A circumferential flame stabilizer in an aircraft engine

Abstract

The present application belongs to the technical field of design of circumferential flame stabilizers in aircraft engines, and specifically relates to a circumferential flame stabilizer in aircraft engines, comprising a U-shaped outer groove, a U-shaped inner groove, a U-shaped outer air duct baffle, and a tail plate; the front end of the U-shaped outer groove is provided with an internal gas inlet; the U-shaped inner groove is arranged in the U-shaped outer groove; there are two U-shaped outer air duct baffles, which are connected between the inner side of the U-shaped outer groove and the outer side of the U-shaped inner groove; an internal gas flow channel is formed between the two U-shaped baffles, and the internal gas flow channel is connected to the internal gas inlet; the tail plate is arranged in the U-shaped outer groove, and has a plurality of longitudinal gas outflow seams thereon; the edges on both sides of the tail plate are connected to the inner side of the U-shaped outer groove; the side walls of the tail plate are connected to the opening of the U-shaped inner groove, and a gas flow channel is formed between the tail plate and the U-shaped inner groove.

Description

Technical Field

[0001] The present application belongs to the technical field of design of circumferential flame stabilizers in aircraft engines, and specifically relates to a circumferential flame stabilizer in an aircraft engine. Background Art

[0002] A circumferential flame stabilizer is provided in the combustion chamber of an aircraft engine to stabilize the flame and to carry out circumferential flame transmission in the combustion chamber.

[0003] The flame stability and circumferential flame transmission performance of the circumferential flame stabilizer are mainly determined by the range and temperature of the recirculation zone formed behind it.

[0004] The range of the recirculation zone formed behind the circumferential flame stabilizer is mainly determined by its width. At present, the circumferential flame stabilizer can usually form a large-scale stable recirculation zone at the rear through width design. However, in order to avoid the circumferential flame stabilizer from being damaged by high temperature, it is usually designed to be cooled by external bypass air. After cooling the circumferential flame stabilizer, the external bypass air will enter the recirculation zone, causing the temperature of the recirculation zone to be low, resulting in poor fuel evaporation effect in the circumferential flame stabilizer and the recirculation zone, seriously affecting the flame stability of the circumferential flame stabilizer and its circumferential flame transfer performance.

[0005] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0006] The purpose of the present application is to provide a circumferential flame stabilizer in an aircraft engine to overcome or alleviate at least one of the technical deficiencies of the known ones.

[0007] The technical solution of this application is:

[0008] A circumferential flame stabilizer in an aircraft engine, comprising a U-shaped outer groove, a U-shaped inner groove, a U-shaped outer duct baffle, and a tail plate;

[0009] The front end of the U-shaped outer groove has an internal air inlet;

[0010] The U-shaped inner groove is arranged inside the U-shaped outer groove;

[0011] There are two U-shaped outer culvert baffles, connected between the inner side of the U-shaped outer trough and the outer side of the U-shaped inner trough;

[0012] An internal gas flow channel is formed between the two U-shaped partitions, and the internal gas flow channel is connected to the internal gas inlet;

[0013] The tail plate is set in the U-shaped outer groove and has multiple longitudinal gas outflow slots;

[0014] The edges on both sides of the tail plate are connected to the inner side of the U-shaped outer groove;

[0015] The side wall of the tail plate is connected to the opening of the U-shaped inner groove, and a gas flow channel is formed between the side wall of the tail plate and the U-shaped inner groove.

[0016] Optionally, in the circumferential flame stabilizer in the above-mentioned aircraft engine, the two U-shaped outer air duct baffles are welded to the inner side of the U-shaped outer groove and the outer side of the U-shaped inner groove.

[0017] Optionally, in the above-mentioned circumferential flame stabilizer in the aircraft engine, the edges on both sides of the tail plate are welded to the inner side of the U-shaped outer groove.

[0018] Optionally, in the above-mentioned circumferential flame stabilizer in the aircraft engine, the side wall of the tail plate is welded to the opening of the U-shaped inner groove.

[0019] Optionally, the aforementioned circumferential flame stabilizer in an aircraft engine further includes a support plate nut;

[0020] There are two pairs of support plate nuts, which are connected to the inner side of the U-shaped outer groove and distributed on the outside of the two U-shaped outer air culverts. The U-shaped inner groove is connected to the inner side of the U-shaped outer groove with the help of bolts.

[0021] This application has at least the following beneficial technical effects:

[0022] Provided is a circumferential flame stabilizer in an aircraft engine, which is designed to utilize circumferential air to mix and evaporate with fuel, and to cool the circumferential flame stabilizer, especially being able to well protect the tail plate from high-temperature damage. In addition, internal air is introduced through structural design to improve the temperature conditions in the circumferential flame stabilizer and the recirculation zone behind it, thereby effectively promoting the mixing and evaporation of fuel and circumferential air in the circumferential flame stabilizer and the recirculation zone behind it, and improving the flame stabilization of the circumferential flame stabilizer and its circumferential flame transmission performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of a circumferential flame stabilizer in an aircraft engine provided by an embodiment of the present application;

[0024] Figure 2 This is a schematic diagram of a U-shaped outer groove (1) and its supporting plate nut provided in an embodiment of the present application;

[0025] Figure 3 This is a schematic diagram of a U-shaped inner tank (2) and its U-shaped outer air separator provided in an embodiment of the present application;

[0026] Figure 4 Schematic diagram of the circumferentially spaced arrangement of the circumferential flame stabilizer and the radial flame stabilizer in the combustion chamber of the aircraft engine disclosed in the above embodiment provided by the present application;

[0027] Figure 5 Schematic diagram of the operation of a circumferential flame stabilizer in an aircraft engine provided by an embodiment of the present application;

[0028] in:

[0029] 1-U-shaped outer groove; 2-U-shaped inner groove; 3-U-shaped outer air duct baffle; 4-support plate nut; 5-tail plate; 6-fuel nozzle.

[0030] 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 limiting this application. DETAILED DESCRIPTION

[0031] 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.

[0032] 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.

[0033] 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.

[0034] The circumferential flame stabilizer in the aircraft engine is set in the inner part, and the inner part gas has a higher temperature. Based on this, the present application provides a circumferential flame stabilizer in the aircraft engine, such as Figure 1 shown.

[0035] The circumferential flame stabilizer in an aircraft engine comprises a U-shaped outer groove 1, a U-shaped inner groove 2, a U-shaped outer duct baffle 3, a support plate nut 4, and a tail plate 5.

[0036] The front end of the U-shaped outer groove 1 has an internal air inlet, such as Figure 2 shown.

[0037] The U-shaped inner groove 2 is arranged in the U-shaped outer groove 1, such as Figure 3 shown.

[0038] There are two U-shaped outer culvert air baffles 3, which are connected between the inner side of the U-shaped outer groove 1 and the outer side of the U-shaped inner groove 2. Specifically, welding can be used to form an inner gas flow channel between the two U-shaped baffles 3, and the inner gas flow channel is connected to the inner gas inlet.

[0039] There are two pairs of support plate nuts 4, which are connected to the inner side of the U-shaped outer groove 1 and distributed on the outside of the two U-shaped outer air duct baffles 3. The U-shaped inner groove 2 is connected to the inner side of the U-shaped outer groove 1 with the help of bolts.

[0040] The tail plate 5 is installed within the U-shaped outer trough 1 and features multiple longitudinal gas outlet slots. The edges of the tail plate 5 are connected to the inner side of the U-shaped outer trough 1, typically by welding. The sidewalls of the tail plate 5 are connected to the opening of the U-shaped inner trough 2, typically by welding, forming a gas flow channel between the tail plate 5 and the U-shaped inner trough 2.

[0041] The circumferential flame stabilizer in the aircraft engine disclosed in the above embodiment can be arranged circumferentially spaced apart from the radial flame stabilizer in the combustion chamber in a specific application, such as Figure 4 As shown, the ends of the U-shaped outer groove 1 and the U-shaped inner groove 2 are connected to the radial flame stabilizer so that the external entrapped gas can be introduced, and a fuel nozzle 6 is set at one end or both ends of the U-shaped inner groove 2, as shown in FIG. Figure 5 As shown, the outer duct gas can enter between the U-shaped outer groove 1 and the U-shaped inner groove 2, and enter the gas flow channel, but will be blocked by the U-shaped outer duct gas baffle 3 and cannot enter the inner gas flow channel. The fuel sprayed by the fuel nozzle 6 can enter the gas flow channel, mix and evaporate with the outer duct gas entering the gas flow channel, and then flow out to the recirculation zone at the rear through the longitudinal gas outflow slit, where further mixing, evaporation, and combustion occur. At the same time, the inner gas can flow into the inner gas flow channel through the inner gas inlet, heat the U-shaped inner groove 2, increase the wall temperature of the U-shaped inner groove 2, and then flow out to the recirculation zone at the rear, increase the temperature of the recirculation zone at the rear, thereby improving the temperature conditions in the stabilizer and the recirculation zone at its rear, promoting the mixing and evaporation effects of the fuel and the outer duct gas in the stabilizer and the recirculation zone at its rear, and improving the flame stabilization of the circumferential flame stabilizer and its circumferential flame transmission performance.

[0042] In the circumferential flame stabilizer of the aircraft engine disclosed in the above embodiment, the design utilizes the external bypass air to mix and evaporate with the fuel, and to cool the circumferential flame stabilizer structure, especially to well protect the tail plate 5 from high temperature damage, and introduces the internal bypass air through structural design to improve the temperature conditions in the circumferential flame stabilizer and the recirculation zone behind it, thereby effectively promoting the mixing and evaporation of the fuel and the external bypass air in the circumferential flame stabilizer and the recirculation zone behind it, and improving the flame stabilization of the circumferential flame stabilizer and its circumferential flame transfer performance.

[0043] 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 circumferential flame stabilizer in an aircraft engine, characterized in that: It includes a U-shaped outer trough (1), a U-shaped inner trough (2), a U-shaped outer air duct baffle (3), and a tail plate (5); The front end of the U-shaped outer groove (1) has an internal air inlet; The U-shaped inner groove (2) is arranged in the U-shaped outer groove (1); There are two U-shaped outer air culvert baffles (3) connected between the inner side of the U-shaped outer trough (1) and the outer side of the U-shaped inner trough (2); An internal gas flow channel is formed between the two U-shaped partitions (3), and the internal gas flow channel is connected to the internal gas inlet; The tail plate (5) is arranged in the U-shaped outer groove (1) and has a plurality of longitudinal gas outflow slots; The edges of both sides of the tail plate (5) are connected to the inner side of the U-shaped outer groove (1); The side wall of the tail plate (5) is connected to the opening of the U-shaped inner groove (2), and a gas flow channel is formed between the tail plate (5) and the U-shaped inner groove (2); A fuel nozzle (6) is provided at one end or both ends of the U-shaped inner groove (2).

2. The circumferential flame stabilizer in an aircraft engine according to claim 1, characterized in that: The two U-shaped outer air culvert baffles (3) are welded to the inner side of the U-shaped outer trough (1) and the outer side of the U-shaped inner trough (2).

3. The circumferential flame stabilizer in an aircraft engine according to claim 1, characterized in that: The edges on both sides of the tail plate (5) are welded to the inner side of the U-shaped outer groove (1).

4. The circumferential flame stabilizer in an aircraft engine according to claim 1, characterized in that: The side wall of the tail plate (5) is welded to the opening of the U-shaped inner groove (2).

5. The circumferential flame stabilizer in an aircraft engine according to claim 1, characterized in that: Also includes a support plate nut (4); There are two pairs of support plate nuts (4), which are connected to the inner side of the U-shaped outer groove (1) and distributed on the outer sides of the two U-shaped outer air culverts (3). The U-shaped inner groove (2) is connected to the inner side of the U-shaped outer groove (1) with the help of bolts.

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