Aero-engine infrared radiation signal control S-bend nozzle

Abstract

The application belongs to the technical field of S-bend nozzle design of an aero-engine, and particularly relates to an aero-engine infrared radiation signal control S-bend nozzle, which comprises a round-to-square section, an inlet end of which is used to be connected to the rear end of a low-pressure turbine; an S-bend left side wall, an S-bend right side wall, an S-bend lower side wall and an S-bend upper side wall are connected to the outlet end of the round-to-square section, are spliced with each other, and the S-bend upper side wall has a plurality of impact cooling holes on the rearward visible part thereof, and the outer wall has an annular support edge surrounding the rearward visible part; a cover plate is connected to the annular support edge and has a low-temperature medium inlet hole thereon; a flow divider plate is arranged in the annular support edge, is connected to the cover plate, forms a flow dividing cavity with the cover plate, has a plurality of flow dividing holes thereon, and forms an impact cooling cavity with the S-bend upper side wall; a heat shield is connected to the inner side of the S-bend upper side wall, covers the rearward visible part, forms a heat insulation cavity with the S-bend upper side wall, and has a plurality of air film holes thereon.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of S-bend nozzle design of an aero-engine, and particularly relates to an aero-engine infrared radiation signal control S-bend nozzle. BACKGROUND

[0002] The S-bend nozzle is adopted in the design of an aero-engine, and the S-shaped bend is used to shield the low-pressure turbine high-temperature components at the rear end of the aero-engine, so as to reduce the infrared radiation signal strength and improve the infrared stealth performance of the aero-engine.

[0003] The exhaust gas of the aero-engine has a high temperature, which causes the upper side wall curved part of the S-bend nozzle to have a high temperature. Meanwhile, the part is a rearward visible part, the infrared radiation signal of which will be captured, affecting the infrared stealth performance of the aero-engine, and the S-bend nozzle does not have the adjustment and control ability for the infrared radiation signal strength, and it is difficult to quickly reduce the strength of the infrared radiation signal in a short time, which cannot meet the demand of the aero-engine in some situations to quickly enhance the infrared stealth performance in a short time.

[0004] The present application is proposed in view 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 an aero-engine infrared radiation signal suppression S-bend nozzle to overcome or alleviate at least one aspect of the known technical defects.

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

[0008] An aero-engine infrared radiation signal control S-bend nozzle, comprising:

[0009] a round-to-square section, the inlet end of which is connected to the rear end of a low-pressure turbine;

[0010] a S-bend left side wall, the front end of which is connected to the left side of the outlet end of the round-to-square section;

[0011] a S-bend right side wall, the front end of which is connected to the right side of the outlet end of the round-to-square section;

[0012] a S-bend lower side wall, the front end of which is connected to the lower side of the outlet end of the round-to-square section;

[0013] The S-bend upper side wall is connected to the upper side of the outlet end of the round-to-square section, and is connected to the left side wall of the S-bend, the right side wall of the S-bend and the lower side wall of the S-bend, and a plurality of impact cooling holes are arranged on the rear visual part of the S-bend upper side wall, and the outer wall has an annular support edge surrounding the rear visual part;

[0014] The cover plate is connected to the annular support edge, and has a low-temperature medium inlet hole;

[0015] The flow distribution plate is arranged in the annular support edge and connected to the cover plate, and forms a flow distribution cavity with the cover plate, and has a plurality of flow distribution holes, and forms an impact cooling cavity with the S-bend upper side wall;

[0016] The heat shield is connected to the inner side of the S-bend upper side wall and covers the rear visual part, and forms a heat insulation cavity with the S-bend upper side wall, and has a plurality of air film holes.

[0017] According to at least one embodiment of the present application, in the above-mentioned S-bend nozzle controlled by an aero-engine infrared radiation signal, the annular support edge has an outward annular fold;

[0018] The edge part of the cover plate is connected to the outward annular fold by a bolt.

[0019] According to at least one embodiment of the present application, in the above-mentioned S-bend nozzle controlled by an aero-engine infrared radiation signal, a plurality of supports are designed between the cover plate and the flow distribution plate and connected by bolts.

[0020] According to at least one embodiment of the present application, in the above-mentioned S-bend nozzle controlled by an aero-engine infrared radiation signal, the rear visual part of the inner side of the S-bend upper side wall is locally recessed to form a groove;

[0021] The edge part of the heat shield is bent to form a bent edge, the bent edge is clamped into the groove, and the heat shield is supported on the inner side of the S-bend upper side wall, so that the heat shield is flush with the inner side of the S-bend upper side wall and smoothly transitions.

[0022] According to at least one embodiment of the present application, in the above-mentioned S-bend nozzle controlled by an aero-engine infrared radiation signal, the S-bend upper side wall and the heat shield are fastened by bolts.

[0023] According to at least one embodiment of the present application, in the above-mentioned S-bend nozzle controlled by an aero-engine infrared radiation signal, further comprising:

[0024] The horn mouth is connected to the cover plate and communicates with the low-temperature medium inlet hole, and communicates with a low-temperature medium source through a pipeline, and the low-temperature medium source is low-temperature air or liquid nitrogen. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a schematic diagram of an aero-engine infrared radiation signal controlled S-bend nozzle provided by the embodiments of the present application;

[0026] Figure 2 is an assembly schematic diagram of the S-shaped nozzle controlled by the infrared radiation signal of the aero-engine provided by the embodiment of the present application;

[0027] Figure 3 is a partial schematic diagram of the S-shaped nozzle controlled by the infrared radiation signal of the aero-engine provided by the embodiment of the present application;

[0028] Figure 4 is a schematic diagram of the rearward visible part of the S-shaped nozzle controlled by the infrared radiation signal of the aero-engine provided by the embodiment of the present application;

[0029] wherein:

[0030] 1-circular-to-square segment; 2-left side wall of S-shaped nozzle; 3-right side wall of S-shaped nozzle; 4-lower side wall of S-shaped nozzle; 5-upper side wall of S-shaped nozzle; 6-cover plate; 7-dividing plate; 8-heat shield; 9-horn.

[0031] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0032] 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 and completely described below in combination with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application, but not to limit the present application. It should be noted that, for the convenience 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.

[0033] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the application shall be understood as having the common meaning to those of ordinary skill in the art to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like, which indicate orientation in the description of the application, are used only to indicate relative directional or positional relationship, and not to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and when the absolute position of the described object changes, the relative positional relationship may also change accordingly, and therefore cannot be understood as a limitation on the application. The words "first", "second", "third" and the like used in the description of the 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 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 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.

[0034] 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 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 internal communication of two elements, and those skilled in the art can understand the specific meaning of the words in the application according to the specific circumstances.

[0035] The following will be described in detail in combination with the accompanying drawings Figures 1 to 4 The application will be further described in detail.

[0036] An aero-engine infrared radiation signal control S-bend nozzle, as shown in the figure, comprising: Figure 2

[0037] The circular-to-square segment 1 is connected to the low-pressure turbine at the inlet end.

[0038] The S-bend left side wall 2 is connected to the left side of the outlet end of the circular-to-square segment 1.

[0039] The S-bend right side wall 3 is connected to the right side of the outlet end of the circular-to-square segment 1.

[0040] The S-bend lower side wall 4 is connected to the lower side of the outlet end of the circular-to-square segment 1.

[0041] ​S-bend upper side wall 5, front end connected to the upper side of the outlet end of the round-to-square section 1, and spliced with the S-bend left side wall 2, the S-bend right side wall 3, and the S-bend lower side wall 4, and has a plurality of impact cooling holes on the rearward visible part, and the outer wall has an annular support edge surrounding the rearward visible part;

[0042] Cover plate 6 connected to the annular support edge, and having a low-temperature medium inlet hole thereon;

[0043] Flow distribution plate 7 arranged in the annular support edge and connected to the cover plate 6, forming a flow distribution cavity therebetween, and having a plurality of flow distribution holes thereon, and forming an impact cooling cavity between the S-bend upper side wall 5;

[0044] Thermal shield 8 connected to the inner side of the S-bend upper side wall 5, covering the rearward visible part, and forming a thermal insulation cavity therebetween, and having a plurality of air film holes thereon.

[0045] The above embodiment discloses an aero-engine infrared radiation signal control S-bend nozzle. When the aero-engine is working, low-temperature medium can be introduced into the flow distribution cavity through the low-temperature medium inlet hole, and the low-temperature medium is uniformly distributed in the flow distribution cavity and uniformly flows into the impact cooling cavity through the flow distribution holes, uniformly impact-cooling the rearward visible part of the S-bend upper side wall 5, and then flows into the thermal insulation cavity through the impact cooling holes and flows out through the air film holes, and is mixed into the aero-engine exhaust, as shown in Figure 3 , so that the rearward visible part of the S-bend nozzle maintains a lower temperature, thereby reducing the infrared radiation signal intensity of the rearward visible part of the S-bend nozzle and improving the infrared stealth performance of the aero-engine. Moreover, by controlling the flow of low-temperature medium, the temperature of the rearward visible part of the S-bend nozzle and its infrared radiation signal intensity can be controlled, so that the aero-engine can maintain stable infrared stealth performance. In addition, by controlling a large amount of low-temperature medium to be introduced in a short time, the temperature of the rearward visible part of the S-bend nozzle can be rapidly reduced in a short time, so that the infrared radiation signal intensity of the aero-engine can be rapidly suppressed in a short time, meeting the demand for rapidly enhancing the infrared stealth performance of the aero-engine in some situations in a short time.

[0046] In some optional embodiments, the aero-engine infrared radiation signal control S-bend nozzle described above has an outward annular folded edge on the annular support edge;

[0047] The edge part of the cover plate 6 is connected to the outward annular folded edge by bolts.

[0048] In some optional embodiments, the aero-engine infrared radiation signal control S-bend nozzle described above has a plurality of supports designed between the cover plate 6 and the flow distribution plate 7, and connected by bolts.

[0049] In some optional embodiments, in the above-mentioned aircraft engine infrared radiation signal control S-bend nozzle, the inner rearward visible part of the upper sidewall 5 of the S-bend is locally recessed to form a groove.

[0050] The edge of the heat insulation screen 8 is bent to form a bent edge, which is inserted into the groove and supported on the inner side of the upper side wall 5 of the S-bend. This stable heat insulation cavity is constructed, and the heat insulation screen 8 is flush with the inner side of the upper side wall 5 of the S-bend, with a smooth transition to ensure aerodynamic performance.

[0051] In some optional embodiments, in the above-mentioned aircraft engine infrared radiation signal control S-bend nozzle, the upper sidewall 5 of the S-bend and the heat shield 8 are fastened together by bolts.

[0052] In some optional embodiments, the aforementioned aircraft engine infrared radiation signal controlled S-curve nozzle further includes:

[0053] The flared mouth 9 is connected to the cover plate 6 and communicates with the cryogenic medium inlet. It is connected to the cryogenic medium source through a pipeline. The cryogenic medium source is cryogenic air or liquid nitrogen, which has a low temperature. The cryogenic medium can flow into the flared mouth 9 through the pipeline, where it is diffused and its speed reduced to make the flow smooth. Then it flows into the diversion chamber through the cryogenic medium inlet. The flow rate of the cryogenic medium can be controlled by setting appropriate valves on the pipeline and connecting to the aero-engine control system.

[0054] In some optional embodiments, in the aforementioned aircraft engine infrared radiation signal controlled S-curve nozzle, to ensure temperature control of the rearward visible portion of the upper sidewall 5 of the S-curve, the cover plate 6, the diffuser 7, the heat shield 8, and their corresponding structures can be designed to cover an area slightly larger than the rearward visible portion of the upper sidewall 5 of the S-curve. Figure 4 As shown.

[0055] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0056] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 all fall within the scope of protection of this application.

Claims

1. An S-curve nozzle for controlling infrared radiation signals in an aero-engine, characterized in that, include: The round-to-square section (1) has its inlet end connected to the rear end of the low-pressure turbine; The left side wall (2) of the S-bend is connected at the left end of the exit end of the round-to-square section (1); The right side wall (3) of the S-bend is connected at the right end of the exit end of the round-to-square section (1); The lower side wall of the S-bend (4) is connected at the front end to the lower side of the outlet end of the round-to-square section (1); The upper side wall (5) of the S-bend is connected to the upper side of the outlet end of the round-to-square section (1) and is spliced ​​with the left side wall (2), the right side wall (3) of the S-bend, and the lower side wall (4) of the S-bend. The upper rear visible part has multiple impact cooling holes, and the outer wall has an annular support edge surrounding the rear visible part. Cover plate (6) is connected to the annular support edge and has a low temperature medium inlet hole; The flow divider (7) is set inside the annular support edge and connected to the cover plate (6). It forms a flow divider cavity with the cover plate (6) and has multiple flow divider holes. It forms an impact cooling cavity with the upper side wall (5) of the S-bend. The heat insulation screen (8) is connected to the inner side of the upper sidewall (5) of the S-bend, covering the rear visible part, and forming a heat insulation cavity between it and the upper sidewall (5) of the S-bend, and has multiple air film holes. The flared mouth (9) is connected to the cover plate (6) and communicates with the low temperature medium inlet hole. It is connected to the low temperature medium source through the pipeline. The low temperature medium source is liquid nitrogen. The cover plate (6), the diversion plate (7), the heat shield (8) and their corresponding structures cover an area slightly larger than the rearward visible part on the upper sidewall (5) of the S-bend; The upper sidewall (5) of the S-bend and the heat insulation screen (8) are fastened together with bolts.

2. The S-curve nozzle for controlling infrared radiation signals of an aero-engine according to claim 1, characterized in that, The annular support edge has an outward annular folded edge; The edge of the cover plate (6) is connected to the outward annular folded edge by bolts.

3. The S-curve nozzle for controlling infrared radiation signals of an aero-engine according to claim 1, characterized in that, Multiple supports are designed between the cover plate (6) and the diverter plate (7), which are connected by bolts.

4. The S-curve nozzle for controlling infrared radiation signals of an aero-engine according to claim 1, characterized in that, The inner rear visible part of the upper sidewall (5) of the S-bend is locally recessed, forming a groove; The edge of the heat insulation screen (8) is bent to form a bent edge. The bent edge is inserted into the groove and supported on the inner side of the upper side wall (5) of the S-bend, so that the heat insulation screen (8) is flush with the inner side of the upper side wall (5) of the S-bend and the transition is smooth.

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