CN113606609A - Combined stabilizer based on center step ignition and working method thereof - Google Patents
Combined stabilizer based on center step ignition and working method thereof Download PDFInfo
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- CN113606609A CN113606609A CN202110812231.2A CN202110812231A CN113606609A CN 113606609 A CN113606609 A CN 113606609A CN 202110812231 A CN202110812231 A CN 202110812231A CN 113606609 A CN113606609 A CN 113606609A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03343—Pilot burners operating in premixed mode
Abstract
The invention discloses a combined stabilizer based on center step ignition and a working method thereof. The combined stabilizer comprises an on-duty stabilizer, a variable cross-section radial stabilizer and an oil supply system; the on-duty stabilizer comprises a first section of horizontally extending central cone, a second section of downwards extending arc-shaped step arranged at the tail end of the first section of central cone and a third section of central cone downwards extending along the tail end of the second section of arc-shaped step; the variable cross-section radial stabilizer comprises a first straight-section radial stabilizer with a V-shaped cross section and a second straight-section radial stabilizer with a rectangular cross section, wherein the second straight-section radial stabilizer is arranged at the rear end of the first straight-section radial stabilizer. On the premise of not increasing flow loss, the invention improves the soft ignition performance of the combustion chamber, widens the flameout boundary, ensures the structural stability of the connection of the variable cross-section radial stabilizer and the central cone, and also ensures the radial flame transmission performance of the radial stabilizer and the circumferential flame coupling performance close to the periphery.
Description
Technical Field
The invention relates to a turbo/ramjet combined engine and a turbofan engine afterburner/ramjet combustion chamber, in particular to a combined stabilizer based on central step ignition and a working method thereof.
Background
The combined turbine/ram cycle engine is of great interest to broaden flight envelope, achieve conventional takeoff and landing, reusable performance advantages, and is currently considered the most potential hypersonic aircraft power plant. In order to achieve a larger thrust-weight ratio, the modern advanced turbofan engine has large flow and faster flow speed, and simultaneously, because of the ultra-wide working range of the turbine/stamping combined cycle engine, the inflow conditions of an stressing/stamping multi-mode combustion chamber entering a series-type turbine/stamping combined cycle engine are changed greatly, the highest inflow speed is greatly improved, and the difficulty coefficient of stable tissue combustion is increased.
In afterburners or ramjets, both center-fire and wall-fire are typically used as the on-duty ignition. The central ignition generally utilizes a central cone truncated cone or a step to generate a local backflow region, so that good ignition performance is obtained, after ignition, flame can be rapidly transmitted circumferentially, and flame stabilization of an ignition region on duty is realized; and after the ignition is successful, the flame stabilizing area is small, the heat load is low, and the cooling is easy. The truncated cone ignition on duty adopts a sudden expansion mode to establish a stable reflux area for ignition, but the size of the reflux area of the truncated cone is large, so that the reflux rate (the proportion of reflux flow to main flow) is large, and the flow loss is large. Moreover, when the multi-mode stamping combustion chamber flows down at high speed and high temperature and ignition is successful, firstly, the instantaneous heat release rate is high, flame is easy to pass back, the performance of the combustion chamber is damaged, and the soft ignition of the engine is not facilitated; secondly, the ignition pressure pulsation is large, the returned pressure pulsation can damage the working performance of the rotary machine in front of the engine, and the surge of the engine is easily caused.
In a high-speed flow field, the outer wall type flame stabilizer is used as an on-duty flame stabilizer, and compared with central ignition, 5% to 10% of additional flow loss is caused. Moreover, the outer wall type flame stabilizer is located at the maximum outer diameter of the combustion chamber, the radial distance from the heat shield is small, when the high-Mach-number stamping mode is adopted, the cooling air temperature of the heat shield is high, the cooling potential is reduced, in addition, the outer wall type flame stabilizer is close to the heat shield, the heat load of the heat shield is extremely large, the equivalence ratio of an on-duty area is reduced, the heat load of the heat shield when the Mach-number is high can be reduced, the flame temperature of the on-duty area is low, and the supporting performance of the on-duty area on main oil combustion is reduced.
After the ignition is successful, the rapid realization of the radial flame transmission and the circumferential flame connection behind the flame stabilizer is the basis for ensuring the efficient and stable combustion, and the problem of difficult flame transmission of the integrated flame stabilizer when the multi-mode combustion chamber is wide in working range and large in incoming flow condition change needs to be solved at the moment. In the multi-mode combustion chamber, in order to improve the flame coupling capability of the radial stabilizer, the variable-section V-shaped radial stabilizer is widely applied, and the groove width of the general variable-section V-shaped radial stabilizer is linearly changed in the radial direction. Under the condition of keeping certain jam ratio, this has just resulted in when the upper slot width is great, and circumferential flame transmission performance is better, and lower slot width will be too little, is unfavorable for the radial flame transmission of combustion chamber center department, because the area of contact undersize of stabilizer and central awl moreover, lacks structural stability under the adverse circumstances of high-speed high temperature. When the lower groove width is larger, the radial flame transmission performance is met and the structure stability is maintained, the upper groove width is reduced, the peripheral circumferential flame transmission performance is weakened, and the outlet temperature distribution uniformity is reduced.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the problems that a thrust augmentation/stamping combustion chamber in the prior art adopts a central cone truncated cone for on-duty ignition, but the flow loss is large, the pressure pulsation is large, and the like, which are not beneficial to the soft ignition of an engine, the invention provides a combined stabilizer based on central step ignition. The invention also provides a working method of the combined stabilizer.
The technical scheme is as follows: the invention relates to a combined stabilizer based on central step ignition, which comprises an on-duty stabilizer and a variable cross-section radial stabilizer arranged above the on-duty stabilizer; the on-duty stabilizer comprises a first section of horizontally extending central cone, a second section of downwards extending arc-shaped step arranged at the tail end of the first section of central cone and a third section of central cone downwards extending along the tail end of the second section of arc-shaped step; the variable cross-section radial stabilizer comprises a straight-section radial stabilizer arranged above the first-section central cone and a variable-section radial stabilizer arranged above the straight-section radial stabilizer; the straight-section radial stabilizer comprises a first straight-section radial stabilizer with a V-shaped section and a second straight-section radial stabilizer with a rectangular section, wherein the second straight-section radial stabilizer is arranged at the rear end of the first straight-section radial stabilizer; the variable section radial stabilizer comprises a first variable section radial stabilizer and a second variable section radial stabilizer arranged at the rear end of the first variable section radial stabilizer; the two side surfaces of the first change section radial stabilizer are gradually expanded outwards along the extending direction of the Z axis and the extending direction of the Y axis.
And the two side surfaces of the second variable section radial stabilizer are of inverted quadrangular frustum structures which are expanded outwards.
As a preferred structure of the present invention, the combined stabilizer of the present invention further includes an oil supply system, where the oil supply system includes a bleed air pipe extending to the inside of the variable cross-section radial stabilizer, an oil spray rod extending downward into the variable cross-section radial stabilizer and communicating with the bleed air pipe, an ignition electric nozzle located above the second section of arc-shaped step, a splash plate disposed in the bleed air pipe, and an evaporation cavity disposed at an air outlet of the bleed air pipe.
As a preferable structure of the invention, an air inlet of the air-entraining pipe is arranged at the front end of the straight-section radial stabilizer, the air-entraining pipe is distributed in the straight-section radial stabilizer in a circular arc shape, the evaporation cavity is positioned at the front end of the concave cavity of the second section of arc-shaped step, and the rear wall surface of the evaporation cavity is provided with a plurality of oil gas outlets communicated with the evaporation cavity.
In a preferred structure of the present invention, the extending direction of the oil spray bar is perpendicular to the tangential direction of the bleed air pipe.
As a preferable structure of the present invention, the splash plate is located in the middle of the bleed air duct and a normal direction of the splash plate is perpendicular to a tangential direction of the bleed air duct.
As a preferable structure of the present invention, the variable cross-section radial stabilizer extends obliquely backward from bottom to top.
As a preferable structure of the invention, the evaporation cavity is a rectangular cavity arranged at the joint of the first section of the central cone and the second section of the arc-shaped step.
In a preferred structure of the present invention, a trailing edge of the variable cross-section radial stabilizer extends beyond an end of the first section of the central cone, and the ignition tip is disposed at the trailing edge of the variable cross-section radial stabilizer.
In a preferred structure of the present invention, the rear end surface of the variable segment radial flame stabilizer has a trapezoidal cross section.
The invention relates to a working method of a combined stabilizer based on center step ignition, which comprises the following steps:
(a) the incoming flow forms an on-duty backflow region at the second section of arc step along the positive direction of the Z axis, and a main backflow region is formed behind the variable cross-section radial stabilizer;
(b) the aviation kerosene enters the middle part of the air guide pipe from the oil injection rod, impacts the surface of the splash plate to carry out primary atomization to form an oil film, then secondary atomization is carried out under the action of aerodynamic force of air entering from the air guide pipe to break the oil film into oil drops with different particle sizes, the oil drops in the air guide pipe enter the evaporation cavity along with airflow, and the evaporated rich-fuel mixed gas enters the concave cavity formed by the second section of arc-shaped step from the oil gas outlet;
(c) the oil gas outlet is close to the flowing shear layer, and the mixing of air and rich fuel mixed gas can be enhanced by the huge velocity gradient in the shear layer; the mixed oil gas reaches the proper oil gas ratio in the low-speed backflow area of the second section of arc-shaped step, continuous and stable on-duty flame is formed after the mixed oil gas is discharged and ignited by the ignition electric nozzle, and the on-duty flame heats the cavity wall of the evaporation cavity to improve the gas-phase oil gas ratio in the evaporation cavity;
(d) the flame on duty is sucked by a main reflux region behind the variable cross-section radial stabilizer in the process of moving along with the main flow, radially spreads from the tail edge of the variable cross-section radial stabilizer to the periphery of the combustion chamber, and circumferentially spreads through the variable cross-section radial stabilizer to form continuous and stable flame in the combustion chamber.
Has the advantages that: (1) compared with the conventional central conical step, the second section of arc-shaped step has better flameout performance on the premise of not increasing pressure loss, reduces pressure pulsation and is beneficial to realizing soft ignition of an engine; (2) compared with the conventional central truncated cone, the central step of the on-duty stabilizer reduces the sudden expansion height, further reduces the size of a reflux area and reflux quantity for on-duty ignition, reduces the reflux quantity, correspondingly reduces the total pressure loss, has small instantaneous heat release rate for successful ignition and small ignition pressure pulsation, and is beneficial to realizing the soft ignition of an engine; (3) the on-duty flame stabilizing area is far away from the central line position, and is connected with the second section of arc-shaped step by virtue of the inclined plane of the third section of central cone, so that the high-temperature area of the flame is easy to diffuse, the process from the high-temperature area to the outlet is gradually uniform, and the infrared stealth of an aircraft is facilitated; (4) compared with the conventional variable-section radial stabilizer, the variable-section radial stabilizer has the advantages that the groove width of the rear end face of the variable-section radial stabilizer is not linearly gradually changed, but a straight section and linear gradual change combined mode is adopted, so that the structural stability of the connection of the variable-section radial stabilizer and a central cone is ensured, and the radial flame transmission performance and the circumferential flame linkage performance close to the periphery of the variable-section radial stabilizer are also ensured; (5) the premixing and pre-evaporating oil supply system integrated with the variable cross-section radial stabilizer is adopted, so that the atomization and mixing performance of fuel oil is improved, the circumferential distribution uniformity of the fuel oil is improved, and the problem of easy coking of the fuel oil is effectively prevented; the premixing and pre-evaporating oil supply system can improve the atomization and mixing performance of fuel oil, improve the gas-phase oil-gas ratio in the on-duty stabilizer, improve the gas mixing quality and widen the flameout limit of a lean oil point; (6) the variable cross-section radial stabilizer has small groove width close to the central cone and large groove width close to the periphery, and can better realize circumferential propagation of flame under the condition of certain blockage ratio.
Drawings
FIG. 1 is a schematic structural view of a Y-Z axis section of the combined stabilizer of the present invention
FIG. 2 is a side view of the composite stabilizer of the present invention;
FIG. 3 is a cross-sectional view of a variable cross-section radial stabilizer of the present invention;
FIG. 4 is a top view of the composite stabilizer of the present invention;
FIG. 5 is a perspective view of the composite stabilizer of the present invention;
FIG. 6 is a perspective view of the composite stabilizer of the present invention;
FIG. 7 is a top view of a straight segment radial stabilizer of the present invention;
FIG. 8 is a flow chart of a method of operation of the combination stabilizer of the present invention;
fig. 9 shows the flow of the composite stabilizer of the present invention.
Detailed Description
Example 1: the invention discloses a combined stabilizer based on central step ignition, which comprises an on-duty stabilizer 1, a variable cross-section radial stabilizer 2 and an oil supply system 3. As shown in fig. 1, the axial direction in the present invention is the Z-axis direction, the radial direction is the Y-axis direction, and the circumferential direction is the X-axis direction. In the present embodiment, the direction from bottom to top refers to the extending direction of the Y axis in fig. 1, and the direction from front to back refers to the extending direction of the Z axis.
The duty stabilizer 1 comprises a first section of central cone 11 extending horizontally, a second section of arc-shaped step 12 arranged at the tail end of the first section of central cone 11 and extending downwards, and a third section of central cone 13 extending downwards along the tail end of the second section of arc-shaped step 12; the second arc-shaped step 12 is concave to form a concave cavity 100, the third section of the central cone 13 forms a cone angle with the horizontal direction (the direction in which the Z axis extends), and the cone angle theta is set to meet the requirement that no backflow area is generated on the third section of the central cone 13 to increase extra flow loss, and in the embodiment, the cone angle theta is 15 degrees.
As shown in fig. 2 to 6, the variable cross-section radial stabilizer 2 is disposed on the upper wall surface of the first section central cone 11, and includes a straight section radial stabilizer 21 having a rectangular rear end surface (X-Y axis plane) and a variable section radial stabilizer 22 disposed above the straight section radial stabilizer 21 and having two side surfaces expanding outward.
Specifically, the straight radial flame stabilizer 21 is a radial stabilizer with a constant trailing edge groove width, and as shown in fig. 2, 6 and 7, the straight radial flame stabilizer 21 includes a first straight radial stabilizer 211 with a V-shaped cross section (X-axis-Z-axis cross section) and a second straight radial stabilizer 212 with a rectangular cross section (X-axis-Z-axis cross section) disposed at the rear end of the first straight radial stabilizer 211, that is, the first straight radial stabilizer 211 is a triangular prism structure with a V-shaped cross section, and the second straight radial stabilizer 212 is a stabilizer with a cylindrical structure disposed at the rear end of the first straight radial stabilizer 211.
As shown in fig. 4, 5 and 6, in the present embodiment, the variation radial flame stabilizer 22 includes a first variation radial stabilizer 221 and a second variation radial stabilizer 222 disposed at the rear end of the first variation radial stabilizer 221, two side surfaces of the first variation radial stabilizer 221 are outwardly expanded from the front end to the rear end, a width of a tail edge groove of the first variation radial stabilizer 221 is gradually increased along a bottom-to-top direction, and two side surfaces of the first variation radial stabilizer 221 are twisted (two side surfaces of the first variation radial stabilizer 221 are outwardly expanded along a Z-axis extending direction and a Y-axis extending direction). The rear end surface cross section of the second variation section radial stabilizer 222 is trapezoidal (X axis-Y axis cross section), two side surfaces of the second variation section radial stabilizer 222 are inwardly contracted along the Z axis direction, that is, the width of the tail edge groove of the second variation section radial stabilizer 222 is gradually reduced along the Z axis direction, two side surfaces of the second variation section radial stabilizer 222 are outwardly expanded along the Y axis direction, and the whole structure is an approximately inverted quadrangular frustum pyramid structure.
The tail edge of the variable cross-section radial stabilizer 2 exceeds the tail end of the first section of the central cone 11, the variable cross-section radial stabilizer 2 inclines backwards and extends from bottom to top, partial coverage is formed above the concave cavity 100, the ignition performance of the on-duty stabilizer is improved, and the on-duty flame radial propagation is facilitated.
In a specific application, as shown in FIG. 3, (FIG. 3 is a schematic view of the structure of the tail edge of the variable cross-section radial stabilizer) the straight-section radial flame stabilizer 21 has a groove width W21Height h, minimum groove width W of the varying section radial flame holder 2222minMaximum groove width of W22maxAnd the height is H.
The oil supply system 3 comprises a bleed air pipe 31 arranged inside the straight-section radial flame stabilizer 21, an oil injection rod 32 arranged in the variable-section radial flame stabilizer 3 and communicated with the bleed air pipe 31, an ignition electric nozzle 33 positioned above the second-section arc-shaped step 12, a splash plate 34 arranged in the bleed air pipe 31 and an evaporation cavity 35 arranged at an air outlet of the bleed air pipe 31.
The air-entraining pipe 31 of the present invention is located above the first section central cone 11, specifically, an air inlet of the air-entraining pipe 31 is disposed at the front end of the straight section radial flame stabilizer 21, the air-entraining pipe 31 is a circular pipe, and an air outlet of the air-entraining pipe 31 is communicated with the evaporation cavity 35. One section of the bleed pipe 31 is positioned outside the variable cross-section radial stabilizer 2 and is opposite to incoming flow, and the other section of the bleed pipe 31 is arranged inside the straight section radial flame stabilizer 21. The bleed pipe 31 arranged inside the straight radial flame stabilizer 21 is communicated with the fuel injection rod 32, the fuel injection rod 32 and the variable cross-section radial stabilizer 2 extend in the same radial inclined direction, the fuel injection rod 32 extends in the variable cross-section radial stabilizer 2 along the radial inclined direction, and the tail end of the fuel injection rod 34 is communicated with the bleed pipe 31 through a fuel nozzle 37, wherein the diameter of the fuel nozzle is 0.5mm in the embodiment. The air guide pipe 31 is of an arc structure at the intersection with the oil injection rod 32, and the extension direction of the oil injection rod 32 is perpendicular to the tangential direction of the arc section of the air guide pipe 31. A splash plate 34 is arranged in the bleed air duct 31, the splash plate 34 being located in the middle of the bleed air duct 5, the normal direction of the splash plate 34 being oriented tangentially (O) to the arc-shaped section of the bleed air duct 312) And is vertical.
In the present embodiment, the ignition torch 33 is arranged inside the trailing edge of the variable-section radial stabilizer 2, and in particular, the ignition torch 33 is arranged at the end of the trailing edge of the variable-section radial stabilizer 2 covering the cavity 100.
The evaporation cavity 35 is located the cavity 100 front end of second section arc step 12, specifically, in this embodiment, the evaporation cavity 35 sets up the front end at the internal face of first section centre cone 11 and the internal face juncture of second section arc step 12, and evaporation cavity 35 is the rectangle chamber along the X axle direction, and the back wall of evaporation cavity 35 is provided with a plurality of oil gas export 36, and in this embodiment, the oil gas export is the oil gas export that the cross-section is the rectangle. The oil gas outlets 36 are arranged in two rows at the rear side of the evaporation cavity 35 and avoid the position right below the radial stabilizer, so that the phenomenon that the discharged rich-fuel mixed gas is directly sucked into the main flow by the main backflow area behind the variable-section radial stabilizer 2 to cause the ignition performance on duty to be poor is avoided. The mixed gas from the oil gas outlet 36 moves along the axial direction, and has larger jet flow depth and expansion angle compared with a circular hole.
As shown in fig. 8 and 9, the operation method of the center step ignition based composite stabilizer of the present invention comprises the steps of:
(a) the coming flow forms an on-duty reflux area at the second section of arc step 12 along the positive direction of the Z axis, and forms a main reflux area behind the variable cross-section radial stabilizer 2;
(b) aviation kerosene enters the middle part of the air guide pipe 31 from the oil injection rod 32, impacts the surface of the splash plate 34 to carry out primary atomization to form an oil film, then secondary atomization is carried out under the action of aerodynamic force of air entering from the air guide pipe 31, the oil film is crushed into oil drops with different particle sizes, the oil drops in the air guide pipe 31 enter the evaporation cavity 35 along with air flow, and evaporated rich-fuel mixed gas enters the concave cavity 100 formed by the second section of arc-shaped step 12 from the oil gas outlet 36;
(c) the oil gas outlet 36 is close to the flowing shear layer, and the mixing of air and rich fuel mixed gas can be enhanced by the huge velocity gradient in the shear layer; the rectangular oil gas outlet 36 has a jet flow depth and an expansion angle larger than those of the circular air outlet holes, so that the mixing effect of fresh air and rich-combustion mixed gas is further enhanced; the mixed oil gas reaches the oil gas proper ratio in the low-speed backflow area of the second section of arc-shaped step 12, continuous and stable on-duty flame is formed after the mixed oil gas is discharged and ignited by the ignition electric nozzle 32, and the on-duty flame heats the cavity wall of the evaporation cavity 35 to improve the gas-phase oil gas ratio in the evaporation cavity 35;
(d) the flame on duty is sucked by a main reflux region behind the variable cross-section radial stabilizer 2 in the process of moving along with the main flow, is radially transmitted from the tail edge of the variable cross-section radial stabilizer 2 to the periphery of the combustion chamber, and is transmitted in the circumferential direction through the variable cross-section radial stabilizer 2 to form continuous and stable flame in the combustion chamber.
Claims (10)
1. A combined stabilizer based on center step ignition is characterized by comprising an on-duty stabilizer (1) and a variable cross-section radial stabilizer (2) arranged above the on-duty stabilizer (1); the duty stabilizer (1) comprises a first section of central cone (11) extending horizontally, a second section of arc-shaped step (12) arranged at the tail end of the first section of central cone (11) and extending downwards, and a third section of central cone (13) extending downwards along the tail end of the second section of arc-shaped step (12); the variable cross-section radial stabilizer (2) comprises a straight-section radial stabilizer (21) arranged above the first-section central cone (11) and a variable-section radial stabilizer (22) arranged above the straight-section radial stabilizer (21); the straight-section radial stabilizer (21) comprises a first straight-section radial stabilizer (211) with a V-shaped section and a second straight-section radial stabilizer (212) with a rectangular section, wherein the second straight-section radial stabilizer is arranged at the rear end of the first straight-section radial stabilizer (211); the variable segment radial stabilizer (22) comprises a first variable segment radial stabilizer (221) and a second variable segment radial stabilizer (222) arranged at the rear end of the first variable segment radial stabilizer (221); the two side surfaces of the first change segment radial stabilizer (221) are gradually expanded outwards along the extending direction of the Z axis and the extending direction of the Y axis.
2. The center step ignition based combination stabilizer of claim 1, wherein the second varying section radial stabilizer (222) is an inverted quadrangular frustum structure with two outwardly flared sides.
3. The combination stabilizer based on center step ignition of claim 1, characterized by further comprising an oil supply system (3), wherein the oil supply system (3) comprises a bleed air pipe (31) extending to the inside of the variable cross-section radial stabilizer (2), an oil spray bar (32) extending to the inside of the variable cross-section radial stabilizer (2) and communicating with the bleed air pipe (31), an ignition electric nozzle (33) located above the second arc-shaped step (12), a splash plate (34) arranged in the bleed air pipe (31), and an evaporation cavity (35) arranged at the air outlet of the bleed air pipe (31).
4. The combination stabilizer based on central step ignition of claim 3, characterized in that the air inlet of the air-entraining pipe (31) is arranged at the front end of the straight radial stabilizer (21), the air-entraining pipe (31) is distributed in the straight radial stabilizer (21) in a circular arc shape, the evaporation cavity (35) is arranged at the front end of the cavity (100) of the second section of the arc-shaped step (12), and the rear wall surface of the evaporation cavity (35) is provided with a plurality of oil and gas outlets (36) communicated with the evaporation cavity (35).
5. Combined stabilizer based on center step ignition according to claim 4 characterized in that the extension direction of the lance (32) is perpendicular to the tangential direction of the bleed duct (31).
6. The combination stabilizer based on center step ignition of claim 5, characterized in that the splash plate (34) is located in the middle of the bleed duct (31) and the normal direction of the splash plate (34) is perpendicular to the tangential direction of the bleed duct (31).
7. Combined stabilizer based on center step ignition according to claim 6 characterized in that the variable section radial stabilizer (2) extends from bottom to top inclined backwards.
8. The combination stabilizer based on center step ignition of claim 7, characterized in that the evaporation cavity (35) is a rectangular cavity provided at the junction of the first section center cone (11) and the second section arc step (12).
9. Combined stabilizer based on center step ignition according to claim 7 characterized in that the trailing edge of the variable cross section radial stabilizer (2) is beyond the end of the first section central cone (11) and the ignition nozzle (33) is arranged at the trailing edge of the variable cross section radial stabilizer (2).
10. The method of operating a combination stabilizer based on center step ignition of claim 1, comprising the steps of:
(a) the coming flow forms an on-duty reflux area at the second section of arc step (12) along the positive direction of the Z axis, and a main reflux area is formed behind the variable cross-section radial stabilizer (2);
(b) aviation kerosene enters the middle part of the air guide pipe (31) from the oil injection rod (32), impacts the surface of the splash plate (34) to carry out primary atomization to form an oil film, then secondary atomization is carried out under the action of aerodynamic force of air entering from the air guide pipe (31), the oil film is crushed into oil drops with different particle sizes, the oil drops in the air guide pipe (31) enter the evaporation cavity (35) along with air flow, and evaporated rich-fuel mixed gas enters the concave cavity (100) formed by the second section of arc-shaped step (12) from the oil-gas outlet (36);
(c) the oil gas outlet (36) is close to the flowing shear layer, and the mixing of air and rich fuel mixed gas can be enhanced through the huge velocity gradient in the shear layer; the mixed oil gas reaches the oil gas proper ratio in the low-speed backflow area of the second section of arc-shaped step (12), continuous and stable on-duty flame is formed after the mixed oil gas is discharged and ignited by the ignition electric nozzle (32), and the on-duty flame heats the cavity wall of the evaporation cavity (35) to improve the gas-phase oil gas ratio in the evaporation cavity (35);
(d) the on-duty flame is sucked by a main backflow region behind the variable cross-section radial stabilizer (2) in the process of moving along with the main flow, radially spreads from the tail edge of the variable cross-section radial stabilizer (2) to the periphery outside the combustion chamber, and circumferentially spreads flame through the variable cross-section radial stabilizer (2) to form continuous and stable flame in the combustion chamber.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115164234A (en) * | 2022-05-12 | 2022-10-11 | 中国航发四川燃气涡轮研究院 | Afterburner flame stabilizer |
| CN115307179A (en) * | 2022-08-15 | 2022-11-08 | 北京航空航天大学 | Double-cavity integrated afterburner with bent support plate |
| CN115371080A (en) * | 2022-07-05 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Enhanced tissue combustion chamber |
| CN117212836A (en) * | 2023-10-26 | 2023-12-12 | 融通航空发动机科技有限公司 | Supersonic aircraft and independent oil supply combined flame stabilizer |
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| 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 |
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| CA2859435A1 (en) * | 2013-08-16 | 2015-02-16 | Alstom Technology Ltd. | Burner arrangement and method for operating a burner arrangement |
| 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 |
| CN109780571A (en) * | 2018-12-26 | 2019-05-21 | 南京航空航天大学 | A kind of vaporation-type combination flameholder |
| CN110762555A (en) * | 2019-10-24 | 2020-02-07 | 南京航空航天大学 | Pneumatic auxiliary type flame stabilizer with concave cavity supporting plate |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115164234A (en) * | 2022-05-12 | 2022-10-11 | 中国航发四川燃气涡轮研究院 | Afterburner flame stabilizer |
| CN115164234B (en) * | 2022-05-12 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Afterburner flame stabilizer |
| CN115371080A (en) * | 2022-07-05 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Enhanced tissue combustion chamber |
| CN115371080B (en) * | 2022-07-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Reinforced tissue combustion chamber |
| CN115307179A (en) * | 2022-08-15 | 2022-11-08 | 北京航空航天大学 | Double-cavity integrated afterburner with bent support plate |
| CN117212836A (en) * | 2023-10-26 | 2023-12-12 | 融通航空发动机科技有限公司 | Supersonic aircraft and independent oil supply combined flame stabilizer |
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| CN113606609B (en) | 2022-10-11 |
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