Double-support-plate integrated afterburner

Abstract

The double-supporting-plate integrated afterburner comprises a center cone, a main supporting plate, an auxiliary supporting plate, a flow dividing ring, an outer shell, an oil injection rod and a heat insulation screen. Wherein the main support plate plays roles in supplying oil and stabilizing flame, and incoming flow forms a backflow area behind the tail edge of the main support plate and organizes combustion; the auxiliary support plate adopts a hollow wing-shaped design and plays a role in rectifying and shielding a rotor part; the main supporting plates and the auxiliary supporting plates are distributed in a main duct annular airflow channel formed by the flow dividing ring and the center cone in a spaced mode. The integrated afterburner stabilizer supporting plate can cope with the adverse effect of non-uniform incoming flow represented by strong residual rotation on a backflow area behind the integrated afterburner stabilizer supporting plate, fuel oil distribution can be improved, the infrared shielding area is increased, and the stealth capacity of an aero-engine in the non-afterburner state can be improved.

Description

Technical Field

[0001] The present disclosure relates to the technical field of afterburner chambers for aircraft engines, and in particular to a double-bracket integrated afterburner chamber. Background Art

[0002] The continuous evolution of aircraft engine technology has made the improvement of thrust-to-weight ratio an inevitable trend, which has put forward more stringent requirements on the compactness of the afterburner. In response to this, the new generation of afterburners moves the rear support device of the traditional turbine components to the inside of the afterburner, uses the straightening support plate of the afterburner to take into account the role of structural support, and integrates the straightening support plate, flame stabilizer and fuel nozzle into an integrated design, thereby greatly reducing the overall weight of the aircraft engine and effectively improving the engine's thrust-to-weight ratio.

[0003] However, this change also brings many challenges. Since the inlet section of the integrated afterburner is moved to the outlet section of the turbine blades, the unevenness of the turbine outlet velocity caused by various factors such as the wake effect generated by the high-speed rotation of the turbine blades, the non-steady-state characteristics of the turbine during operation, and the cooling effect of the cooling airflow on the turbine wall will cause the intake conditions of the afterburner to deteriorate sharply, thereby causing a non-uniform state in the direction of the afterburner inlet velocity, which will have a very significant impact on the flow field characteristics and combustion characteristics of the support plate in the afterburner, hindering the engineering application progress of high-performance integrated afterburner.

[0004] The velocity direction of the afterburner inlet in a non-uniform state is usually expressed as a cosine angle, that is, the angle between the airflow velocity at the inlet of the afterburner and the axial direction. Depending on the aircraft engine model and operating conditions, the maximum cosine angle can vary between 0-60°. In the non-uniform incoming flow state, the integrated structure of the support plate-stabilizer-injection rod in the prior art is difficult to ensure that the afterburner achieves the expected working performance indicators: due to the cosine angle of the incoming flow, the fuel sprayed from the injection rod will have different atomization effects on both sides of the circumference of the integrated structure, greatly reducing the combustion stability and distribution uniformity. In response to this, some prior arts use a long bent and twisted support plate structure to weaken the impact of non-uniform incoming flow, but the rectification effect of a single support plate is not enough to meet the needs of stable combustion; other prior arts use a multi-support plate relay rectification method. Although the rectification effect is improved, it greatly increases the length and weight of the support plate, increases the difficulty of cooling, and sacrifices the total pressure recovery coefficient of the afterburner part.

[0005] It should also be noted that the design requirements of the new generation of afterburner combustion chambers also include infrared stealth capabilities in the non-afterburner state of the aircraft engine. Therefore, effectively shielding the turbine rotor components in the non-afterburner state becomes the key to reducing infrared radiation leaking from the tail of the engine. In the existing technology, effective infrared shielding is usually achieved by arranging a support plate stabilizer with a larger inclination angle. However, the larger inclination angle brings about technical problems such as the support plate stabilizer structure is not compact and the flow loss is large. Summary of the invention

[0006] In view of the above technical problems, the present invention aims to provide a double-support plate integrated afterburner combustion chamber, which not only has a compact structure, but also has a good rectification effect in the afterburner state and low infrared radiation in the non-afterburner state.

[0007] The present invention provides a double-bracket integrated afterburner, wherein the interior of the double-bracket integrated afterburner includes an inner region located between a central cone and a flow divider ring, and an outer region located between the flow divider ring and an outer shell, wherein the inlet flow of the inner region is deflected at an angle α relative to the axial direction, and the double-bracket integrated afterburner further includes:

[0008] The main support plates are evenly distributed in the inner region along the circumferential direction, and in the cross section perpendicular to the radial direction, the cross section of the main support plates is an axisymmetric figure with the symmetry axis parallel to the axial direction;

[0009] a secondary support plate, which is disposed between two adjacent primary support plates in the circumferential direction, is located in front of the primary support plate in the axial direction and overlaps at least partially with the projection of the primary support plate in the axial direction; in a cross section perpendicular to the radial direction, the cross section of the secondary support plate is an airfoil; the chord length direction of the airfoil is deflected by an angle β relative to the axial direction; the deflection direction of the angle β is the same as the deflection direction of the angle α, and the magnitude of the angle β is smaller than the magnitude of the angle α; and

[0010] The fuel injection rod is fixedly arranged on the outer shell and extends through the diverter ring to the inside of the main support plate, so as to supply fuel and spray the fuel outward from the outer wall surface of the main support plate.

[0011] Preferably, the circumferential spacing d between the main support plate and the secondary support plate is 1 to 1.5 times the maximum circumferential width D of the main support plate, and the overlapping length l of the axial projections of the main support plate and the secondary support plate is 1 / 5 to 1 / 3 of the axial length L of the main support plate.

[0012] Preferably, the airfoil of the secondary strut obtains a maximum thickness T at 20-40% of the chord length C, and the maximum thickness T is 9-15% of the chord length C; the airfoil of the secondary strut obtains a maximum camber R at 35-45% of the chord length C, and the maximum camber R is 4-8% of the chord length C.

[0013] Preferably, the main support plate and the auxiliary support plate are hollow structures, and the main support plate and the auxiliary support plate are connected to the outer culvert area through the diverter ring on the radial outside.

[0014] Preferably, the main support plate includes a main body region and a head region. On a cross section perpendicular to the radial direction, the cross-sectional shape of the head region is a streamlined configuration, and the main body region is connected to the rear of the head region and extends axially rearward.

[0015] Preferably, the double-support plate integrated afterburner chamber further comprises:

[0016] a first fuel nozzle, symmetrically arranged on two circumferential side walls of the main body region, and in a cross section perpendicular to the circumference, a projection of the first fuel nozzle falls within the range of the injection rod;

[0017] A second oil spray nozzle is symmetrically arranged on two circumferential side walls of the main body region near one end of the head region; and / or

[0018] a third fuel nozzle disposed at a front end of the head region;

[0019] Wherein, the first fuel nozzle, the second fuel nozzle and / or the third fuel nozzle are connected to the fuel injection rod through a fuel branch pipe.

[0020] Preferably, a partition is provided in the hollow structure of the auxiliary support plate, and the partition separates the auxiliary support plate into a cooling chamber close to the incoming flow direction and an oil supply chamber away from the incoming flow direction. The oil supply chamber is provided with a fourth fuel nozzle on the suction surface side of the auxiliary support plate, and the fourth fuel nozzle is connected to the oil supply chamber.

[0021] Preferably, the double-support plate integrated afterburner chamber further comprises:

[0022] An actuating device is arranged in the outer region and connected to the auxiliary support plate to adjust the angle β between the chord length direction and the axial direction of the auxiliary support plate according to working conditions.

[0023] Preferably, the actuating device is configured to adjust the angle β so that when the double-bracket integrated afterburner chamber is in the afterburner state, the angle β is equal to the angle α minus 10-20°.

[0024] Preferably, the actuating device is configured to adjust the β angle so that the β angle when the double-bracket integrated afterburner combustion chamber is in the afterburner state is smaller than the β angle when the double-bracket integrated afterburner combustion chamber is in the non-afterburner state.

[0025] The above technical scheme adopted by the present invention has the following technical effects: the distribution design between the main / auxiliary support plates can cope with the adverse effects of non-uniform incoming flow represented by strong residual swirl on the recirculation area behind the stabilizer support plate of the integrated afterburner, can improve the fuel distribution, and effectively increase the infrared shielding area, which can improve the stealth capability of the aircraft engine and is more conducive to meeting the needs of high-performance integrated afterburner engineering applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of a 1 / 12 sector structure of a double-support plate integrated afterburner chamber of the present invention;

[0027] Figure 2 It is a structural schematic diagram of the double-support plate integrated afterburner chamber of the present invention from a rear view angle;

[0028] Figure 3 It is a schematic cross-sectional view perpendicular to the radial direction of the single-zone fuel supply scheme of the double-support plate integrated afterburner of the present invention;

[0029] Figure 4 It is a schematic cross-sectional view perpendicular to the radial direction of the multi-zone fuel supply scheme of the double-support plate integrated afterburner of the present invention;

[0030] Figure 5 The velocity cloud diagram and streamline diagram of the single-zone fuel supply scheme of the double-support plate integrated afterburner in the present invention on the cross section perpendicular to the radial direction;

[0031] Figure 6 This is a cloud diagram of fuel distribution concentration on a cross section perpendicular to the radial direction for a single-zone fuel supply scheme of a double-support plate integrated afterburner of the present invention.

[0032] In the figure, 1-center cone; 2-main support plate; 201-hollow structure of main support plate; 21-main body area; 22-head area; 3-auxiliary support plate; 301-hollow structure of auxiliary support plate; 31-cooling chamber; 32-fuel supply chamber; 321-fourth fuel nozzle; 4-diverter ring; 5-outer shell; 6-injection rod; 61-first fuel nozzle; 62-second fuel nozzle; 63-third fuel nozzle; 64-fuel branch pipe; 7-heat shield. DETAILED DESCRIPTION

[0033] The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings:

[0034] The present invention may be implemented in many different forms and should not be considered limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0035] like Figure 1-6As shown, the present invention provides a double-bracket integrated afterburner, the main structure of which is a center cone 1, a main bracket 2 (or stabilizer bracket), a secondary bracket 3 (or rectifying bracket), a diverter ring 4, an outer shell 5, a fuel injection rod 6 and a heat shield 7. Figure 1 The interior of the double-bracket integrated afterburner chamber includes an inner region between the center cone 1 and the diverter ring 4, and an outer region between the diverter ring 4 and the outer shell 5. The main support plate 2 and the secondary support plate 3 are evenly distributed along the circumferential direction between the center cone 1 and the diverter ring 4, and are arranged at intervals from each other. A fuel injection rod 6 is arranged inside the main support plate 2. The outer end of the fuel injection rod 6 is fixedly arranged on the outer shell 5, and the inner end passes through the diverter ring 4 and extends to the inside of the main support plate 2, so as to supply fuel and spray the fuel outward from the outer wall of the main support plate 2. Behind the trailing edge of the main support plate 2, the area surrounded by the heat shield 7 is the afterburner area. Through the fuel supply of the fuel injection rod 6, a stable afterburner area is organized behind the main support plate 2.

[0036] In order to cope with the flow field environment of non-uniform incoming flow, the present invention adopts a double branch plate structural design. The main branch plate and the auxiliary branch plate are arranged in the annular airflow channel formed by the diverter ring and the central cone. The main branch plate is a stabilizer branch plate, which plays the role of oil supply and flame stabilization, and the auxiliary branch plate is a rectifying branch plate, which plays the role of rectifying and shielding.

[0037] Specifically, the secondary support plate 3 is disposed between two adjacent primary support plates 2 along the circumferential direction, and is located in front of the primary support plate 2 along the axial direction and overlaps at least partially with the projection of the primary support plate 2 in the axial direction, that is, the rear section of the secondary support plate and the leading edge of the primary support plate are located at approximately the same circumferential position. In the cross section perpendicular to the radial direction, the cross section of the secondary support plate 3 is airfoil-shaped, and the chord length direction of the airfoil is deflected by an angle β relative to the axial direction. Figure 3-4 , considering the inlet airflow deflection with an angle α with the axial direction, the angle β with the same deflection direction as the angle α can effectively adjust the direction of the inlet airflow: see the attached Figure 5, when flowing through the secondary branch plate 3, the inlet flow is divided into two airflows, namely the pressure surface (or the windward surface, the ventral surface of the blade) and the suction surface (or the leeward surface, the back surface of the blade). The airflow on the pressure surface is incident on the ventral surface of the secondary branch plate 3 at an angle α, and smoothly changes its own angle along the airfoil structure of the secondary branch plate 3 until it basically returns to the axial flow direction when it reaches the trailing edge of the secondary branch plate 3; the airflow on the suction surface is squeezed by the surrounding gas to the back surface of the blade that fits the secondary branch plate 3 at a higher flow speed and lower pressure when flowing through the back surface of the blade of the secondary branch plate 3, and gradually changes its own flow direction along the curvature of the back surface of the blade until it basically returns to the axial flow direction when it reaches the trailing edge of the secondary branch plate 3. It can be seen that the present invention can successfully adjust the angle α of the uneven incoming flow by arranging the secondary branch plate 3, so that the rectified airflow basically flows in the axial direction. On this basis, the present invention arranges the main branch plate 2 axially rearward of the secondary branch plate 3, so that the main branch plate 2 can receive the airflow basically in the axial direction after rectification from the secondary branch plate 3.

[0038] Furthermore, if Figure 3 and Figure 4 As shown, in the cross section perpendicular to the radial direction, the present invention constructs the main support plate 2 into an axisymmetric figure with the symmetry axis parallel to the axial direction, so that the airflow flowing through the two circumferential side walls of the main support plate 2 can be basically symmetrical. In this case, the fuel sprayed from the two side walls of the main support plate 2 will be mixed with the airflow flowing along the two side walls of the main support plate 2, so that the oil-gas mixture is as follows at the downstream of the main support plate 2 Figure 6 The basically symmetrical distribution state shown makes the distribution state of the fuel close to the designed oil-gas ratio, making it easier to organize combustion and avoiding the undesirable state where the oil-gas mixture on both sides of the main support plate 2 is too rich or too lean and does not fall into the combustible boundary.

[0039] Compared with the afterburner in the prior art, the present invention adds a secondary support plate 3, but due to the airfoil section of the secondary support plate 3, its flow loss is extremely small. At the same time, by controlling the deflection direction of the β angle to be the same as the deflection direction of the α angle, and controlling the size of the β angle to be smaller than the size of the α angle, the present invention can obtain a smaller total pressure loss on the basis of completing effective rectification, and has excellent performance in fluidity. Since the chord of the secondary support plate is deflected around the axial direction by an angle of β, the rear-view shielding area is increased, and the present invention also has better infrared stealth characteristics.

[0040] It should be noted that the directions of the angles α and β of the present invention adopt the definition of general direction angles, that is, from the axial direction to the rear ( Figure 3 and Figure 4 The horizontal right in the figure is 0°, the counterclockwise direction is positive, and the clockwise direction is negative. The angles α and β refer to the absolute values ​​of the angles regardless of direction. Figure 3-4 As shown, in a typical embodiment of the present invention, the angle α is +30° and the angle β is +10°.

[0041] In some embodiments, considering that the incoming airflow deflection angle is affected by the working conditions of the aircraft engine, the deflection angle β of the secondary strut 3 can also be dynamically adjusted with the angle α of the incoming airflow deflection. In this embodiment, the present invention sets an actuating device in the outer region, and connects the actuating device to the secondary strut 3 to adjust the angle β between the chord length direction and the axial direction of the secondary strut 3 according to the working conditions. The above-mentioned actuating device can be, for example, an adjustment ring connecting all the secondary struts 3 and an actuating cylinder matched therewith. The relevant structure is relatively mature in the prior art and will not be discussed as the focus here.

[0042] In some embodiments, the present invention may adopt the following adjustment method: the actuating device is configured to adjust the angle β so that when the dual-bracket integrated afterburner chamber is in the afterburner state, the angle β is equal to the angle α minus 10-20°. Thus, the deflection angle β of the secondary branch plate 3 will be adjusted in real time with the unevenness of the incoming flow velocity direction, so that the velocity direction of the incoming flow on the upper and lower walls of the secondary branch plate after being rectified by the secondary branch plate is basically along the axial direction.

[0043] In some embodiments, the present invention may also adopt the following adjustment method: the actuator is configured to adjust the β angle so that the β angle when the dual-bracket integrated afterburner is in the afterburner state is smaller than the β angle when the afterburner is not in the afterburner state. For this, those skilled in the art understand that the infrared shielding capability in the non-afterburner state is characterized by the rear-view area shielding rate (i.e., the rear-view area ratio of the relatively low-temperature component shielding the high-temperature area), the main support plate 2 has a fixed rear-view area shielding rate, and the rear-view shielding rate of the secondary support plate 3 is determined by the chord length and the chord rotation angle. In the case where the secondary support plate 3 has a certain chord length, the present invention can adjust the infrared stealth characteristics of the afterburner of the present invention by adjusting the size of the β angle.

[0044] With regard to the above adjustment method, those skilled in the art understand that, for an aircraft engine having an afterburner of the present invention, if it is in an afterburner state, it means that the situation is relatively urgent at this time, and the aircraft may need to significantly increase thrust for air combat or has been detected by radar, and urgently needs to accelerate to get rid of it or make complex maneuvers. Therefore, there is no need to pay extra attention to the infrared stealth effect and adjust the secondary support plate 3 to a smaller β angle with the axis to enhance the rectifying effect to provide more power; correspondingly, if the present invention is in a non-afterburner state, it means that the aircraft is in a cruising state at this time and has not been detected by radar. At this time, the infrared stealth effect can be considered more and the secondary support plate 3 can be adjusted to a larger β angle with the axis to expand the rear view shielding area of ​​the secondary support plate 3 and improve the infrared stealth performance of the engine.

[0045] Of course, compared with the prior art using a single support plate, the present invention has increased the infrared stealth performance by setting up main and secondary double support plates. For reference, in one embodiment of the present invention, the chord deflection angle β of the secondary support plate 3 is 10°. When the flow loss remains almost unchanged, the area shielding rate is increased by 15%, thereby significantly improving the infrared stealth capability of the aircraft engine in the non-afterburner state.

[0046] For the afterburner using double support plates, the design parameters of the main / secondary support plates mainly include the circumferential spacing d of the main / secondary support plates and the axial overlap length l of the main / secondary support plates. The reasonable design of the two can make the addition of the secondary support plate 3 basically unchanged in the blockage ratio, and the blockage ratio of the main duct is only related to the structural parameters of the main support plate 2, thereby ensuring good air flow capacity and low total pressure loss in the main duct. Based on this, in a preferred embodiment of the present invention, the circumferential spacing d between the main support plate 2 and the secondary support plate 3 is 1 to 1.5 times the maximum circumferential width D of the main support plate 2, and the axial projection overlap length l of the main support plate 2 and the secondary support plate 3 is 1 / 5 to 1 / 3 of the axial length L of the main support plate. In a more specific embodiment of the present invention, the circumferential spacing d between the main and auxiliary support plates is 70 mm, the axial overlap length l between the main and auxiliary support plates is 50 mm, the maximum circumferential width D of the main support plate 2 is 40 mm, and the axial length L of the main support plate 2 is 150 mm. The blockage ratio calculated thereby is 0.27, and the total pressure recovery coefficient is above 0.953.

[0047] The secondary support plate 3 of the present invention adopts an airfoil design, which is smaller in size than the main support plate 2, and due to its own streamlined characteristics, the flow loss is extremely small. When the inlet flow flows through the secondary support plate 3, the secondary support plate 3 rectifies the inlet non-uniform flow, so that the flow direction of the flow gradually returns to the axial direction. In the embodiment of the present invention, the airfoil of the secondary support plate 3 obtains the maximum thickness T at 20-40% of the chord length C, and the maximum thickness T is 9-15% of the chord length C. The maximum thickness T of the secondary support plate 3 is not less than 9% of the chord length C, so that the amount of cold air that can enter the cold air channel is increased, and the heat load resistance and structural strength are enhanced. The maximum thickness T of the secondary support plate 3 does not exceed 15% of the chord length C, which can avoid the adverse consequences of increased aerodynamic resistance due to excessive thickness. The airfoil of the auxiliary support plate 3 achieves a maximum camber R at 35-45% of the chord length C, and the maximum camber R is 4-8% of the chord length C. This value range allows the auxiliary support plate 3 to ensure a straightening effect with sufficient camber without causing aerodynamic separation due to excessive camber.

[0048] Preferably, the main support plate 2 and the secondary support plate 3 are hollow structures, and the main support plate 2 and the secondary support plate 3 are connected to the outer duct area through the diverter ring 4 on the radial outside, so that the cold air in the outer duct area can enter the interior of the main support plate 2 and the secondary support plate 3 through the hollow structure, and cool the main support plate 2 and the secondary support plate 3, so that the main support plate 2 and the secondary support plate 3 can work normally and reliably under the high-temperature airflow at the turbine outlet.

[0049] Preferably, the main support plate 2 includes a main body area 21 and a head area 22. In the section perpendicular to the radial direction, the cross-sectional figure of the head area 22 is a streamlined configuration to obtain lower flow resistance, and the main body area 21 is connected to the rear of the head area 22 and extends axially backward, thereby forming a stable combustion area behind the main support plate 2.

[0050] On this basis, in order to better organize combustion, in some embodiments, the double-bracket integrated afterburner of the present invention also includes a plurality of fuel nozzles arranged on the main support plate 2, wherein the first fuel nozzle 61 is symmetrically arranged on the two circumferential side walls of the main body area 21, and on the cross section perpendicular to the circumference, the projection of the first fuel nozzle 61 falls within the range of the injection rod 6; the second injection nozzle 62 is symmetrically arranged on the two circumferential side walls of the main body area 21 near one end of the head area 22; and / or the third fuel nozzle 63 is arranged at the front end of the head area 22; and the first fuel nozzle 61, the second fuel nozzle 62 and / or the third fuel nozzle 63 are connected to the injection rod 6 through the fuel branch pipe 64.

[0051] Furthermore, corresponding fuel nozzles can also be arranged on the secondary support plate 3. However, since the size of the secondary support plate 3 is much smaller than the main support plate 2, the secondary support plate 3 of the present invention adopts the following structure to realize fuel supply and fuel injection: a partition is provided in the hollow structure of the secondary support plate 3, and the partition separates the secondary support plate 3 into a cooling chamber 31 close to the high-temperature flow direction and an oil supply chamber 32 away from the high-temperature flow direction. The oil supply chamber 32 is provided with a fourth fuel nozzle 321 on the suction side of the secondary support plate 3, and the fourth fuel nozzle 321 is connected to the oil supply chamber 32.

[0052] Based on the above-mentioned multiple fuel nozzles, the present invention can flexibly select a fuel supply scheme according to the complex working conditions of the afterburner and the working requirements of organizing stable combustion. In one embodiment, Figure 3 As shown, the present invention can adopt a single-zone fuel supply scheme, where only the first fuel nozzle 61 located at the trailing edge of the main support plate 2 supplies fuel for combustion. The technical effect can be referred to Figure 5 The cross-sectional velocity cloud diagram and streamline diagram shown in the figure show that the recirculation area behind the main support plate 2 forms two symmetrical vortex centers, which greatly reduces the adverse effect of non-uniform incoming flow on the flow field in the recirculation area. Figure 6 The cross section of fuel (aviation kerosene C 12 H 23) concentration cloud diagram, the fuel is symmetrically distributed on both sides of the trailing edge of the main support plate 2, and is basically not affected by the airflow deflection caused by the non-uniform incoming flow, which will be extremely beneficial to the organization and stability of combustion.

[0053] In another embodiment of the present invention, Figure 4 As shown, the first fuel nozzle 61, the second fuel nozzle 62, the third fuel nozzle 63 and the fourth fuel nozzle 321 jointly supply fuel to form a four-zone fuel supply scheme, in which the fuel sprayed by the first fuel nozzle 61 can ensure the fuel flow rate sucked into the recirculation zone and ensure stable combustion; the fuel sprayed by the second fuel nozzle 62 can have a longer expansion distance, so that the flame has a longer penetration distance, and improve the cross-flame performance in the afterburner; the fuel sprayed by the third fuel nozzle 63 can weaken the heat load caused by the high-temperature combustion gas at the turbine outlet directly impacting the main support plate, and greatly enhance the atomization effect; and the fuel sprayed by the fourth fuel nozzle of the auxiliary support plate 3 can use the disturbance and wake of the airflow at the trailing edge of the suction surface of the airfoil support plate to enhance atomization, further enhance the cross-flame effect, and improve combustion efficiency. It can be seen that compared with the single-zone fuel supply scheme, the four-zone fuel supply scheme can better take into account the requirements of stable combustion and improved combustion efficiency.

[0054] However, taking into account the difficulty of processing and the production cost, in some embodiments, the present invention only sets a first fuel nozzle 61 on the main support plate 2. The first fuel nozzle 61 is preferably a straight-injection nozzle that sprays fuel vertically to both sides of the circumference, so that the fuel and the incoming flow are mixed with each other at a basically orthogonal angle, thereby improving the fuel atomization effect and promoting the fuel to enter the combustion area behind the main support plate 2 more evenly.

[0055] To sum up, the main / auxiliary support plate distribution design adopted in the present invention can cope with the adverse effects of non-uniform incoming flow represented by strong residual swirl on the recirculation area behind the integrated afterburner stabilizer support plate, improve fuel distribution, effectively increase the infrared shielding area, and enhance the stealth capability of the aircraft engine, which is more conducive to meeting the needs of high-performance integrated afterburner engineering applications.

[0056] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as those generally understood by those skilled in the art in the art to which the present invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0057] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A double-support plate integrated afterburner, characterized in that: The interior of the double-bracket integrated afterburner chamber comprises an inner region located between the central cone (1) and the flow divider ring (4), and an outer region located between the flow divider ring (4) and the outer shell (5), wherein the inlet flow of the inner region is deflected by an angle α relative to the axial direction, and the double-bracket integrated afterburner chamber further comprises: The main support plates (2) are evenly distributed in the inner region along the circumferential direction, and in a cross section perpendicular to the radial direction, the cross section of the main support plates (2) is an axisymmetric figure with the symmetry axis parallel to the axial direction; A secondary support plate (3) is arranged between two adjacent primary support plates (2) along the circumferential direction, is located in front of the primary support plate (2) along the axial direction and overlaps at least part of the projection of the primary support plate (2) in the axial direction, and in a cross section perpendicular to the radial direction, the cross section of the secondary support plate (3) is an airfoil, the chord length direction of the airfoil is deflected by an angle β relative to the axial direction, the deflection direction of the angle β is the same as the deflection direction of the angle α, and the size of the angle β is smaller than the size of the angle α; and The fuel injection rod (6) is fixedly arranged on the outer shell (5) and extends through the diverter ring (4) to the inside of the main support plate (2) to supply fuel and spray the fuel outward from the outer wall of the main support plate (2).

2. The double-support plate integrated afterburner according to claim 1, characterized in that: The circumferential spacing d between the main support plate (2) and the secondary support plate (3) is 1 to 1.5 times the maximum circumferential width D of the main support plate (2), and the axial projection overlap length l of the main support plate (2) and the secondary support plate (3) is 1 / 5 to 1 / 3 of the axial length L of the main support plate.

3. The double-support plate integrated afterburner according to claim 1, characterized in that: The airfoil of the secondary support plate (3) obtains a maximum thickness T at 20-40% of the chord length C, and the size of the maximum thickness T is 9-15% of the chord length C. The airfoil of the secondary support plate (3) obtains a maximum camber R at 35-45% of the chord length C, and the size of the maximum camber R is 4-8% of the chord length C.

4. The double-support plate integrated afterburner according to claim 1, characterized in that: The main support plate (2) and the auxiliary support plate (3) are hollow structures, and the main support plate (2) and the auxiliary support plate (3) pass through the diverter ring (4) on the radial outside to communicate with the outer culvert area.

5. The double-support plate integrated afterburner according to claim 4, characterized in that: The main support plate (2) comprises a main body region (21) and a head region (22); in a cross section perpendicular to a radial direction, the cross-sectional shape of the head region (22) is streamlined; the main body region (21) is connected to the rear of the head region (22) and extends rearwardly in the axial direction.

6. The double-support plate integrated afterburner according to claim 5, characterized in that: Also includes: A first fuel nozzle (61) is symmetrically arranged on two circumferential side walls of the main body region (21), and in a cross section perpendicular to the circumference, a projection of the first fuel nozzle (61) falls within the range of the fuel injection rod (6); a second oil spray nozzle (62) symmetrically arranged on two circumferential side walls of the main body region (21) close to one end of the head region (22); and / or a third fuel nozzle (63) disposed at the front end of the head region (22); The first fuel nozzle (61), the second fuel nozzle (62) and / or the third fuel nozzle (63) are connected to the fuel injection rod (6) via a fuel branch pipe (64).

7. The double-support plate integrated afterburner according to claim 4, characterized in that: A partition is provided in the hollow structure of the auxiliary support plate (3), and the partition divides the auxiliary support plate (3) into a cooling chamber (31) close to the incoming flow direction and an oil supply chamber (32) away from the incoming flow direction. The oil supply chamber (32) is provided with a fourth fuel nozzle (321) on one side of the suction surface of the auxiliary support plate (3), and the fourth fuel nozzle (321) is connected to the oil supply chamber (32).

8. The double-support plate integrated afterburner according to claim 1, characterized in that: Also includes: An actuating device is arranged in the outer region and connected to the auxiliary support plate (3) to adjust the angle β between the chord length direction and the axial direction of the auxiliary support plate (3) according to working conditions.

9. The double-support plate integrated afterburner according to claim 8, characterized in that: The actuating device is configured to adjust the angle β so that when the double-bracket integrated afterburner chamber is in the afterburner state, the angle β is equal to the angle α minus 10-20°.

10. The double-support plate integrated afterburner according to claim 8, characterized in that: The actuating device is configured to adjust the β angle so that the β angle when the double-bracket integrated afterburner combustion chamber is in an afterburner state is smaller than the β angle when the double-bracket integrated afterburner combustion chamber is in a non-afterburner state.

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