A dual strut integrated afterburner

Abstract

The application discloses a double-support-plate integrated afterburning chamber, which comprises a center cone, a main support plate, a secondary support plate, a flow divider ring, an outer shell, an oil injection rod and a heat shield, wherein the main support plate plays a role of oil supply and flame stabilization, and a backflow area is formed behind a tail edge of the main support plate and combustion is organized; the secondary support plate is designed in a hollow airfoil type and plays a role of flow regulation and rotor component shielding; the main support plate and the secondary support plate are arranged in a main duct annular airflow channel formed by the flow divider ring and the center cone. The application can cope with the adverse effect of non-uniform airflow, represented by strong residual rotation, on the backflow area behind the stabilizer support plate of the integrated afterburning chamber, can improve fuel distribution, increases the infrared shielding area, and can improve the stealth capability of the aero-engine in a non-afterburning state.

Description

Technical Field

[0001] This disclosure relates to the field of afterburner technology for aero-engines, and more particularly to an integrated afterburner with dual support plates. Background Technology

[0002] The continuous evolution of aero-engine technology has made increasing thrust-to-weight ratio an inevitable trend, which places more stringent demands on the compactness of afterburners. To address this, the new generation of afterburners relocates the rear support structure of traditional turbine components to the interior of the afterburner. The afterburner's flow straightener also serves as a structural support, and the flow straightener, flame stabilizer, and fuel nozzles are integrated into a single design. This significantly reduces the overall weight of the aero-engine and effectively improves its thrust-to-weight ratio.

[0003] However, this transformation has also brought many challenges. Since the inlet section of the integrated afterburner is moved to the outlet section of the turbine blades, the non-uniformity of the turbine outlet velocity caused by various factors, such as the wake effect generated by the turbine blades during high-speed rotation, the unsteady characteristics of the turbine during operation, and the cooling effect of the cooling airflow on the turbine wall, will drastically deteriorate the intake conditions of the afterburner. This will lead to a non-uniform state in the inlet velocity direction of the afterburner, which will have a significant impact on the flow field characteristics and combustion characteristics of the inner support plate of the afterburner, thus hindering the progress of the engineering application of high-performance integrated afterburners.

[0004] The inlet velocity direction of a non-uniform afterburner is typically described as a cosine angle, which is the angle between the airflow velocity at the afterburner inlet and the axial direction. Depending on the aero-engine model and operating conditions, the cosine angle can vary from 0 to 60°. Under non-uniform inflow conditions, the existing integrated structure of the support plate, stabilizer, and injector rod is insufficient to ensure the afterburner achieves its expected performance indicators. Due to the cosine angle of the inflow, the fuel injected from the injector rod will have different atomization effects on both sides of the integrated structure's circumference, significantly reducing combustion stability and distribution uniformity. To address this, some existing technologies employ long, twisted support plate structures to weaken the impact of non-uniform inflow; however, the rectification effect of a single support plate is insufficient to meet the requirements for stable combustion. Other existing technologies use a multi-support plate relay rectification method, which improves the rectification effect but significantly increases the support plate length and weight, increases cooling difficulty, and sacrifices the total pressure recovery coefficient of the afterburner section.

[0005] It should also be noted that the design requirements of the new generation of afterburners also include infrared stealth capability in the non-afterburning state of the aero-engine. Therefore, effectively shielding the turbine rotor components in the non-afterburning state becomes the key to reducing infrared radiation leaking from the engine tail. In the existing technology, effective infrared shielding is usually achieved by arranging support plate stabilizers with a large tilt angle. However, the large tilt angle brings technical problems such as non-compact structure of the support plate stabilizer and large flow loss. Summary of the Invention

[0006] To address the aforementioned technical problems, this invention aims to provide an integrated afterburner with dual support plates, which not only has a compact structure but also exhibits good rectification performance in afterburner mode and low infrared radiation in non-afterburner mode.

[0007] This invention provides a dual-support integrated afterburner, the internal part of which 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. The inlet flow of the inner region is deflected by an angle α relative to the axial direction. The dual-support integrated afterburner further includes:

[0008] The main support plate is evenly distributed circumferentially within the inner region, and in a cross section perpendicular to the radial direction, the cross section of the main support plate is an axisymmetric figure with the axis of symmetry parallel to the axial direction.

[0009] A secondary support plate is circumferentially disposed between two adjacent main support plates, and axially located in front of the main support plates, at least partially projecting onto the main support plates in the axial direction. In a cross-section perpendicular to the radial direction, the secondary support plate has an airfoil shape, the chord direction of which is deflected by an angle β relative to the axial direction. The deflection direction of the angle β is the same as that of the angle α, and the magnitude of the angle β is smaller than the magnitude of the angle α.

[0010] The fuel injector is fixedly mounted on the housing and extends through the splitter ring into the interior of the main support plate to supply fuel and spray fuel outward from the outer wall of the main support plate.

[0011] Preferably, the circumferential distance 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 axial projection overlap length l 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 support plate achieves 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 airfoil of the secondary support plate achieves the 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 secondary support plate are hollow structures, and the main support plate and the secondary support plate pass through the diversion ring on the radially outer side and communicate with the outer culvert region.

[0014] Preferably, the main support plate includes a main body region and a head region. In a cross-section perpendicular to the radial direction, the cross-sectional shape of the head region is streamlined. The main body region is attached to the rear of the head region and extends rearward along the axial direction.

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

[0016] The first fuel nozzle is symmetrically arranged on two circumferential sidewalls of the main body area, and the projection of the first fuel nozzle falls within the range of the fuel injection rod in a cross section perpendicular to the circumferential direction.

[0017] The second fuel injection nozzle is symmetrically disposed on one end of the two circumferential sidewalls of the main body area, near the head area; and / or

[0018] A third fuel injector is disposed at the front end of the head region;

[0019] The first fuel nozzle, the second fuel nozzle, and / or the third fuel nozzle are connected to the fuel injector rod via a fuel branch pipe.

[0020] Preferably, the hollow structure of the sub-support plate is provided with a partition, which divides the sub-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 side of the sub-support plate, and the fourth fuel nozzle is connected to the oil supply chamber.

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

[0022] An actuating device is disposed in the outer culvert area and connected to the secondary support plate to adjust the β angle between the chordal direction and the axial direction of the secondary support plate according to the working conditions.

[0023] Preferably, the actuating device is configured to adjust the β angle such that when the dual-support integrated afterburner is in an afterburning state, the size of the β angle is equal to the size of the α angle minus 10-20°.

[0024] Preferably, the actuating device is configured to adjust the β angle such that the β angle is smaller when the dual-support integrated afterburner is in an afterburning state than the β angle is in a non-afterburning state.

[0025] The present invention adopts the above technical solution and has the following technical effects: the main / sub-support plate arrangement design can cope with the adverse effects of non-uniform incoming flow represented by strong afterspin on the backflow area of ​​the stabilizer plate of the integrated afterburner, improve fuel distribution, and effectively increase the infrared shielding area, which can improve the stealth capability of aero engines and is more conducive to meeting the needs of high-performance integrated afterburner engineering applications. Attached Figure Description

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

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

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

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

[0030] Figure 5 The velocity contour plot and streamline diagram of the single-zone fuel supply scheme of the integrated double-support plate afterburner of the present invention are shown on a cross section perpendicular to the radial direction.

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

[0032] In the diagram, 1-Central cone; 2-Main support plate; 201-Hollow structure of main support plate; 21-Main body area; 22-Head area; 3-Secondary support plate; 301-Hollow structure of secondary support plate; 31-Cooling chamber; 32-Fuel supply chamber; 321-Fourth fuel nozzle; 4-Flow divider ring; 5-Outer shell; 6-Fuel injector rod; 61-First fuel nozzle; 62-Second fuel nozzle; 63-Third fuel nozzle; 64-Fuel branch pipe; 7-Heat insulation screen. Detailed Implementation

[0033] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings:

[0034] This invention can be implemented in many different forms and should not be considered as limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully express the scope of the invention to those skilled in the art.

[0035] like Figure 1-6As shown, this invention provides an integrated afterburner with dual support plates, the main structure of which consists of a central cone 1, a main support plate 2 (or stabilizer support plate), a secondary support plate 3 (or rectifier support plate), a flow divider ring 4, an outer shell 5, an injection rod 6, and a heat shield 7. See details. Figure 1 The integrated afterburner chamber with dual support plates includes 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. The main support plate 2 and the auxiliary support plate 3 are evenly distributed circumferentially between the central cone 1 and the flow divider ring 4, and are spaced apart from each other. A fuel injector 6 is provided inside the main support plate 2. The outer end of the fuel injector 6 is fixed to the outer shell 5, and the inner end passes through the flow divider ring 4 and extends into the interior of the main support plate 2 to supply fuel and spray it outward from the outer wall of the main support plate 2. The area behind the trailing edge of the main support plate 2, surrounded by a heat shield 7, is the afterburner zone. The fuel supply from the fuel injector 6 creates a stable afterburner zone behind the main support plate 2.

[0036] To cope with the non-uniform flow field environment, this invention adopts a double support plate structure design. The main support plate and the secondary support plate are arranged in the annular airflow channel formed by the flow splitting ring and the central cone. The main support plate is a stabilizer support plate, which plays a role in fuel supply and flame stabilization, while the secondary support plate is a rectifier support plate, which plays a role in rectification and shielding.

[0037] Specifically, the secondary support plate 3 is circumferentially positioned between two adjacent main support plates 2, and axially located in front of the main support plate 2, at least partially coinciding with its axial projection. That is, the rear section of the secondary support plate is approximately in the same circumferential position as the leading edge of the main support plate. In a cross-section perpendicular to the radial direction, the secondary support plate 3 has an airfoil shape, and the chord length of the airfoil is deflected by an angle β relative to the axial direction. (Refer to...) Figure 3-4 Considering the inlet airflow deflection at an angle α with the axial direction, an angle β, which has the same deflection direction as angle α, can effectively adjust the direction of the inlet flow. (See Appendix for further details.) Figure 5The incoming airflow is divided into two streams as it passes through the secondary support plate 3: the pressure surface (or windward surface, blade underside) and the suction surface (or leeward surface, blade backside). The airflow on the pressure surface is incident on the blade underside of the secondary support plate 3 at an angle α, and smoothly changes its angle according to the airfoil structure of the secondary support plate 3 until it reaches the trailing edge of the secondary support plate 3 and basically returns to the axial flow direction. The airflow on the suction surface, as it flows through the blade backside of the secondary support plate 3, is squeezed by the surrounding gas at a higher flow velocity and lower pressure to adhere to the blade backside of the secondary support plate 3. It gradually changes its flow direction according to the curvature of the blade backside until it reaches the trailing edge of the secondary support plate 3 and basically returns to the axial flow direction. As can be seen, by arranging the secondary support plate 3, the present invention can successfully adjust the α angle of the uneven incoming flow, so that the rectified airflow flows basically along the axial direction. Based on this, the present invention arranges the main support plate 2 axially behind the secondary support plate 3, so that the main support plate 2 can receive the basically axial airflow from the secondary support plate 3 after rectification.

[0038] Furthermore, such as Figure 3 and Figure 4 As shown, in a cross-section perpendicular to the radial direction, the present invention constructs the main support plate 2 as an axisymmetric figure with its axis of symmetry parallel to the axial direction. This ensures that the airflow flowing through the two circumferential side walls of the main support plate 2 is substantially symmetrical. In this case, the fuel injected from the two side walls of the main support plate 2 will mix with the airflow flowing along the two side walls of the main support plate 2, causing the fuel-air mixture to exhibit a similar appearance downstream of the main support plate 2. Figure 6 The basically symmetrical distribution shown makes the fuel distribution close to the design fuel-air ratio, making it easier to organize combustion and avoiding the undesirable state where the fuel-air 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 to existing afterburners, this invention adds a secondary support plate 3, but due to the airfoil cross-section of the secondary support plate 3, its flow loss is extremely small. Furthermore, by controlling the deflection direction of the β angle to be the same as that of the α angle, and by controlling the size of the β angle to be smaller than that of the α angle, this invention can achieve a smaller total pressure loss while completing effective rectification, resulting in excellent flow performance. Moreover, because the chord of the secondary support plate deflects around the axial direction by the β angle, the rear-view shielding area is increased, giving this invention superior infrared stealth characteristics.

[0040] It should be noted that the directions of angles α and β in this invention adopt the general definition of direction angles, that is, axially backward ( Figure 3 and Figure 4 In this context, 0° is defined as the horizontal direction to the right, with counter-clockwise rotation being positive and clockwise rotation being negative. The magnitudes of angles α and β refer to their absolute values ​​without considering direction. For example... Figure 3-4 As shown, in a typical embodiment of the present invention, angle α is +30° and angle β is +10°.

[0041] In some embodiments, considering that the incoming flow deflection angle is affected by the operating conditions of the aero-engine, the deflection angle β of the secondary support plate 3 can also be dynamically adjusted according to the deflection angle α of the incoming flow. In this embodiment, the present invention provides an actuating device in the outer bypass region and connects the actuating device to the secondary support plate 3 to adjust the β angle between the chordal direction and the axial direction of the secondary support plate 3 according to the operating conditions. The aforementioned actuating device may be, for example, an adjusting ring connecting all the secondary support plates 3 and a matching actuating cylinder. The relevant structure is already relatively mature in the prior art and will not be discussed in detail here.

[0042] In some embodiments, the present invention may employ the following adjustment method: the actuating device is configured to adjust the β angle such that, when the integrated afterburner with dual support plates is in an afterburning state, the size of the β angle is equal to the size of the α angle minus 10-20°. Thus, the deflection angle β of the secondary support plate 3 will be adjusted in real time according to the non-uniformity of the incoming flow velocity direction, ensuring that the velocity direction of the incoming flow on the upper and lower walls of the secondary support plate after rectification is substantially axial.

[0043] In some embodiments, the present invention can also employ the following adjustment method: the actuating device is configured to adjust the β angle so that the size of the β angle when the dual-support integrated afterburner is in the afterburning state is smaller than the size of the β angle when it is not in the afterburning state. Those skilled in the art will understand that the infrared shielding capability in the non-afterburning state is characterized by the rearview area shielding rate (i.e., the ratio of the rearview area shielded by the relatively low-temperature component to the high-temperature area). The main support plate 2 has a fixed rearview area shielding rate, while the rearview shielding rate of the secondary support plate 3 is determined by the chord length and the chord rotation angle. Given that the secondary support plate 3 has a fixed chord length, the present invention can adjust the infrared stealth characteristics of the afterburner by adjusting the size of the β angle.

[0044] Regarding the above-mentioned adjustment methods, those skilled in the art will understand that for an aero-engine with the afterburner of the present invention, if it is in afterburner mode, it indicates that the situation is relatively urgent, the aircraft may need to significantly increase thrust for air combat or has been detected by radar, and urgently needs to accelerate to escape or perform complex maneuvers. Therefore, there is no need to pay extra attention to the infrared stealth effect and adjust the sub-support plate 3 to form a smaller β angle with the axis to enhance the rectification effect and provide more power. Correspondingly, if the present invention is in non-afterburner mode, it indicates that the aircraft is in cruise mode and has not yet been detected by radar. At this time, more attention can be paid to the infrared stealth effect and the sub-support plate 3 can be adjusted to form a larger β angle with the axis to increase the rearward shielding area of ​​the sub-support plate 3 and improve the infrared stealth performance of the engine.

[0045] Of course, compared with the existing technology that uses a single support plate, the present invention has increased the infrared stealth performance by setting a main and a secondary double support plate. For reference, in one embodiment of the present invention, the chord deflection angle β of the secondary support plate 3 is 10°. With almost no change in flow loss, the area obscuration rate is increased by 15%, thereby significantly improving the infrared stealth capability of the aero-engine in non-afterburning state.

[0046] For a booster combustion chamber employing dual support plates, the design parameters for the main / secondary support plates mainly include the circumferential distance *d* between the main and secondary support plates and the axial overlap length *l* between them. A well-designed main support plate 3 ensures that the addition of the secondary support plate 3 does not significantly alter the blockage ratio, and the main duct blockage ratio is only related to the structural parameters of the main support plate 2, thereby guaranteeing good airflow capacity and low total pressure loss within the main duct. Based on this, in a preferred embodiment of the present invention, the circumferential distance *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* between 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 of 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 calculated blocking ratio is 0.27, and the total pressure recovery coefficient reaches more than 0.953.

[0047] The secondary support plate 3 of this invention adopts an airfoil design, which is smaller in volume than the main support plate 2, and its streamlined characteristics result in minimal flow loss. When the incoming flow passes through the secondary support plate 3, the secondary support plate 3 rectifyes the non-uniform incoming flow, causing the flow direction to gradually return to the axial direction. In this embodiment of the invention, the airfoil of the secondary support plate 3 achieves its 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, which increases the amount of cold air that can enter the cold air passage, enhances the heat load resistance and structural strength, and avoids the adverse consequences of increased air resistance due to excessive thickness by not exceeding 15% of the chord length C. The airfoil of the secondary support plate 3 achieves the maximum camber R at 35-45% of the chord length C, and the magnitude of the maximum camber R is 4-8% of the chord length C. This range of values ​​allows the secondary support plate 3 to ensure the rectification 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. The main support plate 2 and the secondary support plate 3 pass through the diversion ring 4 on the radial outer side and are connected to the outer culvert region. The cold air in the outer culvert region can enter the interior of the main support plate 2 and the secondary support plate 3 through the hollow structure to 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 region 21 and a head region 22. In a cross section perpendicular to the radial direction, the cross section of the head region 22 has a streamlined configuration to obtain lower flow resistance, while the main body region 21 is attached to the rear of the head region 22 and extends axially rearward, thereby forming a stable combustion zone behind the main support plate 2.

[0050] Based on this, in order to better organize combustion, in some embodiments, the dual-support plate integrated afterburner of the present invention further includes a plurality of fuel nozzles disposed on the main support plate 2, wherein the first fuel nozzle 61 is symmetrically disposed on two circumferential sidewalls of the main body region 21, and the projection of the first fuel nozzle 61 falls within the range of the fuel injection rod 6 in a cross section perpendicular to the circumferential direction; the second fuel nozzle 62 is symmetrically disposed on one end of the two circumferential sidewalls of the main body region 21 near the head region 22; and / or the third fuel nozzle 63 is disposed at the front end of the head region 22; and 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 through a fuel branch pipe 64.

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

[0052] Based on the aforementioned multiple fuel injectors, this invention can flexibly select a fuel supply scheme according to the complex operating conditions of the afterburner and the requirements for stable combustion. In one embodiment, such as... Figure 3 As shown, the present invention can adopt a single-zone fuel supply scheme, with fuel combustion supplied only by the first fuel nozzle 61 located at the tail edge of the main support plate 2. Its technical effects can be referenced. Figure 5 The cross-sectional velocity contour plot and streamline diagram shown indicate that two symmetrical vortex centers are formed in the recirculation zone behind the main support plate 2, which greatly reduces the adverse effects of non-uniform incoming flow on the flow field in the recirculation zone. (Refer to...) Figure 6 The cross-section of fuel (aviation kerosene C) shown 12 H 23The concentration cloud map shows that the fuel is symmetrically distributed on both sides of the tail edge of the main support plate 2, and is basically unaffected by the airflow deflection caused by the non-uniform incoming flow. This will be extremely beneficial to the organization of combustion and the stability of combustion.

[0053] In another embodiment of the invention, such as 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, forming a four-zone fuel supply scheme. The fuel injected by the first fuel nozzle 61 ensures the fuel flow rate entrained into the recirculation zone, guaranteeing stable combustion. The fuel injected by the second fuel nozzle 62 has a longer expansion distance, allowing the flame to penetrate further and improving the flame propagation performance within the afterburner. The fuel injected by the third fuel nozzle 63 reduces the heat load caused by the direct impact of the high-temperature exhaust gas from the turbine outlet on the main support plate, while significantly enhancing atomization. The fuel injected by the fourth fuel nozzle on the secondary support plate 3 utilizes the disturbance and wake of the airflow at the suction surface trailing edge of the airfoil support plate to enhance atomization, further enhancing the flame propagation effect and improving combustion efficiency. Therefore, compared to a single-zone fuel supply scheme, the four-zone fuel supply scheme better balances the requirements of stable combustion and improved combustion efficiency.

[0054] However, considering the processing difficulty and production cost, in some embodiments, the present invention only provides a first fuel nozzle 61 on the main support plate 2. The first fuel nozzle 61 is preferably a direct-injection nozzle that sprays fuel vertically to both sides of the circumference, so that the fuel and the incoming flow mix with each other at a basically orthogonal angle, improve the fuel atomization effect, and promote the fuel to enter the combustion area behind the main support plate 2 more evenly.

[0055] In summary, the main / sub-support plate arrangement design of this invention can address the adverse effects of non-uniform incoming flow, represented by strong swirl, on the backflow zone behind the stabilizer plate of the integrated afterburner, improve fuel distribution, effectively increase the infrared shielding area, enhance the stealth capability of aero engines, and better meet 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 used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0057] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment 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 within the protection scope of the present invention.

Claims

1. A double-support plate integrated afterburner, characterized in that, The integrated afterburner with dual support plates includes 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). The inlet flow of the inner region is deflected by an angle α relative to the axial direction. The integrated afterburner with dual support plates also includes: The main support plate (2) is evenly distributed in the inner region along the circumference, and in the section perpendicular to the radial direction, the section of the main support plate (2) is an axisymmetric figure with the axis of symmetry parallel to the axial direction; A secondary support plate (3) is circumferentially disposed between two adjacent main support plates (2), and axially located on the front side of the main support plate (2) and at least partially projected onto the main support plate (2) in the axial direction. In a cross-section perpendicular to the radial direction, the cross-section of the secondary support plate (3) is airfoil-shaped, with the chord direction of the airfoil deflected by an angle β relative to the axial direction. The deflection direction of the angle β is the same as that of the angle α, and the magnitude of the angle β is smaller than that of the angle α. The fuel injector (6) is fixedly installed on the outer casing (5) and extends through the split ring (4) to the interior of the main support plate (2) to supply fuel and spray fuel outward from the outer wall of the main support plate (2); The circumferential distance 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. The airfoil of the sub-support plate (3) achieves 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 airfoil of the sub-support plate (3) achieves the maximum camber R at 35-45% of the chord length C, and the maximum camber R is 4-8% of the chord length C. An actuating device is provided in the outer culvert area and connected to the secondary support plate (3) to adjust the β angle between the chord direction and the axial direction of the secondary support plate (3) according to the working conditions; The actuating device is configured to adjust the β angle such that when the dual-support integrated afterburner is in an afterburning state, the size of the β angle is equal to the size of the α angle minus 10-20°. The actuating device is configured to adjust the β angle such that the β angle is smaller when the dual-support integrated afterburner is in an afterburning state than the β angle is in a non-afterburning state.

2. The integrated double-support plate afterburner according to claim 1, characterized in that, The main support plate (2) and the secondary support plate (3) are hollow structures. The main support plate (2) and the secondary support plate (3) pass through the diversion ring (4) on the radial outer side and are connected to the outer culvert region.

3. The integrated double-support plate afterburner according to claim 2, characterized in that, The main support plate (2) includes a main body region (21) and a head region (22). In a cross section perpendicular to the radial direction, the cross section of the head region (22) has a streamlined shape. The main body region (21) is attached to the rear of the head region (22) and extends axially backward.

4. The integrated double-support plate afterburner according to claim 3, characterized in that, Also includes: The first fuel nozzle (61) is symmetrically arranged on the two circumferential sidewalls of the main body area (21), and the projection of the first fuel nozzle (61) falls within the range of the fuel injection rod (6) in a cross section perpendicular to the circumferential direction. The second fuel nozzle (62) is symmetrically disposed on one end of the two circumferential sidewalls of the main body region (21) near the head region (22); and / or The third fuel nozzle (63) is 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 injector (6) via a fuel branch pipe (64).

5. The integrated afterburner with dual support plates according to claim 2, characterized in that, The hollow structure of the sub-support plate (3) is provided with a partition, which divides the sub-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 the suction side of the sub-support plate (3), and the fourth fuel nozzle (321) is connected to the oil supply chamber (32).

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