A radar stealth structure for an annular flame holder in an afterburner of an aeroengine

Abstract

This application belongs to the technical field of radar stealth design for annular flame holders in afterburners of aeroengines, and specifically relates to a radar stealth structure for an annular flame holder in an afterburner of an aeroengine. A baffle is added to the annular flame holder, and an adjustment structure composed of an outer slide plate, an inner slide plate, a support rod, a transmission rod, a linkage rod, and a linkage ring is provided. By driving the linkage ring to move axially, the outer slide plate can be driven to slide through the linkage rod and the transmission rod, and then the baffle can be rotated around the hinge point with the support rod, so as to change the inclination angle of the baffle, avoid the radar scattered waves at a specific angle from returning along the incident direction, and can adaptively reduce the intensity of the radar scattered characteristic signal within the omnidirectional range, ensuring the radar stealth performance of the aeroengine. When the baffle rotates, the inner slide plate is driven to slide, which can make the whole structure operate smoothly.

Description

Technical Field

[0001] This application belongs to the technical field of radar stealth design for annular flame holders in afterburners of aero-engines, and specifically relates to a radar stealth structure for an annular flame holder in an afterburner of aero-engine. Background Technique

[0002] The annular flame holder is arranged at the outlet of the afterburner of the aero-engine. It is an important component that propagates the flame and forms a stable recirculation zone during the ignition and combustion of the afterburner. Its cross-section is U-shaped. When the radar wave irradiates its inner surface horizontally, the scattered wave often returns along the incident direction, as Figure 1 shown, which is extremely unfavorable to the radar stealth performance of the aero-engine.

[0003] Currently, in order to reduce the radar scattering characteristic signal of the annular flame holder, its trailing edge is modified, and a baffle with a certain inclination angle is set to shield the inner surface of the annular flame holder. As Figure 2 shown, when the radar wave irradiates horizontally, the baffle scatters the radar wave into the cavity, enabling the scattered wave to avoid returning along the incident direction, which can effectively reduce the intensity of the radar scattering characteristic signal and improve the radar stealth performance of the aero-engine. However, when the aircraft climbs or dives, the inclination angle of the baffle changes relative to the horizontally irradiated radar wave. At a specific angle, the baffle forms a specular scattering source, causing the radar scattered wave to return along the incident direction, which to a certain extent enhances the intensity of the radar scattering characteristic signal and reduces the radar stealth performance of the aero-engine, and cannot ensure the radar stealth performance of the aero-engine in all directions.

[0004] In view of the existence of the above technical defects, this application is proposed.

[0005] It should be noted that the disclosure of the above background technical 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 this application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background technology should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a radar stealth structure for an annular flame holder in an afterburner of aero-engine to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] A radar stealth structure for an annular flame holder in an afterburner of aero-engine, comprising:

[0009] An annular flame holder, on the outer wall of which there are a plurality of guiding through holes extending axially;

[0010] A plurality of baffles are circumferentially arranged at the trailing edge of the annular flame stabilizer;

[0011] A plurality of outer sliding plates, one end of which is connected to the outer edge of each baffle, and the other end extends into the annular flame stabilizer, and has outer sliding grooves extending axially thereon;

[0012] A plurality of inner sliding plates, one end of which is connected to the inner edge of each baffle, and the other end extends into the annular flame stabilizer, and has inner sliding grooves extending axially thereon;

[0013] A plurality of support rods, one end of which is connected to the outer side wall of the annular flame stabilizer through each outer sliding groove, and the side wall of this end has outer limit blocks, and each outer limit block makes each outer sliding plate abut against the outer side wall of the annular flame stabilizer; the other end of each support rod is connected to the inner side wall of the annular flame stabilizer through each inner sliding groove, and the side wall of this end has inner limit blocks, and each inner limit block makes each inner sliding plate abut against the inner side wall of the annular flame stabilizer; each support rod has a support protrusion, and each support protrusion is hinged to each baffle;

[0014] A plurality of transmission rods, one end of which passes through each guiding hole and is connected to each outer sliding plate;

[0015] A plurality of linkage rods, one end of which is hinged to the other end of each transmission rod;

[0016] A linkage ring is sleeved on the outer periphery of the annular flame stabilizer, and the inner side is connected to the other end of each linkage rod.

[0017] According to at least one embodiment of the present application, in the above-mentioned radar stealth structure of the annular flame stabilizer of the afterburner of an aeroengine, corresponding to each baffle, the annular flame stabilizer is divided into multiple segments, and the segments are spliced with each other to form a polygon.

[0018] According to at least one embodiment of the present application, in the above-mentioned radar stealth structure of the annular flame stabilizer of the afterburner of an aeroengine, the upper edge of each baffle has a plurality of upper edge protruding parts and lower edge protruding parts; runway-shaped holes are provided on each upper edge protruding part and lower edge protruding part;

[0019] One end of each outer sliding plate facing the baffle has a plurality of outer sliding plate protruding parts; through holes are provided on each outer sliding plate protruding part;

[0020] The outer sliding plate protruding parts on each outer sliding plate and the upper edge protruding parts on each baffle are alternately distributed, and are hinged through the runway-shaped holes and through holes penetrating through their long axes;

[0021] One end of each inner sliding plate facing the baffle has a plurality of inner sliding plate protruding parts; through holes are provided on each inner sliding plate protruding part;

[0022] The protruding parts of the inner sliding plates on each inner sliding plate and the protruding parts at the lower edges of each baffle are distributed alternately, and are hinged through a runway-shaped hole and a through hole with a long axis passing through them.

[0023] According to at least one embodiment of the present application, in the above-mentioned radar stealth structure of the annular flame stabilizer of the aero-engine afterburner, between each support protrusion and each baffle, they are hinged by a pin through a lug structure.

[0024] According to at least one embodiment of the present application, in the above-mentioned radar stealth structure of the annular flame stabilizer of the aero-engine afterburner, between one end of each linkage rod facing away from the linkage ring and one end of each transmission rod facing away from the outer sliding plate, they are hinged by a pin through a lug structure.

[0025] According to at least one embodiment of the present application, in the above-mentioned radar stealth structure of the annular flame stabilizer of the aero-engine afterburner, there are two support rods corresponding to each baffle, outer sliding plate, and inner sliding plate. Description of the Drawings

[0026] Figure 1 is a schematic diagram of the scattering of existing radar waves irradiated on the inner surface of the annular flame stabilizer;

[0027] Figure 2 is a schematic diagram of modifying the trailing edge of the annular flame stabilizer and installing a baffle;

[0028] Figure 3 is a schematic diagram of the upper edge of the baffle of the radar stealth structure of the annular flame stabilizer of the aero-engine afterburner provided by the embodiment of the present application moving forward and the lower edge moving backward to the extreme positions;

[0029] Figure 4 is Figure 3 a partial schematic diagram of;

[0030] Figure 5 is a schematic diagram of the upper edge of the baffle of the radar stealth structure of the annular flame stabilizer of the aero-engine afterburner provided by the embodiment of the present application moving backward and the lower edge moving forward to the extreme positions;

[0031] Figure 6 is Figure 5 a partial schematic diagram of;

[0032] Figure 7 is Figure 6 a partial schematic diagram of;

[0033] Wherein:

[0034] 1 - annular flame stabilizer; 2 - baffle; 3 - outer sliding plate; 4 - inner sliding plate; 5 - support rod; 6 - transmission rod; 7 - linkage rod; 8 - linkage ring.

[0035] To better illustrate this embodiment, some components in the drawings are omitted, enlarged, or reduced, which do not represent the dimensions of actual products. In addition, the drawings are only for illustrative purposes and should not be construed as a limitation on this application. Detailed implementation manners

[0036] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely in conjunction with the drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments and the technical features in the embodiments in this application can be combined with each other to obtain new embodiments.

[0037] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the field to which this application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to indicate relative directions or position relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative position relationship may also change accordingly. Therefore, it should not be construed as a limitation on this application. The terms "first", "second", "third", and similar terms used in the description of this application are only for descriptive purposes to distinguish different components and cannot be understood as indicating or implying relative importance. The similar words such as "a", "one", or "the" used in the description of this application should not be understood as an absolute limitation on the quantity but should be understood as having at least one. The similar words such as "including" or "comprising" used in the description of this application are intended to mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0038] In addition, it should be noted that unless otherwise clearly specified and limited, the similar words such as "installed", "connected", and "coupled" 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 directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two elements. Those skilled in the art can understand their specific meanings in this application according to specific circumstances.

[0039] The following will Figures 1 to 7 make a further detailed description of this application.

[0040] An annular flame stabilizer radar stealth structure for an aeroengine afterburner, comprising:

[0041] An annular flame stabilizer 1, on the outer wall of which there are a plurality of guiding through holes extending axially;

[0042] A plurality of baffles 2, arranged circumferentially along the trailing edge of the annular flame stabilizer 1;

[0043] A plurality of outer sliding plates 3, one end of which is connected to the outer edge of each baffle 2, and the other end extends into the annular flame stabilizer 1, and there are outer sliding grooves extending axially thereon;

[0044] A plurality of inner sliding plates 4, one end of which is connected to the inner edge of each baffle 2, and the other end extends into the annular flame stabilizer 1, and there are inner sliding grooves extending axially thereon;

[0045] A plurality of support rods 5, one end of which is connected to the outer side wall of the annular flame stabilizer 1 through each outer sliding groove, and the side wall of this end has outer limit blocks, and each outer limit block makes each outer sliding plate 3 abut against the outer side wall of the annular flame stabilizer 1; the other end of each support rod 5 is connected to the inner side wall of the annular flame stabilizer 1 through each inner sliding groove, and the side wall of this end has inner limit blocks, and each inner limit block makes each inner sliding plate 4 abut against the inner side wall of the annular flame stabilizer 1; each support rod 5 has a support protrusion, and each support protrusion is hinged to each baffle 2;

[0046] A plurality of transmission rods 6, one end of which passes through each guiding hole and is connected to each outer sliding plate 3;

[0047] A plurality of linkage rods 7, one end of which is hinged to the other end of each transmission rod 6;

[0048] A linkage ring 8, sleeved on the outer periphery of the annular flame stabilizer 1, and the inner side is connected to the other end of each linkage rod 7.

[0049] For the annular flame stabilizer radar stealth structure of the aeroengine afterburner disclosed in the above embodiments, those skilled in the art can understand that by adding a baffle 2 on the annular flame stabilizer 1 and setting an adjustment structure composed of an outer sliding plate 3, an inner sliding plate 4, a support rod 5, a transmission rod 6, a linkage rod 7, and a linkage ring 8, the linkage ring 8 can be driven to move axially, specifically, an actuator can be set for driving, the outer sliding plate 3 is driven to slide through the linkage rod 7 and the transmission rod 6, and then the baffle 2 is rotated around the hinge point with the support rod 5, so as to be able to change the inclination angle of the baffle 2, avoid the radar scattered wave at a specific angle from returning along the incident direction, and can adaptively reduce the radar scattering characteristic signal intensity within the omnidirectional range, ensure the radar stealth performance of the aeroengine. While the baffle 2 rotates, the inner sliding plate 4 is driven to slide, which can make the whole structure move smoothly.

[0050] In the above-described radar stealth structure of the annular flame stabilizer in the afterburner of an aeroengine, when the linkage rod 7 moves forward, it drives the upper edge of the baffle to move forward and the lower edge to move backward to the extreme position, as Figures 3 - 4 shown;

[0051] In the above-described radar stealth structure of the annular flame stabilizer in the afterburner of an aeroengine, when the linkage rod 7 moves backward, it drives the upper edge of the baffle to move backward and the lower edge to move forward to the extreme position, as Figures 5 - 6 shown.

[0052] In the radar stealth structure of the annular flame stabilizer in the afterburner of an aeroengine disclosed in the above embodiment, a baffle 2 is additionally provided on the annular flame stabilizer 1, and a driving is designed by using an adjusting structure composed of an outer slide plate 3, an inner slide plate 4, a support rod 5, a transmission rod 6, a linkage rod 7, and a linkage ring 8. Only a plurality of axially extending guiding through holes need to be opened on the outer wall of the annular flame stabilizer 1, and each baffle 2 does not need to rotate into the inner side of the annular flame stabilizer 1, which will not greatly affect the performance of the annular flame stabilizer 1 and can ensure the original performance of the annular flame stabilizer 1.

[0053] In some alternative embodiments, in the above-described radar stealth structure of the annular flame stabilizer in the afterburner of an aeroengine, corresponding to each baffle 2, the annular flame stabilizer 1 is divided into multiple segments, and the segments are spliced with each other to form a polygon for easy assembly.

[0054] In some alternative embodiments, in the above-described radar stealth structure of the annular flame stabilizer in the afterburner of an aeroengine, the upper edge of each baffle 2 has a plurality of upper edge protruding parts and lower edge protruding parts; runway-shaped holes are provided on each upper edge protruding part and lower edge protruding part;

[0055] One end of each outer slide plate 3 facing the baffle 2 has a plurality of outer slide plate protruding parts; through holes are provided on each outer slide plate protruding part;

[0056] The outer slide plate protruding parts on each outer slide plate 3 and the upper edge protruding parts on each baffle 2 are alternately distributed, and are hinged through the runway-shaped holes and through holes with their long axes passing through them. The design of the runway-shaped holes leaves a margin of movement, which can avoid jamming during the rotation of the baffle 2;

[0057] One end of each inner slide plate 4 facing the baffle 2 has a plurality of inner slide plate protruding parts; through holes are provided on each inner slide plate protruding part;

[0058] The inner slide plate protruding parts on each inner slide plate 4 and the lower edge protruding parts on each baffle 2 are alternately distributed, and are hinged through the runway-shaped holes and through holes with their long axes passing through them. The design of the runway-shaped holes leaves a margin of movement, which can avoid jamming during the rotation of the baffle 2.

[0059] In some alternative embodiments, in the above-described annular flame stabilizer radar stealth structure of an aeroengine afterburner, between each support protrusion and each baffle 2, they are hinged by a pin through a lug structure.

[0060] In some alternative embodiments, in the above-described annular flame stabilizer radar stealth structure of an aeroengine afterburner, between one end of each linkage rod 7 facing away from the linkage ring 8 and one end of each transmission rod 6 facing away from the outer slide plate 3, they are hinged by a pin through a lug structure.

[0061] In some alternative embodiments, in the above-described annular flame stabilizer radar stealth structure of an aeroengine afterburner, there are two support rods 5 corresponding to each baffle 2, outer slide plate 3, and inner slide plate 4 to ensure the smoothness of the structural movement.

[0062] The various embodiments in the specification are described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0063] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle 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 protection scope of the present application.

Claims

1. An annular flame stabilizer radar stealth structure for an afterburner of an aeroengine, characterized in that Comprising: A circular flame stabilizer (1) with a plurality of axially extending guiding through holes formed on its outer wall; A plurality of baffles (2) circumferentially arranged at the trailing edge of the circular flame stabilizer (1); A plurality of outer sliding plates (3), one end of which is connected to the outer edge of each baffle (2), and the other end extends into the circular flame stabilizer (1), and has an outer sliding groove axially extending thereon; A plurality of inner sliding plates (4), one end of which is connected to the inner edge of each baffle (2), and the other end extends into the circular flame stabilizer (1), and has an inner sliding groove axially extending thereon; A plurality of support rods (5), one end of which is connected to the outer side wall of the circular flame stabilizer (1) through each outer sliding groove, and the side wall of this end has an outer limit block, and each outer limit block makes each outer sliding plate (3) abut against the outer side wall of the circular flame stabilizer (1); the other end of each support rod (5) is connected to the inner side wall of the circular flame stabilizer (1) through each inner sliding groove, and the side wall of this end has an inner limit block, and each inner limit block makes each inner sliding plate (4) abut against the inner side wall of the circular flame stabilizer (1); each support rod (5) has a support protrusion, and each support protrusion is hinged to each baffle (2); A plurality of transmission rods (6), one end of which passes through each guiding hole and is connected to each outer sliding plate (3); A plurality of linkage rods (7), one end of which is hinged to the other end of each transmission rod (6); A linkage ring (8) sleeved on the outer periphery of the circular flame stabilizer (1), and the inner side is connected to the other end of each linkage rod (7).

2. The annular flame stabilizer radar stealth structure for an afterburner of an aeroengine according to claim 1, characterized in that Corresponding to each baffle (2), the circular flame stabilizer (1) is divided into multiple segments, and the segments are spliced with each other to form a polygon.

3. The annular flame stabilizer radar stealth structure for an afterburner of an aeroengine according to claim 1, characterized in that Each baffle (2) has a plurality of upper edge protruding parts and lower edge protruding parts at the upper edge; there are oval-shaped holes on each upper edge protruding part and lower edge protruding part; One end of each outer sliding plate (3) facing the baffle (2) has a plurality of outer sliding plate protruding parts; there are through holes on each outer sliding plate protruding part; The outer sliding plate protruding parts on each outer sliding plate (3) and the upper edge protruding parts on each baffle (2) are alternately distributed, and are hinged by passing the long axis through the oval-shaped holes and through holes thereon; One end of each inner sliding plate (4) facing the baffle (2) has a plurality of inner sliding plate protruding parts; there are through holes on each inner sliding plate protruding part; The inner sliding plate protruding parts on each inner sliding plate (4) and the lower edge protruding parts on each baffle (2) are alternately distributed, and are hinged by passing the long axis through the oval-shaped holes and through holes thereon.

4. The annular flame stabilizer radar stealth structure for an afterburner of an aeroengine according to claim 1, characterized in that Between each support protrusion and each baffle (2), they are hinged by a pin shaft through an earpiece structure.

5. The annular flame stabilizer radar stealth structure for an afterburner of an aeroengine according to claim 1, characterized in that Between the end of each linkage rod (7) facing away from the linkage ring (8) and the end of each transmission rod (6) facing away from the outer sliding plate (3), they are hinged by a pin shaft through an earpiece structure.

6. The annular flame stabilizer radar stealth structure for an afterburner of an aeroengine according to claim 1, characterized in that There are two support rods (5) corresponding to each baffle (2), outer sliding plate (3), and inner sliding plate (4).

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