An aircraft engine turbine post-combustion supercharging device

Abstract

The present application belongs to the technical field of non-variable volume engine component design, and specifically relates to an aircraft engine turbine post-recombustion boosting device, comprising: an annular outer wall; a plurality of radial flame stabilizers, each having a U-shaped cross-section, one end connected to the inner side of the annular outer wall along the circumferential direction, and the other end tilted backward and pointing to the center of the annular outer wall; the side walls on both sides of each radial flame stabilizer are staggered in height; a plurality of radial spaced stabilizers, each having a U-shaped cross-section, the thickness of which is smaller than the thickness of the radial flame stabilizer, one end connected to the inner side of the annular outer wall along the circumferential direction, and the other end pointing to the center of the annular outer wall, and spaced apart from each radial flame stabilizer, with the leading edge located before the trailing edge of the radial flame stabilizer and the trailing edge located after the trailing edge of the radial flame stabilizer.

Description

Technical Field

[0001] The present application belongs to the technical field of non-variable volume engine component design, and specifically relates to an aircraft engine turbine post-combustion supercharging device. Background Art

[0002] In order to increase the thrust of an aircraft engine, a reburning and supercharging device is provided behind the engine turbine. The device mainly comprises an annular outer wall, a merging ring provided inside the annular outer wall, and an inner cone provided inside the merging ring. The annular outer wall, the merging ring and the front end of the inner cone are connected to the rear end of the turbine. The annular outer wall and the merging ring form an outer conduit, and the merging ring and the inner cone form an inner conduit. Fuel is sprayed into the inner conduit for reburning and supercharging, thereby increasing the thrust of the engine.

[0003] To promote stable combustion in the post-turbine reburning supercharging device of an aircraft engine, radial flame stabilizers are currently mostly installed therein. The cross-section of the radial flame stabilizer is U-shaped. Multiple radial flame stabilizers are arranged circumferentially within the annular outer wall and located at the trailing edge of the converging ring. One end of the radial flame stabilizers is connected to the inner side of the annular outer wall, and the other end points to the center of the annular outer wall. The recirculation zone formed at the trailing edge is used to organize combustion and promote combustion stability. This technical solution has the following defects:

[0004] The trailing edges of the radial flame stabilizers are on the same cross section, the heat release of the flames is relatively concentrated, and the flames are close to each other. The flame fluctuations are easy to interfere with each other, which can easily induce oscillating combustion and have poor anti-disturbance ability.

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

[0006] 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 the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0007] The purpose of the present application is to provide an aircraft engine turbine post-combustion supercharging device to overcome or alleviate at least one of the existing technical defects.

[0008] The technical solution of this application is:

[0009] An aircraft engine turbine post-combustion supercharging device, comprising:

[0010] annular outer wall;

[0011] Multiple radial flame stabilizers, with a U-shaped cross-section, one end connected circumferentially to the inner side of the annular outer wall, and the other end tilted backward towards the center of the annular outer wall; the side walls on both sides of each radial flame stabilizer are staggered in height;

[0012] Multiple radially spaced stabilizers, with a U-shaped cross-section, smaller in thickness than the radial flame stabilizers, one end connected circumferentially to the inner side of the annular outer wall, and the other end pointing towards the center of the annular outer wall, distributed at intervals with each radial flame stabilizer, and the leading edge is before the trailing edge of the radial flame stabilizer, and the trailing edge is after the trailing edge of the radial flame stabilizer.

[0013] According to at least one embodiment of the present application, in the above-mentioned post-turbine re-combustion and supercharging device of an aero-engine, the distance L by which the trailing edge of each radially spaced stabilizer extends beyond the trailing edge of the radial flame stabilizer is less than d / tgα, where:

[0014] d is the distance between the side wall of the radially spaced stabilizer and the side wall of the adjacent radial flame stabilizer;

[0015] α is the half angle of the flame front on the side walls on both sides of the radial flame stabilizer.

[0016] According to at least one embodiment of the present application, in the above-mentioned post-turbine re-combustion and supercharging device of an aero-engine, there are multiple vibration-absorbing small holes on the side walls of each radially spaced stabilizer.

[0017] According to at least one embodiment of the present application, in the above-mentioned post-turbine re-combustion and supercharging device of an aero-engine, each radial flame stabilizer is divided into two types of radial flame stabilizers with longer lengths and shorter lengths;

[0018] The radial flame stabilizers with longer lengths and the radial flame stabilizers with shorter lengths are distributed at intervals in the circumferential direction of the annular outer wall.

[0019] The present application has at least the following beneficial technical effects:

[0020] Provided is a post-turbine re-combustion and supercharging device of an aero-engine, in which each radial flame stabilizer inside the annular outer wall is designed to tilt backward, which can extend the length of the flame distribution line behind the trailing edge of the radial flame stabilizer, avoid heat release concentration in the same cross-section, and reduce the mutual interference between flame fluctuations. In addition, the side walls on both sides of each radial flame stabilizer are designed to be staggered in height, that is, the side walls on both sides of the radial flame stabilizer have different lengths, which can lengthen the distance between the flames behind the trailing edges of the side walls on both sides of the same radial flame stabilizer and the distance between the flames behind the trailing edges of the side walls on both sides of adjacent radial flame stabilizers, so as to further reduce the mutual interference between flame fluctuations, enhance the anti-disturbance ability of the re-combustion and supercharging device, and avoid oscillatory combustion.

[0021] In the above-mentioned aircraft engine turbine post-reburning booster device, radial spacing stabilizers are also arranged between each radial flame stabilizer, and the leading edge of each radial spacing stabilizer is located before the trailing edge of the radial flame stabilizer, and the trailing edge is located after the trailing edge of the radial flame stabilizer, which can block the flame fronts behind the trailing edges of two adjacent radial flame stabilizers, further prevent mutual interference between flame fluctuations, and avoid oscillating combustion. In addition, the thickness of each radial spacing stabilizer is designed to be small. Although the ability to stabilize the flame alone is limited, the fluid resistance is small, and the flame front behind its trailing edge can be ignited by the flame behind the trailing edge of the radial flame stabilizer, and can support each other with each radial flame stabilizer, thereby better ensuring the stability of combustion in the reburning booster device. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Schematic diagram of an aircraft engine turbine post-recombustion supercharging device provided in an embodiment of the present application;

[0023] Figure 2 Schematic diagram of the relationship between the radial flame stabilizer and the annular outer wall provided in an embodiment of the present application;

[0024] Figure 3 Schematic diagram of the relationship between the radial flame stabilizer and the radial spacer stabilizer provided in the embodiment of the present application;

[0025] in:

[0026] 1- radial flame stabilizer; 2- annular outer wall; 3- radial spacer stabilizer.

[0027] 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

[0028] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease 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 of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0029] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0030] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" 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 a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0031] The following is combined with Figures 1 to 3 This application is described in further detail.

[0032] An aircraft engine turbine post-combustion supercharging device, such as Figure 1 As shown, including:

[0033] annular outer wall 2;

[0034] A plurality of radial flame stabilizers 1 are U-shaped in cross section, one end of which is connected to the inner side of the annular outer wall 2 along the circumferential direction, and the other end of which is tilted backward and points to the center of the annular outer wall 2. Figure 2 As shown; the side walls of each radial flame stabilizer 1 are staggered in height;

[0035] A plurality of radially spaced stabilizers 3, having a U-shaped cross-section and being thinner in thickness than the radial flame stabilizer 1, are circumferentially connected to the inner side of the annular outer wall 2 at one end, and the other end points towards the center of the annular outer wall 2. They are distributed at intervals from each radial flame stabilizer 1, with the leading edge located before the trailing edge of the radial flame stabilizer 1 and the trailing edge located after the trailing edge of the radial flame stabilizer 1, as Figure 3 shown.

[0036] In the post-combustion supercharging device for an aeroengine turbine disclosed in the above embodiment, each radial flame stabilizer 1 in the annular outer wall 2 is designed to be inclined backward, which can extend the length of the flame distribution line behind the trailing edge of the radial flame stabilizer 1, avoid heat release concentration in the same cross-section, and reduce the mutual interference between flame fluctuations. In addition, the side walls on both sides of each radial flame stabilizer 1 are designed to be staggered in height, that is, the lengths of the side walls on both sides of the radial flame stabilizer 1 are different, which can lengthen the distance between the flames behind the trailing edges of the side walls on both sides of the same radial flame stabilizer 1 and the distance between the flames behind the trailing edges of the side walls on both sides of adjacent radial flame stabilizers 1, thereby further reducing the mutual interference between flame fluctuations, enhancing the anti-disturbance ability of the post-combustion supercharging device, and avoiding oscillatory combustion.

[0037] In the post-combustion supercharging device for an aeroengine turbine disclosed in the above embodiment, radial spacing stabilizers 3 are provided between each radial flame stabilizer 1, and the leading edge of each radial spacing stabilizer 3 is located before the trailing edge of the radial flame stabilizer 1 and the trailing edge is located after the trailing edge of the radial flame stabilizer 1, which can block the flame front behind the trailing edges of two adjacent radial flame stabilizers 1, further prevent the mutual interference between flame fluctuations, and avoid oscillatory combustion. In addition, each radial spacing stabilizer 3 is designed to have a small thickness. Although its ability to stabilize the flame alone is limited, its fluid resistance is small, and the flame front behind its trailing edge can be ignited by the flame behind the trailing edge of the radial flame stabilizer 1, and it can support each radial flame stabilizer 1, preferably ensuring the stability of combustion in the post-combustion supercharging device.

[0038] In some optional embodiments, in the above post-combustion supercharging device for an aeroengine turbine, the distance L by which the trailing edge of each radial spacing stabilizer 3 extends beyond the trailing edge of the radial flame stabilizer 1 is less than d / tgα, where d is the distance between the side wall of the radial spacing stabilizer 3 and the side wall of the adjacent radial flame stabilizer 1, and α is the half angle of the flame front on both sides of the radial flame stabilizer 1, that is, the distance by which the trailing edge of each radial spacing stabilizer 3 protrudes beyond the trailing edge of the radial flame stabilizer 1 is limited to avoid excessive protrusion distance, so that the side walls on both sides of each radial spacing stabilizer 3 are under the high-temperature flame behind the trailing edge of the radial flame stabilizer 1 and are eroded by the high-temperature flame.

[0039] In some optional embodiments, in the above-mentioned aircraft engine turbine post-reburning boosting device, each radially spaced stabilizer 3 is a hollow box-type structure with multiple vibration-absorbing holes on the side walls on both sides. The vibration-absorbing holes can be used to efficiently absorb the energy of the oscillating combustion of the reburning boosting device, effectively suppress the oscillating combustion, and ensure the stability of combustion.

[0040] In some optional embodiments, in the above-mentioned aircraft engine turbine post-recombustion supercharging device, each radial flame stabilizer 1 is divided into two types of radial flame stabilizers 1: a longer length and a shorter length;

[0041] The radial flame stabilizers 1 with a longer length and the radial flame stabilizers 1 with a shorter length are spaced apart in the circumferential direction of the annular outer wall 2 to avoid interference with each other.

[0042] 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 referred to in detail.

[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. An aircraft engine turbine post-combustion supercharging device, characterized in that: Comprising: Annular outer wall (2); A plurality of radial flame stabilizers (1), having a U-shaped cross-section, one end of which is circumferentially connected to the inner side of the annular outer wall (2), and the other end is inclined backward and points to the center of the annular outer wall (2); the side walls on both sides of each radial flame stabilizer (1) are staggered in height; A plurality of radially spaced stabilizers (3), having a U-shaped cross-section, with a thickness smaller than that of the radial flame stabilizer (1), one end of which is circumferentially connected to the inner side of the annular outer wall (2), and the other end points to the center of the annular outer wall (2), being distributed at intervals with each radial flame stabilizer (1), and the leading edge is located before the trailing edge of the radial flame stabilizer (1), and the trailing edge is located after the trailing edge of the radial flame stabilizer (1).

2. The post-combustion supercharging device for an aero-engine turbine according to claim 1, wherein The distance L by which the trailing edge of each radially spaced stabilizer (3) extends beyond the trailing edge of the radial flame stabilizer (1) is < d / tgα, where: d is the distance between the side wall of the radially spaced stabilizer (3) and the side wall of the adjacent radial flame stabilizer (1); α is the half angle of the flame front of the side walls on both sides of the radial flame stabilizer (1).

3. The post-combustion supercharging device for an aero-engine turbine according to claim 1, wherein Each radially spaced stabilizer (3) has a plurality of vibration-absorbing small holes on its side wall.

4. The post-combustion supercharging device for an aero-engine turbine according to claim 1, wherein Each radial flame stabilizer (1) is divided into two types of radial flame stabilizers (1) with longer lengths and shorter lengths; Each radial flame stabilizer (1) with a longer length and each radial flame stabilizer (1) with a shorter length are circumferentially distributed at intervals on the annular outer wall (2).

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