A radar stealthy control structure for a radial flame channel of an afterburner of an aeroengine

Abstract

The application relates to a radar stealth control structure of a radial flame channel of an aero-engine afterburner, which comprises the following: a plurality of radial flame channels, which are arranged in a circumferential direction in a V-shaped cross section in an outer wall of the afterburner and are connected to trailing edges of an outer annular flame stabilizer and an inner annular flame stabilizer; a plurality of pairs of baffles, which are hinged to two side walls of each radial flame channel; a plurality of driving rods, one end of each of which extends into each radial flame channel from an outer end; a plurality of pairs of hinged rods, which are arranged in each radial flame channel and are hinged between each pair of baffles and each driving rod; a linkage ring, which is sleeved around an outer periphery of the outer annular flame stabilizer, is connected to the other end of each driving rod, can move in an axial direction of the outer wall of the afterburner, and then drives each pair of baffles to close or open through each driving rod and each pair of hinged rods; when each pair of baffles is closed, an included angle exists therebetween; and when each pair of baffles is opened, the two side walls of each radial flame channel are flattened.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of radar stealth design of the radial flame transmission groove of the afterburner of an aero-engine, and particularly relates to a radar stealth operating structure of the radial flame transmission groove of the afterburner of an aero-engine. BACKGROUND

[0002] An outer annular flame stabilizer 2 is arranged in the outer wall 1 of the afterburner of the aero-engine, and an inner annular flame stabilizer 3 is arranged in the outer annular flame stabilizer 2, the cross sections of the outer annular flame stabilizer 2 and the inner annular flame stabilizer 3 are V-shaped, so that the flame can be transmitted circumferentially and a stable recirculation zone can be formed when the afterburner is ignited and burns, in addition, in order to transmit the flame radially and form a stable recirculation zone, a plurality of radial flame transmission grooves 4 are arranged along the circumferential direction at the trailing edges of the outer annular flame stabilizer 2 and the inner annular flame stabilizer 3, the cross sections of the radial flame transmission grooves 4 are also V-shaped, as shown in Figures 1-2 .

[0003] The radial flame transmission groove 4 is similar to an angle reflector, after the radar wave is irradiated to the inner surface thereof, the scattered wave is returned along the incident direction, the radar characteristic signal is strong, and the radar stealth performance of the aero-engine is extremely unfavorable, if the radial flame transmission groove 4 is modified, the radar characteristic signal thereof can be reduced, and the radar stealth performance of the aero-engine can be improved, but the flame transmission function of the radial flame transmission groove 4 in the afterburning state is affected, and the afterburner cannot work stably.

[0004] The present application is proposed in view of the existence of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide a radar stealth operating structure of the radial flame transmission groove of the afterburner of an aero-engine, so as to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] A radar stealth operating structure of the radial flame transmission groove of the afterburner of an aero-engine, comprising:

[0009] A plurality of radial flame transmission grooves, the cross sections of which are V-shaped, are arranged along the circumferential direction in the outer wall of the afterburner, and are connected to the trailing edges of the outer annular flame stabilizer and the inner annular flame stabilizer;

[0010] a plurality of pairs of baffle plates, hinged on the two side walls of each radial flame channel;

[0011] a plurality of driving rods, one end of each extending into the interior of each radial flame channel;

[0012] a plurality of pairs of hinged rods, arranged in each radial flame channel, hinged between each pair of baffle plates and each driving rod;

[0013] a linkage ring, sleeved on the outer periphery of the outer annular flame stabilizer, connected to the other end of each driving rod, capable of moving axially along the outer wall of the afterburner, and further capable of driving each pair of baffle plates to close or open through each driving rod and each pair of hinged rods;

[0014] each pair of baffle plates has an included angle when closed;

[0015] each pair of baffle plates is flattened with the two side walls of each radial flame channel when opened.

[0016] According to at least one embodiment of the present application, in the above-mentioned radar stealth control structure of the radial flame channel of the afterburner of the aero-engine, one end of each pair of baffle plates is hinged on the trailing edge of the two side walls of each radial flame channel through a rotating shaft.

[0017] According to at least one embodiment of the present application, in the above-mentioned radar stealth control structure of the radial flame channel of the afterburner of the aero-engine, one end of each pair of hinged rods is hinged on the end of each driving rod extending into the interior of the radial flame channel through a pin, and the other end is hinged on the inner side of each pair of baffle plates through the cooperation of a single-ear structure and a double-ear structure using a pin shaft.

[0018] According to at least one embodiment of the present application, in the above-mentioned radar stealth control structure of the radial flame channel of the afterburner of the aero-engine, each pair of baffle plates has an included angle of 45°-75° when closed.

[0019] According to at least one embodiment of the present application, in the above-mentioned radar stealth control structure of the radial flame channel of the afterburner of the aero-engine, each pair of baffle plates has an inclined surface contact with the two side walls of each radial flame channel when opened. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is a schematic diagram of the outer annular flame stabilizer, the inner annular flame stabilizer and the radial flame channel thereof arranged in the outer wall of the afterburner of the existing aero-engine;

[0021] Figure 2 is a partial schematic diagram of Figure 1 ;

[0022] Figure 3 is a schematic diagram of the closing of each pair of baffle plates in the radar stealth control structure of the radial flame channel of the afterburner of the aero-engine provided by the embodiment of the present application;

[0023] Figure 4 is a partial view of the schematic diagram of Figure 3

[0024] Figure 5 is a partial sectional view of the schematic diagram of Figure 4

[0025] Figure 6 is a schematic diagram of the opening of each pair of baffles in the radar stealth control structure of the radial flame channel of the afterburner of the aero-engine provided by the embodiments of the present application;

[0026] Figure 7 is a partial view of the schematic diagram of Figure 6

[0027] Figure 8 is a partial top view of the schematic diagram of Figure 7

[0028] wherein:

[0029] 1 - outer wall of the afterburner; 2 - outer annular flame stabilizer; 3 - inner annular flame stabilizer; 4 - radial flame channel; 5 - baffle; 6 - driving rod; 7 - hinged rod; 8 - linkage ring.

[0030] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual size of the product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly, completely and specifically described below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0032] ​​​​In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application indicate relative directions or positional relationships, and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship can change accordingly when the absolute position of the described object changes, and therefore cannot be understood as a limitation on the present application. The words "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The words "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as the presence of at least one. The words "including" or "containing" and the like used in the description of the present application mean that the elements or objects appearing before the words are encompassed by the elements or objects listed after the words and their equivalents, and other elements or objects are not excluded.

[0033] In addition, it should be noted that, unless otherwise specified and limited, the words "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood broadly, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the connection between two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0034] The following will be described in detail in combination with the accompanying drawings Figures 1 to 8 The present application will be further described in detail.

[0035] An aero-engine afterburner radial flame channel radar stealth control structure, comprising:

[0036] A plurality of radial flame channels 4, which are V-shaped in cross section, are arranged circumferentially in the outer wall 1 of the afterburner, and are connected to the trailing edges of the outer annular flame stabilizer 2 and the inner annular flame stabilizer 3;

[0037] A plurality of pairs of baffles 5 are hinged on the two side walls of each radial flame channel 4;

[0038] A plurality of drive rods 6 extend into the interior of each radial flame channel 4 from the outer end;

[0039] A plurality of pairs of hinged rods 7 are arranged in each radial flame channel 4 and are hinged between each pair of baffles 5 and each drive rod 6;

[0040] The linkage ring 8 is sleeved on the outer periphery of the outer annular flame stabilizer 2, connects the other ends of the driving rods 6, can move axially along the outer wall 1 of the afterburner, and further drives the pairs of baffles 5 to close or open through the driving rods 6 and the pairs of hinged rods 7.

[0041] When the pairs of baffles 5 are closed, there is an included angle therebetween.

[0042] When the pairs of baffles 5 are opened, the pairs of baffles 5 are flattened with the two side walls of the radial flame transmission grooves 4.

[0043] For the above-mentioned afterburner radial flame transmission groove radar stealth control structure of the aero-engine, those skilled in the art can understand that a plurality of pairs of baffles 5 are additionally arranged in each radial flame transmission groove 4, and a control mechanism composed of the driving rods 6, the hinged rods 7 and the linkage ring 8 is designed. When the aero-engine is in normal operation, like in subsonic cruise requiring radar stealth, the actuating cylinder drives the linkage ring 8 to move axially along the outer wall 1 of the afterburner forward, and drives the pairs of baffles 5 to close through the driving rods 6 and the pairs of hinged rods 7, so as to shield the inner surfaces of the radial flame transmission grooves 4. As shown in the figure, at this time, the radar wave can only irradiate the outer surfaces of the pairs of baffles 5, but cannot irradiate the inner surfaces of the radial flame transmission grooves 4, and there is an included angle between the pairs of baffles 5 when they are closed, so that the scattering wave of the radar wave irradiating the outer surfaces of the pairs of baffles 5 is scattered inwardly along the outer wall 1 of the afterburner, but will not return along the incident direction, so as to reduce the radar characteristic signal and ensure the radar stealth performance of the aero-engine. When the aero-engine is in afterburning state, the actuating cylinder drives the linkage ring 8 to move axially along the outer wall 1 of the afterburner backward, and drives the pairs of baffles 5 to open through the driving rods 6 and the pairs of hinged rods 7. As shown in the figure, at this time, the pairs of baffles 5 are flattened with the two side walls of the radial flame transmission grooves 4, which can be regarded as the extension of the two side walls of the radial flame transmission grooves 4, and will not damage the flame transmission function of the radial flame transmission grooves 4 in the afterburning state, so as to ensure the stable operation of the afterburner and effectively balance the radar stealth performance required when the aero-engine is in normal operation and the stable operation of the aero-engine in the afterburning state. Figures 3-5 Figures 6-8

[0044] In some optional embodiments, in the above-mentioned afterburner radial flame transmission groove radar stealth control structure of the aero-engine, one end of each pair of baffles 5 is hinged to the trailing edge of the two side walls of each radial flame transmission groove 4 through a rotating shaft.

[0045] In some optional embodiments, in the above-mentioned afterburner radial flame transmission groove radar stealth control structure of the aero-engine, one end of each pair of hinged rods 7 is hinged to the end of each driving rod 6 extending into the interior of the radial flame transmission groove 4 through a pin, and the other end is hinged to the inner side of each pair of baffles 5 through the cooperation of the single and double ear structures and a pin shaft.

[0046] ​​In some alternative embodiments, in the above-mentioned radar stealthy control structure of the radial flame channel of the afterburner of the aero-engine, when each pair of baffles 5 is closed, the angle between the two sides is between 45° and 75°, so as to ensure the radar stealth performance of the aero-engine in a large angle range.

[0047] In some alternative embodiments, in the above-mentioned radar stealthy control structure of the radial flame channel of the afterburner of the aero-engine, when each pair of baffles 5 is closed, the angle between the two sides is between 45° and 75°, so as to ensure the radar stealth performance of the aero-engine in a large angle range.

[0048] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts between each embodiment can be referred to each other.

[0049] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Without deviating from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the related technical features. The technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A radar-invisible thrust chamber control structure for a radial flame channel of a turbojet engine, characterized in that, It comprises: a plurality of radial flame channels (4) in the shape of V cross-section, circumferentially arranged in the outer wall (1) of the afterburner, connected to the trailing edges of the outer annular flame holder (2) and the inner annular flame holder (3); a plurality of pairs of baffles (5) hinged to the two side walls of each radial flame channel (4); a plurality of drive rods (6) with one end extending into each radial flame channel (4) from the outer end; a plurality of pairs of hinged rods (7) arranged in each radial flame channel (4) and hinged between each pair of baffles (5) and each drive rod (6); a linkage ring (8) sleeved on the outer periphery of the outer annular flame holder (2) and connected to the other end of each drive rod (6), capable of moving axially along the outer wall (1) of the afterburner, thereby driving each pair of baffles (5) to close or open through each drive rod (6) and each pair of hinged rods (7); when each pair of baffles (5) is closed, there is an included angle between them; when each pair of baffles (5) is opened, it is in contact with the two side walls of each radial flame channel (4).

2. The radar stealth control structure of the radial flame channel of the afterburner of the aero-engine according to claim 1, wherein one end of each pair of baffles (5) is hinged to the trailing edge of the two side walls of each radial flame channel (4) through a rotating shaft.

3. The radar stealth control structure of the radial flame channel of the afterburner of the aero-engine according to claim 1, wherein one end of each pair of hinged rods (7) is hinged to the end of each drive rod (6) extending into the radial flame channel (4) through a pin, and the other end is hinged to the inner side of each pair of baffles (5) through the cooperation of a single and double ear structure using a pin shaft.

4. The radar stealth control structure of the radial flame channel of the afterburner of the aero-engine according to claim 1, wherein when each pair of baffles (5) is closed, they are in contact with each other at an angle of 45°-75°.

5. The radar stealth control structure of the radial flame channel of the afterburner of the aero-engine according to claim 1, wherein when each pair of baffles (5) is opened, it is in contact with the two side walls of each radial flame channel (4) at an angle.

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