Oil-gas synergistic cooling type integrated flame stabilizer

Abstract

The invention provides an oil-gas collaborative cooling type integrated flame stabilizer. The oil-gas collaborative cooling type integrated flame stabilizer comprises a flame stabilizer body, an oil injection rod, a cooling gas inlet pipe, a trailing edge wing plate and a trailing edge cooling cavity. Wherein the oil injection rods are located in the tail edge cooling cavities correspondingly and cooperate with cooling gas to cool the tail edge, so that the temperature of the tail edge is reduced, and the ablation problem caused by the too high temperature of the tail edge is prevented; meanwhile, the fuel oil can flow in the trailing edge cooling cavity for a longer time and continuously collides and makes contact with the wall face of the trailing edge cooling cavity, so that space distribution of the fuel oil is more uniform, due to the fact that the fuel oil exchanges heat with the wall face of the trailing edge, the temperature of the fuel oil is increased, and evaporation and mixing of the fuel oil are further enhanced.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engines, relates to an afterburner combustion chamber, and specifically relates to an oil-gas coordinated cooling type integrated flame stabilizer. Background Art

[0002] The afterburner is a component used to increase the thrust of an aircraft engine in a short period of time. It sprays oil into the gas or fan airflow and organizes combustion to increase the airflow temperature. The afterburner consists of a diffuser, a fuel supply device, an igniter, a nozzle, a flame stabilizer, an anti-vibration heat shield, and a barrel. Under typical working conditions, the airflow velocity at the diffuser of the afterburner can reach 120 to 180 m / s. Such a high airflow velocity is not conducive to the stable combustion of the flame, so a flame stabilizer is needed to stabilize the flame in the high-speed airflow.

[0003] With the continuous improvement of aircraft engine technical indicators, the temperature rise of the main combustion chamber has gradually increased, and the temperature before the turbine has also continued to increase. This has led to a continuous increase in the inlet flow temperature of the afterburner, which has caused each component in the afterburner to bear greater cooling pressure, especially the flame stabilizer, which is almost completely surrounded by the high-temperature gas flow, making it more prone to ablation problems. Traditional cooling solutions often rely on introducing more cooling air into the flame stabilizer to deal with the ablation problem caused by excessive temperatures. However, the improvement of engine performance means that more components need to face the challenge of high temperatures close to the temperature rise limit of the material, the increasing cooling air temperature, and the pursuit of more gas volume to participate in work in order to reduce losses and increase thrust. This has led to the need for the afterburner to consider optimizing its own structure and device when the cooling air temperature is higher and the cooling air volume is less.

[0004] For example, Chinese patent CN202311340500.5 discloses an integrated flame stabilizer with a trailing edge cavity, which forms a trailing edge cavity through a trailing edge wing plate structure, and forms a cooling vortex in the trailing edge cavity to protect and cool the trailing edge of the stabilizer. However, the applicant has found through research that as the technical indicators of aircraft engines continue to improve, the cooling effect of the flame stabilizer in this patent can no longer fully meet more advanced technical requirements, especially for the cooling of the end of the trailing edge wing plate is not sufficient, and the cooling gas still has some interference with the reflow zone.

[0005] When the cooling air is not enough to fully undertake the cooling task, the designers began to seek other cooling media to achieve the cooling of the flame stabilizer. For example, Chinese patent CN202410325794.2 discloses a flame stabilizer with fuel directional impact cooling, which introduces fuel at the trailing edge of the flame stabilizer and uses the vaporization heat absorption of the fuel to achieve cooling. However, for the afterburner, it works in cruise mode for a longer time and only sprays fuel for a short time. Therefore, this technical solution will cause the fuel to stay in the flame stabilizer for a longer time, and carbonize and coke under the influence of the high temperature of the cruise mode, blocking the flame stabilizer's injection hole, thereby causing more serious ablation and even structural damage. Technical problems. Summary of the invention

[0006] In view of this, the present invention provides an oil-gas collaborative cooling integrated flame stabilizer, which can realize oil injection, flame stabilization and cooling in an integrated manner, and uses oil to cool the trailing edge of the stabilizer, which can greatly reduce the temperature of the end of the trailing edge wing plate, so that the flame stabilizer can still maintain a good cooling effect under a smaller amount of cooling air or a higher cooling air temperature, and at the same time has less impact on the recirculation zone, and the spatial distribution uniformity of the fuel is better.

[0007] The present invention provides an oil-gas coordinated cooling integrated flame stabilizer, which is characterized by comprising:

[0008] A stabilizer cavity, comprising a leading edge cooling cavity and two symmetrically distributed trailing edge cooling cavities located at the rear of the leading edge cooling cavity, the leading edge cooling cavity and the trailing edge cooling cavity are separated by a porous partition plate, and a rear side plate of the leading edge cooling cavity is arranged between two trailing edge wing plates of the trailing edge cooling cavities facing each other, air flow holes are opened on the rear side plate, and oil and gas holes are opened on the trailing edge cooling cavity;

[0009] An oil spray rod is disposed inside the trailing edge cooling cavity; and

[0010] The cooling air inlet pipe is connected to the interior of the leading edge cooling cavity.

[0011] Preferably, the stabilizer cavity has a radially extending structure, and on a cross section perpendicular to the radial direction, the front portion of the stabilizer cavity has a streamlined configuration that gradually contracts forward, and the side wall surface of the stabilizer cavity extends backward in a direction basically perpendicular to the circumferential direction and covers the leading edge cooling cavity and the trailing edge cooling cavity.

[0012] Preferably, the leading edge of the trailing edge wing panel is connected to the rear side panel of the leading edge cooling cavity, and the trailing edge of the trailing edge wing panel is connected to the trailing edge of the side wall surface of the stabilizer cavity, whereby the trailing edge wing panel is tilted outward from its leading edge to its trailing edge, so that the spacing between the two trailing edge wing panels gradually increases along the flow direction, so that the tail of the stabilizer cavity has a dovetail configuration.

[0013] Preferably, the air flow holes are arranged in a row along the radial direction on the rear side plate, and the air outlet directions of the two rows of air flow holes closest to the trailing edge wing plate are inclined backward along the flow direction and toward the trailing edge wing plates on both sides.

[0014] Preferably, the air outlet directions of the two rows of air flow holes closest to the trailing edge wing plate are respectively parallel to the trailing edge wing plates on both sides.

[0015] Preferably, the trailing edge cooling cavity is provided with at least one row of the oil and gas holes in a radial direction on the side wall surface of the stabilizer cavity, and the outlet direction of the oil injection holes on the oil injection rod is not directly facing the oil and gas holes.

[0016] Preferably, the multiple fuel injection holes on the fuel injection rod are constructed as straight-injection nozzles and / or fan-shaped nozzles, wherein the nozzle direction of the straight-injection nozzle is toward the trailing edge of the trailing edge wing panel, and the bisector of the central angle of the injection fan of the fan-shaped nozzle is toward the trailing edge of the trailing edge wing panel.

[0017] Preferably, relative to a circumferential projection center line of the oil spray rod on the side wall surface of the stabilizer cavity, at least one row of the oil and gas holes is distributed above or in front of the circumferential projection center line.

[0018] Preferably, the opening direction of the oil and gas holes forms an angle of 30° to 60° backward along the flow direction with respect to the perpendicular direction of the side wall of the stabilizer cavity.

[0019] Preferably, the front end of the porous partition plate is connected to the side wall surface of the stabilizer cavity, and the rear end of the porous partition plate is connected to the rear side plate, and the distance between the two porous partition plates gradually decreases along the flow direction; and the air intake area of ​​the cooling air intake pipe is larger than the sum of the opening area of ​​the porous partition plate and the area of ​​the air flow holes, and the opening area of ​​the porous partition plate of each of the trailing edge cooling cavities is larger than the opening area of ​​the oil and gas holes.

[0020] The present invention provides an oil-gas collaborative cooling type integrated flame stabilizer, which adopts an oil-gas collaborative cooling method. Under normal non-afterburner conditions, the entire stabilizer is cooled only by cooling air. Under the afterburner state, on the basis of air cooling, oil cooling is added to the stabilizer trailing edge wing plate that is prone to high-temperature ablation, thereby greatly reducing the temperature of the trailing edge end, thereby avoiding high-temperature ablation. At the same time, because of the addition of oil cooling, the present invention has a more tolerant margin for the temperature and amount of cooling air, and can meet the cooling requirements of the stabilizer under conditions of higher temperature cooling air or less cooling air. In addition, based on the oil-gas collaborative cooling method, the present invention is able to open a smaller number of cooling holes on the rear side plate of the flame stabilizer, and by controlling the direction of the opening to be consistent with the direction of the inner wall of the trailing edge wing plate, the cooling air discharged from the cooling hole has less impact on the reflow zone. And because the fuel will go through a series of flow processes of colliding with the wall and changing the flow direction in the trailing edge cooling cavity, in this process, in addition to enhancing the heat exchange between the fuel and the wall of the trailing edge cooling cavity, the fuel temperature is increased, which is more conducive to the evaporation and mixing of the fuel, and to a certain extent increases the spatial distribution uniformity of the fuel in the radial direction, making the oil-gas mixture discharged from the oil-gas hole more uniform. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings are used to provide a further understanding of the technical solution of the present application and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the technical solution of the present application, but do not constitute a limitation on the technical solution of the present application.

[0022] Figure 1 A schematic diagram of the three-dimensional structure of the oil-gas collaborative cooling integrated flame stabilizer provided by the present invention;

[0023] Figure 2 A schematic diagram of the three-dimensional structure of the oil-gas cooperative cooling integrated flame stabilizer provided by the present invention along a cross section perpendicular to the axial direction;

[0024] Figure 3 A schematic diagram of the three-dimensional structure of the oil-gas cooperative cooling integrated flame stabilizer provided by the present invention along a section perpendicular to the radial direction;

[0025] Figure 4 The temperature cloud and streamline diagram of the longitudinal section of the oil-gas collaborative cooling integrated flame stabilizer provided by the present invention;

[0026] Reference numerals:

[0027] 1-stabilizer cavity, 11-trailing edge cooling cavity, 12-leading edge cooling cavity, 13-porous partition plate, 14-recirculation zone; 2-injection rod; 3-cooling air intake pipe; 4-trailing edge wing plate, 41-trailing edge cavity; 5-air flow hole; 6-oil and gas hole. DETAILED DESCRIPTION

[0028] Various exemplary embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and is not intended to be any limitation on the present invention and its application or use. The present invention can be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are provided to make the present invention clear and complete and to fully express the scope of the present invention to those skilled in the art. It should be noted that unless otherwise specifically stated, the relative arrangement of the components and steps described in these embodiments should be interpreted as being merely exemplary and not as a limitation.

[0029] like Figure 1-4 As shown, the present invention provides an oil-gas coordinated cooling integrated flame stabilizer, comprising a stabilizer cavity 1, an oil spray rod 2 and a cooling gas inlet pipe 3. Figure 1-3 The stabilizer cavity 1 includes a leading edge cooling cavity 12 and two trailing edge cooling cavities 11 symmetrically distributed at the rear of the leading edge cooling cavity 12. The leading edge cooling cavity 12 and the trailing edge cooling cavity 11 are separated by a porous partition plate 13. Based on the multi-cavity structure of the flame stabilizer, the cooling air intake pipe 3 is connected to the inside of the leading edge cooling cavity 12, and the two fuel injection rods 2 are respectively arranged in the two trailing edge cooling cavities 11.

[0030] The rear side plate of the leading edge cooling cavity 12 is arranged between two porous partition plates 13, and the rear side plate is simultaneously connected between two trailing edge wing plates 4 opposite to each other in the two trailing edge cooling cavities 11, that is, Figure 3 Each of the two circumferential sides of the rear side plate of the leading edge cooling cavity 12 shown is connected to the porous partition plate 13 and the trailing edge wing plate 4, so that the airflow hole 5 opened on the rear side plate will serve as an airflow outlet of the stabilizer cavity 1, and discharge the cooling air into the trailing edge cavity 41, so as to isolate the stabilizer cavity 1 from the high-temperature combustion area of ​​the recirculation zone 14 behind it, and reduce the high temperature effect on the trailing edge cooling cavity 11. The porous partition plate 13 will serve as another airflow outlet of the stabilizer cavity 1, and guide the cooling air into the interior of the trailing edge cooling cavity 11, where the cooling air will be mixed with the fuel sprayed from the injection rod 2, and discharged from the oil and gas hole 6 opened on the trailing edge cooling cavity 11, and be entrained by the incoming flow to the recirculation zone 14 behind the flame stabilizer for stable combustion.

[0031] In the present invention, the cooling air in the leading edge cooling cavity 12 is usually low-temperature air from the outer duct, or can be air from the compressor. In the non-afterburner state, since no ignition combustion occurs, the overall temperature of the flame stabilizer is relatively low compared to the afterburner state, so the cooling air is sufficient to complete the overall cooling of the stabilizer. In the afterburner state, the recirculation zone will become a stable combustion zone, and due to the extension of the trailing edge wing plate 4, the end of the trailing edge wing plate 4 is very close to the recirculation zone, which poses a risk of over-temperature ablation. In this regard, the present invention uses fuel and cooling gas to cool the stabilizer in coordination, wherein the cooling effect of the cooling gas on the flame stabilizer 1 is the same as that in the non-afterburner state, and the trailing edge of the flame stabilizer will be isolated from the ignition zone by the cooling gas discharged to the trailing edge cavity 41, and the fuel is sprayed from the spray rod 2 into the trailing edge cooling cavity 11, and the injection process will impact cool the high-temperature trailing edge wing plate, and then the fuel will continuously collide and flow in the trailing edge cooling cavity 11, in this process, the fuel and the trailing edge wing plate 4 are fully exchanged with heat, and its own temperature is gradually increased, thereby not only cooling the trailing edge wing plate, but also more conducive to the evaporation of the fuel. In addition, the fuel gradually atomizes into small droplets during the impact, flow and collision process, which is more conducive to the evaporation and mixing of the fuel, and is beneficial to the organization of combustion in the recirculation zone 14. At the same time, the fuel is sprayed into the trailing edge cooling cavity 11 and undergoes a series of collisions and flows before being sprayed into the incoming flow together with the cooling gas. This will significantly enhance the spatial distribution uniformity of the fuel in the radial direction compared to the method of directly spraying the fuel into the incoming flow, and is more conducive to organizing combustion.

[0032] Preferably, if Figure 3 As shown in FIG. 1 , the stabilizer cavity 1 of the present invention is a radially extending structure and has the characteristics of a typical radial flame stabilizer: on a cross section perpendicular to the radial direction, the front portion of the stabilizer cavity 1 is a streamline configuration that gradually contracts forward, which can effectively reduce flow resistance and pressure loss, while the side wall surface of the stabilizer cavity 1 extends backward in a direction substantially perpendicular to the circumferential direction and covers the leading edge cooling cavity 12 and the trailing edge cooling cavity 11, thereby forming a structure as shown in FIG. Figure 4 The recirculation zone 14 is shown, and flame combustion is organized in the recirculation zone 14.

[0033] Preferably, reference Figure 1 and Figure 3The front edge of the trailing edge wing plate 4 is connected to the rear side plate of the leading edge cooling cavity 12, and the rear edge of the trailing edge wing plate 4 is connected to the rear edge of the side wall surface of the stabilizer cavity 1, so that the trailing edge wing plate 4 is constructed to be arranged at an outwardly inclined angle from its front edge to its rear edge, so that the spacing between the two trailing edge wing plates 4 gradually increases along the flow direction, so that the tail of the stabilizer cavity 1 presents a dovetail configuration. On the one hand, the dovetail configuration ensures that the cavity structure of the trailing edge cooling cavity 11 has sufficient circumferential width, so that the injection rod 2 can be protected inside the trailing edge cooling cavity 11 to avoid direct burning by the high-temperature incoming flow, and can be uninterruptedly fully cooled by the cooling gas flowing in from the porous partition plate 13. On the other hand, the dovetail configuration also forms a trailing edge cavity 41 in the space between the trailing edge wing plates 4, thereby effectively blocking the thermal influence of the high-temperature combustion gas in the reflow zone 14 on the rear of the stabilizer cavity 1.

[0034] For the dovetail configuration at the tail of the stabilizer cavity 1, Figure 2-4 As shown, the present invention arranges the multiple airflow holes 5 on the rear side plate of the leading edge cooling cavity 12 to be arranged in a row along the radial direction on the rear side plate. In particular, the outlet direction of the two rows of airflow holes 5 closest to the trailing edge wing plate 4 is tilted backward along the flow direction and toward the trailing edge wing plates 4 on both sides, which will cause the cooling air flowing out of the airflow holes 5 to impact the surface of the trailing edge wing plate 4, providing cooling for the trailing edge wing plate 4. Preferably, the outlet directions of the two rows of airflow holes 5 closest to the trailing edge wing plate 4 are respectively parallel to the trailing edge wing plates 4 on both sides. Such a design has two advantages: first, the cooling air blown out of the airflow holes 5 can be used to provide a layer of air film for the trailing edge wing plate 4, providing a more balanced cooling effect for the entire plate surface of the trailing edge wing plate 4, thereby better protecting the trailing edge wing plate from high temperature; second, the influence of the ejection of the cooling air at the rear end of the stabilizer on the formation of the reflow zone can be minimized.

[0035] like Figure 1 , Figure 3 and Figure 4 As shown, the oil and gas holes 6 are arranged in a radial row on the trailing edge cooling cavity 11 on the side wall of the stabilizer cavity 1, and the outlet direction of the oil injection hole on the injection rod 2 is not directly facing the oil and gas holes 6, so that the fuel sprayed from the injection rod 6 will experience multiple collisions in the trailing edge cooling cavity 11 and gradually atomize into small oil droplets, and even evaporate into fuel vapor before being discharged from the oil and gas holes 6 together with the cooling gas, so that the residence time of the fuel in the trailing edge cooling cavity 11 will be longer, which is beneficial to the evaporation and atomization of the fuel and the coordinated cooling of the oil and gas in the trailing edge cooling cavity 11.

[0036] Preferably, the plurality of injection holes on the injection rod 2 are constructed as straight-injection nozzles and / or fan-shaped nozzles, wherein the nozzle direction of the straight-injection nozzle is toward the rear edge of the trailing edge wing plate 4, so that the fuel is sprayed from the injection rod 2 and directly impacts the end of the trailing edge wing plate 4, and the extreme end of the high-temperature trailing edge wing plate is cooled to a certain extent by impact cooling; and the injection fan of the fan-shaped nozzle is perpendicular to the circumferential direction and the angular bisector of the central angle of the injection fan is toward the rear edge of the trailing edge wing plate (4), so that most of the fuel sprayed from the fan-shaped nozzle, that is, the part of the fuel sprayed along the direction of the angular bisector of the central angle of the injection fan, can impact the extreme end of the high-temperature trailing edge wing plate with a larger flow velocity component, and at the same time, the part of the fuel sprayed away from the direction of the angular bisector can diffuse to the space between adjacent nozzles with a larger radial velocity component, thereby effectively improving the uniformity of fuel distribution.

[0037] In actual use, only a single type of nozzle can be used on the spray rod, or a direct nozzle and a fan nozzle can be used at the same time. For example, the direct nozzle and the fan nozzle can be arranged at intervals, thereby taking into account the stronger impact cooling efficiency and low processing cost of the direct nozzle, and the better atomization ability and more uniform fuel spatial distribution of the fan nozzle.

[0038] Preferably, relative to the circumferential projection center line of the fuel injection rod 2 on the side wall surface of the stabilizer cavity 1, at least one row of oil and gas holes 6 is distributed above or before the circumferential projection center line. As a result, the fuel will be sprayed toward the end of the trailing edge wing plate 4 in the trailing edge cooling cavity 11, and after impacting the end of the trailing edge wing plate, it will be divided into two streams along the wall surface and then flow and diffuse, and finally mixed with the cooling air entering the trailing edge cooling cavity 11 from the porous partition plate 13, and then discharged from the oil and gas holes 6 together, and further mixed with the incoming flow.

[0039] like Figure 3-4 As shown, the present invention sets the opening direction of the oil and gas hole 6 on the side wall of the stabilizer cavity 1 to be at an angle of 30° to 60° backward along the flow direction with respect to the vertical direction of the side wall of the stabilizer cavity 1. Compared with the opening angle perpendicular to the side wall, the exit direction inclined backward along the flow direction can give the oil and gas mixture a certain flow velocity component. Such a design can make the oil and gas mixture emitted from the oil and gas hole 6 more easily pressurized to the flame stabilizer wall by the external flow, thereby providing air film cooling protection while being more easily affected by the pressure behind the stabilizer to enter the recirculation zone to participate in organizing combustion.

[0040] like Figure 3As shown, the front end of the porous partition plate 13 in the present invention is connected to the side wall surface of the stabilizer cavity 1, and the rear end of the porous partition plate 13 is connected to the rear side plate, and the spacing between the two porous partition plates 13 gradually decreases along the flow direction, forming a wedge-shaped flow channel with a gradually shrinking channel area, thereby improving the cooling air velocity and / or pressure in the air flow hole 5 to a certain extent, thereby improving the wall cooling effect of the trailing edge wing plate 4. At the same time, the inclination angle of the porous partition plate 13 relative to the flow direction can also effectively control the ratio of the cooling air entering the trailing edge cooling cavity 11 and the air flow flowing out of the leading edge cooling cavity 12 through the air flow hole 5: the larger the inclination angle, the more cooling air will enter the trailing edge cooling cavity 11, and conversely, the more air will flow out of the leading edge cooling cavity 12 through the air flow hole 5.

[0041] Furthermore, in order to control the pressure distribution and cooling air direction in the flame stabilizer, the present invention sets the air intake area of ​​the cooling air intake pipe to be larger than the sum of the opening area of ​​the porous partition plate and the area of ​​the air flow hole, and sets the opening area of ​​the porous partition plate of each trailing edge cooling cavity to be larger than the opening area of ​​the oil and gas hole. Thus, the cooling air will enter the air cooling cavity 12 from the cooling air intake pipe 3, and flow to the front end of the flame stabilizer 1, the rear end of the flame stabilizer 1 and the trailing edge cooling cavity 11 through the partition plate 13 under the action of pressure, and then mix with the fuel sprayed by the spray rod 2 in the trailing edge cooling cavity, and spray out from the oil and gas hole 6 opened on the outer wall of the flame stabilizer 1 together, and reach the reflow zone for combustion under the entrainment of the incoming flow.

[0042] like Figure 4 As shown in the temperature cloud diagram in the figure, the present invention adopts an oil-gas synergistic cooling method to specially design and cool the trailing edge of the stabilizer wing panel, which is most susceptible to high temperatures, thereby reducing the trailing edge temperature and greatly reducing the risk of ablation of the trailing edge wing panel of the stabilizer. Figure 4 In the streamline diagram, on the cross section perpendicular to the radial direction, the external incoming flow of the flame stabilizer is divided into two streams at the leading edge of the stabilizer and flows to the tail end along the side wall of the stabilizer cavity 1. In this process, the incoming flow will press the oil-gas mixture ejected from the oil-gas hole 6 to the side wall of the stabilizer cavity 1, so that it flows to the recirculation zone in a manner that fits the outer wall. At the same time, since the opening direction of the airflow hole 5 is parallel to the wall of the trailing edge wing plate 4, this cooling air will promote the formation of the recirculation zone without seriously interfering with or inhibiting the formation of the recirculation zone.

[0043] In summary, the oil-gas collaborative cooling integrated flame stabilizer provided by the present invention adopts an oil-gas collaborative cooling method. In normal non-afterburner conditions, the entire stabilizer is cooled only by cooling air. In the afterburner state, on the basis of air cooling, oil cooling is added to the stabilizer trailing edge wing plate that is prone to high-temperature ablation, thereby greatly reducing the temperature of the trailing edge end, thereby avoiding high-temperature ablation. At the same time, due to the addition of oil cooling, the present invention has a more tolerant margin for the temperature and amount of cooling air, and can meet the cooling needs of the stabilizer under the conditions of higher temperature cooling air or less cooling air.

[0044] In addition, based on the oil-gas collaborative cooling method, the present invention is able to open a smaller number of cooling holes on the rear side plate of the flame stabilizer, and by controlling the direction of the opening to be consistent with the direction of the inner wall of the trailing edge wing plate, the cooling gas discharged from the cooling hole has a smaller impact on the reflow zone. And because the fuel will go through a series of flow processes of colliding with the wall and changing the flow direction in the trailing edge cooling cavity, in this process, in addition to enhancing the heat exchange between the fuel and the wall of the trailing edge cooling cavity, the fuel temperature is increased, which is more conducive to the evaporation and mixing of the fuel, and to a certain extent, the spatial distribution uniformity of the fuel in the radial direction is increased, making the oil-gas mixture discharged from the oil-gas hole more uniform.

[0045] The above are only specific implementations of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An oil-gas coordinated cooling integrated flame stabilizer, characterized in that: include: A stabilizer cavity (1), comprising a leading edge cooling cavity (12) and two trailing edge cooling cavities (11) symmetrically distributed at the rear of the leading edge cooling cavity (12), the leading edge cooling cavity (12) and the trailing edge cooling cavity (11) being separated by a porous partition plate (13), and a rear side plate of the leading edge cooling cavity (12) being arranged between two trailing edge wing plates (4) of the trailing edge cooling cavities (11) facing each other, an airflow hole (5) being provided on the rear side plate, and an oil and gas hole (6) being provided on the trailing edge cooling cavity (11); A fuel injection rod (2) is arranged inside the trailing edge cooling cavity (11); and The cooling air inlet pipe (3) is connected to the interior of the leading edge cooling cavity (12).

2. The oil-gas coordinated cooling integrated flame stabilizer according to claim 1, characterized in that: The stabilizer cavity (1) is a radially extending structure. On a cross section perpendicular to the radial direction, the front portion of the stabilizer cavity (1) is a streamlined configuration that gradually contracts forward. The side wall surface of the stabilizer cavity (1) extends backward in a direction substantially perpendicular to the circumferential direction and covers the leading edge cooling cavity (12) and the trailing edge cooling cavity (11).

3. The oil-gas coordinated cooling integrated flame stabilizer according to claim 2 is characterized in that: The front edge of the trailing edge wing panel (4) is connected to the rear side panel of the leading edge cooling cavity (12), and the rear edge of the trailing edge wing panel (4) is connected to the rear edge of the side wall surface of the stabilizer cavity (1), so that the trailing edge wing panel (4) is tilted outward from its front edge to its rear edge, so that the distance between the two trailing edge wing panels (4) gradually increases along the flow direction, so that the tail of the stabilizer cavity (1) has a dovetail configuration.

4. The oil-gas coordinated cooling integrated flame stabilizer according to claim 1 or 3, characterized in that: The air flow holes (5) are arranged in a row along the radial direction on the rear side plate, and the air outlet directions of the two rows of air flow holes (5) closest to the trailing edge wing plate (4) are inclined backward along the flow direction and toward the trailing edge wing plates (4) on both sides.

5. The oil-gas coordinated cooling integrated flame stabilizer according to claim 4 is characterized in that: The air outlet directions of the two rows of air flow holes (5) closest to the trailing edge wing plate (4) are respectively parallel to the trailing edge wing plates (4) on both sides.

6. The oil-gas coordinated cooling integrated flame stabilizer according to claim 2, characterized in that: The trailing edge cooling cavity (11) is provided with at least one row of oil and gas holes (6) in a radial direction on the side wall surface of the stabilizer cavity (1), and the outlet direction of the oil injection holes on the oil injection rod (2) is not directly facing the oil and gas holes (6).

7. The oil-gas coordinated cooling integrated flame stabilizer according to claim 6, characterized in that: The plurality of injection holes on the injection rod (2) are constructed as straight-injection nozzles and / or fan-shaped nozzles, wherein the nozzle direction of the straight-injection nozzle is toward the rear edge of the trailing edge wing plate (4), and the injection fan of the fan-shaped nozzle is perpendicular to the circumferential direction and the bisector of the central angle of the injection fan is toward the rear edge of the trailing edge wing plate (4).

8. The oil-gas coordinated cooling integrated flame stabilizer according to claim 7, characterized in that: Relative to the circumferential projection center line of the oil injection rod (2) on the side wall surface of the stabilizer cavity (1), at least one row of the oil and gas holes (6) is distributed above or in front of the circumferential projection center line.

9. The oil-gas coordinated cooling integrated flame stabilizer according to claim 2, characterized in that: The opening direction of the oil and gas hole (6) and the vertical direction of the side wall of the stabilizer cavity (1) form an angle of 30° to 60° backward along the flow direction.

10. The oil-gas coordinated cooling integrated flame stabilizer according to claim 1, characterized in that: The front end of the porous partition plate (13) is connected to the side wall surface of the stabilizer cavity (1), and the rear end of the porous partition plate (13) is connected to the rear side plate, and the distance between the two porous partition plates (13) gradually decreases along the flow direction; and the air intake area of ​​the cooling air intake pipe (3) is larger than the sum of the opening area of ​​the porous partition plate (13) and the area of ​​the air flow hole (5), and the opening area of ​​the porous partition plate (13) of each of the trailing edge cooling cavities (11) is larger than the opening area of ​​the oil and gas holes (6).

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