by Fluent software.
Detailed Description
Examples: as shown in fig. 1 to 4, the X direction described in the present embodiment is the front wall upper end to lower end (end) direction; the Y direction is the flow direction of the inlet airflow of the combustion chamber and is also the extending direction from the front end to the rear end; the Z-axis direction is the radial direction; the horizontal extension is the plane parallel direction formed by the Z-Y axis; the vertical extension is the parallel direction of the plane formed by the X-Z axis. The fuel pre-evaporation type cavity trapped vortex flame stabilizer comprises a cavity trapped vortex flame stabilizer 1, an evaporation cavity 2 arranged at the front end of the cavity trapped vortex flame stabilizer 1 and an connotation bleed air flow channel 3 arranged at the front end of the evaporation cavity 2, wherein the evaporation cavity 2 is communicated with the cavity trapped vortex flame stabilizer 1 through a cavity bleed air flow channel 4. The evaporating cavity 2 arranged at the front side of the concave cavity standing vortex flame stabilizer 1 and the oil supply mechanism 5 communicated with the evaporating cavity 2 form a pre-evaporating oil supply mechanism. The connotation high-temperature fuel gas entering the evaporation cavity 2 is introduced through the connotation air-entraining flow channel 3, the fuel oil is pre-evaporated in the evaporation cavity to form premixed gas, and the concave cavity air-entraining flow channel 4 sends the premixed gas formed in the evaporation cavity 2 into the concave cavity 100 of the concave cavity standing vortex flame stabilizer 1. As a preferred structure of the embodiment, the inclusion bleed air flow channel 3 is located below the evaporation cavity 2 and is a horizontally extending air flow channel.
According to the invention, the connotation and pre-evaporation oil supply mechanism and the concave cavity trapped vortex flame stabilizer 1 are communicated through the connotation air-entraining flow channel 3 and the concave cavity air-entraining flow channel 4, so that the integrated design of fuel pre-evaporation and concave cavity trapped vortex is realized, the rapid atomization and evaporation of fuel are realized through introducing connotation high-temperature fuel gas into the evaporation cavity, and a backflow area is formed in the abrupt space of the evaporation cavity through connotation airflow, so that the premixing of gaseous fuel and connotation airflow is realized.
As a specific embodiment, the cavity standing vortex flame stabilizer 1 has a cavity 100 and a main plate 101, a front wall 102 and a rear wall 103 enclosing the cavity 100. The front wall 102 and the rear wall 103 are fixed to the front end and the rear end of the main plate 101, respectively, and the front wall 102 and the rear wall 103 are disposed perpendicularly to the main plate 101, respectively. The main panel 101, the front wall 102 and the rear wall 103 enclose a cavity 100 located below the main panel 101. Meanwhile, the rear wall 103 is horizontally extended at its end with a second flow dividing plate 7.
In order to realize high-speed air flow, the cavity resident vortex area is less influenced by main flow, and meanwhile, after ignition, flame in the cavity resident vortex area can be transferred to the main flow, the height of the front wall 102 of the cavity resident vortex flame stabilizer is larger than that of the rear wall 103, and the ratio of the front wall height to the rear wall height is preferably 0.5-0.8.
The evaporation cavity 2 comprises an evaporation cavity upper wall 201 which extends obliquely upwards and is connected with the front end of the main board 101, and an evaporation cavity lower wall 202 which extends horizontally and is connected with the tail end of the front wall 102, the evaporation cavity lower wall 202 extends horizontally and is vertical to the front wall 102, the evaporation cavity upper wall 201 and the evaporation cavity lower wall 202 are connected through the front wall 102 to form the evaporation cavity 2, and a low-speed backflow area can be formed in a sudden space after the content high-temperature airflow enters the evaporation cavity 2 through the content air-entraining runner 3. The return region in the evaporation cavity 2 can prolong the residence time of the fuel, is favorable for evaporation of the fuel, and can be uniformly mixed with the connotation airflow through the return region, so that the uniformity of oil gas distribution in the concave cavity return region is ensured.
The front end of the upper wall 201 of the evaporation cavity horizontally extends to form a first flow dividing plate 6, the first flow dividing plate 6 is arranged in parallel with the lower wall 202 of the evaporation cavity, a long and narrow inclusion air flow channel 3 for introducing the inclusion air flow into the evaporation cavity is formed between the first flow dividing plate 6 and the lower wall 202 of the evaporation cavity, and the cross section (X axis-Y axis) of the inclusion air flow channel 3 is rectangular. The outlet of the content bleed air runner 3 is communicated with the evaporation cavity 2, the evaporation cavity 2 is communicated with the concave cavity 100 through a rectangular concave cavity bleed air runner 4 arranged above the front wall 102 (the concave cavity bleed air runner 4 extends along the Z-axis direction), and the concave cavity bleed air runner 4 is used as an outlet of premix air. In this embodiment, the cavity bleed flow channel 4 is disposed above the front wall 102, which improves the residence time of the premixed gas in the evaporation cavity 2, is beneficial to more fuel evaporation and uniform blending, and in addition, the cavity bleed flow channel 4 is disposed above the evaporation cavity 2, can form a backflow zone in the cavity 100, and is beneficial to rapidly spreading flame to the main stream after ignition.
In the invention, in order to reduce the excessive flow loss of the content high-temperature fuel gas in the pre-evaporation type oil supply mechanism, the structures of the content air-entraining runner 3 and the concave cavity air-entraining runner 4 are elongated rectangular channels serving as air inlet slits. In order to prevent the flame in the cavity from being transferred into the evaporation cavity, the ratio of the width (X direction) of the cavity bleed air flow channel 4 to the width (X direction) of the content bleed air flow channel 3 is preferably 0.2-0.8, so that the flame is quenched when entering the air inlet slit.
As a preferred embodiment of the present invention, the evaporation chamber 2 of the present invention can reduce the flow resistance of the air flow introduced from the concave cavity and the flow resistance of the air flow introduced from the external through the chamber which is configured to have a triangular cross section (X-axis-Y-axis plane). In addition, the pre-evaporation type oil supply mechanism is arranged close to the concave cavity standing vortex flame stabilizer, and the complexity of the stabilizer structure is reduced through the structural design.
As shown in fig. 1 and 2, the oil is supplied to the evaporation cavity 2 in two modes, one is directly injected into the evaporation cavity through the oil injection device 5, and the pre-evaporation is realized by utilizing the temperature and aerodynamic force of the inclusion air flow; another type of fuel is injected on the lower wall 202 of the evaporation cavity through the fuel injection device 5, the atomized fuel is crushed firstly, and then the temperature and aerodynamic force of the content bleed air flow are utilized for pre-evaporation. In particular, the injection device 5 of the present invention is arranged above the first flow dividing plate 6 in communication with the content bleed air flow channel 3 (indirectly in communication with the evaporation chamber 2). Or the oil supply device 5 is arranged on the upper wall 201 of the evaporation cavity and is directly communicated with the evaporation cavity 2. The oil spraying device 5 adopts the centrifugal nozzle with the existing structure, and the fuel oil sprayed by the centrifugal nozzle has smaller particle size, can be quickly evaporated in high-temperature fuel gas, and further improves the oil-gas ratio in the concave cavity.
The working flow of the fuel oil pre-evaporation type concave cavity standing vortex flame stabilizer is as follows:
(a) Before the combustion chamber ignites, as shown in fig. 5, the inner air flow and the outer air flow respectively flow into the combustion chamber from the inner side and the outer side of the first splitter plate 6, wherein the inner air flow forms a low-speed backflow area in the evaporation cavity 2 after passing through the inner air flow channel 3;
(b) The pre-evaporation type oil supply mechanism starts to supply oil to the evaporation cavity through the oil injection device 5, liquid fuel is preheated and aerodynamic force by the high-temperature air flow of connotation in the evaporation cavity 2, and is evaporated into a gaseous state, and at the moment, a low-speed backflow area in the evaporation cavity 2 has double functions: firstly, the low-speed backflow area prolongs the residence time of the fuel in the evaporation cavity, which is beneficial to the evaporation of more liquid fuel; secondly, the evaporated fuel oil can be uniformly mixed with the connotation airflow through a low-speed backflow area, and premixed gas is formed before entering the concave cavity;
(c) The premixed gas in the evaporation cavity 2 flows into the cavity standing vortex flame stabilizer through the cavity bleed air flow channel 4, a stable vortex structure is formed in the cavity 100, as shown in fig. 6, the complicated vortex structure in the cavity 100 is beneficial to the diffusion of the premixed gas to any area of the cavity, and meanwhile, the low-speed backflow area formed in the cavity 100 can increase the residence time of the premixed gas, so that a beneficial condition is created for the ignition on duty of the combustion chamber;
(d) And the high-energy spark discharge ignition ignites the gas mixture with proper gas-oil ratio in the cavity standing vortex area to form duty flame.
Application example: FIG. 6 shows the streamline distribution in the fuel pre-evaporation type concave cavity standing vortex flame stabilizer calculated by adopting Fluent software, the incoming flow speed is 100m/s, the incoming flow temperature is 900K, and the incoming flow temperature is 600K. As can be seen in fig. 6, a low-velocity recirculation zone is formed within the vaporization chamber of the pre-vaporization oil supply mechanism. As can also be seen from fig. 6, a triple vortex structure is formed in the concave cavity trapped vortex stabilizer, which is an angular vortex located at the upper left corner, a main vortex in the middle of the concave cavity and a sub-vortex below the concave cavity, respectively; the auxiliary vortex below the concave cavity not only can protect the main vortex from being influenced by the connotation main flow, but also can enhance the mass exchange between the main vortex and the main flow, and can spread high-temperature products generated by the main vortex to the main flow after ignition. In addition, the complex vortex flow structure formed in the concave cavity of the concave cavity standing vortex duty stabilizer is beneficial to improving the performance of the combustion chamber: 1) The complex flow field can improve the distribution uniformity of fuel oil and avoid local rich oil; 2) The high-temperature products gather in the concave cavity, and the air flow in the main flow is not involved in the concave cavity, so that the flame stabilizing performance is improved.
Claims (9)
1. The fuel oil pre-evaporation type cavity standing vortex flame stabilizer is characterized by comprising a cavity standing vortex flame stabilizer (1), an evaporation cavity (2) arranged at the front end of the cavity standing vortex flame stabilizer (1) and an inclusion bleed air flow passage (3) arranged at the front end of the evaporation cavity (2), wherein the evaporation cavity (2) is communicated with the cavity standing vortex flame stabilizer (1) through a cavity bleed air flow passage (4); the evaporation cavity (2) is a protruding cavity with a triangular section; the width of the inclusion bleed air flow passage (3) is larger than that of the concave cavity bleed air flow passage (4).
2. The fuel pre-evaporation type concave cavity standing vortex flame stabilizer according to claim 1, wherein a fuel injection device (5) is arranged above the inclusion air-guiding flow channel (3) or the evaporation cavity (2).
3. The fuel pre-evaporation type concave cavity standing vortex flame stabilizer according to claim 1, wherein the inclusion air flow channel (3) is a long and narrow air flow channel arranged at the front end of the evaporation cavity (2).
4. A fuel pre-evaporation type cavity trapped vortex flame holder as claimed in claim 3, wherein the cavity bleed air flow channel (4) is an air flow channel arranged above the cavity trapped vortex flame holder (1); and/or the cavity bleed air runner (4) is rectangular.
5. The fuel pre-evaporation type concave cavity trapped vortex flame holder according to claim 1, wherein a first flow dividing plate (6) is arranged at the front end of the evaporation cavity (2).
6. The fuel pre-evaporation type concave cavity trapped vortex flame holder according to claim 5, wherein a second flow dividing plate (7) is arranged at the rear end of the concave cavity trapped vortex flame holder (1).
7. The fuel pre-evaporation type cavity trapped vortex flame holder as claimed in claim 6, wherein the cavity trapped vortex flame holder (1) comprises a horizontally extending main plate (101), a front wall (102) arranged at the front end of the main plate (101) and arranged vertically to the main plate (101), and a rear wall (103) arranged at the rear end of the main plate (101) and arranged vertically to the main plate (101); and/or the height of the front wall (102) is greater than the height of the rear wall (103).
8. The fuel pre-evaporation type cavity standing vortex flame holder according to claim 7, wherein the evaporation cavity (2) comprises an evaporation cavity front wall (201) extending obliquely downwards and arranged at the front end of the main plate (101), and an evaporation cavity lower wall (202) extending horizontally and arranged at the lower end of the front wall (102).
9. The method of operating a fuel pre-evaporative re-entrant vortex flame holder as claimed in claim 1, comprising the steps of:
(a) Before the combustion chamber ignites, the internal air flow and the external air flow respectively flow into the combustion chamber from the inner side and the outer side of the first flow dividing plate, wherein the internal air flow forms a low-speed backflow area in the evaporation cavity (2) after passing through the internal air flow dividing channel (3);
(b) The oil injection device (5) starts to supply oil to the evaporation cavity (2), and the liquid fuel is preheated and aerodynamic force by the content high-temperature airflow in the evaporation cavity (2) and evaporated into gas state to form premixed gas;
(c) Premixed gas in the evaporating cavity (2) flows into the cavity vortex flame stabilizer (1) through the cavity bleed air flow channel (4) to form a stable low-speed vortex structure in the cavity;
(d) The high-energy spark discharge ignites mixed gas in the cavity resident vortex area to form duty flame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210616629.3A CN115076722B (en) | 2022-06-01 | 2022-06-01 | Fuel pre-evaporation type concave cavity vortex flame stabilizer and working method thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210616629.3A CN115076722B (en) | 2022-06-01 | 2022-06-01 | Fuel pre-evaporation type concave cavity vortex flame stabilizer and working method thereof |
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| CN115076722A CN115076722A (en) | 2022-09-20 |
| CN115076722B true CN115076722B (en) | 2023-06-06 |
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| CN112610982A (en) * | 2020-12-16 | 2021-04-06 | 江苏科技大学 | Standing vortex combustor head device capable of inhibiting main flow from being sucked into cavity |
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| US6481209B1 (en) * | 2000-06-28 | 2002-11-19 | General Electric Company | Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer |
| AU2009352301B2 (en) * | 2009-09-13 | 2015-07-30 | Lean Flame, Inc. | Inlet premixer for combustion apparatus |
| US9068751B2 (en) * | 2010-01-29 | 2015-06-30 | United Technologies Corporation | Gas turbine combustor with staged combustion |
| CN103277816B (en) * | 2013-05-10 | 2015-09-09 | 南京航空航天大学 | Lean premixed preevaporated low emission standing vortex burning chamber |
| CN106907739B (en) * | 2017-02-08 | 2019-06-04 | 南京航空航天大学 | A kind of standing vortex burning chamber head device and its working method |
| CN111706879B (en) * | 2020-06-10 | 2023-06-27 | 中国空气动力研究与发展中心 | Flame-stabilizing concave cavity and oil-gas matching device for duty stage of vortex-holding combustion chamber |
| CN113757723B (en) * | 2021-09-03 | 2022-10-21 | 南京航空航天大学 | Composite impact air film cooling wall type flame stabilizer and combustion chamber |
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| CN112610982A (en) * | 2020-12-16 | 2021-04-06 | 江苏科技大学 | Standing vortex combustor head device capable of inhibiting main flow from being sucked into cavity |
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