A fuel injection stabilizing integrated evaporative type stabilizer

Abstract

This invention provides an integrated evaporative flame stabilizer with fuel injection and stabilization, applied to an afterburner. It includes a stabilizer cooling chamber, a stabilizer control structure, and a fuel system. This invention integrates the stabilizer, fuel system, and fuel plate into a single design. The main fuel injection rod is located within the stabilizer cooling chamber. Low-temperature airflow from the outer bypass is introduced to cool the stabilizer and the main fuel injection rod. Furthermore, the evaporative stabilizer and circumferential stabilizer are designed to work together, with high-temperature airflow introduced from the side intake channel of the evaporative stabilizer. This airflow mixes and evaporates with the fuel in the intake manifold and fuel distribution pipe. Additionally, a radial gap is provided between the fuel distribution pipe and the baffle to allow for thermal expansion of the fuel distribution pipe. This invention overcomes the shortcomings of traditional flame stabilizers, offering advantages such as a wider lean-out threshold, lower flow loss, and higher structural reliability under complex operating conditions.

Description

Technical Field

[0001] This invention belongs to the aerospace field, specifically relating to an integrated evaporative stabilizer for fuel injection and stabilization in afterburners. Background Technology

[0002] To improve the maneuverability and short takeoff capability of fighter jets, aero engines widely adopt the method of installing afterburners to increase thrust. As one of the core components of the afterburner, the flame stabilizer plays a decisive role in flame stabilization, flame coupling, and combustion organization.

[0003] With the further development of modern aero engines, the inlet temperature and velocity of afterburners have increased significantly. While the increased inlet temperature is beneficial for fuel atomization and improving the chemical reaction rate, it inevitably leads to malfunctions such as erosion, deformation, and coking / clogging of the fuel injector and stabilizer assemblies. The further increase in airflow velocity also makes the inlet conditions of afterburners more complex, and since traditional flame stabilizers and fuel injector assemblies are directly positioned within the airflow, significant flow losses are unavoidable. Therefore, afterburners face enormous challenges in ignition, cooling, combustion organization, and reducing flow losses.

[0004] To address these challenges, US patents US5385015 and US5685140 proposed an integrated design for the afterburner of the turbine rear frame. This design integrates the stabilizer with the turbine rear fairing and embeds the fuel injector within the stabilizer, preventing coking and erosion of the fuel injection device, reducing flow resistance loss and weight, and improving the reliability of the afterburner. However, due to the close coupling between the fuel injection device and the stabilizer, only a small portion of the fuel injected laterally from both sides in front of the stabilizer is entrained into the recirculation zone behind the stabilizer, resulting in a narrow ignition / quenching threshold and poor flame stabilization and flame coupling capabilities. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention proposes an integrated evaporative fuel injection stabilizer for use in afterburners, which integrates cooling, fuel injection, and flame stabilization functions. Specifically, this invention effectively achieves stable and reliable standby ignition under complex operating conditions, widens the lean-point flameout threshold of the stabilizer, and improves the flame stabilization and flame connection capabilities of the afterburner.

[0006] The specific technical solution of the present invention is as follows:

[0007] This invention provides an integrated evaporative stabilizer with fuel injection, comprising a cavity structure formed by a front edge, a side wall, and a rear edge of the stabilizer, and a fuel system disposed within the cavity structure. The front part of the cavity structure is a stabilizer cooling chamber, and the rear part is a stabilizer duty structure. The stabilizer cooling chamber and the stabilizer duty structure are separated by a partition. The fuel system includes a main fuel line system located within the stabilizer cooling chamber and a duty fuel line system located within the stabilizer duty structure.

[0008] The main oil circuit system inside the underbody stabilizer cooling chamber is used to inject fuel to the outside, and the radial outer end of the underbody stabilizer cooling chamber is connected to the outer duct to introduce cooling gas from the outer duct into the underbody stabilizer cooling chamber to cool the main oil circuit system.

[0009] The stabilizer support structure has an intake pipe with an opening at the front end and a fuel distribution pipe connected to the rear end of the intake pipe. The fuel circuit system is connected to the front end of the intake pipe. The side wall of the support plate has a side intake channel in the area where the stabilizer support structure is located. The side intake channel is located in front of the intake pipe so that the gas inside enters the intake pipe and the fuel distribution pipe through the side intake channel and promotes the atomization and evaporation of the fuel in the intake pipe and the fuel distribution pipe.

[0010] Preferably, the baffles are distributed at least on the radially inner side, radially outer side, and forward side of the support plate stabilizer duty structure, thereby isolating the support plate stabilizer duty structure from the low-temperature airflow of the outer duct.

[0011] Preferably, the duty oil circuit system includes a duty oil circuit injection rod and a shielding pipe. The shielding pipe is spaced out on the outside of the duty oil circuit injection rod. The radially outer opening of the shielding pipe is located in the outer duct. The duty oil circuit injection rod and the shielding pipe pass through the partition located radially outside the duty structure of the support plate stabilizer from the outer duct and enter the interior of the duty structure of the support plate stabilizer.

[0012] Preferably, the duty fuel line injection rod and the shielding tube are disposed on one side of the circumference of the intake pipe, the intake pipe is provided with a duty fuel line injection hole, and the duty fuel line injection rod and the shielding tube are provided with corresponding injection ports on one side of the duty fuel line injection hole, so that the duty fuel impacts the inner wall of the intake pipe through the duty fuel line injection hole.

[0013] Preferably, the front area of ​​the radially outer side of the support plate stabilizer cooling cavity without the partition is connected to the outer duct to form a cooling channel inlet, and a cooling channel outlet is provided at the bottom of the support plate stabilizer cooling cavity, so that the outer duct airflow enters the interior of the support plate stabilizer cooling cavity through the cooling channel inlet and is discharged through the cooling channel outlet.

[0014] Preferably, the main oil circuit system includes a main oil circuit injection rod extending from the outer duct through the cooling channel inlet to the interior of the cooling cavity of the support plate stabilizer. The main oil circuit injection rod is provided with a main oil circuit injection port. The support plate cavity structure has a main oil circuit injection hole on the side wall of the support plate corresponding to the main oil circuit injection port. The injection direction of the main oil circuit injection hole is circumferentially towards both sides of the support plate cavity structure.

[0015] Preferably, the intake pipe extends along the flow direction and has multiple portions distributed in the radial direction. The multiple intake pipes are evenly connected to the radially extending fuel distribution pipe. The fuel distribution pipe has multiple air outlets evenly distributed in the radial direction on both sides of its circumference, thereby injecting duty fuel outward in the circumferential direction over the entire length of the fuel distribution pipe.

[0016] Preferably, the stabilizer support structure further includes an air intake panel disposed on the front side of the fuel distribution pipe. The air intake panel is located on the rear side of the side air intake channel and sandwiched between the two side walls of the support cavity structure, and has multiple air intake holes.

[0017] Preferably, the side wall of the support plate has a window in the area corresponding to the fuel distribution pipe, so that part of the air outlet can directly discharge fuel to the circumferential outer side of the support plate cavity structure through the window.

[0018] Preferably, the support plate stabilizer duty structure further includes a circumferential stabilizer disposed in the window, the circumferential stabilizer having a bent plate structure with a closed front end, an open rear end, and a cross-sectional area that gradually expands along the flow direction.

[0019] Therefore, the beneficial technical effects of the present invention include at least the following:

[0020] 1. This invention integrates the support plate, stabilizer and fuel injection system into a single design, combining the functions of each component, reducing the number of components, reducing flow loss, making the structure more compact, and effectively shortening the length of the afterburner to achieve the purpose of weight reduction.

[0021] 2. This invention combines an evaporative stabilizer with a circumferential stabilizer to facilitate the entry of high-temperature airflow into the stabilizer's operating structure. The airflow mixes with fuel in the intake pipe and fuel distribution pipe to form a fuel-air mixture. The intake pipe and fuel distribution pipe ensure uniform fuel distribution and effectively extend the fuel-air mixing time, providing favorable conditions for ignition. This widens the stabilizer's ignition / extinguishing boundary and improves the flame stabilizer's ability to ignite and stabilize the flame under complex operating conditions.

[0022] 3. This invention places the main fuel line injector rod inside the cooling chamber of the support plate stabilizer, introducing a portion of the external low-temperature airflow to cool the support plate stabilizer and the injector rod; while the shift fuel line injector rod is an air-cooled injector rod, introducing a portion of the low-temperature airflow into the gap between the shift fuel line injector rod and the shielding pipe to provide cooling for the shift fuel line injector rod and prevent coking and blockage of the injector rod; in addition, a gap is provided between the fuel distribution pipe and the baffle in the radial direction to allow for a certain expansion space for the fuel distribution pipe to expand under heat, improving structural reliability; therefore, the overall design improves the structural durability and reliability of the support plate stabilizer. Attached Figure Description

[0023] The accompanying drawings are used to provide a further understanding of the technical solutions of this application and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of this application, but do not constitute a limitation on the technical solutions of this application.

[0024] Figure 1 A three-dimensional structural diagram of an integrated evaporative stabilizer and circumferential stabilizer for oil injection stabilization provided by the present invention;

[0025] Figure 2 A three-dimensional structural schematic diagram of an integrated evaporative stabilizer for oil injection stabilization provided by the present invention;

[0026] Figure 3 A cross-sectional view of an integrated oil-injection stabilizer with an evaporative support plate provided by the present invention;

[0027] Figure 4 for Figure 3 Cross-sectional view at point AA;

[0028] Explanation of reference numerals in the attached figures:

[0029] 1-Support plate cavity structure; Ⅰ-Support plate stabilizer cooling cavity; Ⅱ-Support plate stabilizer duty structure; 11-Support plate leading edge; 12-Support plate side wall; 121-Main fuel line injection hole; 122-Side air intake passage; 13-Baffle plate; 14-Air intake panel; 141-Air intake hole; 15-Air intake pipe; 151-Duty fuel line injection hole; 16-Fuel distribution pipe; 161-Air outlet; 17-Support plate trailing edge; 18-Cooling passage inlet; 19-Cooling passage outlet;

[0030] 2-Fuel system; 21-Stationary fuel system; 211-Stationary fuel system injector; 212-Shielding pipe; 22-Main fuel system; 221-Main fuel system injector; 222-Main fuel system injector.

[0031] 3-Circumferential stabilizer;

[0032] a-Inner core high-temperature airflow; b-Outer core low-temperature airflow; c-Fuel fuel; d-Gas-fuel mixture; Detailed Implementation

[0033] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. The descriptions of the exemplary embodiments are merely illustrative and are not intended to limit the invention or its application or use in any way. The invention can be embodied in many different forms and is not limited to the embodiments described herein. These embodiments are provided to make the invention clear and complete, and to fully express the scope of the invention to those skilled in the art. It should be noted that, unless otherwise specifically stated, the relative arrangement of components and steps set forth in these embodiments should be interpreted as merely exemplary and not as limiting.

[0034] like Figure 1-4 As shown, the present invention provides an integrated evaporative stabilizer with fuel injection and stabilization, which includes a support plate cavity structure 1 formed by a support plate front edge 11, a support plate side wall 12 and a support plate rear edge 17, and a fuel system 2 disposed within the support plate cavity structure 1. The front part of the support plate cavity structure 1 is a support plate stabilizer cooling chamber I, and the rear part is a support plate stabilizer duty structure II, and the support plate stabilizer cooling chamber I and the support plate stabilizer duty structure II are separated by a partition 13.

[0035] The front edge of the support plate cavity structure 1 is set as a curved wall, and the side wall 12 of the support plate is provided with main oil passage injection holes 121 evenly distributed in the radial direction near the front edge 11 of the support plate. The support plate cavity structure 1 adopts a streamlined structure in the cross section perpendicular to the radial direction, and its front edge can be inclined relative to the radial direction. The inclination can be forward or backward, and the inclination angle is not greater than 35°, which helps to reduce flow resistance.

[0036] The fuel system 2 includes a main fuel line system 22 located in the cooling chamber I of the support plate stabilizer and a duty fuel line system 21 located in the duty structure II of the support plate stabilizer. The main oil circuit system 22 inside the support plate stabilizer cooling chamber I is used to inject fuel to the outside, and the radial outer end of the support plate stabilizer cooling chamber I is connected to the outer duct to introduce cooling gas from the outer duct into the support plate stabilizer cooling chamber I to cool the main oil circuit system 22. The support plate stabilizer duty structure II is provided with an intake pipe 15 with a front opening and a fuel distribution pipe 16 connected to the rear end of the intake pipe 15. The duty oil circuit system 21 is connected to the front end of the intake pipe 15. The support plate sidewall 12 has a side intake channel 122 in the area where the support plate stabilizer duty structure II is located. The side intake channel 122 is located in front of the intake pipe 15 so that the internal gas enters the intake pipe 15 and the fuel distribution pipe 16 through the side intake channel 122 and promotes the atomization and evaporation of the duty fuel in the intake pipe 15 and the fuel distribution pipe 16.

[0037] Thus, the high-temperature internal airflow 'a' enters the interior of the support plate cavity structure 1 through the side air intake channel 122 and enters the intake pipe 15 through the front opening of the intake pipe 15. Simultaneously, the standby fuel supplied by the standby fuel system 21 enters the intake pipe 15, allowing the high-temperature internal airflow 'a' and the standby fuel to mix thoroughly within the intake pipe 15 and promoting the evaporation of the standby fuel. Subsequently, the premixed and pre-evaporated standby fuel within the intake pipe 15 enters the fuel distribution pipe 16 and is discharged from the fuel distribution pipe 16, where combustion is organized in the recirculation zone after the standby stabilizer standby structure II, serving as a standby and stable ignition source. Under conditions of higher demand, the main fuel system 22 begins to supply fuel and sprays fuel outward through the support plate cavity structure 1. The main fuel, after being atomized and evaporated by the high-temperature internal airflow outside the support plate, ignites and burns under the influence of the stable ignition source generated by the standby fuel, thereby providing higher thrust for the aero engine.

[0038] Preferably, such as Figure 1-2 As shown, the baffle 13 is distributed at least radially inner, radially outer, and forward-flowing sides of the support plate stabilizer duty structure II, thereby isolating the support plate stabilizer duty structure II from the low-temperature airflow b from the outer bypass. Consequently, the high-temperature airflow a introduced from the side intake channel 122 will remain in the area where the support plate stabilizer duty structure II is located within the support plate cavity structure 1 for a longer period, promoting fuel evaporation in the duty oil circuit system 21 and reducing the airflow velocity exiting from the trailing edge of the support plate stabilizer duty structure II to a certain extent, thus improving the flame stabilization effect.

[0039] If a larger radial distribution of the standby fuel is desired, the standby stabilizer structure II can have a larger radial dimension. In the extreme case, the baffle 13 will only be distributed on the radially outer side and the forward side of the standby stabilizer structure II. At this time, the internal high-temperature airflow a can also enter the area where the standby stabilizer structure II is located within the support cavity structure 1 from the radially inner side. It is understandable that the atomization and evaporation effect of the standby fuel will be enhanced at this time. However, due to the introduction of more internal high-temperature airflow a, in order to ensure that the fuel-air ratio is still within the combustible boundary, the injection quantity of the standby fuel needs to be increased.

[0040] Preferably, the front region of the support plate stabilizer cooling cavity I, without the partition 13, is connected to the outer duct to form a cooling channel inlet 18, and a cooling channel outlet 19 is provided at the bottom of the support plate stabilizer cooling cavity I. This allows the outer duct airflow to enter the interior of the support plate stabilizer cooling cavity I through the cooling channel inlet 18 and then exit through the cooling channel outlet 19. Thus, the outer duct airflow enters the interior of the support plate cavity structure 1 through the front region, ensuring that both the support plate cavity structure 1, which directly faces the high-temperature airflow a, and the main oil circuit system 22 located inside the support plate cavity structure 1 are adequately cooled, effectively preventing coking and blockage of the fuel injector rod.

[0041] Preferably, the main fuel system 22 includes a main fuel injection rod 221 extending from the outer duct through the cooling channel inlet 18 to the interior of the support plate stabilizer cooling cavity I. The main fuel injection rod 221 is provided with a main fuel injection port 222. The support plate sidewall 12 of the support plate cavity structure 1 is provided with a main fuel injection hole 121 corresponding to the main fuel injection port 222. The injection direction of the main fuel injection hole 121 is circumferentially oriented towards both sides of the support plate cavity structure 1. Thus, the fuel injected by the main fuel system 22 leaves the support plate at a certain circumferential injection velocity, is carried by the high-temperature airflow a, and flows along the flow field constructed by the outer surface of the support plate cavity structure 1 to the downstream of the support plate. There, it is ignited by a stable ignition source located in the return flow zone behind the support plate stabilizer duty structure II, formed by the duty fuel, and then combustion is organized.

[0042] Preferably, the duty oil circuit system 21 includes a duty oil circuit injector 211 and a shielding tube 212. The shielding tube 212 is spaced out on the outside of the duty oil circuit injector 211, and the radially outer opening of the shielding tube 212 is located in the outer duct. The duty oil circuit injector 211 and the shielding tube 212 pass through the partition 13 located radially outside the duty structure II of the support plate stabilizer from the outer duct and enter the interior of the duty structure II of the support plate stabilizer. As a result, the cooling airflow from the outer duct will enter the gap between the duty oil circuit injector 211 and the shielding tube 212, and fully cool both of them, effectively preventing coking and blockage of the duty oil circuit injector 211. In order to ensure that the gap between the duty fuel injector 211 and the shield tube 212 can maintain its design size during the operation of the aero-engine, and to prevent the duty fuel injector 211 and the shield tube 212 from colliding with each other and causing structural damage, damping rings can be installed at intervals along the length of the gap between the two to absorb vibration and ensure that the gap size between the duty fuel injector 211 and the shield tube 212 is maintained.

[0043] Preferably, the shift fuel injector 211 and the shielding tube 212 are disposed on one side of the circumference of the intake pipe 15. The intake pipe 15 is provided with a shift fuel injection hole 151, and the shift fuel injector 211 and the shielding tube 212 have corresponding injection ports on one side of the shift fuel injection hole 151, so that the shift fuel impacts the inner wall of the intake pipe 15 through the shift fuel injection hole 151. Through the impact, the shift fuel can be effectively atomized from large fuel droplets into small fuel droplets, thereby further promoting the atomization and evaporation of the shift fuel, as well as the mixing with the internal high-temperature airflow a, and improving the flame stability effect.

[0044] Preferably, the intake pipes 15 extend along the flow direction and are distributed in multiple radial directions. These intake pipes 15 are evenly connected radially to the radially extending fuel distribution pipe 16. Multiple exhaust holes 161 are evenly distributed radially on both sides of the fuel distribution pipe 16, allowing the pre-mixed and pre-evaporated standby fuel within the intake pipes 15 to enter the fuel distribution pipe 16 and be injected circumferentially outward from the multiple exhaust holes along the entire length of the fuel distribution pipe 16. By providing multiple intake pipes 15, this invention enables the standby fuel to be evenly divided into multiple streams within the multiple intake pipes 15 for sufficient atomization and evaporation. The multiple exhaust holes 161 ensure that the standby fuel is evenly distributed along the entire radial length of the fuel distribution pipe 16, avoiding the problem of unsuccessful ignition in the backflow area behind the standby stabilizer standby structure II due to excessively high or low local fuel-air ratios.

[0045] Preferably, the area of ​​the side air intake channel 122 satisfies 2*A. in ≤A outTo ensure unobstructed airflow into the intake pipe 15 and the intake port 141, wherein A in A represents the area of ​​the side air intake channel 122 of the support plate. out This represents the sum of the areas of the air outlet 161 and the air inlet 141 of the fuel distribution pipe 16.

[0046] Preferably, the gap between the fuel distribution pipe 16 and the baffle 13 allows for sufficient expansion space when the fuel distribution pipe 16 is heated. The gap between the fuel distribution pipe 16 and the baffle 13 is set to 2-4 mm. When the gap between the fuel distribution pipe 16 and the baffle 13 is less than 2 mm, they are prone to collision and compression when heated, which can damage the structure and reduce reliability. When the gap is greater than 4 mm, the distribution of the oil-gas mixture d in the fuel distribution pipe 16 behind the support plate stabilizer duty structure II will be restricted in the radial direction, which is not conducive to duty flame stabilization.

[0047] Preferably, the stabilizer support structure II further includes an air intake panel 14 disposed on the front side of the fuel distribution pipe 16. The air intake panel 14 is located behind the side air intake channel 122 and sandwiched between the two side walls 12 of the support cavity structure 1, and has multiple air intake holes 141. That is, the air intake holes 141 are evenly distributed on the air intake panel 14, and the air intake holes 141 are symmetrically distributed about the center line of the air intake panel 14.

[0048] By setting the air intake panel 14, the high-temperature airflow a inside the chamber where the support plate stabilizer duty structure II is located, which enters from the side air intake channel 122, is forced to flow backward through multiple air intake holes 141. This causes the airflow to impact the oil-gas mixture d sprayed from multiple air outlet holes 161 in a preset airflow direction, further promoting the atomization and evaporation of the duty fuel and its mixing with the high-temperature airflow a. This ensures that the oil-gas mixture d obtained by premixing and preevaporating the duty fuel is within the combustible boundary in terms of oil-gas ratio, flow rate, and temperature, thus ensuring the stable combustion of the duty fuel.

[0049] Preferably, the air outlet 161 on the fuel distribution pipe 16 is positioned at a location with a small flow area to ensure that the airflow introduced from the air inlet 141 has a high velocity, resulting in a strong shearing atomization and mixing effect on the fuel-air mixture, thereby improving the atomization and mixing of the fuel and facilitating combustion.

[0050] Preferably, the sidewall 12 of the support plate has a window in the area corresponding to the fuel distribution pipe 16, so that a portion of the vent holes 161 can directly discharge fuel to the circumferential outer side of the support plate cavity structure 1 through the window. The fuel discharged from the window will effectively extend the circumferential distribution range of the standby fuel and improve the range of the stable ignition source downstream of the support plate cavity structure 1. Especially when multiple evaporative support plate stabilizers are evenly distributed circumferentially in the afterburner, the windows opposite adjacent evaporative support plate stabilizers discharge standby fuel, thereby effectively improving the flame connection effect of the afterburner circumferentially.

[0051] Preferably, the support plate stabilizer duty structure II further includes a circumferential stabilizer 3 disposed at the window. The circumferential stabilizer 3 is a bent plate structure with a closed front end, an open rear end, and a cross-sectional area that gradually expands along the flow direction. Thus, under the shielding effect of the circumferential stabilizer 3, the duty fuel discharged from the window will be less affected by the high-temperature internal airflow a along the flow direction, thereby expanding the circumferential diffusion range of the duty fuel. Furthermore, the circumferential stabilizer 3 can also generate a circumferentially distributed annular recirculation zone downstream, allowing the duty fuel flowing out of the window to organize combustion in this low-speed annular recirculation zone, further improving the flame stabilization effect.

[0052] As will be understood by those skilled in the art, the evaporative stabilizer provided by this invention is installed in the afterburner chamber of an aero-engine, and its working principle is as follows: Figure 4 As shown: When the high-temperature airflow a inside the afterburner passes through the evaporative stabilizer and the circumferential stabilizer 3, the high-temperature airflow a enters the evaporative stabilizer through the side intake channel 122. Part of the high-temperature airflow enters the intake pipe 15, carrying fuel injected from the duty fuel injection hole 151 into the fuel distribution pipe 16. After mixing in the fuel distribution pipe 16, a fuel-air mixture d is formed. The fuel-air mixture d is ejected from the outlet hole 161 of the distribution pipe. Another part of the high-temperature airflow flows out through the intake hole 141 on the intake panel 14, which shears the fuel-air mixture d ejected from the outlet hole 161 of the distribution pipe, further enhancing the fuel-air mixing and carrying it into the recirculation zone behind the duty structure II of the stabilizer. The fuel-air mixture d reaches the appropriate fuel-air ratio in the recirculation zone and forms a stable duty flame in the radial direction after ignition.

[0053] Meanwhile, after the high-speed, high-temperature airflow from the inner inlet passes over the leading edge 11 of the support plate, the fuel injected laterally along the main oil passage injection hole 121 is sheared and atomized by the high-speed, high-temperature airflow, reducing the diameter of the fuel droplets and forming an oil-gas mixture d that flows toward the trailing edge 17 of the support plate. Part of the oil-gas mixture d is entrained into the recirculation zone of the trailing edge 17 of the support plate. Then, the radially directed standby flame ignites the oil-gas mixture d in the recirculation zone behind the trailing edge 17 of the support plate, and the flame propagates from behind the standby stabilizer standby structure II toward the center of the afterburner.

[0054] In addition, some low-temperature airflow from the outer duct of the afterburner enters the interior of the support plate structure to provide cooling for the main oil circuit injector rod 221 and the stabilizer. Some low-temperature airflow enters the gap between the duty oil circuit injector rod 211 and the shielding pipe 212 to provide cooling for the duty oil circuit injector rod 211, thus preventing the injector rod from coking and clogging due to overheating.

[0055] Therefore, the beneficial technical effects of the present invention include at least the following:

[0056] This invention integrates the support plate, stabilizer, and fuel injection system into a single design, combining the functions of each component, reducing the number of components, lowering flow losses, making the structure more compact, and effectively shortening the length of the afterburner to achieve weight reduction.

[0057] This invention integrates the evaporative support plate stabilizer and the circumferential stabilizer 3 into a single design, so that the high-temperature airflow a inside can enter the evaporative stabilizer and mix and evaporate with the fuel in the intake pipe 15 and the fuel distribution pipe 16 to form an oil-gas mixture d. With the help of the fuel distribution pipe 16 and the intake pipe 15, the fuel is evenly distributed and the oil-gas mixing time is effectively extended, providing favorable conditions for ignition, widening the ignition and flameout boundary of the stabilizer, and improving the flame stabilizer's ability to ignite and stabilize the flame under complex working conditions.

[0058] This invention places the main fuel line injector 221 inside the support plate stabilizer, and introduces a portion of the external low-temperature airflow b to cool the support plate stabilizer and the injector. Meanwhile, the shift fuel line injector 211 is an air-cooled injector, and a portion of the external low-temperature airflow is introduced into the gap between the shift fuel line injector 211 and the shielding pipe 212 to provide cooling for the shift fuel line injector 211, preventing coking and blockage of the injector. Furthermore, a gap is provided between the fuel distribution pipe 16 and the baffle 13 in the radial direction, allowing for expansion space for the fuel distribution pipe 16 under heat, thus improving structural reliability. Therefore, the overall design improves the structural durability and reliability of the support plate stabilizer.

[0059] In this summary, specific embodiments of the present invention have been described in detail through examples. However, those skilled in the art should understand that the above examples are for illustrative purposes only and are not intended to limit the scope of the invention. It should be understood that modifications can be made to the above embodiments or equivalent substitutions can be made to some technical features without departing from the scope and spirit of the invention. The scope of the invention is defined by the appended claims.

Claims

1. A fuel injection stabilization integrated evaporative support plate stabilizer, characterized in that, The system includes a support plate cavity structure (1) formed by the front edge (11), the side wall (12), and the rear edge (17) of the support plate, and a fuel system (2) disposed within the support plate cavity structure (1). The front part of the support plate cavity structure (1) is a support plate stabilizer cooling chamber (Ⅰ), and the rear part is a support plate stabilizer duty structure (Ⅱ). The support plate stabilizer cooling chamber (Ⅰ) and the support plate stabilizer duty structure (Ⅱ) are separated by a partition (13), while the fuel system (2) is... It includes a main oil circuit system (22) located in the cooling chamber (I) of the stabilizer and a duty oil circuit system (21) located in the duty structure (II) of the stabilizer; the main oil circuit system (22) inside the cooling chamber (I) of the stabilizer is used to inject fuel to the outside, and the radial outer end of the cooling chamber (I) of the stabilizer is connected to the outer duct to introduce cooling gas from the outer duct into the cooling chamber (I) of the stabilizer to cool the main oil circuit system (22). The stabilizer support structure (II) is provided with an intake pipe (15) with an open front end and a fuel distribution pipe (16) connected to the rear end of the intake pipe (15). The shift oil circuit system (21) is connected to the front end of the intake pipe (15). The side wall (12) of the support plate is provided with a side intake channel (122) in the area where the stabilizer support structure (II) is located. The side intake channel (122) is located in front of the intake pipe (15) so that the gas inside enters the intake pipe (15) and the fuel distribution pipe (16) through the side intake channel (122) and promotes the atomization and evaporation of the shift fuel in the intake pipe (15) and the fuel distribution pipe (16). The baffle (13) is distributed at least radially inner, radially outer and forward of the support plate stabilizer duty structure (II), thereby isolating the support plate stabilizer duty structure (II) from the duct cryogenic airflow; The duty oil circuit system (21) includes a duty oil circuit injection rod (211) and a shielding tube (212). The shielding tube (212) is spaced out on the outside of the duty oil circuit injection rod (211). The radially outer opening of the shielding tube (212) is located in the outer duct. The duty oil circuit injection rod (211) and the shielding tube (212) pass through the partition (13) located radially outside the duty structure (II) of the support plate stabilizer from the outer duct and enter the interior of the duty structure (II).

2. The integrated evaporative stabilizer with fuel injection stabilization according to claim 1, characterized in that, The duty fuel line injection rod (211) and the shielding tube (212) are disposed on one side of the circumference of the air intake pipe (15). The air intake pipe (15) is provided with a duty fuel line injection hole (151). The duty fuel line injection rod (211) and the shielding tube (212) are provided with corresponding injection ports on one side of the duty fuel line injection hole (151) so that the duty fuel is impacted by the duty fuel line injection hole (151) and hits the inner wall of the air intake pipe (15).

3. The integrated evaporative stabilizer with fuel injection stabilization according to claim 1, characterized in that, The front area of ​​the cooling cavity (I) of the support plate stabilizer without the partition (13) is connected to the outer duct to form a cooling channel inlet (18), and a cooling channel outlet (19) is provided at the bottom of the cooling cavity (I), so that the airflow of the outer duct enters the interior of the cooling cavity (I) through the cooling channel inlet (18) and is discharged through the cooling channel outlet (19).

4. The integrated evaporative stabilizer with fuel injection and stabilization as described in claim 3, characterized in that, The main oil circuit system (22) includes a main oil circuit injection rod (221) extending from the outer duct through the cooling channel inlet (18) to the interior of the support plate stabilizer cooling cavity (I). The main oil circuit injection rod (221) is provided with a main oil circuit injection port (222). The support plate cavity structure (1) has a main oil circuit injection hole (121) on the side wall (12) of the support plate, which corresponds to the main oil circuit injection port (222). The injection direction of the main oil circuit injection hole (121) is circumferentially directed toward both sides of the support plate cavity structure (1).

5. The integrated evaporative stabilizer with fuel injection stabilization according to claim 1, characterized in that, The intake pipe (15) extends along the flow direction and is distributed in multiple radial directions. The multiple intake pipes (15) are evenly connected to the fuel distribution pipe (16) that extends radially. Multiple air outlets (161) are evenly distributed on both sides of the circumferential direction of the fuel distribution pipe (16), thereby injecting the fuel-air mixture outward in the circumferential direction over the entire length of the fuel distribution pipe (16).

6. The integrated evaporative stabilizer with fuel injection stabilization according to claim 5, characterized in that, The support plate stabilizer duty structure (II) also includes an air intake panel (14) located on the front side of the fuel distribution pipe (16). The air intake panel (14) is located on the rear side of the side air intake channel (122) and sandwiched between the two support plate side walls (12) of the support plate cavity structure (1), and has multiple air intake holes (141) on it.

7. The integrated evaporative stabilizer with fuel injection stabilization according to claim 5, characterized in that, The side wall (12) of the support plate has a window in the area corresponding to the fuel distribution pipe (16) so that part of the air outlet (161) can directly discharge fuel to the circumferential outer side of the support plate cavity structure (1) through the window.

8. The integrated evaporative stabilizer with fuel injection stabilization according to claim 7, characterized in that, The support plate stabilizer duty structure (II) also includes a circumferential stabilizer (3) set in the window. The circumferential stabilizer (3) is a bent plate structure with a closed front end, an open rear end, and a cross-sectional area that gradually expands along the flow direction.

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