Austausch der schrauben in der luftfahrzeugtriebwerk nachbrenn- k

Abstract

A kind of afterburner in aero-engine, comprising: outer casing;Converging ring, be arranged in outer casing;Inner cone, be arranged in converging ring, hollow structure, rear end has multiple circumferentially distributed flame holes;Multiple support plates, are supported between converging ring, inner cone along the circumference;Precombustion chamber, be arranged in inner cone, for sandwich structure, inner wall is corrugated structure and has multiple air bleed holes, front end has oil injection port, rear end is shaped with multiple flame pipes;Each flame pipe is connected to inner cone, and the outlet of each flame pipe is communicated with a flame hole corresponding;Ignition electrode, pass through outer casing, converging ring, inner cone and a support plate are arranged, and ignition end is inserted into precombustion chamber;Air bleed pipe, pass through outer casing, converging ring, inner cone and a support plate are arranged, and outlet end is communicated to the sandwich of precombustion chamber;Oil injection nozzle, pass through outer casing, converging ring, inner cone and a support plate are arranged, and oil injection end is inserted into oil injection port.

Description

Technical Field

[0001] This application belongs to the field of afterburner design technology in aero-engines, and specifically relates to an afterburner in an aero-engine. Background Technology

[0002] Currently, afterburners in aircraft engines are mostly designed with concave cavity structures to form a recirculation zone, and ignition electrodes are placed at the boundary layer of the recirculation zone for direct ignition. This technical solution suffers from poor ignition reliability when the inlet airflow angle of the afterburner reaches 35° or more, due to the influence of a strong and complex flow field. Furthermore, the inlet temperature of the afterburner is as high as 1300K, requiring cooling protection. The flow path design and cooling design within the afterburner are complex. In addition, it is difficult to meet the requirements of lightweight, high efficiency and undetectability.

[0003] This application is made in view of the aforementioned technical deficiencies.

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

[0005] The purpose of this application is to provide an afterburner for an aircraft engine to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] An afterburner chamber in an aircraft engine includes:

[0008] Outer casing;

[0009] The confluence ring is installed inside the outer casing;

[0010] The inner cone, set within the confluence ring, is a hollow structure with multiple circumferentially distributed flame holes at the rear end.

[0011] Multiple support plates are circumferentially supported between the confluence ring and the inner cone;

[0012] The pre-combustion chamber is set inside the inner cone and has a sandwich structure. The inner wall has a corrugated structure and multiple air intake holes. The front end has an oil injection port and the rear end has multiple flame tubes. Each flame tube is connected to the inner cone and each flame tube outlet is connected to a corresponding flame hole.

[0013] The ignition nozzle is installed through the outer casing, confluence ring, inner cone, and a support plate, with the ignition end extending into the pre-combustion chamber;

[0014] The exhaust pipe runs through the outer casing, the confluence ring, the inner cone, and a support plate, with the exhaust end connected to the pre-combustion chamber interlayer.

[0015] The fuel injector is installed through the outer casing, the confluence ring, the inner cone, and a support plate, with the injection end extending into the fuel injection port.

[0016] According to at least one embodiment of this application, in the afterburner chamber of the above-mentioned aero-engine, an air bleed pipe mounting seat is formed on the upper outer wall of the pre-combustion chamber to connect the air bleed pipe;

[0017] An ignition nozzle mounting base is formed on the outer wall of the pre-combustion chamber to connect the ignition nozzle.

[0018] According to at least one embodiment of this application, in the afterburner chamber of the aforementioned aero-engine, a baffle is formed on the inner wall of the front end of the pre-combustion chamber, surrounding the fuel injection port and shielding the inner side of the front end of the pre-combustion chamber.

[0019] According to at least one embodiment of this application, in the afterburner chamber of the aforementioned aero-engine, each nozzle is located behind a support plate.

[0020] According to at least one embodiment of this application, in the afterburner chamber of the aforementioned aero-engine, each flame tube has the same tilt angle with the trailing edge of the corresponding support plate.

[0021] According to at least one embodiment of this application, the afterburner chamber of the aforementioned aero-engine further includes:

[0022] The mounting bracket is placed between the pre-combustion chamber and the inner cone. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the afterburner chamber in an aero-engine provided in an embodiment of this application;

[0024] Figure 2 This is a partial schematic diagram of the afterburner chamber in an aero-engine provided in an embodiment of this application;

[0025] in:

[0026] 1-Outer casing; 2-Combining ring; 3-Inner cone; 4-Support plate; 5-Pre-combustion chamber; 6-Ignition nozzle; 7-Air bleed pipe; 8-Fuel injector; 9-Air bleed pipe mounting base; 10-Ignition nozzle mounting base; 11-Mounting bracket; 12-Flame pipe.

[0027] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0028] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some 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 related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0029] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or 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, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0030] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a 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 or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0031] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0032] An afterburner chamber in an aircraft engine includes:

[0033] Outer casing 1;

[0034] The confluence ring 2 is installed inside the outer casing 1;

[0035] The inner cone 3 is set inside the confluence ring 2, forming a diffuser flow path with the confluence ring 2. It is a hollow structure with multiple circumferentially distributed flame holes at the rear end.

[0036] Multiple support plates 4 are circumferentially supported between the confluence ring 2 and the inner cone 3;

[0037] The pre-combustion chamber 5 is set inside the inner cone 3. It has a sandwich structure with a corrugated inner wall and multiple air intake holes. It has an oil injection port at the front end and multiple flame tubes 12 formed at the rear end. Each flame tube 12 is connected to the inner cone 3, and the outlet of each flame tube 12 is connected to a corresponding flame hole.

[0038] The ignition nozzle 6 is installed through the outer casing 1, the confluence ring 2, the inner cone 3 and a support plate 4, with the ignition end extending into the pre-combustion chamber 5;

[0039] The air intake pipe 7 is installed through the outer casing 1, the confluence ring 2, the inner cone 3 and a support plate 4, and the air outlet end is connected to the interlayer of the pre-combustion chamber 5;

[0040] The fuel injector 8 is installed through the outer casing 1, the confluence ring 2, the inner cone 3 and a support plate 4, with the fuel injection end extending into the fuel injection port.

[0041] When the afterburner of the aero-engine disclosed in the above embodiments is working, the intake end of the bleed pipe 7 can be connected to the rear of the high-pressure compressor to bleed air into the interlayer of the pre-combustion chamber 5. Part of the bleed air can enter the interior of the pre-combustion chamber 5 through the bleed hole on the inner wall of the front end of the pre-combustion chamber 5, mix with the fuel injected by the fuel injector 8 to form a fuel-air mixture, and be ignited by the ignition nozzle 6. The remaining bleed air can enter the interior of the pre-combustion chamber 5 through the bleed hole on the side of the inner wall of the pre-combustion chamber 5, form a gas film cooling on the inner wall, and participate in the combustion inside the pre-combustion chamber 5. The combustion flame is ejected from the inner cone 3 through the flame pipe 12 to form a stable ignition source and achieve reliable ignition. In addition, the pre-combustion chamber 5 is located inside the inner cone 3, is not affected by the high temperature of the inlet, is not easily detected, has fewer parts, simple connection, built-in pipeline, and is lightweight and efficient.

[0042] Regarding the afterburner in the aero-engine disclosed in the above embodiments, those skilled in the art will understand that the design of the pre-combustion chamber 5 with a corrugated inner wall allows the gas entering the interlayer to undergo sufficient impact heat exchange with the inner wall, thereby improving the cooling effect of the pre-combustion chamber 5. It can be further designed with a tongue on the inner side of the inner wall of the pre-combustion chamber 5, with the opening facing backward, so that the airflow flowing into the pre-combustion chamber 5 from the air intake hole at this location can effectively adhere to the wall to form an air film, ensuring the cooling effect of the pre-combustion chamber 5.

[0043] Regarding the afterburner in the aero-engine disclosed in the above embodiments, those skilled in the art will understand that the automatic distribution of combustion gas and cooling gas can be achieved by designing the size, number, and distribution of the air vents at the front end and side of the inner wall of the pre-combustion chamber 5, so as to effectively ensure reliable combustion in the pre-combustion chamber 5 and efficient cooling of the pre-combustion chamber 5.

[0044] In some optional embodiments, in the afterburner of the above-mentioned aero-engine, the outer wall of the pre-combustion chamber 5 is formed with an air duct mounting seat 9, which is connected to the air duct 7;

[0045] An ignition nozzle mounting base 10 is formed on the outer wall of the pre-combustion chamber 5, and an ignition nozzle 6 is connected thereto.

[0046] In some optional embodiments, in the afterburner of the above-mentioned aero-engine, the inner wall of the front end of the pre-combustion chamber 5 is formed with a baffle plate, which surrounds the fuel injector and shields the inner side of the front end of the pre-combustion chamber 5, forming an annular gap with the inner wall of the front end. This can protect the front end of the pre-combustion chamber 5 from high-temperature damage, and at the same time form a backflow area behind the baffle plate, which facilitates the ignition of the fuel-air mixture by the ignition nozzle 6.

[0047] In some alternative embodiments, in the afterburner of the aforementioned aero-engine, the pre-combustion chamber 5 is connected to the molded structure thereon, and adopts an integrated design and 3D printing technology, which allows for complete replacement in case of damage, making it convenient and quick.

[0048] In some optional embodiments, in the afterburner chamber of the above-mentioned aero-engine, each flame nozzle is located behind a support plate 4 to make full use of the recirculation zone at the rear edge of the support plate 4, ensuring the stability of ignition and combustion. Furthermore, each flame nozzle 12 can be designed to have the same tilt angle as the corresponding rear edge of the support plate 4 to further promote the stability of ignition and combustion.

[0049] In some optional embodiments, the afterburner chamber of the aforementioned aero-engine further includes:

[0050] Mounting bracket 11 is supported between pre-combustion chamber 5 and inner cone 3. Mounting support plate 4 can be designed as a ring structure and welded to pre-combustion chamber 5 to stably support pre-combustion chamber 5 inside inner cone 3.

[0051] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0052] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 all fall within the scope of protection of this application.

Claims

1. An afterburner chamber for an aero-engine, characterized in that, include: Outer casing (1); A confluence ring (2) is installed inside the outer casing (1); The inner cone (3) is set inside the confluence ring (2) and is a hollow structure with multiple circumferentially distributed flame holes at the rear end; Multiple support plates (4) are circumferentially supported between the confluence ring (2) and the inner cone (3); The pre-combustion chamber (5) is set inside the inner cone (3) and has a sandwich structure. The inner wall has a corrugated structure and multiple air intake holes. The front end has an oil spray port and the rear end has multiple flame pipes (12). Each flame pipe (12) is connected to the inner cone (3), and the outlet of each flame pipe (12) is connected to a corresponding flame hole. The ignition nozzle (6) is installed through the outer casing (1), the confluence ring (2), the inner cone (3) and a support plate (4), with the ignition end extending into the pre-combustion chamber (5); An air intake pipe (7) is installed through the outer casing (1), the confluence ring (2), the inner cone (3) and a support plate (4), and the air outlet is connected to the interlayer of the pre-combustion chamber (5); The fuel injector (8) is installed through the outer casing (1), the confluence ring (2), the inner cone (3) and a support plate (4), with the fuel injection end extending into the fuel injection port; The front end inner wall of the pre-combustion chamber (5) is formed with a baffle plate, which surrounds the fuel injection port and blocks the front end inner side of the pre-combustion chamber (5); Each flame-emitting hole is located behind a support plate (4); Each flamethrower tube (12) has the same tilt angle as the rear edge of the corresponding support plate (4).

2. The afterburner chamber in an aero-engine according to claim 1, characterized in that, The upper outer wall of the pre-combustion chamber (5) is formed with an air duct mounting seat (9) for connecting the air duct (7); An ignition nozzle mounting base (10) is formed on the outer wall of the pre-combustion chamber (5) and connected to the ignition nozzle (6).

3. The afterburner chamber in an aero-engine according to claim 1, characterized in that, Also includes: The mounting bracket (11) is placed between the pre-combustion chamber (5) and the inner cone (3).

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