A device for increasing the turbine thrust of an aviation turbofan engine

Abstract

The present application belongs to the technical field of non-variable volume engine component design, and specifically relates to an aviation turbofan engine turbine thrust increase device, which is designed to ignite and organize combustion in the form of a radial stabilizer and a flame transfer groove, and mainly includes an outer casing, a confluence ring, an inner cone, a radial stabilizer, a fuel injection rod, an outer flame transfer groove section, a flame transfer groove section tail plate, an inner flame transfer groove section, a flame transfer groove section baffle and other components, which can effectively improve the ignition, flame transfer and combustion organization capabilities of the turbine thrust increase device.

Description

Technical Field

[0001] The present application belongs to the technical field of non-variable volume engine component design, and specifically relates to a device for increasing turbine thrust of an aviation turbofan engine. Background Art

[0002] A thrust increasing device is arranged behind the turbine of a high-performance small bypass ratio aviation turbofan engine to increase thrust. The thrust increasing device is mostly in the form of a radial stabilizer and a flame transfer groove, and uses an ignition nozzle or jet ignition for ignition and combustion organization. At present, the flame transfer groove mostly adopts a V-shaped or double V-shaped structure, and mainly relies on the trapped vortex formed in the recirculation zone behind the trailing edge to suck the evaporated oil and gas nearby for combustion organization, and is greatly affected by the thrust increasing device inlet temperature and fuel concentration distribution. In addition, the flame transfer groove and its radial stabilizer are partially in the inner casing. In order to protect them from the high temperature erosion of the inner casing, the design uses the outer casing airflow for cooling, resulting in poor ignition, flame transfer and combustion organization capabilities of the thrust increasing device behind the turbine on low temperature days and at the left boundary of the envelope.

[0003] This application is proposed in view of the above-mentioned technical defects.

[0004] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the invention

[0005] The purpose of the present application is to provide a device for increasing the turbine thrust of an aviation turbofan engine to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] A device for increasing turbine thrust of an aviation turbofan engine, comprising:

[0008] Outer receiver;

[0009] The confluence ring is arranged in the outer casing and forms an outer culvert with the outer casing;

[0010] The inner cone is arranged inside the confluence ring and forms an inner part between the confluence ring and the confluence ring;

[0011] A plurality of radial stabilizers are connected to the trailing edge of the confluence ring along the circumferential direction, the outer ends of which are connected to the outer casing, the inner ends of which point to the inner cone, the leading edges of which have an outer culvert inlet, and the side walls of which have a plurality of inner culvert outflow holes; wherein the outer culvert inlet is located in the outer culvert; and each inner culvert outflow hole is located in the inner culvert;

[0012] A plurality of fuel injection rods are arranged through the outer casing; each fuel injection rod extends into a corresponding radial stabilizer;

[0013] A plurality of outer flame transmission slot sections are located in the inner part, with the slot openings facing backwards; each outer flame transmission slot section is correspondingly connected between the side walls of two adjacent radial stabilizers and communicated with the interiors of the corresponding two stabilizers;

[0014] A plurality of flame transmission slot segment tail plates, each flame transmission slot segment tail plate correspondingly blocks an outer flame transmission slot segment slot opening, and has a plurality of mixing outlet holes and cooling outlet holes thereon;

[0015] Multiple inner flame transmission slot sections, each inner flame transmission slot section is arranged in a corresponding outer flame transmission slot section, the slot opening is connected to the corresponding flame transmission slot section tail plate, the interior is connected to each mixed gas outlet hole on the corresponding flame transmission slot section tail plate, one end is open, the end is facing the corresponding fuel injection hole on the fuel injection rod, and the other end is blocked;

[0016] Multiple flame transfer trough section baffles, each flame transfer trough section baffle is arranged in a corresponding inner flame transfer trough section, one end is connected to the corresponding flame transfer trough section tail plate, this end is located at the opening end of the corresponding inner flame transfer trough section, and the other end extends toward the blocked end of the corresponding flame transfer trough section and is tilted away from the corresponding flame transfer trough section tail plate.

[0017] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the trailing edge of the confluence ring has a plurality of notches;

[0018] Each radial stabilizer is correspondingly engaged in a notch.

[0019] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the cross-section of each outer flame transfer groove segment is V-shaped.

[0020] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each outer flame transfer slot segment and its corresponding flame transfer slot segment tail plate, inner flame transfer slot segment, and flame transfer slot segment deflector are close to the merging ring.

[0021] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the tail plate of each flame transfer slot segment is recessed in the corresponding outer flame transfer slot segment, and forms a flame transfer slot between the notch of the corresponding outer flame transfer slot segment.

[0022] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the two side edges of the tail plate of each flame transfer slot segment have backward folded edges, which are connected to the two side walls of the corresponding outer flame transfer slot segment with two backward folded edges.

[0023] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the opening density and / or size of the mixing outlet holes on the tail plate of each flame transfer groove segment gradually increases from the corresponding inner flame transfer groove segment blocked end to the open end.

[0024] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each cooling air outlet hole on the tail plate of each flame transfer slot section is divided into two rows, distributed close to both sides, and each mixing air outlet hole thereon is located between the two rows of cooling air outlet holes.

[0025] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the inner side wall of each inner flame transmission groove segment is partially inclined from the opening end to the blocking end, toward the corresponding flame transmission groove segment tail plate.

[0026] According to at least one embodiment of the present application, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each radial stabilizer has a supporting edge on both side walls, and the supporting edge has a supporting edge through hole;

[0027] Both ends of each outer flame transmission slot segment are clamped in the corresponding support edge, and the front edge portion has a flame transmission slot segment through hole;

[0028] The front edges of both ends of each inner flame transmission groove section are connected with ear pieces;

[0029] Each ear piece is arranged through the corresponding flame transmission slot section perforation and the supporting edge perforation, and a cushion block is sleeved thereon;

[0030] The parts of each ear piece that leak out of the outer flame transmission groove section are connected to the clamping blocks on both sides by flared bolts and nuts;

[0031] Each pad cooperates with the corresponding clamping block to clamp the corresponding outer flame transmission groove section and the supporting edge;

[0032] The shape of the side wall of each pad in contact with the corresponding outer flame transmission groove section is matched with the shape of the inner wall of the outer flame transmission groove section, and the opposite side walls are planes.

[0033] This application has at least the following beneficial technical effects:

[0034] Provided is an aviation turbofan engine turbine thrust increasing device, which is designed to ignite and organize combustion in the form of a radial stabilizer and a flame transfer groove, and mainly includes an outer casing, a confluence ring, an inner cone, a radial stabilizer, a fuel injection rod, an outer flame transfer groove section, a flame transfer groove section tail plate, an inner flame transfer groove section, a flame transfer groove section baffle and other components, and can effectively improve the ignition, flame transfer and combustion organization capabilities of the turbine thrust increasing device. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1It is a schematic diagram of a device for increasing the turbine thrust of an aviation turbofan engine provided in an embodiment of the present application;

[0036] Figure 2 yes Figure 1 A partial view of the

[0037] Figure 3 It is a schematic diagram of the appearance of a partial structure of a device for increasing the turbine thrust of an aviation turbofan engine provided in an embodiment of the present application;

[0038] Figure 4 yes Figure 3 A cross-sectional view of

[0039] Figure 5 It is a schematic diagram of the outer flame trough section provided in the embodiment of the present application;

[0040] Figure 6 It is a schematic diagram of the tail plate of the flame transmission slot section provided in an embodiment of the present application;

[0041] Figure 7 is a schematic diagram of an inner flame transmission slot section provided in an embodiment of the present application;

[0042] Figure 8 Schematic diagram of the baffle plate of the flame transfer slot section provided in the embodiment of the present application;

[0043] Fig. 9 It is a schematic diagram of the combination of the tail plate of the flame transmission groove section, the inner flame transmission groove section and its ear piece and the cushion block provided in the embodiment of the present application;

[0044] in:

[0045] 1-outer casing; 2-merging ring; 3-inner cone; 4-radial stabilizer; 5-injection rod; 6-outer flame transfer slot section; 7-flame transfer slot section tail plate; 8-inner flame transfer slot section; 9-flame transfer slot section baffle; 10-ear piece; 11-pad; 12-clamp block; 13-flared bolt and its nut.

[0046] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0047] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0048] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inside", "outside" and other words indicating orientation used in the description of this application are only used to indicate the relative direction or positional relationship, and do not imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, so it cannot be understood as a limitation on this application. The "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words "one", "one" or "the" used in the description of this application should not be understood as an absolute limitation on quantity, but should be understood as the existence of at least one. The similar words "including" or "comprising" used in the description of this application mean that the elements or objects appearing in front of the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0049] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installed", "connected", "connected" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0050] The following is combined with Figures 1 to 9 This application is described in further detail.

[0051] A device for increasing turbine thrust of an aviation turbofan engine, comprising:

[0052] Outer casing 1;

[0053] The confluence ring 2 is arranged in the outer casing 1 and forms an outer culvert with the outer casing 1;

[0054] The inner cone 3 is arranged in the confluence ring 2 and forms an inner part with the confluence ring 2;

[0055] A plurality of radial stabilizers 4 are connected to the trailing edge of the confluence ring 2 along the circumferential direction, the outer ends of which are connected to the outer casing 1, the inner ends of which are directed to the inner cone 3, the leading edges of which have an outer culvert inlet, and the side walls of which have a plurality of inner culvert outflow holes; wherein the outer culvert inlet is located in the outer culvert; and each inner culvert outflow hole is located in the inner culvert;

[0056] A plurality of spray rods 5 are arranged through the outer casing 1; each spray rod 5 extends into a corresponding radial stabilizer 4, and a nozzle thereon can extend from each inner outflow hole;

[0057] A plurality of outer flame transmission slot sections 6 are located in the inner part, with the slot opening facing backwards; each outer flame transmission slot section 6 is connected between the side walls of two adjacent radial stabilizers 4 and communicates with the interiors of the corresponding two stabilizers 4;

[0058] A plurality of flame transmission slot segment tail plates 7, each flame transmission slot segment tail plate 7 correspondingly blocks a slot opening of an outer flame transmission slot segment 6, and has a plurality of mixing outlet holes and cooling outlet holes thereon;

[0059] A plurality of inner flame transmission slot sections 8, each inner flame transmission slot section 8 is arranged in a corresponding outer flame transmission slot section 6, the slot opening is connected to the corresponding flame transmission slot section tail plate 7, the interior is connected to each mixed gas outlet hole on the corresponding flame transmission slot section tail plate 7, one end is open, the end is facing the corresponding fuel injection hole on the fuel injection rod 5, and the other end is blocked;

[0060] There are multiple flame transfer trough section baffles 9, each flame transfer trough section baffle 9 is arranged in a corresponding inner flame transfer trough section 8, one end is connected to the corresponding flame transfer trough section tail plate 7, this end is located at the opening end of the corresponding inner flame transfer trough section 8, and the other end extends toward the blocked end of the corresponding flame transfer trough section 8 and is tilted away from the corresponding flame transfer trough section tail plate 7.

[0061] The aviation turbofan engine turbine thrust increasing device disclosed in the above-mentioned embodiment is designed to ignite and organize combustion in the form of a radial stabilizer and a flame transfer groove. When the aviation turbofan engine is working, fuel can be sprayed into the radial stabilizer 4 through each injection rod 5, and then sprayed into the inner part through the inner outflow hole on the side wall of the radial stabilizer 4, atomized and evaporated in the inner part, mixed with the inner airflow to form an oil-gas mixture, and then enter the trailing edge of the radial stabilizer 4 to form a reflow zone for ignition.

[0062] The aviation turbofan engine turbine thrust increasing device disclosed in the above-mentioned embodiment can introduce an outer duct airflow into the radial stabilizer 4 through the outer duct inflow hole on the radial stabilizer 4 when the aviation turbofan engine is working. The outer duct airflow entering the radial stabilizer 4 can be preliminarily mixed with the fuel in the radial stabilizer 4, and then sprayed into the inner duct from the inner duct outflow hole on the side wall of the radial stabilizer 4 to ensure the reliability of ignition of the turbine thrust increasing device, and can use the outer duct air to efficiently cool the radial stabilizer 4 and its injection rod 5 to protect the radial stabilizer 4 and its injection rod 5 from high-temperature ablation.

[0063] The above-mentioned embodiment discloses a device for increasing the turbine thrust of an aviation turbofan engine. When the aviation turbofan engine is working, part of the fuel entering the radial stabilizer 4 can enter the inner flame transfer groove section 8. At the same time, part of the outer flow entering the radial stabilizer 4 enters the inner flame transfer groove section 8. The fuel and the outer flow entering the inner flame transfer groove section 8 are mixed while flowing. After flowing to the blocked end of the inner flame transfer groove section 8, they are deflected toward the gap between the deflector 9 of the flame transfer groove section and the tail plate 7 of the flame transfer groove section, and then flow out from the mixing outlet hole on the tail plate 7 of the flame transfer groove section, and are sprayed into the notch of the outer flame transfer groove section 6 to form a reflow zone for flame transfer combustion.

[0064] The aviation turbofan engine turbine thrust increasing device disclosed in the above-mentioned embodiment enables the fuel to be pre-mixed with the outer bypass airflow through the design of the inner flame transfer groove section 8 and the flame transfer groove section tail plate 7, and is designed with the flame transfer groove section baffle 9 to increase the mixing stroke, so that the fuel can be fully mixed with the outer bypass airflow in a limited space, thereby ensuring the flame transfer and combustion organization ability of the turbine thrust increasing device.

[0065] In the aviation turbofan engine turbine thrust increasing device disclosed in the above-mentioned embodiment, the flame transfer groove section baffle 9 is designed to be located at the open end of the inner flame transfer groove section 8, one end of which is connected to the flame transfer groove section tail plate 7, and the other end extends toward the blocked end of the flame transfer groove section 8, and is tilted away from the corresponding flame transfer groove section tail plate 7. This can gradually shrink the flow area of ​​the fuel and the outer duct airflow entering the inner flame transfer groove section 8 along the mixing stroke, and gradually increase the flow rate, thereby promoting sufficient mixing of the fuel and the outer duct airflow.

[0066] The above-mentioned embodiment discloses a device for increasing the turbine thrust of an aviation turbofan engine. When the aviation turbofan engine is working, part of the external airflow entering the radial stabilizer 4 will enter the outer flame transfer slot section 6, cool the outer flame transfer slot section 6, the flame transfer slot section tail plate 7, the inner flame transfer slot section 8 and its flame transfer slot section tail plate 7, and then flow out through the cooling air outlet holes on the flame transfer slot section tail plate 7 to blow away the flame behind the flame transfer slot section tail plate 7, avoid wall burning, and avoid high-temperature ablation of the flame transfer slot section tail plate 7.

[0067] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the trailing edge of the merge ring 2 has a plurality of notches;

[0068] Each radial stabilizer 4 is correspondingly engaged in a notch.

[0069] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the cross-section of each outer flame transfer slot segment 6 is V-shaped.

[0070] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each outer flame transmission slot segment 6 and its corresponding flame transmission slot segment tail plate 7, inner flame transmission slot segment 8, and flame transmission slot segment baffle 9 are arc-shaped, concentric with the outer casing 1, the merging ring 2, and the inner cone 3, and are distributed close to the merging ring 2, that is, close to the inner outer area, so as to ensure the flame transmission and combustion organization ability of the turbine thrust increasing device.

[0071] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each flame transfer slot segment tail plate 7 is recessed in the corresponding outer flame transfer slot segment 6, and a flame transfer slot is formed between the corresponding outer flame transfer slot segment 6 and the slot, so that a larger stable reflow zone can be formed behind the slot of the outer flame transfer slot segment 6.

[0072] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the two side edges of the tail plate 7 of each flame transfer slot segment have backward folded edges, which are connected to the two side walls of the corresponding outer flame transfer slot segment 6 with two backward folded edges.

[0073] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the opening density and / or size of the mixed air outlet holes on the tail plate 7 of each flame transfer groove segment gradually increases from the closed end to the open end of the corresponding inner flame transfer groove segment 8.

[0074] In the aviation turbofan engine turbine thrust increasing device disclosed in the above-mentioned embodiment, the fuel and the outer duct airflow entering the inner flame transfer groove section 8 flow to the blocked end of the inner flame transfer groove section 8, and are deflected toward the gap between the flame transfer groove section baffle 9 and the flame transfer groove section tail plate 7. Then, the static pressure gradually decreases along the mixing stroke. The opening density and / or size of the mixing air holes on the flame transfer groove section tail plate 7 are designed to gradually increase from the corresponding blocked end of the inner flame transfer groove section 8 to the open end. This can promote the fuel and the outer duct airflow flowing out of the mixing air holes to be mixed evenly at all locations, thereby ensuring the flame transmission and combustion organization capability of the turbine thrust increasing device.

[0075] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each cooling air outlet hole on each flame transfer slot section tail plate 7 is divided into two rows, respectively distributed close to the two sides, and each mixing air outlet hole thereon is located between the two rows of cooling air outlet holes. The external airflow flowing out from the two rows of cooling air outlet holes can efficiently blow away the flame from the upper and lower sides, so as to prevent the flame transfer slot section tail plate 7 from being burned by high temperature.

[0076] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, the inner wall of each inner flame transfer groove section 8 is partially inclined from the open end to the blocked end, toward the corresponding flame transfer groove section tail plate 7, so that the fuel entering the inner flame transfer groove section 8 can hit the inclined wall surface at this location and break into pieces, and the inclination at this location can avoid increasing turbulence and enhance the mixing effect of the fuel and the external airflow.

[0077] In some optional embodiments, in the above-mentioned aviation turbofan engine turbine thrust increasing device, each radial stabilizer 4 has a supporting edge on both side walls, and the supporting edge has a supporting edge through hole;

[0078] Both ends of each outer flame transmission slot segment 6 are stuck in the corresponding support edge, and the front edge portion has a flame transmission slot segment perforation;

[0079] The front edges of both ends of each inner flame transmission groove section 8 are connected with ear pieces 10;

[0080] Each ear piece 10 is arranged through the corresponding flame transmission slot section perforation and the supporting edge perforation, and a cushion block 11 is sleeved thereon;

[0081] The parts of each ear piece 10 that are exposed outside the flame transmission groove section 6 are connected to the clamping block 12 on both sides by the expansion bolt and its nut 13;

[0082] Each cushion block 11 cooperates with the corresponding clamping block 12 to clamp the corresponding outer flame transmission groove section 6 and the supporting edge;

[0083] The shape of the side wall of each pad 11 in contact with the corresponding outer flame transmission groove section 6 is adapted to the shape of the inner wall of the outer flame transmission groove section 6, and the opposite side wall is a plane;

[0084] The top of the bolt in the expanded bolt and its nut 13 is an expanded structure. After matching with the nut, the top needs to be expanded with an expanding pliers, and the end of the nut has a self-locking structure to ensure the reliability of the bolt and nut matching;

[0085] The wall temperature of the outer flame transfer groove section 6 is lower, while the wall temperature of the inner flame transfer groove section 8 is higher. The inner flame transfer groove section 8 has a larger amount of expansion backward, and is connected by means of the cooperation of structures such as the ear piece 10, the gasket 11, the clamping block 12, the flared bolt and its nut 13. This can effectively coordinate the problem of the large difference in expansion amount caused by the inconsistent wall temperature between the outer flame transfer groove section 6 and the inner flame transfer groove section 8.

[0086] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0087] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A device for increasing the turbine thrust of an aviation turbofan engine. It is characterized in that include: Outer casing (1); A confluence ring (2) is arranged inside the outer casing (1) and forms an outer culvert with the outer casing (1); The inner cone (3) is arranged inside the confluence ring (2) and forms an inner portion with the confluence ring (2); A plurality of radial stabilizers (4) are connected to the trailing edge of the confluence ring (2) along the circumferential direction, the outer ends of which are connected to the outer casing (1), the inner ends of which are directed toward the inner cone (3), the leading edges of which have an outer culvert inlet, and the side walls of which have a plurality of inner culvert outflow holes; wherein the outer culvert inlet is located in the outer culvert; and each inner culvert outflow hole is located in the inner culvert; A plurality of fuel injection rods (5) are arranged to penetrate the outer casing (1); each fuel injection rod (5) extends into a corresponding radial stabilizer (4); A plurality of outer flame transmission slot sections (6) are located in the inner portion, with the slot openings facing backwards; each outer flame transmission slot section (6) is connected between the side walls of two adjacent radial stabilizers (4) and is in communication with the interiors of the corresponding two stabilizers (4); A plurality of flame transmission slot segment tail plates (7), each flame transmission slot segment tail plate (7) correspondingly blocks a slot opening of an outer flame transmission slot segment (6), and having a plurality of mixing air outlet holes and cooling air outlet holes thereon; A plurality of inner flame transmission slot sections (8), each inner flame transmission slot section (8) being arranged in a corresponding outer flame transmission slot section (6), the slot opening being connected to the corresponding flame transmission slot section tail plate (7), the interior of the slot section being connected to each mixing gas outlet hole on the corresponding flame transmission slot section tail plate (7), one end of the slot section being open and facing an oil injection hole on the corresponding oil injection rod (5), and the other end being blocked; A plurality of flame transmission trough segment baffles (9), each flame transmission trough segment baffle (9) being arranged in a corresponding inner flame transmission trough segment (8), one end of which is connected to the corresponding flame transmission trough segment tail plate (7), the end being located at the opening end of the corresponding inner flame transmission trough segment (8), and the other end extending toward the blocking end of the corresponding flame transmission trough segment (8) and tilting away from the corresponding flame transmission trough segment tail plate (7).

2. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that The trailing edge of the confluence ring (2) has a plurality of notches; Each radial stabilizer (4) is correspondingly engaged in a notch.

3. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that The cross section of each outer flame transmission groove section (6) is V-shaped.

4. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that Each outer flame transfer slot segment (6) and its corresponding flame transfer slot segment tail plate (7), inner flame transfer slot segment (8), and flame transfer slot segment baffle plate (9) are close to the converging ring (2).

5. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that Each flame transmission groove section tail plate (7) is sunken in the corresponding outer flame transmission groove section (6), and forms a flame transmission groove with the corresponding notch of the outer flame transmission groove section (6).

6. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 5, It is characterized in that The two side edges of the tail plate (7) of each flame transmission groove section have rearward folded edges, and are connected to the two side walls of the corresponding outer flame transmission groove section (6) through the two rearward folded edges.

7. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that The opening density and / or size of the mixed gas outlet holes on the tail plate (7) of each flame transmission groove section gradually increases from the blocked end to the open end of the corresponding inner flame transmission groove section (8).

8. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that The cooling air outlet holes on the tail plate (7) of each flame transmission slot section are divided into two rows, respectively distributed close to the two sides, and the mixing air outlet holes thereon are located between the two rows of cooling air outlet holes.

9. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that The inner side wall of each inner flame transmission groove section (8) is partially inclined from the opening end to the blocking end, toward the corresponding flame transmission groove section tail plate (7).

10. The device for increasing the turbine thrust of an aviation turbofan engine according to claim 1, It is characterized in that Each radial stabilizer (4) has supporting edges on both side walls, and the supporting edges have supporting edge through holes; Both ends of each outer flame transmission groove segment (6) are clamped in the corresponding support edge, and the front edge portion has a flame transmission groove segment through hole; The front edges of both ends of each inner flame transmission groove section (8) are connected with ear pieces (10); Each ear piece (10) is passed through the corresponding flame transmission slot section perforation and the supporting edge perforation, and a cushion block (11) is sleeved thereon; The parts of each ear piece (10) protruding from the outer flame transmission groove section (6) are connected to the clamping blocks (12) on both sides by flared bolts and nuts (13); Each cushion block (11) cooperates with a corresponding clamping block (12) to clamp the corresponding outer flame transmission groove section (6) and the supporting edge; The shape of the side wall of each cushion block (11) in contact with the corresponding outer flame transmission groove section (6) matches the shape of the inner wall of the outer flame transmission groove section (6), and the opposite side walls are flat.

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