An integrated flame holder having a trailing edge cavity

Abstract

The application provides an integrated flame stabilizer with a tail edge cavity, which comprises a flame stabilizer, an oil injection rod, a cooling gas inlet pipe and a tail edge wing plate arranged at the rear side of the flame stabilizer, and a stable backflow ignition area is formed in the downstream area of the flame stabilizer; a plurality of cooling channels are arranged on the rear side plate of the flame stabilizer between the two tail edge wing plates, and the airflow direction at the outlet of the cooling channels is inclined to the flow direction, so that a cooling vortex is formed in the tail edge cavity, the flame stabilizer and the backflow ignition area are spaced from each other, the flame stabilizer and the downstream backflow ignition area are isolated from each other to reduce the thermal load of the components such as the flame stabilizer and the fuel injection pipe, the ablation and coking problems are avoided, meanwhile, the flame stabilizing function of the flame stabilizer is not damaged, and the influence on the backflow ignition area behind the stabilizer is small.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engines, and relates to a variable cycle engine, in particular to an integrated flame stabilizer with a trailing edge cavity. BACKGROUND

[0002] As a power device capable of maintaining low fuel consumption during subsonic cruise and high thrust during supersonic cruise, a variable cycle engine (VCE) has the performance advantages of both turbojet and turbofan engines. By adjusting the structure shape or position of components, the VCE changes the thermodynamic cycle of the engine to meet the performance requirements of the engine in various tasks and environments. The VCE is the focus of development in the field of aero-engines.

[0003] A afterburner is one of the important components of an aero-engine. Compared with the third generation afterburner, the inlet temperature of the afterburner of a variable cycle engine is greatly increased, being between 900-1400K, and the maximum inlet temperature of the afterburner of a high-performance military aero-engine can exceed 1300K. The great increase in the inlet temperature of the afterburner greatly increases the thermal load of components such as the flame stabilizer and fuel nozzle, which introduces new scientific problems and design difficulties. Firstly, the extremely high temperature in the afterburner has exceeded the tolerance temperature of nickel-based single-crystal alloy, which can cause ablation and coking of the oil injection rod and the flame stabilizer, especially the trailing edge of the flame stabilizer, which is closest to the flame zone and is most susceptible to ablation, thereby affecting the reliability and safety of the aero-engine. Secondly, air cooling technology is one of the most widely used cooling technologies for high-temperature components of aero-engines, but the exhaust method of the cooling gas can affect the backflow area behind the stabilizer, thereby affecting the ignition performance and combustion stability of the aero-engine. SUMMARY

[0004] Therefore, the present application provides an integrated flame stabilizer with a trailing edge cavity, which can integrally realize oil injection, flame stabilization and cooling, effectively solve the ablation and coking problems of the oil injection rod and the flame stabilizer in the afterburner of a variable cycle engine, and has little effect on the backflow area behind the stabilizer.

[0005] The present application provides an integrated flame stabilizer with a trailing edge cavity, which comprises:

[0006] a flame stabilizer, which is provided with an oil-gas mixing chamber and a cooling gas chamber that are in communication with each other, and a stable backflow ignition area is formed in the downstream area of the flame stabilizer;

[0007] an oil injection rod, which is connected to the inside of the oil-gas mixing chamber;

[0008] a cooling gas inlet pipe, which is connected to the inside of the cooling gas chamber; and

[0009] Tail edge wing plates arranged at the rear side of the flame holder and extending rearward from the rear ends of the two circumferential side plates of the flame holder, so as to form a tail edge cavity between the two tail edge wing plates;

[0010] Wherein, a plurality of cooling channels are arranged on the rear side plate of the flame holder between the two tail edge wing plates, and the airflow direction of the outlet of the cooling channels is inclined to the flow direction, so as to form cooling vortices in the tail edge cavity, so as to separate the flame holder and the backflow ignition area from each other.

[0011] Preferably, the angle between the airflow direction of the outlet of the cooling channels and the flow direction is 30° to 60°.

[0012] Preferably, the airflow direction of the outlet of the plurality of cooling channels is inclined to the radial direction of the flame holder relative to the flow direction, so as to form a plurality of cooling vortices with vorticity extending in the circumferential direction in the tail edge cavity, and the plurality of cooling vortices are arranged in the radial direction.

[0013] Preferably, the airflow direction of the outlet of the plurality of cooling channels is inclined to the radial inner side of the flame holder relative to the flow direction, and the plurality of cooling channels are uniformly arranged in the radial direction, so that the cooling vortex formed by the cooling gas discharged from each cooling channel can cool the part of the rear side wall between the cooling channel and the adjacent cooling channel located on the radial inner side.

[0014] Preferably, the airflow direction of the outlet of the plurality of cooling channels is inclined to the circumferential direction of the flame holder relative to the flow direction, so as to form the cooling vortices with vorticity extending in the radial direction in the tail edge cavity.

[0015] Preferably, the plurality of cooling channels are divided into two parts in the circumferential direction, and the airflow direction of the outlet of the cooling channels in each part is inclined to the tail edge wing plate on the side close to the cooling channels in the part relative to the flow direction, so that a plurality of pairs of cooling vortices arranged in the circumferential direction are formed in the tail edge cavity by the cooling channels in the two parts.

[0016] Preferably, the rear side plate of the flame holder is in a folded plate structure, and at least one plate surface in the folded plate structure is arranged perpendicular to the flow direction, and the two plate surfaces located at the outermost side in the circumferential direction in the folded plate structure are connected to the rear edges of the tail edge wing plates.

[0017] Preferably, the cooling channels are arranged on the two plate surfaces located on the outer side in the circumferential direction in the folded plate structure, and the angle between the airflow direction of the outlet of the cooling channels and the flow direction is greater than 90°, so as to form a pair of cooling vortices with vorticity extending in the radial direction on the rear side of the folded plate structure.

[0018] Preferably, the flame stabilizer further comprises:

[0019] a front impact baffle, which is arranged between the oil-gas mixing chamber and the cooling gas chamber and is provided with a plurality of impact gas holes; and

[0020] a rear impact baffle, which is arranged in front of the rear side plate of the flame stabilizer and is provided with a plurality of impact gas holes.

[0021] Preferably, the cooling channel comprises a cooling slit and / or a cooling hole.

[0022] Based on this, the present application forms a trailing edge cavity behind the rear side plate of the flame stabilizer through the trailing edge wing plate, and forms a cooling vortex in the trailing edge cavity through the cooling channel constructed on the rear side plate, so as to isolate the flame stabilizer from the recirculation ignition area downstream, thereby reducing the thermal load of the flame stabilizer and components such as the fuel nozzle, avoiding the problems of ablation and coking, and at the same time, without damaging the flame stabilization function of the flame stabilizer, the influence on the recirculation ignition area behind the stabilizer is small. BRIEF DESCRIPTION OF DRAWINGS

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

[0024] Figure 1 The first embodiment of the integrated flame stabilizer with a trailing edge cavity provided by the present application is shown in a vertical structure schematic view along a circumferential section plane;

[0025] Figure 2 The first embodiment of the integrated flame stabilizer with a trailing edge cavity provided by the present application is shown in a vertical structure schematic view along a circumferential section plane;

[0026] Figure 3 The second embodiment of the integrated flame stabilizer with a trailing edge cavity provided by the present application is shown in a vertical structure schematic view along a circumferential section plane;

[0027] Figure 4 The second embodiment of the integrated flame stabilizer with a trailing edge cavity provided by the present application is shown in a vertical structure schematic view along a circumferential section plane;

[0028] Figure 5 The third embodiment of the integrated flame stabilizer with a trailing edge cavity provided by the present application is shown in a vertical structure schematic view along a circumferential section plane;

[0029] Figure 6A third embodiment of the integrated flame holder with a trailing edge cavity provided by the present application is shown in a perspective view along a radial cross-section;

[0030] Figure 7 A fourth embodiment of the integrated flame holder with a trailing edge cavity provided by the present application is shown in a perspective view along a radial cross-section;

[0031] Figure 8 A fourth embodiment of the integrated flame holder with a trailing edge cavity provided by the present application is shown in a perspective view along a radial cross-section;

[0032] Figure 9 A fourth embodiment of the integrated flame holder with a trailing edge cavity provided by the present application is shown in a longitudinal cross-section temperature contour plot;

[0033] Reference numerals:

[0034] 1 - flame holder, 11 - oil-gas mixing chamber, 12 - cooling gas chamber, 13 - recirculation ignition zone, 14 - circumferential side plate, 15 - rear side plate, 16 - front impingement baffle, 17 - rear impingement baffle;

[0035] 2 - oil injection rod;

[0036] 3 - cooling gas inlet tube;

[0037] 4 - trailing edge wing, 41 - trailing edge cavity;

[0038] 5 - cooling passage, 51 - cooling vortex, 52 - cooling slot, 53 - cooling hole. DETAILED DESCRIPTION

[0039] Various exemplary embodiments of the present application will be described herein below, with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and not restrictive, and is not intended to limit the present application and its application or use in any way. The present application can be implemented in many different forms, and is not limited to the embodiments described herein. These embodiments are provided so that the present application is clear and complete, and fully conveys the scope of the present application to those skilled in the art. It should be noted that the relative arrangement of the components and steps set forth in these embodiments should be interpreted as merely exemplary, and not as a limitation, unless otherwise specifically stated.

[0040] As Figures 1-9As shown, the integrated flame stabilizer with a trailing edge cavity provided by the present invention includes a flame stabilizer 1, a fuel injector 2, a cooling gas inlet pipe 3, and a trailing edge wing 4. The flame stabilizer 1 has an interconnected fuel-air mixing chamber 11 and a cooling gas chamber 12. The fuel injector 2 is connected to the interior of the fuel-air mixing chamber 11, while the cooling gas inlet pipe 3 is connected to the interior of the cooling gas chamber 12. Cooling gas enters the cooling gas chamber 12 from the cooling gas inlet pipe 3 and flows to the fuel-air mixing chamber 11 under the action of a pressure difference. There, it mixes with the fuel injected from the fuel injector 2 inside the fuel-air mixing chamber 11 and is finally ejected from the fuel injection holes on the wall of the fuel-air mixing chamber 11, flowing downstream of the flame stabilizer 1 and igniting.

[0041] The aforementioned cooling air can be taken from the relatively low-temperature outer bypass region of the afterburner or directly from the even lower-temperature compressor, thus ensuring that the cooling air can adequately cool the flame stabilizer 1 regardless of whether it is in afterburner or non-afterburner mode. In afterburner mode, fuel is injected from several injection holes on the fuel injector 2. As it is injected and impacts the inner wall of the fuel-air mixing chamber 11, it gradually atomizes into small droplets and evaporates under the influence of the high-temperature incoming flow from outside the fuel-air mixing chamber 11, thereby filling the fuel-air mixing chamber 11. These small fuel droplets or fuel vapors will further mix with the cooling air from the cooling air chamber 12 and be ejected from the injection holes to organize combustion.

[0042] The oil-gas mixing chamber 11 of the flame stabilizer 1 of the present invention is located in the upstream region of the cooling gas chamber 12, and the oil-gas mixing chamber 11 has a streamlined windward structure, while the wall of the cooling gas chamber 12 extends along the flow direction. This allows the oil-gas mixing chamber 11 to come into contact with the incoming flow at a higher temperature to promote fuel evaporation, and on the other hand, it allows a stable recirculation ignition region 13 to be formed in the downstream region of the flame stabilizer 1.

[0043] Specifically, such as Figure 9 As shown, in a cross-section perpendicular to the radial direction, the lines in the temperature cloud diagram indicate that the airflow is split into two streams at the leading edge of the flame stabilizer 1 and flows along the two circumferential side plates 14 of the flame stabilizer 1 to the trailing edge of the flame stabilizer 1. After the airflow leaves the trailing edge of the flame stabilizer 1, due to the lower pressure on the inner side of the airflow circumferentially, it tends to move inward and forms a stable recirculation ignition region 13 downstream of the flame stabilizer 1. It can be understood that this recirculation ignition region 13 entrains a large amount of oil-gas mixture ejected from the injection holes on the wall of the oil-gas mixing chamber 11. This oil-gas mixture will spontaneously combust under high temperature to form a stable ignition source, thereby helping to organize and stabilize afterburner combustion.

[0044] Further, the present application sets the trailing edge wing plates 4 on the rear side of the flame stabilizer 1, and makes the trailing edge wing plates 4 respectively extend backward from the two circumferential side plates 14 of the flame stabilizer 1 to the rear end of the side plate 14, so as to form a trailing edge cavity 41 between the two trailing edge wing plates 4. On this basis, the present application sets multiple cooling channels 5 on the rear side plate 15 of the flame stabilizer 1 between the two trailing edge wing plates 4, and sets the airflow direction at the outlet of the cooling channels 5 to be inclined to the flow direction, so as to form a cooling vortex 51 in the trailing edge cavity 41, so as to separate the flame stabilizer 1 and the backflow ignition area 13 from each other, and reduce the heat transfer from the backflow ignition area 13 to the flame stabilizer 1.

[0045] Since the trailing edge wing plates 4 extend backward relative to the two circumferential side plates 14 of the flame stabilizer 1, the position where the airflow separates from the trailing edge of the flame stabilizer 1 can also be extended backward, which on one hand makes the backflow ignition area 13 with higher temperature away from the flame stabilizer 1 and the oil injection rod 2, and reduces the ablation and coking problems caused by the high temperature, and on the other hand, the backflow ignition area 13 is farther away from the flame stabilizer 1, and enough space is formed between the backflow ignition area 13 and the flame stabilizer 1 to form the cooling vortex 51, so as to avoid the adverse effects of the cooling vortex 51 on the backflow ignition area 13.

[0046] Preferably, the included angle between the airflow direction at the outlet of the cooling channels 5 and the flow direction is 30° to 60°. The airflow direction set to be inclined to the flow direction can give the gas discharged from the cooling channels 5 a component velocity perpendicular to the flow direction, so as to help the formation of the cooling vortex 51. And it is found through calculation that if the included angle is less than 30°, the component velocity perpendicular to the flow direction is too small to form a cooling vortex 51 with enough strength, and if the included angle is greater than 60°, the component velocity along the flow direction is too large, and part of the cooling gas flow may directly impact on the backflow area 13 and affect it.

[0047] Preferably, the flame stabilizer 1 further comprises a front impact baffle 16 arranged between the oil-gas mixing chamber 11 and the cooling gas chamber 12, and a rear impact baffle 17 arranged on the front side of the rear side plate 15 of the flame stabilizer 1, and multiple impact gas holes are arranged on the front impact baffle 16 and the rear impact baffle 17.

[0048] The arrangement of the front impact baffle 16 and the rear impact baffle 17 can effectively separate the oil-gas mixing chamber 11, the cooling gas chamber 12 and the rear side plate 15 of the flame stabilizer 1, and prevent heat transfer inside the flame stabilizer 1, and the impact gas holes arranged on the impact baffles can increase the speed of the cooling gas entering the oil-gas mixing chamber 11 from the cooling gas chamber 12 or impacting on the rear side plate 15 of the flame stabilizer 1, so as to further improve the cooling effect.

[0049] The various embodiments of the present application will be further described below with reference to the accompanying drawings.

[0050] like Figures 1-2 As shown, in the first embodiment of the present invention, the airflow direction at the outlet of the plurality of cooling channels 5 is inclined to the radial direction of the flame stabilizer 1 relative to the flow direction, thereby forming a plurality of cooling vortices 51 extending in the circumferential direction in the trailing edge cavity 41, and the plurality of cooling vortices 51 are arranged in the radial direction.

[0051] Considering the size of the cooling vortex 51, a single cooling vortex 51 is difficult to directly fill all areas within the trailing edge cavity 41. Therefore, the present invention opens multiple cooling channels 5 on the rear sidewall of the flame stabilizer 1 to form multiple cooling vortices 51 extending in the circumferential direction. This effectively fills the trailing edge cavity 41 by arranging multiple cooling vortices 51 in the radial direction, ensuring the spacing and cooling effect of the cooling vortices 51.

[0052] Since the outer radial side of the flame stabilizer 1 is close to the low-temperature region of the outer casing, while the inner radial side is close to the high-temperature region of the inner casing, the cooling demand on the inner radial side of the flame stabilizer 1 will be much greater than that on the outer radial side. To address this, in a preferred embodiment, the airflow direction at the outlets of the multiple cooling channels 5 is inclined relative to the flow direction towards the inner radial side of the flame stabilizer 1, and the multiple cooling channels 5 are uniformly arranged radially. This ensures that the cooling vortex 51 formed by the cooling gas discharged from each cooling channel 5 can cool the portion of the rear wall between that cooling channel 5 and the adjacent cooling channel 5 located on the inner radial side, thereby ensuring the distribution of cooling vortices 51 on the inner radial side of the flame stabilizer 1. For the outer radial side of the flame stabilizer, which has a relatively lower cooling demand, it is directly cooled by a lower-temperature cooling airflow.

[0053] like Figures 3-4 As shown, in the second embodiment of the present invention, the airflow direction at the outlets of the plurality of cooling channels 5 is inclined relative to the flow direction towards the circumferential direction of the flame stabilizer 1, thereby forming a cooling vortex 51 with vorticity extending in the radial direction within the trailing edge cavity 41. In the second embodiment, the radial dimension of the cooling vortex 51 with vorticity extending in the radial direction is substantially equal to that of the flame stabilizer 1, thus the entire trailing edge cavity 41 can be effectively filled by a single cooling vortex 51.

[0054] However, if only one cooling vortex 51 is formed in the trailing edge cavity 41, the single cooling vortex 51 is easily disturbed by the incoming flow and has an unstable shape, which is undoubtedly disadvantageous to the function of the cooling vortex 51 in separating the high-temperature region. Therefore, preferably, the plurality of cooling channels 5 of the present application are divided into two parts in the circumferential direction, and the airflow direction at the outlet of the cooling channel 5 of each part is inclined to the side of the trailing edge airfoil 4 close to the cooling channel 5 of the part relative to the flow direction, so that a plurality of cooling vortices 51 are formed in the trailing edge cavity 41 by the two parts of cooling channels 5, which can be divided into two parts arranged in the circumferential direction and balanced in vortex quantity. Since the cooling vortices 51 formed by the two parts of cooling channels 5 constitute a plurality of pairs of vortices balanced in vortex quantity, the shape of the cooling vortices 51 is more stable and is less likely to be disturbed by the incoming flow and change in shape.

[0055] As shown in FIG. 1, in the first embodiment of the present application, the cooling channel 5 is provided in the form of a cooling slot 52, which is different from the form of the cooling hole 53 in the third embodiment of the present application. The cooling slot 52 can be more accurately controlled in shape by controlling the airflow direction and / or opening size at the outlet of each cooling slot 52. Figures 5-6 As shown in FIG. 1, in the first embodiment of the present application, the cooling channel 5 is provided in the form of a cooling slot 52, which is different from the form of the cooling hole 53 in the third embodiment of the present application. The cooling slot 52 can be more accurately controlled in shape by controlling the airflow direction and / or opening size at the outlet of each cooling slot 52.

[0056] Figures 7-9 As shown in FIG. 1, in the first embodiment of the present application, the cooling channel 5 is provided in the form of a cooling slot 52, which is different from the form of the cooling hole 53 in the third embodiment of the present application. The cooling slot 52 can be more accurately controlled in shape by controlling the airflow direction and / or opening size at the outlet of each cooling slot 52.

[0057] Among them, the plate surface of the folded plate structure arranged perpendicular to the flow direction will provide sufficient accommodation space for the formation of the cooling vortex 51, and the direct connection of the two plate surfaces located at the outermost side of the folded plate structure with the trailing edge of the trailing edge airfoil 4 can form a cooling chamber between the folded plate structure, the trailing edge airfoil 4 and the rear impact baffle 17, which is more conducive to cooling the trailing edge airfoil 4.

[0058] Preferably, the cooling channel 5 is provided on the two plate surfaces located at the outermost side of the folded plate structure in the circumferential direction, and the angle between the airflow direction at the outlet of the cooling channel 5 and the flow direction is greater than 90°, so as to form a pair of cooling vortices 51 extending in the radial direction on the rear side of the folded plate structure.

[0059] ​The present application sets the outlet of the cooling channel 5 at the two plate surfaces located at the outermost side in the circumferential direction in the folded plate structure arranged obliquely relative to the flow direction, and regulates the included angle between the airflow direction at the outlet of the cooling channel 5 and the flow direction to be greater than 90°, so that the velocity component of the airflow in the circumferential direction perpendicular to the flow direction can be more accurately adjusted, and thus the shape of the cooling vortex 51 can be better adjusted.

[0060] Therefore, the present application forms a trailing edge cavity 41 behind the rear side plate 15 of the flame stabilizer 1 by the trailing edge wing plate 4, and forms a cooling vortex 51 in the trailing edge cavity 41 by constructing the cooling channel 5 on the rear side plate 15, so as to isolate the flame stabilizer 1 from the recirculation ignition area 13 downstream, thereby reducing the thermal load of the flame stabilizer 1 and components such as fuel nozzles, avoiding ablation and coking problems, and at the same time, without damaging the flame stabilizing function of the flame stabilizer 1, the influence on the recirculation ignition area 13 behind the stabilizer is small.

[0061] Thus, in the non-afterburning state, the inside of the flame stabilizer 1 is filled with cooling gas, and in the afterburning state, the oil-gas mixing chamber 11 is filled with service fuel, and the cooling gas chamber 12 is filled with cooling gas, which is divided into three parts: the first part of the cooling gas flows backward, passes through the cooling slits 52 or cooling holes 53 opened on the rear side plate 15 to reach the trailing edge cavity 41, and stays in the trailing edge cavity 41 for a period of time to protect the rear side plate 15 and the trailing edge wing plate 4 of the flame stabilizer 1, or forms a cooling gas vortex in the trailing edge cavity 41 to prolong the cooling gas residence time and enhance the cooling effect; the second part of the cooling gas also flows backward, enters the trailing edge inside through the impact gas holes on the rear impact partition plate 17, and impinges and cools the inner wall surface of the rear side plate 15 of the flame stabilizer 1; the third part of the cooling gas flows forward, passes through the impact gas holes on the front impact partition plate 16, reaches the oil-gas mixing chamber 11 of the flame stabilizer 1, cools the oil injection rod 2 and the inner wall surface of the front edge of the oil-gas mixing chamber 11, thereby solving the problem of oil injection rod coking, and finally exits the flame stabilizer 1 from the oil injection holes on the circumferential side plate 14.

Claims

1. An integrated flame holder having a trailing edge cavity, characterized by, The application relates to a flame stabilizer (1) comprising an oil-gas mixing chamber (11) and a cooling gas chamber (12) which are connected with each other, a downstream area of the flame stabilizer (1) forms a stable backflow ignition area (13), an oil injection rod (2) is connected to the inside of the oil-gas mixing chamber (11), a cooling gas inlet pipe (3) is connected to the inside of the cooling gas chamber (12), and tail edge wing plates (4) are arranged on the back side of the flame stabilizer (1) and extend backward from the back ends of two circumferential side plates (14) of the flame stabilizer (1) respectively, so that a tail edge cavity (41) is formed between the two tail edge wing plates (4). Wherein, a plurality of cooling channels (5) are arranged on the back side plate (15) of the flame stabilizer (1) between the two tail edge wing plates (4), the gas flow direction at the outlet of the cooling channels (5) is inclined to the flow direction, so that cooling vortices (51) are formed in the tail edge cavity (41), and the flame stabilizer (1) is spaced from the backflow ignition area (13). The back side plate (15) of the flame stabilizer (1) is in a folded plate structure, at least one plate surface in the folded plate structure is perpendicular to the flow direction, and the two plate surfaces which are located at the outermost sides in the circumferential direction of the folded plate structure are connected with the back edges of the tail edge wing plates (4). The angle between the gas flow direction at the outlet of the cooling channels (5) and the flow direction is 30-60 degrees. The cooling channels (5) are arranged on the two plate surfaces which are located at the outermost sides in the circumferential direction of the folded plate structure, and the angle between the gas flow direction at the outlet of the cooling channels (5) and the flow direction is greater than 90 degrees, so that a pair of cooling vortices (51) whose vorticity extends in the radial direction are formed on the back side of the folded plate structure. The flame stabilizer (1) further comprises a front impact baffle (16) which is arranged between the oil-gas mixing chamber (11) and the cooling gas chamber (12) and is provided with a plurality of impact gas holes, and a rear impact baffle (17) which is arranged on the front side of the back side plate (15) of the flame stabilizer (1) and is provided with a plurality of impact gas holes. The cooling channels (5) comprise cooling slits (52) and / or cooling holes (53).

2. The integrated flame holder having a tail edge cavity of claim 1, wherein, ​ 3. The integrated flame holder having a tail edge cavity of claim 1, wherein, ​ 4. The integrated flame holder having a tail edge cavity of claim 1, wherein, ​ ​ ​ 5. The integrated flame holder having a tail edge cavity of claim 1, wherein, ​

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