A hydrogen-fired aircraft engine afterburner

Abstract

A hydrogen-fueled aircraft engine afterburner combustion chamber comprises: an annular outer wall; a converging ring, forming an outer conduit with the annular outer wall, and having a plurality of circumferentially distributed air bleed holes on the side wall; an inner cone, forming an inner conduit with the converging ring; a plurality of outer conduit hydrogen fuel nozzle rods, inserted into the outer conduit; a plurality of inner conduit hydrogen fuel nozzle rods, inserted into the outer conduit from each outer conduit hole, and matched with the gaps between the outer conduit holes; a plurality of inner conduit nozzle protective covers, arranged in the inner conduit, covering the outer periphery of each inner conduit hydrogen fuel nozzle rod, and having a plurality of injection holes on the outer wall; a main annular stabilizer, arranged behind the converging ring; an outer ring annular stabilizer, located in the outer conduit area; a plurality of outer conduit radial stabilizers, connected between the main annular stabilizer and the outer ring annular stabilizer; an inner ring annular stabilizer, located in the inner conduit area; a plurality of inner conduit radial stabilizers, connected between the main annular stabilizer and the inner ring annular stabilizer; an ignition nozzle, extending into the main annular stabilizer.

Description

Technical Field

[0001] The present application belongs to the technical field of design of afterburner combustion chambers for hydrogen-fired aircraft engines, and specifically relates to a afterburner combustion chamber for hydrogen-fired aircraft engines. Background Art

[0002] Hydrogen-fueled aircraft engines use hydrogen as fuel, achieving clean emissions. In these engines, hydrogen fuel burns in the main combustion chamber, generating high-temperature gases that drive the turbine. Due to limited turbine cooling capacity, large amounts of air are required for cooling. This creates a significant amount of unused oxygen in the airflow behind the turbine. Furthermore, the bypass airflow also contains a significant amount of fresh air, enabling the installation of an afterburner to increase thrust.

[0003] Currently, the afterburner design of hydrogen-powered aircraft engines is typically modeled after the afterburner design of gasoline-powered aircraft engines. These afterburners typically utilize a V-shaped stabilizer, with an annular flame stabilizer and radial flame transmission as the primary combustion mechanism. Fuel injected into the afterburner requires a certain distance for atomization and evaporation. Once the fuel is atomized, it enters the rear of the stabilizer for combustion. Hydrogen fuel has a wide combustion boundary, low ignition energy, and high combustion energy. If the afterburner design of a gasoline-powered aircraft engine is directly replaced with a hydrogen-powered afterburner, the hydrogen fuel injected into the afterburner will be directly vaporized, resulting in spontaneous combustion, ablation of the stabilizer, and oscillation combustion, damaging the afterburner. Furthermore, the hydrogen fuel injected into the afterburner has a low degree of mixing with the airflow, hindering rapid combustion.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0005] The purpose of the present application is to provide a hydrogen-fired aircraft engine afterburner to overcome or alleviate at least one of the existing technical deficiencies.

[0006] The technical solution of this application is:

[0007] A hydrogen-fired aircraft engine afterburner combustion chamber, comprising:

[0008] annular outer wall;

[0009] The confluence ring is arranged inside the annular outer wall to form an outer culvert with the annular outer wall, and has a plurality of air inlet holes distributed along the circumferential direction on the side wall;

[0010] The inner cone is arranged in the confluence ring and forms an inner portion with the confluence ring;

[0011] A plurality of outer culvert hydrogen fuel spray bars are arranged circumferentially through the annular outer wall and inserted into the outer culvert;

[0012] Multiple inner hydrogen fuel spray rods are arranged through the annular outer wall, inserted into the outer culvert from each outer culvert air inlet hole, and matched with the gaps between the outer culvert air inlet holes;

[0013] Multiple internal nozzle protection covers are set in the internal structure, covering the outer periphery of each internal hydrogen fuel nozzle rod, the interior of which is connected to the air bleed hole, and the outer wall of which has multiple injection holes;

[0014] The main annular stabilizer is located behind the confluence ring;

[0015] The outer ring stabilizer is sleeved on the outer periphery of the main ring stabilizer and is located in the outer area;

[0016] A plurality of outer radial stabilizers are connected circumferentially between the main annular stabilizer and the outer ring annular stabilizer;

[0017] The inner ring stabilizer is set inside the main ring stabilizer and is located in the inner region;

[0018] Multiple internal radial stabilizers are connected circumferentially between the main annular stabilizer and the inner ring annular stabilizer;

[0019] The ignition nozzle is arranged through the annular outer wall and extends into the main annular stabilizer.

[0020] According to at least one embodiment of the present application, in the above-mentioned hydrogen-fired aircraft engine afterburner, each outer clad hydrogen fuel nozzle bar is closely matched with the main annular stabilizer, the outer ring annular stabilizer, and the outer clad radial stabilizer, and is no more than 60 mm away from the trailing edge of the main annular stabilizer, the outer ring annular stabilizer, and the outer clad radial stabilizer;

[0021] Each internal hydrogen fuel spray rod is closely matched with the main annular stabilizer, the inner ring annular stabilizer and the internal radial stabilizer, and the distance from the trailing edge of the main annular stabilizer, the inner ring annular stabilizer and the internal radial stabilizer is no more than 60mm.

[0022] According to at least one embodiment of the present application, in the above-mentioned hydrogen-fired aircraft engine afterburner, the outer ring annular stabilizer and the inner ring annular stabilizer are located on the rear side of the main annular stabilizer, and each outer radial stabilizer and inner radial stabilizer are tilted backward.

[0023] According to at least one embodiment of the present application, in the above-mentioned hydrogen-fired aircraft engine afterburner, the cross-sections of the outer annular stabilizer, the outer radial stabilizer, the inner annular stabilizer, and the inner radial stabilizer are V-shaped.

[0024] According to at least one embodiment of the present application, in the above-mentioned hydrogen-fired aircraft engine afterburner, the multiple external hydrogen fuel spray bars and internal hydrogen fuel spray bars are multi-point spray bars, the nozzles thereon have a large distribution density, and the distance between adjacent nozzles does not exceed 1 cm.

[0025] According to at least one embodiment of the present application, in the above-mentioned hydrogen-fired aircraft engine afterburner, there are two ignition nozzles, and the angle between the two ignition nozzles is less than 180°.

[0026] According to at least one embodiment of the present application, the above-mentioned hydrogen-fired aircraft engine afterburner further includes:

[0027] The anti-vibration and heat-insulating screen is arranged on the inner side of the annular outer wall and at the rear edge of the annular outer wall. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a partial cross-sectional view of the afterburner chamber of a hydrogen-fired aircraft engine provided by an embodiment of the present application;

[0029] Figure 2 This is a rear view of the afterburner chamber of a hydrogen-fired aircraft engine provided by an embodiment of the present application;

[0030] Figure 3 Schematic diagram of an external hydrogen fuel nozzle in the afterburner of a hydrogen-fired aircraft engine provided by an embodiment of the present application;

[0031] Figure 4 This is a schematic diagram of a hydrogen fuel nozzle in the afterburner of a hydrogen-fired aircraft engine provided by an embodiment of the present application;

[0032] in:

[0033] 1- annular outer wall; 2- confluence ring; 3- inner cone; 4- outer hydrogen fuel nozzle; 5- inner hydrogen fuel nozzle; 6- inner nozzle shield; 7- main annular stabilizer; 8- outer annular stabilizer; 9- outer radial stabilizer; 10- inner annular stabilizer; 11- inner radial stabilizer; 12- ignition nozzle;

[0034] A-external connotation;

[0035] B-Connotation.

[0036] 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 should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0037] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0038] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0039] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" 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 or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0040] The following is combined with Figures 1 to 4 This application is described in further detail.

[0041] A hydrogen-fired aircraft engine afterburner, such as Figure 1-2 Shown, including:

[0042] annular outer wall 1;

[0043] The confluence ring 2 is arranged inside the annular outer wall 1, forming an outer duct A with the annular outer wall 1, and has a plurality of air inlet holes distributed along the circumferential direction on the side wall;

[0044] The inner cone 3 is arranged inside the merging ring 2 and forms an inner portion B between the inner cone 3 and the merging ring 2;

[0045] A plurality of outer containment hydrogen fuel spray bars 4 are arranged circumferentially through the annular outer wall 1 and inserted into the outer containment A;

[0046] Multiple inner hydrogen fuel spray rods 5 are arranged through the annular outer wall 1, inserted into the outer culvert A from each outer culvert air inlet hole, and matched with the gaps between the outer culvert air inlet holes;

[0047] Multiple internal nozzle protection covers 6 are set in the internal part B, covering the outer periphery of each internal hydrogen fuel nozzle rod 5, the interior of which is connected to the air bleed hole, and the outer wall has multiple injection holes;

[0048] The main annular stabilizer 7 is arranged behind the merging ring 2;

[0049] The outer ring stabilizer 8 is sleeved on the outer periphery of the main ring stabilizer 7 and is located in the outer circumference A area;

[0050] A plurality of outer radial stabilizers 9 are circumferentially connected between the main annular stabilizer 7 and the outer ring annular stabilizer 8;

[0051] The inner ring stabilizer 10 is provided inside the main ring stabilizer 7 and is located in the inner region B;

[0052] A plurality of internal radial stabilizers 11 are connected circumferentially between the main annular stabilizer 7 and the inner ring annular stabilizer 10;

[0053] The ignition nozzle 12 is provided through the annular outer wall 1 and extends into the main annular stabilizer 7 .

[0054] For the hydrogen-fired aircraft engine afterburner chamber disclosed in the above embodiment, it can be understood by those skilled in the art that hydrogen can be injected into the outer liner A through the outer liner hydrogen fuel nozzle rod 4 to mix with the outer liner airflow, and hydrogen can be injected into the inner liner B through the inner liner hydrogen fuel nozzle rod 5 to mix with the inner liner airflow, and the mixed airflows flowing out of the outer liner A and the inner liner B meet at the trailing edge of the merging ring 2, a main annular stabilizer 7 is provided behind the merging ring 2, an outer ring annular stabilizer 8 is provided in the outer liner A area, and an inner ring stabilizer 9 is provided in the inner liner B area. The inner ring annular stabilizer 10, and the outer ring annular stabilizer 8, the inner ring annular stabilizer 10 and the main annular stabilizer 7 are connected with the outer radial stabilizer 9 and the inner radial stabilizer 11, so as to extend into the main annular stabilizer 7. The ignition nozzle 12 can easily ignite the mixed airflow flowing out of the outer A and the inner B, and can utilize the outer radial stabilizer 9, the outer ring annular stabilizer 8, the inner radial stabilizer 11 and the inner ring annular stabilizer 10 to carry out radial and circumferential flame transmission and continuous flame, thereby carrying out highly efficient organized combustion.

[0055] As for the hydrogen-fired aircraft engine afterburner combustion chamber disclosed in the above embodiment, it can be understood by those skilled in the art that its design makes full use of the unused oxygen in the inner airflow and the fresh air in the outer airflow to organize combustion respectively, which can improve the mixing degree of hydrogen fuel and the airflow in the combustion chamber, and is conducive to the rapid development of combustion. Since the temperature of the inner airflow is relatively high, an inner nozzle protective cover 6 is provided on the outer side of each inner hydrogen fuel nozzle rod 5, and the outer airflow is introduced through the air bleed hole opened on the confluence ring 2 to locally cool the hydrogen ejected from the inner hydrogen fuel nozzle rod 5, so as to avoid the hydrogen being directly injected into the inner B to cause spontaneous combustion, ablation of the stabilizer, and oscillation combustion. Burning, damaging the afterburner. In actual design, the nozzle on the inner hydrogen fuel nozzle rod 5 can be designed to be inserted into the upper part of the jet hole of the inner nozzle protective cover 6. The hydrogen can be directly sprayed into the inner B through the nozzle. The outer airflow introduced into the inner nozzle protective cover 6 from the air bleed hole can be ejected through the remaining jet holes to locally cool the hydrogen. The nozzle on the inner hydrogen fuel nozzle rod 5 can also be designed to be in the inner nozzle protective cover 6. The hydrogen ejected from the nozzle is mixed with the outer airflow introduced into the inner nozzle protective cover 6 from the air bleed hole, and then ejected into the inner B through the jet hole on the inner nozzle protective cover 6, so as to achieve local cooling of the hydrogen.

[0056] In some optional embodiments, in the above-mentioned hydrogen-fired aircraft engine afterburner, each outer cladding hydrogen fuel nozzle bar 4 is closely matched with the main annular stabilizer 7, the outer ring annular stabilizer 8, and the outer cladding radial stabilizer 9, and the distance from the trailing edge of the main annular stabilizer 7, the outer ring annular stabilizer 8, and the outer cladding radial stabilizer 9 is no more than 60 mm;

[0057] Each internal hydrogen fuel spray bar 5 is closely matched with the main annular stabilizer 7, the inner ring annular stabilizer 10, and the internal radial stabilizer 11, and the distance from the trailing edge of the main annular stabilizer 7, the inner ring annular stabilizer 10, and the internal radial stabilizer 11 is no more than 60 mm.

[0058] As for the hydrogen-fired aircraft engine afterburner chamber disclosed in the above embodiment, those skilled in the art will understand that the design of the outer hydrogen fuel nozzle rods 4, the inner hydrogen fuel nozzle rods 5 and the stabilizer is closely matched at a distance of no more than 60 mm. This can ensure that the hydrogen injected into the afterburner chamber by the outer hydrogen fuel nozzle rods 4, the inner hydrogen fuel nozzle rods 5 can be fully gasified, thereby preventing the hydrogen injected into the afterburner chamber by the outer hydrogen fuel nozzle rods 4, the inner hydrogen fuel nozzle rods 5 from spontaneously combusting before reaching the stabilizer, ablating the stabilizer, causing oscillating combustion, and damaging the afterburner. In addition, the length of the afterburner chamber and the aircraft engine as a whole can be shortened, the weight of the aircraft engine can be reduced, and the thrust-to-weight ratio of the aircraft engine can be improved.

[0059] In some optional embodiments, in the above-mentioned hydrogen-fired aircraft engine afterburner, the outer ring annular stabilizer 8 and the inner ring annular stabilizer 10 are located on the rear side of the main annular stabilizer 7, and each outer radial stabilizer 9 and inner radial stabilizer 11 are tilted backward.

[0060] Although the propagation speed of hydrogen combustion is relatively fast, the airflow velocity in the afterburner is even higher. In the afterburner of the hydrogen-fired aircraft engine disclosed in the above embodiment, each outer radial stabilizer 9 and inner radial stabilizer 11 is designed to be tilted backward, which can adapt to the differences in the propagation speed of hydrogen combustion and the airflow velocity in the afterburner, and promote efficient organized combustion in the afterburner.

[0061] In some optional embodiments, in the above-mentioned hydrogen-fired aircraft engine afterburner, the cross-sections of the outer annular stabilizer 8, the outer radial stabilizer 9, the inner annular stabilizer 10, and the inner radial stabilizer 11 are V-shaped.

[0062] In some optional embodiments, in the above-mentioned hydrogen-fired aircraft engine afterburner, the plurality of outer hydrogen fuel spray bars 4 and inner hydrogen fuel spray bars 5 are multi-point spray bars, the nozzles thereon have a large distribution density, and the spacing between adjacent nozzles does not exceed 1 cm, such as Figure 3-4 As shown, the multi-point injection method can achieve rapid and uniform mixing of the ejected hydrogen and the airflow in the afterburner, promoting rapid combustion of the hydrogen in the afterburner.

[0063] In some optional embodiments, in the above-mentioned hydrogen-fired aircraft engine afterburner, there are two ignition nozzles 12, and the angle between the two ignition nozzles 12 is less than 180°.

[0064] In some optional embodiments, the above-mentioned hydrogen-fired aircraft engine afterburner further includes:

[0065] The anti-vibration and heat insulation screen 13 is arranged on the inner side of the annular outer wall 1 and is located at the rear edge of the annular outer wall 1. Part of the external airflow will flow into the space between the anti-vibration and heat insulation screen 13 and the rear edge of the annular outer wall 1 to cool the annular outer wall 1, avoid ablation, and suppress oscillating combustion.

[0066] 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. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0067] 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 replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A hydrogen-fired aircraft engine afterburner, characterized in that: include: annular outer wall (1); A confluence ring (2) is arranged inside the annular outer wall (1) to form an outer culvert (A) with the annular outer wall (1), and has a plurality of air inlet holes distributed along the circumferential direction on its side wall; An inner cone (3) is disposed within the merging ring (2) and forms an inner concavity (B) with the merging ring (2); A plurality of outer cladding hydrogen fuel spray bars (4) are arranged circumferentially through the annular outer wall (1) and inserted into the outer cladding (A); A plurality of inner hydrogen fuel spray rods (5) are arranged through the annular outer wall (1), inserted into the outer culvert (A) from the respective outer culvert air inlet holes, and matched with the gaps between the outer culvert air inlet holes; A plurality of internal nozzle protection covers (6) are provided in the internal part (B), covering the outer periphery of each internal hydrogen fuel spray rod (5), the interior of which is connected to the air bleed hole, and the outer wall of which has a plurality of spray holes; A main annular stabilizer (7), arranged behind the merging ring (2); The outer ring stabilizer (8) is sleeved on the outer periphery of the main ring stabilizer (7) and is located in the outer cladding (A) area; A plurality of outer radial stabilizers (9) are connected circumferentially between the main annular stabilizer (7) and the outer ring annular stabilizer (8); An inner ring stabilizer (10) is provided inside the main ring stabilizer (7) and is located in the inner ring (B) region; A plurality of internal radial stabilizers (11) are connected circumferentially between the main annular stabilizer (7) and the inner ring annular stabilizer (10); The ignition nozzle (12) is arranged through the annular outer wall (1) and extends into the main annular stabilizer (7).

2. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: Each outer cladding hydrogen fuel spray bar (4) is closely matched with the main annular stabilizer (7), the outer ring annular stabilizer (8), and the outer cladding radial stabilizer (9), and the distance from the trailing edge of the main annular stabilizer (7), the outer ring annular stabilizer (8), and the outer cladding radial stabilizer (9) is no more than 60 mm; Each internal hydrogen fuel spray rod (5) is closely matched with the main annular stabilizer (7), the inner annular stabilizer (10), and the internal radial stabilizer (11), and the distance from the trailing edge of the main annular stabilizer (7), the inner annular stabilizer (10), and the internal radial stabilizer (11) is no more than 60 mm.

3. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: The outer ring stabilizer (8) and the inner ring stabilizer (10) are located at the rear side of the main ring stabilizer (7), and each outer radial stabilizer (9) and inner radial stabilizer (11) are tilted backward.

4. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: The cross sections of the outer ring stabilizer (8), the outer radial stabilizer (9), the inner ring stabilizer (10) and the inner radial stabilizer (11) are V-shaped.

5. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: The plurality of outer hydrogen fuel spray bars (4) and inner hydrogen fuel spray bars (5) form multi-point spray bars, the nozzles thereon have a relatively large distribution density, and the spacing between adjacent nozzles does not exceed 1 cm.

6. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: There are two ignition nozzles (12), and the angle between the two ignition nozzles (12) is less than 180 degrees.

7. The hydrogen-fired aircraft engine afterburner according to claim 1, characterized in that: Also includes: The anti-vibration and heat-insulating screen (13) is arranged on the inner side of the annular outer wall (1) and is located at the rear edge of the annular outer wall (1).

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