Circumferential flame stabilizer in aero-engine

Abstract

The invention belongs to the technical field of design of circumferential flame stabilizers in aero-engines, and particularly relates to a circumferential flame stabilizer in an aero-engine, which comprises a U-shaped outer groove, a U-shaped inner groove, a U-shaped outer culvert gas partition plate and a tail plate, an inner air inlet is formed in the front end of the U-shaped outer groove; the U-shaped inner groove is formed in the U-shaped outer groove; the two U-shaped outer culvert gas partition plates are connected between the inner side of the U-shaped outer groove and the outer side of the U-shaped inner groove; an inner culvert air flow channel is formed between the two U-shaped partition plates and is communicated with the inner culvert air inlet; the tail plate is arranged in the U-shaped outer groove, and a plurality of longitudinal fuel gas outflow seams are formed in the tail plate; the two side edges of the tail plate are connected to the inner side of the U-shaped outer groove; the side wall of the tail plate is connected to an opening of the U-shaped inner groove, and a fuel gas circulation channel is formed between the side wall 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 in particular 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 transfer 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 stable recirculation zone at the rear through width design. However, in order to avoid high-temperature damage to the circumferential flame stabilizer, it is usually designed to use external bypass air to cool it. 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 evaporation of fuel 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: A circumferential flame stabilizer in an aircraft engine, comprising a U-shaped outer groove, a U-shaped inner groove, a U-shaped outer culvert baffle, and a tail plate; The front end of the U-shaped outer groove has an internal gas inlet; The U-shaped inner groove is arranged inside the U-shaped outer groove; There are two U-shaped outer culvert air baffles, connected between the inner side of the U-shaped outer trough and the outer side of the U-shaped inner trough; An inner gas flow channel is formed between the two U-shaped partitions, and the inner gas flow channel is connected to the inner gas flow inlet; The tail plate is arranged in the U-shaped outer groove and has a plurality of longitudinal gas outflow slots thereon; The edges of both sides of the tail plate are connected to the inner side of the U-shaped outer groove; 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.

[0008] Optionally, in the circumferential flame stabilizer in the above-mentioned aircraft engine, 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.

[0009] 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.

[0010] 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.

[0011] Optionally, the above-mentioned circumferential flame stabilizer in the aircraft engine further includes a support plate nut; 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 outer sides 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.

[0012] This application has at least the following beneficial technical effects: Provided is a circumferential flame stabilizer in an aircraft engine, which is designed to utilize external bypass air to mix and evaporate with fuel, and to cool the circumferential flame stabilizer, especially to well protect the tail plate from high-temperature damage, and to introduce 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 effect of fuel and 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 transmission performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of a circumferential flame stabilizer in an aircraft engine provided by an embodiment of the present application; Figure 2 is a schematic diagram of a U-shaped outer groove (1) and its supporting plate nut provided in an embodiment of the present application; Figure 3 Schematic diagram of a U-shaped inner tank (2) and a U-shaped outer air separator provided in an embodiment of the present application; Figure 4 It is a 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 embodiment of the present application; Figure 5 is a schematic diagram of the operation of a circumferential flame stabilizer in an aircraft engine provided by an embodiment of the present application; in: 1-U-shaped outer groove; 2-U-shaped inner groove; 3-U-shaped outer air baffle; 4-support plate nut; 5-tail plate; 6-fuel nozzle.

[0014] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0015] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to 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.

[0016] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation 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 indicates 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.

[0017] In addition, it should be noted that, unless otherwise clearly specified 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.

[0018] The circumferential flame stabilizer in the aircraft engine is arranged 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.

[0019] The circumferential flame stabilizer in the 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.

[0020] The front end of the U-shaped outer groove 1 has an internal gas inlet, such as Figure 2 shown.

[0021] The U-shaped inner groove 2 is arranged in the U-shaped outer groove 1, such as Figure 3 shown.

[0022] There are two U-shaped outer culvert gas 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, and can be specifically connected by welding. An inner gas flow channel is formed between the two U-shaped baffles 3, and the inner gas flow channel is connected to the inner gas flow inlet.

[0023] 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 duct baffles 3, and cooperate with bolts to connect the U-shaped inner groove 2 to the inner side of the U-shaped outer groove 1.

[0024] The tail plate 5 is arranged in the U-shaped outer groove 1, and has a plurality of longitudinal gas outflow slots. The two side edges of the tail plate 5 are connected to the inner side of the U-shaped outer groove 1, and specifically, welding connection can be adopted. The side wall of the tail plate 5 is connected to the opening of the U-shaped inner groove 2, and specifically, welding connection can be adopted, and a gas flow channel is formed between the tail plate 5 and the U-shaped inner groove 2.

[0025] The circumferential flame stabilizer in the aircraft engine disclosed in the above embodiment can be arranged circumferentially with the radial flame stabilizer in the combustion chamber in a specific application, such as Figure 4 As shown, the two 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 entrapment gas can be introduced, and a fuel nozzle 6 is arranged at one end or both ends of the U-shaped inner groove 2, as shown in FIG. Figure 5 As shown, the outer entrapment 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 entrapment 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 entrapment 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 and evaporation occur and combustion is performed. 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 the rear thereof, promoting the mixing and evaporation effects of the fuel and the outer entrapment gas in the stabilizer and the recirculation zone at the rear thereof, and improving the flame stabilization of the circumferential flame stabilizer and its circumferential flame transmission performance.

[0026] In the circumferential flame stabilizer of the aircraft engine disclosed in the above-mentioned embodiment, it is designed to utilize external entrapment air to mix and evaporate with the fuel, and to cool the circumferential flame stabilizer structure, especially to protect the tail plate 5 from high-temperature damage. The internal entrapment 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 the fuel and external entrapment 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.

[0027] 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 circumferential flame stabilizer in an aircraft engine, characterized in that: It comprises 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) is provided with an inner gas inlet; The U-shaped inner groove (2) is arranged inside 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 inner gas flow channel is formed between the two U-shaped partitions (3), and the inner gas flow channel is connected to the inner gas flow inlet; The tail plate (5) is arranged in the U-shaped outer groove (1) and has a plurality of longitudinal gas outflow slots thereon; 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 and 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 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 of 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 culvert baffles (3), and cooperate with bolts to connect the U-shaped inner groove (2) to the inner side of the U-shaped outer groove (1).

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