Aeroengine dual-mode nozzle

Abstract

The application belongs to the technical field of aero-engine binary nozzle design, and particularly relates to an aero-engine binary nozzle, high-temperature gas in an aero-engine, which can be discharged through a passage formed by a round-to-square section, a converging section, a diverging section, a front section side wall and a rear section side wall, and cooling air can be introduced into a cooling air cavity from the outside through a cooling air introduction hole, part of the cooling air can be discharged through a cooling air discharge hole, the part of the cooling air can cool the converging section, the diverging section and an outer adjusting sheet along the passage, another part of the cooling air can enter a cooling air cavity through a cooling communication hole, and then be discharged through a rearward air discharge slot, the part of the cooling air can cool a front section side wall and a side wall cover along the passage, and the cooling air discharged from the rearward air discharge slot can form a cooling air film on the inner side of the rear section side wall to cool the rear section side wall along the passage.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine binary nozzle design, and particularly relates to an aero-engine binary nozzle. BACKGROUND

[0002] The aero-engine binary nozzle is installed at the end of an aero-engine, uses the converging and expanding movement of internal components such as converging sections and diverging sections for vector adjustment, and is designed with external adjusting pieces and side wall covers to protect the internal components from direct damage by external forces, to regulate the outside, and to reduce the afterbody drag.

[0003] The internal components of the aero-engine binary nozzle directly contact with high-temperature airflow, bear extremely high temperature, are easy to be ablated, and have obvious infrared radiation characteristics. At present, the internal components are cooled by the external bypass airflow to avoid ablation and inhibit infrared radiation characteristics, but the demand for the external bypass airflow is difficult to match the state of the aero-engine in many cases, does not have the ability of active adjustment, and cannot achieve the expected effect. In addition, the internal components of the aero-engine binary nozzle are subjected to radiation of high-temperature airflow, bear high temperature, are easy to deform and warp, have obvious infrared radiation characteristics, and are not conducive to the infrared stealth performance of the aero-engine.

[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 binary 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 binary nozzle comprises:

[0009] A round-to-square section, the front end of which is connected to the rear end of an aero-engine, and the rear end of which has a connecting edge;

[0010] Two converging sections, the front ends of which are hingedly connected to the connecting edges of the two opposite side walls at the rear end of the round-to-square section, and the connecting edges of the two opposite side walls at the rear end of the round-to-square section having cooling bleed holes;

[0011] Two diverging sections, the front ends of which are hingedly connected to the rear ends of the two converging sections;

[0012] Two outer adjusting pieces are located outside the two converging sections and the two diverging sections, the front end of the two outer adjusting pieces is hinged on the connecting edges of the two opposite side walls at the rear end of the round-to-square section, and the rear end side wall is provided with a plurality of cooling exhaust holes;

[0013] Two front section side walls are connected on the connecting edges of the other two opposite side walls at the rear end of the round-to-square section, and form a cooling air guide cavity with the two converging sections, the two diverging sections and the two outer adjusting pieces, and the cooling air guide cavity is provided with a plurality of cooling communication holes; the cooling air guide cavity is connected with each cooling air guide hole, cooling exhaust hole and cooling communication hole;

[0014] Two rear section side walls are connected at the front end of the two front section side walls, and form a rear exhaust slot between the rear end of the two front section side walls;

[0015] Two side wall covers are located outside the two front section side walls and the two rear section side walls, the front end of the two side wall covers is connected on the connecting edges of the two opposite side walls at the rear end of the round-to-square section, and the two side wall covers are connected along the edges of the two front section side walls and the two rear section side walls, and form a cooling exhaust cavity between the two front section side walls and the two rear section side walls; the cooling exhaust cavity is connected with each cooling communication hole and rear exhaust slot.

[0016] According to at least one embodiment of the present application, in the above-mentioned aero-engine binary nozzle, the rear end of the two diverging sections and the two outer adjusting pieces is in a pointed cone shape;

[0017] Each cooling exhaust hole is distributed along the edge of the rear end of the two diverging sections and the two outer adjusting pieces;

[0018] The two front section side walls, the two rear section side walls and the two side wall covers are in a V shape as a whole;

[0019] The rear exhaust slot is in a rearwardly expanding V shape.

[0020] According to at least one embodiment of the present application, in the above-mentioned aero-engine binary nozzle, the flow area of the two cooling air guide holes is 1-2 times the flow area of each cooling exhaust hole and cooling communication hole;

[0021] The flow area of each cooling communication hole is 1-2 times the flow area of the two rear exhaust slots.

[0022] According to at least one embodiment of the present application, in the above-mentioned aero-engine binary nozzle, the two outer adjusting pieces are inwardly converging.

[0023] According to at least one embodiment of the present application, in the above-mentioned aero-engine binary nozzle, further comprising:

[0024] Two pipe connection nozzles are connected on the connecting edges of the two opposite side walls at the rear end of the round-to-square section, and are connected with the two cooling air guide holes;

[0025] Two spherical connection nozzles;

[0026] Two compression caps are sleeved on the outer periphery of the two spherical connectors and are connected with the two pipe connectors through thread cooperation, so as to compress the two spherical connectors on the pipe connector, and the spherical tapered surfaces of the two spherical connectors and the pipe connector are in cooperation and contact;

[0027] Two air injection pipes are connected on the two spherical connectors and are communicated with the external air source.

[0028] Two flow control valves are arranged on the two air injection pipes. BRIEF DESCRIPTION OF DRAWINGS

[0029] Fig. 1 is a schematic diagram of an external shape of an aero-engine dual-element nozzle provided by the embodiment of the present application;

[0030] Fig. 2 is a cross-sectional view of the aero-engine dual-element nozzle along the axial direction provided by the embodiment of the present application;

[0031] Fig. 3 is a schematic diagram of the aero-engine dual-element nozzle without a side wall cover provided by the embodiment of the present application;

[0032] Fig. 4 is a combined schematic diagram of the pipe connector, the spherical connector, the compression cap, the air injection pipe and the flow control valve provided by the embodiment of the present application;

[0033] wherein:

[0034] 1-circular-to-square segment; 2-converging segment; 3-expanding segment; 4-outer adjusting piece; 5-fore segment side wall; 6-aft segment side wall; 7-side wall cover; 8-pipe connector; 9-spherical connector; 10-compression cap; 11-air injection pipe; 12-flow control valve;

[0035] A-cooling air injection hole;

[0036] B-cooling exhaust hole;

[0037] C-cooling communication hole;

[0038] D-aft exhaust slot.

[0039] In order to better illustrate the embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for exemplary illustration and cannot be understood as a limitation on the present application. DETAILED DESCRIPTION

[0040] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described below in conjunction with the drawings. It should be understood that the specific embodiments described herein are only partial 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 general 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.

[0041] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meanings understood by the general technical personnel in the field to which the present application belongs. The words indicating the direction or position relationship such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the present application description are only used to indicate the relative direction or position relationship, but not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and the relative position relationship thereof can also be changed accordingly when the absolute position of the described object is changed, therefore it cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the present application description are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the present application description should not be understood as an absolute limitation on the quantity, but should be understood as the existence of at least one. The "including" or "containing" and the like used in the present application description means that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, and do not exclude other elements or objects.

[0042] In addition, it should be further noted that, unless otherwise specified and limited, the "mounting", "connection", "connection" and the like used in the present application description should be understood in a broad sense, 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 the person skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0043] The technical solutions of the present application will be further described below in conjunction with the drawings Figs. 1 to 4 The present application will be further described below.

[0044] An aero-engine binary nozzle comprises:

[0045] The circular-to-square segment 1 is connected at the front end to the rear end of the aero-engine, and the outer wall of the rear end has a connecting edge;

[0046] Two converging sections 2, the front end is hinged on the connecting edges of the two opposite side walls at the rear end of the round-to-square section 1, and the connecting edges of the two opposite side walls at the rear end of the round-to-square section 1 are provided with cooling air inlet holes A;

[0047] Two diverging sections 3, the front end is hinged on the rear end of the two converging sections 2;

[0048] Two outer adjusting pieces 4, located outside the two converging sections 2 and the diverging sections 3, the front end is hingedly connected on the connecting edges of the two opposite side walls at the rear end of the round-to-square section 1, and the rear end side walls are provided with a plurality of cooling air outlet holes B;

[0049] Two front section side walls 5, the front end is connected on the connecting edges of the other two opposite side walls at the rear end of the round-to-square section 1, and the cooling air inlet cavity is formed between the two converging sections 2, the diverging sections 3 and the outer adjusting pieces 4, and a plurality of cooling communication holes C are distributed thereon; the cooling air inlet cavity is connected with each cooling air inlet hole A, cooling air outlet hole B and cooling communication hole C;

[0050] Two rear section side walls 6, the front end is connected at the rear end of the two front section side walls 5, and the rearward air outlet slot D is formed between the rear end of the two front section side walls 5;

[0051] Two side wall outer covers 7, located outside the two front section side walls 5 and the rear section side walls 6, the front end is connected on the connecting edges of the two opposite side walls at the rear end of the round-to-square section 1, and is connected along the edges with the two front section side walls 5 and the rear section side walls 6, and the cooling air outlet cavity is formed between the two front section side walls 5 and the rear section side walls 6; the cooling air outlet cavity is connected with each cooling communication hole C and rearward air outlet slot D; the cooling air outlet cavity is separated by a partition plate, and forms two independent cavities corresponding to the front section side walls 5 and the rear section side walls 6;

[0052] For the above-mentioned embodiment of the aero-engine binary nozzle, it can be understood by those skilled in the art that the high-temperature gas in the aero-engine can be discharged through the channel formed by the round-to-square section 1, the converging section 2, the diverging section 3, the front section side wall 5 and the rear section side wall 6, and at the same time, cooling air can be introduced into the cooling air inlet cavity from the outside through the cooling air inlet hole A; part of the cooling air can be discharged through the cooling air outlet hole B, and this part of the cooling air can cool the converging section 2, the diverging section 3 and the outer adjusting piece 4 along the way; another part of the cooling air can enter the cooling air outlet cavity through the cooling communication hole C, and then be discharged through the rearward air outlet slot D, and this part of the cooling air can cool the front section side wall 5 and the side wall outer cover 7 along the way; the cooling air discharged from the rearward air outlet slot D can form a cooling air film on the inner side of the rear section side wall 6, and cool the rear section side wall 6 along the way.

[0053] For the above-mentioned aero-engine binary nozzle disclosed in the embodiments, those skilled in the art can understand that the design introduces external cooling gas to cool the internal and external components along the way, such as the convergent section 2, the divergent section 3, the outer adjustment piece 4, the front section side wall 5, the rear section side wall 6, and the side wall cover 7. By controlling the flow of cooling gas, the cooling effect on the internal and external components can be ensured, the infrared radiation characteristics of the internal and external components can be effectively suppressed, the infrared stealth performance of the aero-engine can be ensured, and the internal components can be prevented from being ablated and the external components from being deformed and warped. Moreover, the external flow is not used, and there is no need to worry about the matching problem with the state of the aero-engine.

[0054] In the above-mentioned aero-engine binary nozzle disclosed in the embodiments, the connection relationship and the specific structure design among the round-to-square section 1, the convergent section 2, the divergent section 3, and the outer adjustment piece 4 can be specifically referred to CN113107706, and will not be described in more detail here.

[0055] In some optional embodiments, in the above-mentioned aero-engine binary nozzle, the rear ends of the two divergent sections 3 and the outer adjustment piece 4 are in a pointed cone shape, the cooling exhaust holes B are distributed along the rear end edges of the two divergent sections 3 and the outer adjustment piece 4, the two front section side walls 5, the rear section side wall 6, and the side wall cover 7 are in a V shape as a whole, and the rearward exhaust slots D are in a rearwardly expanding V shape, so as to ensure the aerodynamic performance of the aero-engine binary nozzle, achieve better cooling effect, and have better radar stealth performance.

[0056] In some optional embodiments, in the above-mentioned aero-engine binary nozzle, the flow area of the two cooling air inlet holes A is 1-2 times the flow area of each cooling exhaust hole B and cooling communication hole C, and the flow area of each cooling communication hole C is 1-2 times the flow area of the two rearward exhaust slots D, so as to ensure the flow capacity of the introduced external cooling gas and ensure the cooling effect on the internal and external components.

[0057] In some optional embodiments, in the above-mentioned aero-engine binary nozzle, the two outer adjustment pieces 4 converge inward, so that the cooling gas discharged through each cooling exhaust hole B converges inward, can be wrapped and mixed with the high-temperature gas discharged from the aero-engine binary nozzle, so as to reduce noise and exhaust temperature and improve stealth effect.

[0058] In some optional embodiments, in the above-mentioned aero-engine binary nozzle, it further comprises:

[0059] Two pipe connectors 8 are connected to the connecting edges of the two opposite side walls at the rear end of the round-to-square section 1 and communicate with the two cooling air inlet holes A;

[0060] Two spherical connectors 9;

[0061] Two compression caps 10 are sleeved on the outer periphery of the two spherical connecting nozzles 9 and are connected with the two pipe connecting nozzles 8 in a threaded fit, so as to compress the two spherical connecting nozzles 9 on the pipe connecting nozzles 8, and the spherical taper surfaces of the two spherical connecting nozzles 9 and the pipe connecting nozzles 8 are in fit contact, so as to ensure the sealing performance and facilitate disassembly and assembly;

[0062] Two air induction pipes 11 are connected on the two spherical connecting nozzles 9 and are connected with the external air source, so that the external cooling air can be introduced to the cooling air induction holes by the air induction pipes 11.

[0063] Two flow control valves 12 are arranged on the two air induction pipes 11 and can control the flow of the cooling air.

[0064] At high altitudes, the air temperature is low, and with the increase of the height, the environmental temperature sharply decreases. Under the cruising state of the aircraft, the environmental temperature can reach -70 to -30℃. For example, at 11 km, the air temperature is -50℃, and above 15 km, it reaches below -70℃. The binary nozzle of the aero-engine disclosed in the above embodiment can effectively utilize the external low-temperature air, actively control the introduction of the external low-temperature air into the cavity of the high-temperature nozzle member through the flow control valve 12, cool the high-temperature nozzle member, enhance the stealth capability, and enhance the component life and reliability.

[0065] The binary nozzle of the aero-engine disclosed in the above embodiment can actively control the flow of the introduced cooling air. On the one hand, through the increase of the flow and pressure, the problem of low component life and reliability and poor stealth performance caused by the backflow of the high-temperature main flow in the binary nozzle is solved. On the other hand, according to the actual scene demand, the cooling air flow can be increased or decreased as needed. For example, in the escape, the cooling air flow can be actively controlled to be increased, and in the conventional cruising state, the flow can be adjusted to a moderate state.

[0066] The binary nozzle of the aero-engine disclosed in the above embodiment can flow out the cooling air from the holes on the nozzle cover and the nozzle side wall, which can be mixed with the high-temperature main flow. Especially, the cooling air is discharged from the holes on the nozzle cover, which is discharged to the high-temperature main flow and also sucked into the external air, which can enhance the heat exchange with the high-temperature main flow, reduce the length of the high-temperature core area of the main flow of the exhaust gas of the nozzle, and thus effectively reduce the infrared radiation intensity of the jet flow.

[0067] The progressive manner is adopted in the description of each embodiment in the specification, and each embodiment focuses on the difference from other embodiments. The same and similar parts of each embodiment can be referred to each other.

[0068] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and 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, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A two-dimensional nozzle for an aero-engine, characterized in that, include: The round-to-square section (1) is connected at the front end to the rear end of the aircraft engine, and the outer wall of the rear end has a connecting edge; Two converging segments (2) are hinged at the front end to the connecting edge of the two opposite side walls at the rear end of the round-to-square segment (1). The connecting edge of the two opposite side walls at the rear end of the round-to-square segment (1) has a cooling air vent (A). Two expansion segments (3) are hinged at the front end to the rear end of two convergence segments (2); Two external adjustment plates (4) are located outside the two converging sections (2) and expanding sections (3). The front end is hinged to the connecting edge of the two opposite side walls at the rear end of the round-to-square section (1). Multiple cooling exhaust holes (B) are distributed on the rear side wall. Two front sidewalls (5) are connected at the front end to the connecting edge of the other two opposite sidewalls at the rear end of the round-to-square section (1), forming a cooling air chamber between the two converging sections (2), the expanding section (3), and the outer adjusting plate (4), and multiple cooling connecting holes (C) are distributed on it; the cooling air chamber connects to each cooling air hole (A), cooling exhaust hole (B), and cooling connecting hole (C); Two rear sidewalls (6) are connected at the front end to the rear end of two front sidewalls (5), forming a rearward exhaust slit (D) between them and the rear end of the two front sidewalls (5). Two sidewall covers (7) are located outside the two front sidewalls (5) and the rear sidewalls (6). The front end is connected to the connecting edge of the two opposite sidewalls at the rear end of the round-to-square section (1), and is connected to the two front sidewalls (5) and the rear sidewalls (6) along the edge. A cooling exhaust chamber is formed between the two front sidewalls (5) and the rear sidewalls (6). The cooling exhaust chamber is connected to each cooling connecting hole (C) and the rear exhaust slit (D).

2. The two-dimensional nozzle for an aero-engine according to claim 1, characterized in that, The two expansion sections (3) and the rear end of the outer adjustment plate (4) are conical; Each cooling exhaust hole (B) is distributed along the rear edge of the two expansion sections (3) and the outer adjustment plate (4); The two front sidewalls (5), the rear sidewall (6), and the sidewall cover (7) are V-shaped as a whole; The rear exhaust vent (D) is a V-shaped vent that widens rearward.

3. The two-dimensional nozzle for an aero-engine according to claim 1, characterized in that, The flow area of ​​the two cooling air vents (A) is 1 to 2 times the flow area of ​​each cooling exhaust vent (B) and cooling connecting vent (C); The flow area of ​​each cooling connection hole (C) is 1 to 2 times the flow area of ​​the two rear exhaust slits (D).

4. The two-dimensional nozzle for an aero-engine according to claim 1, characterized in that, The two external adjustment plates (4) converge inward.

5. The two-dimensional nozzle for an aero-engine according to claim 1, characterized in that, Also includes: Two pipe fittings (8) are connected to the connecting edges of the two opposite side walls at the rear end of the round-to-square section (1) and are connected to the two cooling air vents (A). Two spherical connectors (9); Two pressure caps (10) are fitted around the outer periphery of two spherical nozzles (9) and are threadedly connected to two pipe nozzles (8) to press the two spherical nozzles (9) onto the pipe nozzles (8). The spherical conical surfaces of the two spherical nozzles (9) and the pipe nozzles (8) are in contact. Two air intake tubes (11) are connected to two spherical nozzles (9) to connect to an external air source; Two flow control valves (12) are installed on two air intake pipes (11).

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