CN117212836B - Supersonic aircraft and independent oil supply combined flame stabilizer - Google Patents
Supersonic aircraft and independent oil supply combined flame stabilizer Download PDFInfo
- Publication number
- CN117212836B CN117212836B CN202311399554.9A CN202311399554A CN117212836B CN 117212836 B CN117212836 B CN 117212836B CN 202311399554 A CN202311399554 A CN 202311399554A CN 117212836 B CN117212836 B CN 117212836B
- Authority
- CN
- China
- Prior art keywords
- flame
- oil
- stabilizer
- annular
- cone
- 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.)
- Active
Links
- 239000003381 stabilizer Substances 0.000 title claims abstract description 102
- 238000012546 transfer Methods 0.000 claims abstract description 88
- 238000002485 combustion reaction Methods 0.000 claims abstract description 42
- 239000000446 fuel Substances 0.000 claims description 88
- 239000007921 spray Substances 0.000 claims description 32
- 230000004323 axial length Effects 0.000 claims description 9
- 230000000903 blocking effect Effects 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 claims description 4
- 230000000087 stabilizing effect Effects 0.000 abstract description 10
- 238000013461 design Methods 0.000 abstract description 9
- 238000009792 diffusion process Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 141
- 230000000694 effects Effects 0.000 description 18
- 238000000889 atomisation Methods 0.000 description 15
- 239000000295 fuel oil Substances 0.000 description 15
- 239000007789 gas Substances 0.000 description 10
- 238000002156 mixing Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 5
- 238000001704 evaporation Methods 0.000 description 4
- 230000008020 evaporation Effects 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000005507 spraying Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000003416 augmentation Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000010992 reflux Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Landscapes
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention discloses a supersonic aircraft and an independent oil supply combined flame stabilizer, and belongs to the technical field of aircrafts. The device comprises a cone, a rear cavity, an annular stabilizer and a flame transfer groove, wherein the rear part of the cone is connected with the rear cavity, and an annular center concave cavity is formed between the cone and the rear cavity; the rear cavity is provided with a plurality of nozzles which can supply oil to the annular center concave cavity, and the nozzles are communicated with the first oil supply unit; the number of flame transfer grooves corresponds to the number of nozzles, one ends of the flame transfer grooves are fixedly connected with the rear cavity to be in a backward inclined shape and uniformly distributed in the circumferential direction, and the other ends of the flame transfer grooves are connected with the annular stabilizer; each flame transfer groove is opposite to one nozzle and is used for transferring flame-connecting airflow formed by combustion from the annular center concave cavity to the annular stabilizer. By adopting an integrated design, under the condition of smaller cold resistance loss, the flow resistance loss is controlled on the premise of ensuring the ignition and flame transfer capabilities, the stabilizing and diffusion capabilities of each part of stabilizer to the flame are exerted to the maximum extent, and the combustion efficiency of the combustion chamber is greatly improved.
Description
Technical Field
The invention relates to an aircraft, in particular to a supersonic aircraft and an independent oil supply combined flame stabilizer, and belongs to the technical field of aircrafts.
Background
With the pursuit of advanced supersonic combat weapons by countries around the world, vortex-jet boost engines are becoming increasingly important as an important component of supersonic power systems, and considerable research work has been carried out in various countries on flame holders of the important components of afterburners. In the prior art, the V-shaped flame stabilizer is widely applied in an afterburner due to simple structure and rich use experience, the stability of the V-shaped flame stabilizer is closely related to the incoming flow state and the groove width of the stabilizer, the flame in the combustion chamber can be ensured to burn stably under high-altitude, high-speed and low-temperature environments, the V-shaped flame stabilizer needs higher blocking ratio, the groove width of the flame stabilizer in the conventional afterburner is generally about 40mm, and the wider groove width of the stabilizer can cause higher cold resistance loss of the combustion chamber, so that the overall performance of the engine is influenced; meanwhile, the V-shaped flame stabilizer has narrow flame stabilizing boundary, poor stability at low temperature and difficult ignition, when the working condition changes greatly or the fuel oil is supplied insufficiently to enable the combustion chamber to be in a low oil-gas ratio, the flame in the reflux area of the V-shaped flame stabilizer is very easy to separate to cause flameout, and the simple V-shaped flame stabilizer can not meet the requirements of the modern advanced aeroengine combustion chamber.
For the high-performance afterburner and the multi-mode combustor, the problems of low incoming flow temperature of the combustor, overlarge local flow rate and the like can cause difficult ignition and stable combustion of the combustor, and the adoption of an on-duty flame stabilizer for soft ignition is an important means for solving the problems of difficult ignition, flame stabilization and the like of the afterburner. At present, the concave cavity standing vortex flame stabilizer has wider and wider application due to the characteristics of small flow resistance, strong stability, good ignition performance and the like, but when the concave cavity adopts a pneumatic atomization mode for oil supply, the problems of difficult atomization of fuel oil, poor evaporation effect and the like exist at high altitude, low temperature and low flow rate, a good oil gas concentration distribution area easy to ignite cannot be formed in the concave cavity, the ignition is not facilitated, and the success rate of soft ignition of the concave cavity is greatly reduced; the flame propagation capability of the independent cavity stabilizer is weaker, the heat transfer of flame is not facilitated, the radial flame transfer structure is usually arranged at the front wall surface of the cavity in the engineering for matching use, however, the radial flame transfer structure of the front layout of the cavity can damage the cavity vortex, a vortex-free structure which is not suitable for combustion is formed in the circumferential direction in the cavity, the volume of a flame stabilizing area of the cavity is greatly reduced, the temperature rise effect provided by the cavity is limited, and the effect of the cavity is not beneficial to being fully exerted.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a supersonic aircraft and an independent oil supply combined flame stabilizer which can greatly improve the mixing effect and atomization capability of oil gas, reduce the damage of flame transfer airflow to annular center concave cavity vortex system and improve flame stability, temperature rise and overall combustion efficiency.
In order to solve the technical problems, the independent oil supply combined flame stabilizer provided by the invention comprises a cone, a rear cavity, an annular stabilizer and a flame transfer groove, wherein the rear part of the cone is connected with the rear cavity, and an annular center concave cavity is formed between the cone and the rear cavity;
The rear cavity is provided with a plurality of nozzles capable of supplying oil to the annular center concave cavity, and the nozzles are communicated with the first oil supply unit;
the number of the flame transfer grooves corresponds to that of the nozzles, one ends of the flame transfer grooves are fixedly connected with the rear cavity to be uniformly distributed in a backward inclined mode in the circumferential direction, and the other ends of the flame transfer grooves are connected with the annular stabilizer;
And each flame transfer groove is opposite to one nozzle and is used for transferring flame transfer airflow formed by combustion from the annular center concave cavity to the annular stabilizer.
In the invention, the blocking ratio of the independent oil supply combined flame stabilizer; The saidRatio of (3)；
In the method, in the process of the invention,Effective projection area of flame transfer groove,Is the projection area of the annular stabilizer,Is the cross-sectional area of the combustion chamber.
In the invention, the axial length L 4 of the cone is 1-1.5 times of the axial length L 5 of the annular center concave cavity 5; the included angle alpha 4 of the cone is 50-70 degrees.
In the invention, the transverse section of the flame transfer groove is V-shaped, and the included angle alpha 8 is 35-50 degrees; the installation angle theta 8 of the flame transfer groove is 40-60 degrees.
In the invention, the reference circle diameter D 7 of the annular stabilizer is the diameter D 0 of the combustion chamber；
The cross section of the annular stabilizer is V-shaped, and the included angle alpha 7 is 50-70 degrees.
In the invention, the first oil supply unit comprises a fuel pipe and a plurality of branch fuel pipes communicated with the fuel pipe, and the plurality of branch fuel pipes are arranged in the rear cavity in a dispersing way;
Each branch fuel pipe is respectively connected with one nozzle.
In the invention, the cone is provided with a second oil supply unit and a third oil supply unit,
The second oil supply unit is used for supplying oil to the annular stabilizer; the second oil supply unit includes a second oil ring; the second oil ring is provided with a plurality of second oil spray holes uniformly distributed along the circumferential direction; the second oil spray hole is opposite to the annular stabilizer;
the third oil supply unit is used for supplying oil to the flame transfer mechanism; the third oil supply unit includes a third oil ring; the third oil ring is uniformly distributed with a plurality of third oil spray holes along the circumferential direction; the third oil spray hole is opposite to the flame transfer groove.
In the invention, the diameter D 203 of the reference circle of the second oil ring is the same as the reference circle diameter D 7 of the annular stabilizer;
And the reference circle diameter D 303 of the third oil ring is 4-8 mm larger than the diameter D 401 of the rear end surface of the cone.
In the invention, the second oil ring is distributed at the axial position of the coneWhere it is located.
In the invention, the third oil ring is distributed at the axial position of the coneA place;
the third oil spray hole is right opposite to the section where the flame groove is located.
The invention also provides a supersonic aircraft, which comprises a turbojet forced engine, wherein the turbojet forced engine comprises a casing, and the independent oil supply combined flame stabilizer is arranged in the casing.
The invention has the beneficial effects that: (1) The rear end surface of the cone is fixedly connected with the front end surface of the rear cavity through the supporting pipe to form an annular center concave cavity, a strong vortex structure is formed, the mixing effect and atomization capability of oil gas can be greatly improved, and a stable on-duty fire source is formed in the concave cavity; compared with the traditional on-duty flame stabilizer, the invention adopts an integrated design, controls the flow resistance loss on the premise of ensuring the ignition and flame transfer capabilities under the condition of smaller cold resistance loss, plays the stabilizing and diffusing capabilities of each part of the stabilizer to the flame to the maximum extent, and greatly improves the combustion efficiency of the combustion chamber; (2) Compared with the traditional mode that flame transfer structures are arranged on the front end face of the concave cavity, the optimized layout mode that the radial flame transfer grooves are arranged behind the annular center concave cavity in a backward inclined mode is adopted, so that the damage effect of flame transfer airflow on the vortex system of the annular center concave cavity is reduced, the flame stabilizing area of the annular center concave cavity can be expanded to the whole concave cavity circumference, and the flame stability and temperature rise of the annular center concave cavity are improved; (3) The independent oil supply systems can be respectively designed for the stabilizers at different positions according to the structural characteristics and the flow field characteristics of the combined flame stabilizer by the partition oil supply and staged combustion mode formed by the first oil supply unit, the second oil supply unit and the third oil supply unit, the annular central cavity is supplied with oil by adopting a rear centrifugal nozzle, oil gas distribution easy to ignite is formed in the annular central cavity, and the ignition performance is obviously improved; (4) The main flow area is provided with oil rings with different oil supply amounts for the flame transfer grooves and the annular stabilizer by reversely spraying on the cone, the second oil supply unit and the third oil supply unit are reversely sprayed, the diameter of the reference circle of the third oil ring is slightly larger than that of the rear end surface of the cone, the third oil spray holes are as far as possible right toward the flame transfer grooves, the fuel oil sprayed out of the auxiliary oil spray holes can be heated and evaporated by fuel gas when flowing through the annular center concave cavity, and the fuel oil can be quickly combusted by the fuel gas guided from the annular center concave cavity through the flame transfer grooves when reaching the flame transfer groove distribution area, so that the mixing distance of the fuel gas is greatly shortened; (5) The diameter of the index circle of the second oil ring is basically the same as that of the index circle of the annular stabilizer, so that the fuel flow sprayed out of the second oil spray holes can be matched with the flow field structure of the annular stabilizer when passing through the annular stabilizer, the fuel can be fully combusted, and the design length of the combustion chamber can be greatly shortened.
Drawings
FIG. 1 is a schematic diagram of a stand alone oil supply combined flame stabilizer;
FIG. 2 is an enlarged schematic view of a portion of the centrifugal nozzle oil supply;
FIG. 3 is a front view of a stand alone oil supply combined flame holder;
FIG. 4 is a rear view of a stand alone oil supply combination flame holder;
FIG. 5 is a cross-sectional view of an annular center cavity structure of a stand-alone oil supply combined flame holder;
FIG. 6 is a schematic view of the internal structure of the rear chamber of the stand alone oil supply combined flame stabilizer;
FIG. 7 is a schematic view of the main fuel pipe structure;
FIG. 8 is a schematic view of the structure of the secondary fuel pipe;
FIG. 9 is a block diagram of the stand alone fuel supply combination flame holder in an engine FIG. 1;
FIG. 10 is a block diagram of FIG. 2 of a stand alone fuel supply combined flame holder within an engine;
FIG. 11 is a block diagram of FIG. 3 of a stand alone fuel supply combination flame holder within an engine;
FIG. 12 is a flow field diagram of a section where a flame transfer slot is located;
FIG. 13 is a flow field view of a section without flame propagation grooves;
In the figure: 1. a fuel pipe; 101. branching the fuel pipe; 102. a connection channel; 2. a main fuel pipe; 201. A main oil jet orifice; 202. a main oil inlet pipe; 203. a main oil ring; 204. a main oil fixing column; 3. an auxiliary fuel pipe; 301. auxiliary oil spray holes; 302. an auxiliary oil inlet pipe; 303. an auxiliary oil ring; 304. an auxiliary oil fixing column; 4. a cone; 401. the rear end face of the cone; 5. an annular central cavity; 501. a support tube; 6. a rear cavity; 601. a front end surface of the rear cavity; 602. a rear end surface of the rear cavity; 603. a mounting hole; 7. An annular stabilizer; 8. flame transfer grooves; 9. centrifuging the nozzle; 900. an oil inlet; 901. a housing; 902. a plug; 903. an oil inlet hole of the vortex chamber; 904. a vortex chamber; 905. rotating the block; 906. an oil outlet hole; 10. an engine case.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.
In the description of the present invention, it should be noted that, directions or positional relationships indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., are directions or positional relationships based on those shown in the drawings, or are directions or positional relationships conventionally put in use of the inventive product, are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific direction, be constructed and operated in a specific direction, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal," "vertical," "overhang," and the like do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Some embodiments of the present invention are described in detail below with reference to the accompanying drawings. The following embodiments and features of the embodiments may be combined with each other without conflict.
As shown in fig. 1 to 8, the independent oil supply combined flame stabilizer provided in this embodiment includes a fuel pipe 1, a main fuel pipe 2, a sub fuel pipe 3, a cone 4, a rear chamber 6, an annular stabilizer 7, a flame transfer groove 8, and a centrifugal nozzle 9. The fuel pipe 1, the main fuel pipe 2 and the auxiliary fuel pipe 3 are respectively externally connected with an external fuel supply pipeline.
The rear cavity 6 includes a rear cavity front face 601 and a rear cavity rear face 602. The cone rear end surface 401 is fixedly connected with the rear cavity front end surface 601 through a supporting pipe 502, and an annular center concave cavity 5 is formed between the cone rear end surface 401 and the rear cavity 6. The integrated design concept is adopted, and the annular center concave cavity 5, the flame transfer groove 8 and the annular stabilizer 7 form a combined flame stabilizer with low flow resistance; the mixing effect and atomization capability of oil gas can be greatly improved through the strong vortex structure formed by the annular center concave cavity 5, and stable on-duty flame is formed in the annular center concave cavity 5.
In this embodiment, the axial length L 4 of the cone 4 is 1.5 times the axial length L 5 of the annular central cavity 5, and the included angle α 4 of the cone 4 is 62 °, so that the axial length of the cone 4 can be effectively ensured to be shorter, the weight is lighter, and the flow loss is small.
Through tests, in a conventional state, the axial length L 4 of the cone 4 is 1-1.5 times the axial length L 5 of the annular center concave cavity 5, and the included angle alpha 4 of the cone 4 can achieve the aim of the invention under the condition of 50-70 degrees.
As shown in fig. 1, 5 and 6, the cone 4, the support tube 502 and the interior of the rear cavity 6 form a connecting channel 102, the fuel pipe 1 passes through the connecting channel 102 to enter the rear cavity 6, and a certain gap is reserved between the fuel pipe 1 and the connecting channel 102 so as to facilitate air to quickly enter the rear cavity 6. The fuel pipe 1 is divided into a plurality of branch fuel pipes 101 in the rear chamber 6, and each branch fuel pipe 101 is connected with one centrifugal nozzle 9.
A plurality of mounting holes 603 are uniformly distributed on the front end face 601 of the rear cavity in the circumferential direction, the number n 603 of the mounting holes 603 corresponds to the number of the centrifugal nozzles 9, and the centrifugal nozzles 9 are respectively distributed in the mounting holes 603. The fuel oil is independently sprayed to the annular center concave cavity 5 through the fuel oil pipe 1 and the plurality of branch fuel oil pipes 101 by the centrifugal nozzle 9 to form an independent oil supply system, so that stable on-duty flame is formed.
As shown in fig. 2, the centrifugal nozzle 9 includes an oil inlet 900, a casing 901, a plug 902, a swirl chamber oil inlet 903, a swirl chamber 904, a swirl block 905, and an oil outlet 906; the rotary block 905 is riveted with the plug 902 through rotary riveting to form a closed cavity with oil inlet holes 903 of the vortex chamber, the rotary block 905 is screwed with the shell 901, so that after fuel enters the centrifugal nozzle 9 through the oil inlet 900, the fuel can only enter the vortex chamber 904 through the oil inlet holes 903 of the vortex chamber to form tangential and high-speed rotational flow, and after the fuel is accelerated to impact, break and atomize under high pressure, the fuel is sprayed out from the oil outlet hole 906 to enter the annular center concave cavity 5 for atomization, blending, evaporation and combustion. The oil and gas mixing and ignition capability of the annular center concave cavity 5 can be improved by independently supplying oil to the annular center concave cavity 5 through the centrifugal nozzle 9 with high atomization performance.
The characteristic dimension of the vortex chamber 904 is an important influencing factor influencing the atomization performance of the centrifugal nozzle 9, two tangential vortex chamber oil inlets 903 are arranged at the maximum diameter of the vortex chamber 904, and the opening directions of the two vortex chamber oil inlets 903 are parallel.
In this embodiment, the included angle θ 904 of the vortex chamber 904 is in the range of 80 ° to 100 °, the diameter d 904 of the vortex chamber 904 is 6 to 8 times the caliber d 906 of the oil outlet 906, the caliber d 903 of the oil inlet 903 of the vortex chamber is 0.2 to 0.5mm as the caliber d 906 of the oil outlet 906, and the fuel is easier to atomize and break.
As shown in fig. 5 and 6, in the present embodiment, the number n 8 of flame transfer grooves 8 is the same as the number n 603 of the mounting holes 603, so that it is ensured that the flame at the annular center cavity 5 can be quickly transferred to the area behind the rear end surface 602 of the rear cavity through the flame transfer grooves 8. The front ends of the flame transfer grooves 8 are fixedly connected with the rear end surface 602 of the rear cavity and the side surface of the rear cavity 6, and are in a backward inclined shape, and the plurality of flame transfer grooves 8 are uniformly distributed in the circumferential direction. After the flame transfer grooves 8 are fixedly connected with the rear cavity 6, a plurality of centrifugal nozzles 9 are respectively positioned right in front of the flame transfer grooves 8, and the two are in one-to-one correspondence. So that the fuel oil with high atomization performance sprayed from the centrifugal nozzle 9 is matched with the structures and flow fields of the annular center concave cavity 5 and the flame transfer groove 8, namely, the oil-gas ratio and the ignition area which have long residence time and high atomization performance and are easy to ignite are formed in the annular center concave cavity 5; meanwhile, the centrifugal nozzle 9 is positioned right in front of the flame transfer groove 8, and the enriched high-temperature fuel gas can be matched with the flame transfer groove 8, so that the combustion efficiency can be greatly improved.
The radial stabilizer with flame transfer function in the existing combined flame stabilizer is inclined backwards and arranged on a cone, when airflow flows through the radial stabilizer with strong flame transfer capability and reaches the vicinity of the cavity of the annular center cavity, the strong entrainment airflow after the radial stabilizer can damage the original vortex structure in the cavity of the annular center, so that the vortex structure of the cavity of the annular center with the section where the radial stabilizer is located is reduced and weakened, the low-speed stable combustion area of the cavity of the annular center in the circumferential direction is divided into a plurality of relatively independent small areas, the vortex structure difference of the cavity of the annular center in different circumferential areas is large, and the requirement is provided for the selection of the ignition position. In this embodiment, the flame transfer slot 8 is moved to the vicinity of the rear end face 602 of the rear cavity, so that the flame transfer air flows out from the annular center cavity 5 and then passes through the flame transfer mechanism, a space is provided for forming the single vortex of the annular center cavity 5 at the circumferential position corresponding to the flame transfer slot 8, the damage of the flame transfer air flow to the vortex system of the annular center cavity 5 is reduced, the flame stabilizing area of the annular center cavity 5 can be expanded to the circumferential direction of the whole annular center cavity 5, the integrated three-dimensional single vortex flame stabilizing area is formed, the stability and space utilization rate of the flame of the annular center cavity 5 are greatly improved, and the difficulty in selecting the ignition area is reduced.
In this embodiment, as shown in fig. 4, the cross section of the flame transfer groove 8 is V-shaped, the included angle α 8 of the flame transfer groove 8 is 40 °, and the installation angle θ 8 is 50 °, so that the flow loss of the cross flame airflow is small, and the flame propagation capability is strong.
Through tests, the technical effect of the invention can be realized when the included angle alpha 8 of the flame transfer groove 8 is between 35 and 50 degrees and the installation angle theta 8 is between 40 and 60 degrees under the conventional state.
The annular stabilizer 7 is fixedly connected with the rear end of each flame transfer groove 8. In this embodiment, the pitch circle diameter D 7 of the ring stabilizer 7 is the combustion chamber diameter D 0 . The cross section of the annular stabilizer 7 is V-shaped, and the included angle alpha 7 is 60 degrees, so that the flame can be ensured to rapidly propagate to the whole combustion chamber through the annular stabilizer 7.
Tested under normal conditions, the annular stabilizer 7 has a pitch diameter D 7 of the combustion chamber diameter D 0 ~The included angle alpha 7 of the annular stabilizer 7 can achieve the technical effect of the invention within 50-70 degrees.
In the present embodiment, as shown in fig. 1 and 7, the main fuel pipe 2 is distributed at the axial position of the cone 4L 4, is located between the fuel pipe 1 and the secondary fuel pipe 3. The main fuel pipe 2 includes a main oil inlet pipe 202, a main oil ring 203, a main oil fixing column 204, and a main oil injection hole 201. The main oil ring 203 is arranged along the whole body of the cone 4 and is connected with the main oil inlet pipe 202, and the main oil ring 203 is fixedly connected with the engine casing 10 through the main oil fixing column 204. The main oil ring 203 is provided with a plurality of main oil spray holes 201 uniformly distributed along the circumferential direction, and the opening direction of the main oil spray holes 201 is opposite to the annular stabilizer 7 and is consistent with the oil spraying direction of the centrifugal nozzle 9 so as to be used for supplying oil to the annular stabilizer 7.
In this embodiment, the main fuel pipe 2 is distributed at the axial position of the cone 4At L 4, during the use, the distribution position of the main fuel pipe 2 in the cone 4 can be adjusted finely as required.
The diameter D 203 of the reference circle of the main oil ring 203 is basically the same as the diameter D 7 of the reference circle of the annular stabilizer 7, so that the fuel injected from the main oil injection hole 201 can be fully matched with the flow field of the annular stabilizer 7 when flowing through the combined flame stabilizer, more fuel is supplied to be injected from the main oil injection hole 201 of the main oil ring 203, the expansion capability of the flame of the V-shaped flame stabilizer of the annular stabilizer 7 is fully exerted, the combustion efficiency is greatly improved, and the length of a combustion chamber is shortened.
In this embodiment, the direction of the opening of the main oil nozzle 201 is opposite to the air flow direction, and the diameter d 201 of the main oil nozzle 201 is 0.5mm, and the number n 201 of the main oil nozzle 201 is 3 times the number n 8 of the flame transfer slots 8.
The main oil spray hole 201 adopts a reverse spray mode, so that the opposite impact atomization effect of fuel oil and air flow can be greatly improved, the residence time of the fuel oil in a combustion chamber is improved, the evaporation rate of the fuel oil is improved by utilizing the preheating effect of the annular center concave cavity 5, and the mixing distance of the main fuel oil pipe 2 can be shortened.
In order to ensure the atomization effect, the caliber d 201 of the main oil spray hole 201 is not too large or too small, and the technical effect to be achieved by the invention can be realized under the condition that the caliber d 201 of the main oil spray hole 201 is between 0.4 and 0.6mm and the number n 201 of the main oil spray holes 201 is 2 to 6 times of the number n 8 of the flame transfer grooves 8 under the conventional state.
As shown in fig. 1 and 8, the secondary fuel pipe 3 is distributed at the axial position of the cone 4L 4 is located between the main fuel pipe 2 and the annular central cavity 5, before the cone rear face 401. The auxiliary oil ring 303 is arranged along the whole body of the cone 4 like the main oil ring 203, is connected with an auxiliary oil inlet pipe 302, and the auxiliary oil ring 303 is fixedly connected with the engine case 10 through an auxiliary oil fixing column 304. The auxiliary oil ring 303 is provided with a plurality of auxiliary oil spray holes 301 uniformly distributed along the circumferential direction, and the opening directions of the auxiliary oil spray holes 301 are opposite to the flame transfer groove 8 and are consistent with the oil spraying directions of the centrifugal nozzles 9, so as to supply oil to the flame transfer groove 8.
In the embodiment, the auxiliary fuel pipe 3 is distributed at the axial position of the cone 4At L 4, during the application, the distribution position of the secondary fuel pipe 3 in the cone 4 can be adjusted finely as required.
In this embodiment, by uniformly distributing the plurality of auxiliary oil spray holes 301 with the same diameter and reversely spraying on the auxiliary oil ring 303 in the circumferential direction, the opposite impact atomization effect of the fuel and the air flow can be improved, meanwhile, the residence time of the fuel in the combustion chamber is improved, the space of the cone 4 is reasonably utilized, and the oil-gas mixing distance between the auxiliary fuel pipe 3 and the flame transfer groove 8 is greatly shortened.
The diameter D 303 of the index circle of the auxiliary oil ring 303 is 4-8 mm larger than the diameter D 401 of the rear end face 401 of the cone, so that fuel oil sprayed from the auxiliary oil spray hole 301 can be heated and evaporated by fuel gas in the annular center concave cavity 5 when flowing through the combined flame stabilizer, the fuel oil is matched with the flow field of the flame transfer groove 8, and the combustion efficiency is greatly improved; at the same time, it is ensured that not too much fuel flows into the annular central cavity 5, thereby affecting the gas-oil ratio of the annular central cavity 5.
In the present embodiment, the direction of the opening of the auxiliary oil nozzle 301 is opposite to the direction of the air flow, and the auxiliary oil nozzle is also reversely sprayed. The caliber d 301 of the auxiliary oil spray holes 301 is 0.34mm, and the number n 301 of the auxiliary oil spray holes 301 is 1.5 times that of the flame transfer grooves 8.
In the actual assembly process, the opening position of the auxiliary oil spray hole 301 is as close to the section of the flame transfer slot 8 as possible to match the flow field structure of the flame transfer slot 8, so that the combustion efficiency of fuel oil sprayed by the auxiliary oil spray hole 301 is improved, and the length of the combustion chamber is shortened.
In order to ensure the atomization effect, the caliber d 301 of the auxiliary oil spray hole 301 is not too large or too small, and the technical effect to be achieved by the invention can be realized under the condition that the caliber d 301 of the auxiliary oil spray hole 301 is between 0.3 and 0.4mm and the number n 301 of the auxiliary oil spray holes 301 is 1 to 2 times of the number n 8 of the flame transfer grooves 8 under the conventional state.
According to the independent oil supply combined flame stabilizer provided by the embodiment, the partition oil supply and staged combustion tissue combustion mode is adopted, according to the structural characteristics and flow field characteristics of the combined flame stabilizer, the oil supply schemes of different forms are adopted for different positions of the combined flame stabilizer, the mounting holes 603 are uniformly distributed circumferentially on the front end face 601 of the rear cavity, and the centrifugal nozzle 9 supplies oil to the annular center concave cavity 5 independently through the mounting holes 603, so that a good ignition environment and an ignition area are provided. When the annular center concave cavity 5 is successfully ignited, different oil supply modes can be adopted according to the requirements of different working states of the engine, the oil supply pressure of the fuel pipe 1 can be improved in a small state, and the oil supply requirement of the engine can be met only by the working of the centrifugal nozzle 9; as the state of the engine increases, the auxiliary fuel pipe 3 or the main fuel pipe 2 can be respectively opened for independent fuel supply according to the fuel requirement, and the main fuel pipe 2 and the auxiliary fuel pipe 3 can be simultaneously opened for simultaneous fuel supply to the combustion chamber, but the centrifugal nozzle 9 always keeps supplying the fuel to the annular center concave cavity 5 in any state; the fuel sprayed from the main fuel pipe 2 or the auxiliary fuel pipe 3 can improve the opposite impact atomization effect of the fuel and the air flow by adopting reverse injection, and simultaneously improves the residence time of the fuel in the combustion chamber, the fuel can be preheated in advance when flowing through the annular central concave cavity 5 of the combined flame stabilizer, the evaporation rate of the fuel is improved, the mixing distance of the fuel and the air of the main fuel pipe 2 and the auxiliary fuel pipe 3 is greatly shortened, the fuel of the auxiliary fuel pipe 3 is combusted through the flame transfer groove 8 area, the fuel of the main fuel pipe 2 is combusted through the annular stabilizer 7 area, and the fuel supply mode is matched with the structure and the flow field of the combined flame stabilizer, so that the combustion efficiency is greatly improved, and the length of the combustion chamber is shortened.
As shown in fig. 9 to 11, the supersonic aircraft provided in this embodiment adopts a turbojet thrust augmentation engine. The turbojet forced engine comprises an engine casing 10, a cone 4, a rear cavity 6, an annular stabilizer 7, a flame transfer groove 8 and a centrifugal nozzle 9. The fuel pipe 1, the main fuel pipe 2, the auxiliary fuel pipe 3, the cone 4, the rear cavity 6, the annular stabilizer 7, the flame transfer groove 8 and the centrifugal nozzle 9 are all assembled in the engine case 10, and the fuel pipe 1, the main fuel pipe 2 and the auxiliary fuel pipe 3 extend out of the engine case 10 to be connected with an external fuel supply pipeline.
In this embodiment, the ratio of the projection area of the combined flame stabilizer on the cross section of the combustion chamber to the cross section of the combustion chamber is taken as the blocking ratio epsilon of the stabilizer, the 'integrated design' concept is adopted, the optimal blocking ratio epsilon is selected according to design indexes, and the important dimensions of each stabilizer are determined, including the diameter D 401 of the rear end face 401 of the cone, the groove width W 8 of the flame transfer groove 8, the number n 8, the effective projection height H 8 of the flame transfer groove 8, and the pitch circle diameter D 7 and the groove width W 7 of the annular stabilizer 7.
Wherein the projected area of the coneEffective projection area of flame transfer groove 8Wherein the effective projection height of the flame propagation groove 8Projected area of the ring stabilizer 7Cross-sectional area of combustion chamber 。
The area ratio of three groups of different stabilizers of the combined flame stabilizer is kept as much as possible by the optimization concept of' integrated designIn proportions such that the partial stabilizer designs are optimized to optimize the turndown ratio of the combined flame stabilizerThe oil gas mixing capability and the flame stabilizing capability of each part of the combined flame stabilizer are ensured, and the flow resistance loss of the combined flame stabilizer is ensured to be small as much as possible.
In this embodiment, the combined flame stabilizer adopts the configuration that the annular central cavity 5 and the annular stabilizer 7 are fixedly connected in front of and behind the flame transfer groove 8, and the flame transfer groove 8 and the rear cavity 6 are fixedly connected behind the annular central cavity 5, so that the flame transfer air flows out through the annular central cavity 5 before passing through the flame transfer mechanism. As shown in fig. 12 and 13, the vortex structures of the annular center concave cavity 5 with the flame transfer groove 8 and the cross section without the flame transfer groove 8 are basically the same, the design form that the flame transfer groove 8 is arranged behind the annular center concave cavity 5 is described, the damage effect of flame transfer air flow on the vortex system of the annular center concave cavity 5 is reduced, the flame stabilizing area of the annular center concave cavity 5 can be expanded to the circumferential direction of the whole annular center concave cavity 5, a three-dimensional single vortex flame stabilizing area integrated is formed, the flame stability and the space utilization rate of the annular center concave cavity 5 are greatly improved, the vortex structures of each circumferential cross section of the annular center concave cavity 5 are the same, the configuration advantage of the combined flame stabilizer is embodied, and the difficulty in selecting an ignition area is reduced.
The invention provides a concept of a supersonic aircraft and an independent oil supply combined flame stabilizer, and the method and the way for realizing the technical scheme are numerous, the above description is only a preferred embodiment of the invention, and it should be noted that, for a person skilled in the art, a plurality of improvements and modifications can be made without departing from the principle of the invention, and the improvements and modifications are also considered as the protection scope of the invention. The components not explicitly described in this embodiment can be implemented by using the prior art.
Claims (8)
1. Independent oil supply combined flame stabilizer, its characterized in that: the device comprises a cone, a rear cavity, an annular stabilizer and a flame transfer groove, wherein the rear part of the cone is connected with the rear cavity, and an annular center concave cavity is formed between the cone and the rear cavity;
The rear cavity is provided with a plurality of nozzles capable of supplying oil to the annular center concave cavity, and the nozzles are communicated with the first oil supply unit;
The number of the flame transfer grooves corresponds to that of the nozzles, one ends of the flame transfer grooves are fixedly connected with the rear cavity to be uniformly distributed in a backward inclined mode in the circumferential direction, and the other ends of the flame transfer grooves are connected with the annular stabilizer;
Each flame transfer groove is opposite to one nozzle and is used for transferring flame transfer airflow formed by combustion from the annular center concave cavity to the annular stabilizer;
The first oil supply unit comprises a fuel pipe and a plurality of branch fuel pipes communicated with the fuel pipe, and the plurality of branch fuel pipes are arranged in the rear cavity in a dispersing way;
each branch fuel pipe is connected with a nozzle respectively;
the cone is provided with a second oil supply unit and a third oil supply unit,
The second oil supply unit is used for supplying oil to the annular stabilizer; the second oil supply unit includes a second oil ring; the second oil ring is provided with a plurality of second oil spray holes uniformly distributed along the circumferential direction; the second oil spray hole is opposite to the annular stabilizer;
the third oil supply unit is used for supplying oil to the flame transfer mechanism; the third oil supply unit includes a third oil ring; the third oil ring is uniformly distributed with a plurality of third oil spray holes along the circumferential direction; the third oil spray hole is opposite to the flame transfer groove.
2. The self-contained fuel supply combination flame holder of claim 1, wherein: blocking ratio of the independent oil supply combined flame stabilizer
Wherein A 4 is the projected area of the cone, A 8 is the effective projected area of the flame transfer slot, A 7 is the projected area of the annular stabilizer, and A 10 is the cross-sectional area of the combustion chamber.
3. The stand alone oil supply combination flame holder of claim 1 or 2, wherein:
The axial length L 4 of the cone is 1 to 1.5 times of the axial length L 5 of the annular center concave cavity (5); the included angle alpha 4 of the cone is 50-70 degrees.
4. The stand alone oil supply combination flame holder of claim 1 or 2, wherein:
The transverse section of the flame transfer groove is V-shaped, and the included angle alpha 8 is 35-50 degrees; the installation angle theta 8 of the flame transfer groove is 40-60 degrees.
5. The stand alone oil supply combination flame holder of claim 1 or 2, wherein:
The reference circle diameter D 7 of the annular stabilizer is the diameter D 0 of the combustion chamber
The cross section of the annular stabilizer is V-shaped, and the included angle alpha 7 is 50-70 degrees.
6. The self-contained fuel supply combination flame holder of claim 1, wherein: the diameter D 203 of the index circle of the second oil ring is the same as the diameter D 7 of the index circle of the annular stabilizer;
The reference circle diameter D 303 of the third oil ring is 4-8 mm larger than the diameter D 401 of the rear end face of the cone.
7. The self-contained fuel supply combination flame holder of claim 1, wherein:
the second oil ring is distributed at the axial position of the cone A place;
the third oil ring is distributed at the axial position of the cone A place;
the third oil spray hole is right opposite to the section where the flame groove is located.
8. A supersonic aircraft comprising a turbojet boost engine, characterized in that: the turbojet forced engine comprises a casing in which the independent oil supply combined flame stabilizer according to any one of claims 1 or 2 is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311399554.9A CN117212836B (en) | 2023-10-26 | 2023-10-26 | Supersonic aircraft and independent oil supply combined flame stabilizer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311399554.9A CN117212836B (en) | 2023-10-26 | 2023-10-26 | Supersonic aircraft and independent oil supply combined flame stabilizer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117212836A CN117212836A (en) | 2023-12-12 |
| CN117212836B true CN117212836B (en) | 2024-06-07 |
Family
ID=89048397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311399554.9A Active CN117212836B (en) | 2023-10-26 | 2023-10-26 | Supersonic aircraft and independent oil supply combined flame stabilizer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117212836B (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0893555A (en) * | 1994-07-26 | 1996-04-09 | Ishikawajima Harima Heavy Ind Co Ltd | Ram combustion device |
| CN101776283A (en) * | 2009-01-13 | 2010-07-14 | 北京航空航天大学 | Flame stabilizer with jet injection |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN104373964A (en) * | 2014-10-20 | 2015-02-25 | 北京航空航天大学 | Cavity supporting plate flame stabilizer with built-in oil rod |
| WO2016084111A1 (en) * | 2014-11-25 | 2016-06-02 | ENEA - Agenzia nazionale per le nuove tecnologie, l'energia e lo sviluppo economico sostenibile | Multistage hybrid system for the induction, anchorage and stabilization of distributed flame in advanced combustors for gas turbine |
| CN106642201A (en) * | 2016-12-23 | 2017-05-10 | 中航空天发动机研究院有限公司 | Flame stabilizing device for aircraft engine combustion chamber |
| CN106765310A (en) * | 2016-12-23 | 2017-05-31 | 中航空天发动机研究院有限公司 | For the flameholder with pre-blended chamber of engine chamber |
| CN109915858A (en) * | 2019-03-01 | 2019-06-21 | 西北工业大学 | A kind of supporting plate flameholder premixed with standing vortex curved cavity |
| CN110822480A (en) * | 2019-11-27 | 2020-02-21 | 中国人民解放军国防科技大学 | Ignition device in supersonic concave cavity combustion chamber and scramjet engine |
| CN112113242A (en) * | 2020-11-09 | 2020-12-22 | 南昌航空大学 | Inside and outside cavity combination configuration standing vortex combustor |
| CN112503571A (en) * | 2020-12-04 | 2021-03-16 | 中国科学院工程热物理研究所 | Afterburner structure of combined flame stabilizer and control method |
| CN113606609A (en) * | 2021-07-19 | 2021-11-05 | 南京航空航天大学 | Combined stabilizer based on center step ignition and working method thereof |
| CN116658937A (en) * | 2023-06-15 | 2023-08-29 | 中国人民解放军空军工程大学 | Concave cavity plasma excitation integrated afterburner |
| CN116839061A (en) * | 2023-06-30 | 2023-10-03 | 融通航空发动机科技有限公司 | High-atomization-performance central combustion flame stabilizer and working method |
-
2023
- 2023-10-26 CN CN202311399554.9A patent/CN117212836B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0893555A (en) * | 1994-07-26 | 1996-04-09 | Ishikawajima Harima Heavy Ind Co Ltd | Ram combustion device |
| CN101776283A (en) * | 2009-01-13 | 2010-07-14 | 北京航空航天大学 | Flame stabilizer with jet injection |
| CN104019465A (en) * | 2014-05-29 | 2014-09-03 | 南京航空航天大学 | Turbine-based combined cycle engine super-combustion chamber |
| CN104373964A (en) * | 2014-10-20 | 2015-02-25 | 北京航空航天大学 | Cavity supporting plate flame stabilizer with built-in oil rod |
| WO2016084111A1 (en) * | 2014-11-25 | 2016-06-02 | ENEA - Agenzia nazionale per le nuove tecnologie, l'energia e lo sviluppo economico sostenibile | Multistage hybrid system for the induction, anchorage and stabilization of distributed flame in advanced combustors for gas turbine |
| CN106642201A (en) * | 2016-12-23 | 2017-05-10 | 中航空天发动机研究院有限公司 | Flame stabilizing device for aircraft engine combustion chamber |
| CN106765310A (en) * | 2016-12-23 | 2017-05-31 | 中航空天发动机研究院有限公司 | For the flameholder with pre-blended chamber of engine chamber |
| CN109915858A (en) * | 2019-03-01 | 2019-06-21 | 西北工业大学 | A kind of supporting plate flameholder premixed with standing vortex curved cavity |
| CN110822480A (en) * | 2019-11-27 | 2020-02-21 | 中国人民解放军国防科技大学 | Ignition device in supersonic concave cavity combustion chamber and scramjet engine |
| CN112113242A (en) * | 2020-11-09 | 2020-12-22 | 南昌航空大学 | Inside and outside cavity combination configuration standing vortex combustor |
| CN112503571A (en) * | 2020-12-04 | 2021-03-16 | 中国科学院工程热物理研究所 | Afterburner structure of combined flame stabilizer and control method |
| CN113606609A (en) * | 2021-07-19 | 2021-11-05 | 南京航空航天大学 | Combined stabilizer based on center step ignition and working method thereof |
| CN116658937A (en) * | 2023-06-15 | 2023-08-29 | 中国人民解放军空军工程大学 | Concave cavity plasma excitation integrated afterburner |
| CN116839061A (en) * | 2023-06-30 | 2023-10-03 | 融通航空发动机科技有限公司 | High-atomization-performance central combustion flame stabilizer and working method |
Non-Patent Citations (1)
| Title |
|---|
| 凹腔对一体化支板火焰稳定器燃烧性能的影响;刘广海;刘玉英;谢奕;;航空动力学报;20180720(第08期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117212836A (en) | 2023-12-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3649403B1 (en) | Auxiliary torch ignition | |
| EP3649404B1 (en) | Auxiliary torch ignition | |
| CN109595589B (en) | Integrated afterburner with two-stage cyclone | |
| US9239167B2 (en) | Lean burn injectors having multiple pilot circuits | |
| US3931707A (en) | Augmentor flameholding apparatus | |
| US5765376A (en) | Gas turbine engine flame tube cooling system and integral swirler arrangement | |
| CN106594800B (en) | A kind of integrated after-burner of double oil circuits injection and supporting plate jet stream | |
| CN111396927B (en) | Two-dimensional array low-pollution combustion device without traditional swirler | |
| CN101737802A (en) | Central cavity stable fire tangential combustion chamber | |
| CN107270328A (en) | Closure standing vortex chamber igniter for gas-turbine unit enhancer | |
| JPH0618041A (en) | Double annular combustion apparatus | |
| CN110953603B (en) | Multi-oil-path fuel oil spraying device suitable for radial grading main combustion chamber | |
| CN110822474A (en) | Flame stabilizing structure of combustion chamber | |
| CN113028451A (en) | Centrifugal nozzle and swirler integrated combustion chamber head structure | |
| CN114608032B (en) | Combustor with widened stability boundary | |
| US11215365B2 (en) | Nozzle for combustors, combustor, and gas turbine including the same | |
| CN116839061A (en) | High-atomization-performance central combustion flame stabilizer and working method | |
| CN109945233B (en) | Combustion chamber, atomization device thereof and aviation gas turbine engine | |
| CN117212836B (en) | Supersonic aircraft and independent oil supply combined flame stabilizer | |
| CN116557914A (en) | Large-scale hydrogen fuel cylinder combustion chamber | |
| EP2825824A1 (en) | Fuel air premixer for gas turbine engine | |
| US5088287A (en) | Combustor for a turbine | |
| RU2226652C2 (en) | Gas-turbine engine combustion chamber | |
| CN114877376B (en) | Dual-channel detonation combustion chamber | |
| CN219530928U (en) | Flame tube, engine and helicopter |
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 | ||
| GR01 | Patent grant |