CN115076723B - Concave cavity standing vortex stabilizer and working method thereof - Google Patents
Concave cavity standing vortex stabilizer and working method thereof Download PDFInfo
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- CN115076723B CN115076723B CN202210616900.3A CN202210616900A CN115076723B CN 115076723 B CN115076723 B CN 115076723B CN 202210616900 A CN202210616900 A CN 202210616900A CN 115076723 B CN115076723 B CN 115076723B
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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
- F23R3/02—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
- F23R3/34—Feeding into different combustion zones
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses a concave cavity standing vortex stabilizer and a working method thereof. The concave cavity standing vortex stabilizer comprises a concave cavity standing vortex flame stabilizer, a first evaporation cavity and a second evaporation cavity, wherein the first evaporation cavity is arranged in front of the concave cavity standing vortex flame stabilizer, the second evaporation cavity is arranged behind the concave cavity standing vortex flame stabilizer, the first evaporation cavity is communicated with the concave cavity of the concave cavity standing vortex flame stabilizer through a first air-entraining flow passage, and the second evaporation cavity is communicated with the concave cavity of the concave cavity standing vortex flame stabilizer through a second air-entraining flow passage; the front of the first evaporation cavity is communicated with the inner culvert air-entraining flow passage, and the front of the second evaporation cavity is communicated with the outer culvert air-entraining flow passage; a first oil injection device is arranged above the first evaporation cavity, and a second oil injection device is arranged above the second evaporation cavity. The concave cavity standing vortex stabilizer can adjust oxygen content and fuel distribution in an on-duty area, improve gas-phase fuel proportion in a concave cavity backflow area and improve ignition performance of a combustion chamber.
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 concave cavity standing vortex stabilizer and a working method thereof.
Background
As an air-breathing engine, a Turbine-based combined cycle (TBCC) has the performance advantages of wide flight range, conventional take-off and landing, reusability and the like, and is considered to be the most promising hypersonic aircraft power device at the present stage. As one of the important components of the TBCC engine, the reliable operation of the multi-modal combustion chamber is an important guarantee for the propulsion performance of the TBCC engine.
The flow conditions of low incoming flow temperature and excessive local flow velocity inside the TBCC super combustor due to the characteristic that the bypass ratio varies greatly in the whole working range bring difficulties to ignition and flame stabilization inside the multi-mode combustor. In order to ensure reliable ignition performance of the combustion chamber and reduce flow loss caused by the flame stabilizer, the flame stabilizer on duty is usually adopted for soft ignition in the outer ring of the combustion chamber. The concave cavity standing vortex flame stabilizer has the advantages of low resistance loss, good flame stabilizing performance and the like, so that the concave cavity standing vortex flame stabilizer has great potential under the condition of wide incoming flow.
The cavity standing vortex flame stabilizer is directly applied to the multi-mode combustion chamber, and the performance of the cavity standing vortex flame stabilizer is necessarily limited by the harsh flow conditions of the multi-mode combustion chamber. Different from the traditional afterburner with stress application and stamping, in order to ensure that the multi-mode combustor can work reliably in a flight envelope, the flame stabilizer is required to have good flame stabilization and combustion performance in a stress application mode with low oxygen content in incoming flow; the ram mode with the low temperature of the incoming flow, which causes poor fuel evaporation, has wider lean ignition performance. Most of the existing cavity standing vortex flame stabilizers are designed based on a single afterburner or a stamping combustor, have good ignition performance when being applied to a conventional afterburner or stamping combustor, but need to give consideration to the use requirements under afterburning and stamping modes simultaneously in a multi-mode combustor, and have insufficient ignition and flame stabilization performance under wide-range working condition change: when the multi-mode combustion chamber is in a stress application mode, the included incoming flow temperature is high, the oxygen content is low, so that the chemical reaction is obviously weakened, the working condition of the combustion chamber is rapidly deteriorated, and the disadvantage is brought to the flame stabilization; when the multi-mode combustion chamber is in a stamping mode, the oxygen content of the included incoming flow is increased, the temperature is reduced, liquid fuel oil is not easy to evaporate, and the gas-phase fuel oil in a duty area is low in concentration and not beneficial to ignition. Therefore, the oil supply mode and the flow field organization method of the conventional concave cavity standing vortex flame stabilizer need to be redesigned, so that the fuel can be stably organized and combusted in an afterburning mode, and the ignition performance is superior in a stamping mode, so that the use requirement in a multi-mode combustion chamber can be met.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a concave cavity standing vortex stabilizer, which is characterized in that evaporation cavities are arranged at the front end and the rear end of the concave cavity standing vortex stabilizer, so that the flame stabilization and the combustion performance of a combustion chamber are improved; the cavity is supplied with oil in the stamping mode, the fuel oil distribution of the cavity is adjusted, the proportion of gas-phase fuel oil in a cavity backflow region is improved, the ignition performance of a combustion chamber is improved, and the problems that the flame is difficult to stabilize in the stress application mode and difficult to ignite in the stamping mode of the existing cavity standing vortex flame stabilizer are solved. The invention also provides a working method of the concave cavity standing vortex stabilizer.
The technical scheme is as follows: the concave cavity standing vortex stabilizer comprises a concave cavity standing vortex flame stabilizer, a first evaporation cavity arranged in front of the concave cavity standing vortex flame stabilizer and a second evaporation cavity arranged behind the concave cavity standing vortex flame stabilizer, wherein the first evaporation cavity is communicated with the concave cavity of the concave cavity standing vortex flame stabilizer through a first air-entraining flow channel, and the second evaporation cavity is communicated with the concave cavity of the concave cavity standing vortex flame stabilizer through a second air-entraining flow channel; the front of the first evaporation cavity is communicated with the inner culvert air-entraining flow passage, and the front of the second evaporation cavity is communicated with the outer culvert air-entraining flow passage; a first oil injection device is arranged above the first evaporation cavity, and a second oil injection device is arranged above the second evaporation cavity.
The concave cavity standing vortex stabilizer can adjust oxygen content and fuel oil distribution in an on-duty area, and improves flame stabilization and combustion performance of a combustion chamber by arranging a first evaporation cavity and a second evaporation cavity at the front end and the rear end of the concave cavity standing vortex stabilizer, wherein the first evaporation cavity is used for main oil supply of the concave cavity, and the second evaporation cavity is used for introducing external air flow to supplement oxygen for the concave cavity in an afterburning mode; the cavity is supplied with oil in a stamping mode, the distribution of fuel oil of the cavity is adjusted, the proportion of gas-phase fuel oil in a backflow area of the cavity is increased, the ignition performance of a combustion chamber is improved, and the problems that the flame is difficult to stabilize in a stress application mode and the ignition is difficult in the stamping mode of the conventional cavity standing vortex flame stabilizer are solved.
As a preferred embodiment of the present invention, the cavity standing vortex flame stabilizer comprises a cavity, and a front wall, a main plate and a rear wall enclosing the cavity.
In a preferred embodiment of the present invention, the first evaporation chamber includes a first evaporation chamber upper wall plate extending obliquely upward and connected to the main plate, and a first evaporation chamber lower wall plate extending horizontally.
In a preferred embodiment of the present invention, the front end of the upper wall plate of the first evaporation chamber extends horizontally with an inner culvert and an outer culvert splitter plate. As a preferred embodiment of the present invention, a culvert bleed air flow channel for introducing a culvert air flow into the first evaporation chamber is formed between the culvert shunting plates and the lower wall plate of the first evaporation chamber, and the culvert bleed air flow channel is rectangular.
In a preferred embodiment of the present invention, the second evaporation chamber comprises a first flow dividing plate, a second flow dividing plate extending horizontally and a second evaporation chamber upper wall connected with the end of the second flow dividing plate and extending obliquely downwards; as a preferred embodiment of the present invention, a culvert bleed air flow channel for introducing a culvert air flow into the second evaporation chamber is formed between the first flow dividing plate and the main plate, and the culvert bleed air flow channel is rectangular.
In a preferred embodiment of the invention, the second oil injection device is arranged on the first splitter plate.
In a preferred embodiment of the present invention, the first bleed air channel and the second bleed air channel are distributed in a staggered manner.
As a preferred embodiment of the present invention, the first bleed air channel and the second bleed air channel are both rectangular channels.
In a preferred embodiment of the present invention, the first oil injection device is disposed on the first evaporation chamber upper wall plate.
As a preferred embodiment of the invention, the first bleed air channel is arranged above the front wall and the second bleed air channel is arranged below the rear wall.
The working method of the cavity standing vortex stabilizer comprises the following steps:
(a) The multi-mode combustor is in an afterburner mode: the inner culvert high-temperature fuel gas enters the first evaporation cavity through the inner culvert air-entraining flow channel to preheat liquid fuel oil sprayed out by the first oil injection device and entering the first evaporation cavity, the backflow region of the first evaporation cavity is utilized to complete premixing of oil gas, premixed oil gas enters the cavity through the first air-entraining flow channel, a vortex structure formed in the cavity sends the premixed gas to each region of an on-duty region to create favorable conditions for on-duty ignition, at the moment, the second oil injection device does not work, outer culvert airflow enters the second evaporation cavity through the outer culvert air-entraining flow channel and then enters the cavity through the second air-entraining flow channel, the oxygen content of the combustion chamber is improved, and oil mist in the on-duty region is uniformly distributed;
(b) When the multi-mode combustor is switched to the ram mode: the first oil injection device and the second oil injection device work simultaneously, the connotative airflow enters the first evaporation cavity through the connotative air-entraining flow channel to preheat the liquid fuel sprayed by the first oil injection device, and the premixed oil and gas in the first evaporation cavity enters the cavity through the first air-entraining flow channel; the outer culvert air current gets into second evaporation chamber through outer culvert bleed runner, and second fueling injection equipment spun liquid fuel at first passes through the broken atomizing of mainboard, further atomizing evaporation in second evaporation chamber, and the premix gas in the second evaporation chamber gets into the cavity through second bleed runner, plays the effect that adjusts the district's on duty oil gas distribution to form stable low-speed backward flow district with the premix gas that comes from first evaporation chamber, provide the advantage for the ignition on duty.
Has the advantages that: (1) According to the invention, by adding the second evaporation cavity, the second evaporation cavity is used for guiding the outer culvert airflow to supplement oxygen for the cavity combustion area in the stress application mode, so that the flame stabilization and combustion performance of the combustion chamber are improved; the oil is supplied to the concave cavity in the stamping mode, so that the proportion of gas-phase fuel oil of the concave cavity is increased, and the ignition performance of the combustion chamber is improved; (2) According to the invention, the low-speed backflow regions in the first evaporation cavity and the second evaporation cavity can realize the premixing of the gaseous fuel and the air-entraining airflow, so that the uniformity of premixed gas in the backflow region of the concave cavity is ensured, and the ignition position is widened; (3) According to the invention, the first evaporation cavity and the second evaporation cavity are arranged close to the cavity standing vortex stabilizer, the front wall of the cavity standing vortex stabilizer can be cooled by fuel evaporation in the first evaporation cavity, and the main board and the rear wall can be cooled by bypass airflow of the second evaporation cavity, so that the structural complexity of the stabilizer is reduced.
Drawings
FIG. 1 is a three-dimensional model of a reentrant trapped vortex stabilizer of the present invention;
FIG. 2 is a schematic flow diagram of the re-entrant trapped vortex stabilizer of the present invention;
FIG. 3 is a streamline distribution diagram of a concave cavity standing vortex stabilizer obtained by Fluent calculation;
FIG. 4 is a gas phase fuel distribution plot of a Fluent calculated reentrant trapped vortex stabilizer.
Detailed Description
Example 1: as shown in fig. 1, in the present embodiment, a recessed cavity standing vortex stabilizer capable of adjusting oxygen content and fuel distribution in an on-duty area is provided, and a recessed cavity standing vortex flame stabilizer 1 in the present embodiment has a recessed cavity 100, and a front wall 101, a main plate 102 and a rear wall 103 which form the recessed cavity, in the present invention, the front wall 101, the main plate 102 and the rear wall 103 are connected and positioned with respect to each other in an existing structure, and the front wall 101, the main plate 102 and the rear wall 103 jointly enclose the recessed cavity 100 located below the main plate 102. The horizontal extending direction described in this embodiment is a direction parallel to the Z axis-Y axis; extending vertically downward in a direction parallel to the X-axis and the front-to-back direction is in a direction parallel to the Y-axis. As can be seen from fig. 1, the reentrant standing vortex stabilizer comprises a reentrant standing vortex flame stabilizer 1, a first evaporation cavity 2 arranged in front of the reentrant standing vortex flame stabilizer 1, and a second evaporation cavity 3 arranged behind the reentrant standing vortex flame stabilizer 1, wherein the first evaporation cavity 2 is communicated with a reentrant 100 of the reentrant standing vortex flame stabilizer 1 through a first bleed air flow passage 4, and the second evaporation cavity 3 is communicated with the reentrant 100 of the reentrant standing vortex flame stabilizer 1 through a second bleed air flow passage 5; the front of the first evaporation cavity 2 is communicated with a culvert air-entraining flow passage 6, and the front of the second evaporation cavity 3 is communicated with a culvert air-entraining flow passage 7; a first oil injection device 8 is arranged above the first evaporation cavity 2, and a second oil injection device 9 is arranged above the second evaporation cavity 3.
According to the invention, the first evaporation cavity 2 and the second evaporation cavity 3 are respectively arranged in front of and behind the concave cavity 100, the first evaporation cavity 2 and the second evaporation cavity 3 are both of cavity structures with triangular sections (X-Y axes), and evaporation and premixing of fuel oil are realized through the first evaporation cavity 2 and the second evaporation cavity 3. The second evaporation cavity 3 is used for guiding the bypass airflow to supplement oxygen for the cavity in the boost mode, so that the flame stabilization and the combustion performance of the combustion chamber are improved, the cavity is supplied with oil in the stamping mode, the proportion of gas-phase fuel in a cavity backflow area is improved, and the ignition performance of the combustion chamber is improved. According to the invention, through the matching of the first air-entraining flow passage and the second air-entraining flow passage, oil gas of the concave cavity is uniformly distributed, the oil-gas ratio of the concave cavity is adjusted, and the ignition position is widened.
The front wall 101 of the cavity standing vortex flame stabilizer is formed by a wall plate vertically extending downwards from the front end of the main plate 102, a first evaporation cavity 2 is arranged on the front side of the front wall 101, the first evaporation cavity 2 is surrounded by a first evaporation cavity upper wall plate 201, a first evaporation cavity lower wall plate 202 and the front wall 101, specifically, the lower end of the front wall 101 horizontally extends to form the first evaporation cavity lower wall plate 202, and the upper end of the front wall 101 obliquely extends downwards to form the first evaporation cavity upper wall plate 201. The horizontal extension of first evaporation chamber upper wall plate 201 front end has inside and outside culvert flow distribution plate 10, has formed between inside and outside culvert flow distribution plate 10 and the first evaporation chamber lower wall plate 202 that the culvert bleed runner 6, is provided with first oil jet equipment 8 on the first evaporation chamber upper wall 201, and first oil jet equipment 8 is the 2 fuel supplies of first evaporation chamber.
In this embodiment, the rear wall 103 of the recessed cavity trapped vortex flame stabilizer 1 is formed by a wall plate extending vertically downward from the rear end of the main plate 102, a first flow dividing plate 301 is disposed above the rear wall 103, a second evaporation cavity upper wall 303 extends obliquely downward from the rear end of the first flow dividing plate 301, and a second flow dividing plate 302 extends horizontally from the end of the second evaporation cavity upper wall 303. The second splitter plate 302, the rear wall 103 and the upper wall 303 of the second evaporation cavity are connected to form a second evaporation cavity 3, and a bypass bleed air channel is formed between the first splitter plate 301 and the main plate 102. And a second oil injection device 9 is arranged above the first splitter plate 301, and the second oil injection device 9 supplies oil to the second evaporation cavity 3.
In this embodiment, the first oil injection device 8 and the second oil injection device 9 both adopt centrifugal nozzles with existing structures, and fuel oil sprayed by the centrifugal nozzles has smaller particle size, can be quickly evaporated in high-temperature fuel gas, and further improves the oil-gas ratio in the concave cavity.
As can be seen from the structure of fig. 1, the reentrant trapped vortex stabilizer of the present invention forms a culvert bleed air flow passage 6 between the culvert diverter plate 10 and the lower wall 202 of the first evaporation chamber for introducing a culvert air flow into the first evaporation chamber 2, and forms a culvert bleed air flow passage 7 between the main plate 102 and the first diverter plate 301 for introducing a culvert air flow into the second evaporation chamber 3. In addition, the front wall 101 is provided with a first air-entraining channel 4 for introducing the premixed air in the first evaporation cavity 2 into the cavity 100, the rear wall 103 is provided with a second air-entraining channel 5 for introducing the bypass air flow or the premixed air in the second evaporation cavity 3 into the cavity 100, specifically, the first air-entraining channel 4 is provided above the front wall 101, and the second air-entraining channel 5 is provided below the rear wall 103. A first evaporation cavity 2 and a second evaporation cavity 3 which are arranged in the invention are both communicated with a concave cavity 100 of a concave cavity standing vortex flame stabilizer 1 to form a circulation area, the first evaporation cavity 2 is communicated with a culvert through a culvert air-entraining flow passage 6, and is communicated with the concave cavity through a concave cavity first air-entraining flow passage 4; the second evaporation cavity is communicated with the culvert through a culvert air-entraining flow passage and is communicated with the cavity through a cavity second air-entraining flow passage. In order to reduce flow losses, the first bleed air channel 4 and the second bleed air channel 5 are rectangular near-term channels extending in a direction parallel to the Z-axis, and the culvert bleed air channel 6 and the culvert bleed air channel 7 are also configured as elongated rectangular channels serving as air inlet slits.
In order to realize adjustable fuel distribution of the concave cavity, the first fuel injection device 8 is a main fuel supply device, and the second fuel injection device 9 is an auxiliary fuel supply device; meanwhile, the first bleed air channel 4 and the second bleed air channel 5 are distributed in a staggered manner, as shown in fig. 2, the premixed gas in the first evaporation cavity 2 can flow to any position of the cavity 100 through a downstream line of the first bleed air channel 4, and the premixed gas in the second evaporation cavity 3 flows into the cavity 100 through a downstream line of the second bleed air channel 5, so that on one hand, the formation of a cavity backflow area is promoted, and the uniform distribution of cavity fuel oil is realized; on the other hand, the gas-phase fuel which supplements the concave cavity can flow down at the low temperature of the stamping mode, thereby playing the role of adjusting the fuel distribution of the concave cavity. In addition, since the flow direction of the premixed gas entering the cavity from the first evaporation chamber 2 and the second evaporation chamber 3 is the same as the movement direction of the cavity return flow region, the fuel can be diffused to any region of the cavity to expand the arrangement range of the ignition nozzle.
In order to realize oxygen supplementation for the cavity in the stress application mode, the second evaporation cavity 3 introduces airflow with higher oxygen content in the outer culvert through the outer culvert air-entraining flow passage 7, then the air in the outer culvert enters the cavity through the second air-entraining flow passage 5, and the uniform mixing with the premixed gas from the first evaporation cavity 2 is realized through the backflow area formed in the cavity, the premixed gas with higher oxygen content is formed in the cavity, and favorable conditions are created for stable combustion after ignition.
In order to ensure the structural reliability of the hot end component of the cavity trapped vortex stabilizer, the front wall 101 absorbs heat by virtue of the evaporation of the liquid fuel in the first evaporation cavity 2, and the main plate 102 and the rear wall 103 realize cooling by virtue of forced convection when the bypass airflow flows through the bypass bleed air flow passage 7 and the second evaporation cavity 3.
The working method of the cavity standing vortex stabilizer in this embodiment is as follows:
(a) The multi-mode combustor is in a boost mode: the connotation incoming flow temperature is high, and the oxygen content is low for chemical reaction is showing and is weakening, and combustion chamber operating condition sharply worsens, brings the disadvantage for the flame stabilization, for the oxygen content that improves the combustion chamber, and second oil supply unit 9 during afterburning mode is out of work, and the connotation air current gets into second evaporation chamber 3 through connotation bleed runner 7 outward, and rethread second bleed runner 5 gets into the cavity, and the connotation bleed this moment has dual function: 1) Increasing the oxygen content of the combustion chamber; 2) The flow of the duty area is promoted, so that the oil mist distribution of the duty area is uniform; the oil supply of the cavity standing vortex flame stabilizer 1 mainly depends on a first oil injection device 8, the connotative high-temperature fuel gas enters a first evaporation cavity 2 through a connotative air-entraining flow passage 6 to preheat liquid fuel oil sprayed by the first oil supply device 8, the premixing of the fuel oil is completed by utilizing a backflow area of the first evaporation cavity 2, finally the premixed gas enters the cavity through a first air-entraining flow passage 4, and finally the premixed gas is sent to each area of an on-duty area through a vortex system structure formed in the cavity 100, so that favorable conditions are created for on-duty ignition;
(b) When the multi-mode combustor is switched to the ram mode: the oxygen content of the connotative inflow is increased, the temperature is reduced, liquid fuel oil is not easy to evaporate, and the key for ignition is how to ensure that the ignition region on duty has high gas-phase oil-gas ratio. Therefore, in the pressing mode, the first oil supply device 8 and the second oil supply device 9 operate simultaneously. The connotation air flow enters the first evaporation cavity 2 through the connotation air-entraining flow channel 6 to preheat the liquid fuel sprayed by the first fuel supply device 8, the return flow area in the first evaporation cavity 2 can prolong the retention time of the fuel, and the precombustion of the connotation air flow and the gaseous fuel is realized, thereby being beneficial to improving the evaporation effect of the fuel when the incoming flow temperature is reduced. Premixed oil and gas in the first evaporation cavity 2 enter the cavity 100 through the first bleed air flow passage 4. The outer culvert air current gets into second evaporation chamber 3 through outer culvert bleed air runner 7, and the liquid fuel of second oil supply unit 9 spun is at first through the broken atomizing of mainboard, and the aerodynamic force through outer culvert air current is used in further atomizing evaporation in second evaporation chamber 3 again, is favorable to improving the gaseous phase fuel proportion in the middle of the second evaporation chamber mixes the gas in advance. Finally, the premixed gas in the second evaporation cavity enters the cavity 100 through the second air-entraining flow channel 5, so that the oil-gas distribution in the on-duty area is adjusted, and a stable low-speed backflow area is formed with the premixed gas from the first evaporation cavity 2, thereby providing favorable conditions for on-duty ignition.
Application example:
FIG. 3 is a streamline distribution in the reentrant trapped vortex stabilizer calculated by using Fluent software, wherein the incoming flow speed is 100m/s, the internal incoming flow temperature is 900K, and the external incoming flow temperature is 600K. As can be seen from fig. 3, the reentrant trapped vortex stabiliser forms a triple vortex structure, namely a primary vortex located in the middle of the reentrant 100 and two secondary vortices located below the reentrant 100; the main vortex is mainly formed by inner-culvert bleed air and partial outer-culvert bleed air, and the addition of the outer-culvert bleed air can not only supplement oxygen for the main vortex, but also promote the uniform distribution of fuel oil; the auxiliary vortex below the cavity is formed by the shearing action of the main flow of the outer culvert bleed air flow, so that the main vortex can be protected from being influenced by the inner culvert main flow, the mass exchange between the main vortex and the main flow can be enhanced, and a high-temperature product generated by the main vortex can be transmitted to the main flow after ignition.
Fig. 4 shows the gas phase fuel distribution in the cavity calculated by the Fluent software, the first fuel injection device 8 and the second fuel injection device 9 being supplied with fuel at the same time, and the fuel supply equivalence ratio being 1.5. As can be seen from fig. 4, the mass fractions of the gas-phase fuel in the first evaporation cavity 2 and the second evaporation cavity 3 are significantly higher, which is because the reflux area in the evaporation cavities prolongs the residence time of the fuel, which is beneficial to the evaporation of the fuel and improves the proportion of the gas-phase fuel; in the area of the concave cavity 100, the gas-phase fuel oil is uniformly distributed, which shows that the effect of adjusting the gas-phase oil-gas distribution of the concave cavity can be realized by the method of supplying oil to the first evaporation cavity 2 and the second evaporation cavity 3 simultaneously, which is favorable for uniformly distributing the gas-phase fuel oil of the concave cavity and widening the ignition position.
Claims (6)
1. The cavity standing vortex stabilizer is characterized by comprising a cavity standing vortex flame stabilizer (1), a first evaporation cavity (2) arranged in front of the cavity standing vortex flame stabilizer (1), and a second evaporation cavity (3) arranged behind the cavity standing vortex flame stabilizer (1), wherein the first evaporation cavity (2) is communicated with a cavity (100) of the cavity standing vortex flame stabilizer (1) through a first air-entraining flow passage (4), and the second evaporation cavity (3) is communicated with the cavity (100) of the cavity standing vortex flame stabilizer (1) through a second air-entraining flow passage (5); the front of the first evaporation cavity (2) is communicated with a culvert air-entraining flow channel (6), and the front of the second evaporation cavity (3) is communicated with a culvert air-entraining flow channel (7); a first oil injection device (8) is arranged above the first evaporation cavity (2), and a second oil injection device (9) is arranged above the second evaporation cavity (3); the cavity trapped vortex flame stabilizer (1) comprises a cavity (100), a front wall (101), a main plate (102) and a rear wall (103) which enclose the cavity (100), a first evaporation cavity (2) comprises a first evaporation cavity upper wall plate (201) which extends obliquely upwards and is connected with the main plate (102) and a first evaporation cavity lower wall plate (202) which extends horizontally, an inner culvert and an outer culvert splitter plate (10) extend horizontally from the front end of the first evaporation cavity upper wall plate (201), an inner culvert and air entraining flow channel (6) is formed between the inner culvert and the outer culvert splitter plate (10) and the first evaporation cavity lower wall plate (202), and a second evaporation cavity (3) comprises a first splitter plate (301), a second splitter plate (302) which extends horizontally and a second evaporation cavity upper wall (303) which is connected with the tail end of the second splitter plate (302) and extends obliquely downwards; an outer culvert bleed air flow channel (7) is formed between the first flow dividing plate (301) and the main plate (102).
2. The cavity trapped vortex stabiliser as claimed in claim 1, wherein the second oil injection device (9) is provided on the first splitter plate (301).
3. The cavity trapped vortex stabiliser as claimed in claim 2 wherein the first bleed air channel (4) and the second bleed air channel (5) are distributed offset.
4. The cavity trapped vortex stabiliser as claimed in claim 3, wherein the first oil injection means (8) is provided on the first evaporation cavity upper wall plate (201).
5. The cavity trapped vortex stabilizer according to claim 4, characterized in that the first bleed air channel (4) is arranged above the front wall (101) and the second bleed air channel (5) is arranged below the rear wall (103).
6. A method of operating a re-entrant trapped vortex stabiliser as claimed in claim 1, comprising the steps of:
(a) The multi-mode combustor is in an afterburner mode: the inner culvert high-temperature fuel gas enters the first evaporation cavity (2) through the inner culvert air-entraining flow channel (6) to preheat liquid fuel oil sprayed out of the first evaporation cavity (2) and enters the first evaporation cavity (2) by the first oil injection device (8), the backflow area of the first evaporation cavity (2) is utilized to complete premixing of the oil gas, premixed oil gas enters the cavity (100) through the first air-entraining flow channel (4), a vortex system structure formed in the cavity (100) sends the premixed gas to each area of an on-duty area to create favorable conditions for on-duty ignition, at the moment, the second oil injection device (9) does not work, outer culvert air flow enters the second evaporation cavity (3) through the outer culvert air-entraining flow channel (7) and then enters the cavity (100) through the second air-entraining flow channel (5), oxygen content of a combustion chamber is improved, and oil mist in the on-duty area is uniformly distributed;
(b) When the multi-mode combustion chamber is switched to the stamping mode: the first oil injection device (8) and the second oil injection device (9) work simultaneously, the connotative air flow enters the first evaporation cavity (2) through the connotative air-entraining flow passage (6) to preheat liquid fuel sprayed by the first oil injection device (8), and the premixed oil and gas in the first evaporation cavity (2) enters the cavity through the first air-entraining flow passage (4); the outer culvert air current gets into second evaporation chamber (3) through outer culvert bleed runner (7), the liquid fuel of second fueling injection equipment (9) spun is at first through mainboard (102) broken atomizing, further atomizing evaporation in second evaporation chamber (3), the gas in advance in second evaporation chamber (3) gets into cavity (100) through second bleed runner (5), play the effect of adjusting the district's on duty oil gas distribution, and form stable low-speed backward flow district with the gas in advance that comes from first evaporation chamber (2), ignition provides the advantage on duty.
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| 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 |
| CN116181526B (en) * | 2023-02-07 | 2023-09-15 | 中国人民解放军32804部队 | Supersonic combustion chamber low Mach number ignition device and method based on support plate air entraining |
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| 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 |
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| US7467518B1 (en) * | 2006-01-12 | 2008-12-23 | General Electric Company | Externally fueled trapped vortex cavity augmentor |
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