An aircraft engine nozzle

Abstract

The application belongs to the technical field of aero-engine nozzle design, and particularly relates to an aero-engine nozzle, which can pass phase-change cooling medium into a cooling exhaust cavity through a phase-change cooling medium jet pipe in the case that an engine is in a large working condition or needs to be rapidly cooled to improve infrared stealth capability, absorbs heat in the form of phase change to cool a front section side wall, a rear section side wall and a side wall cover, and then is discharged through a backward exhaust gap and a gas film hole, so that a gas film is formed on the inner side of the rear section side wall, rapid cooling of the front section side wall, the rear section side wall and the side wall cover is realized, the temperature of the front section side wall, the rear section side wall and the side wall cover is reduced in a short time, ablation of nozzle components is avoided, the infrared stealth capability of the engine is improved, and the deficiency of cooling capability of an outer-duct airflow is made up.

Description

TECHNICAL FIELD

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

[0002] The aircraft engine nozzle is installed at the end of the engine, uses the converging and expanding movement of internal components such as converging sections and expanding 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 aircraft engine nozzle is subjected to high-temperature airflow and bears extremely high temperature load, and its components are easy to be ablated, and the infrared radiation characteristics are obvious. At present, the engine bypass airflow is used to cool the nozzle components, reduce the temperature of the nozzle components, avoid ablation of the nozzle components, and inhibit the infrared radiation characteristics to improve the infrared stealth capability. However, the bypass airflow also needs to be used to cool other necessary high-temperature parts, and the cooling capacity provided by the nozzle is limited, which cannot well meet the cooling requirements of the aircraft engine nozzle when the aircraft engine is in a large working condition or needs to be rapidly cooled to quickly improve the infrared stealth capability.

[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 clear 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 aircraft engine 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 aircraft engine nozzle comprises:

[0009] A round-to-square section, the front end of which is connected to the rear end of the 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;

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

[0012] Two external adjusting pieces, which are located outside the two converging sections and the expanding sections, and 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;

[0013] Two front segment side walls, front end connected to the connecting edge of the two opposite side walls of the round-to-square segment rear end, and the two opposite side walls of the round-to-square segment rear end have a hole for positioning;

[0014] Two rear segment side walls, front end connected to the rear end of the two front segment side walls, and the rear end of the two front segment side walls form a rear exhaust slot, and the wall surface has a plurality of air film holes;

[0015] Two side wall covers, located outside the two front segment side walls and the rear segment side walls, the front end is connected to the connecting edge of the two opposite side walls of the round-to-square segment rear end, and is connected along the edge with the two front segment side walls and the rear segment side walls, and the cooling exhaust cavity is formed between the two front segment side walls and the rear segment side walls; the cooling exhaust cavity is communicated with each air film hole;

[0016] Two phase change cooling medium jet pipes, one end penetrating through the two holes for positioning into the cooling exhaust cavity, and the side wall penetrating into the cooling exhaust cavity has a plurality of jet holes distributed along the axial direction.

[0017] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle, the rear end of the two expansion segments and the outer adjusting piece is conical;

[0018] The two front segment side walls, the rear segment side walls and the side wall cover are V-shaped as a whole;

[0019] The rear exhaust slot is rearwardly enlarged and V-shaped.

[0020] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle, the two outer adjusting pieces converge inward.

[0021] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle, the end of the two phase change cooling medium jet pipes penetrating into the cooling exhaust cavity is blocked, and the flow area is 1.75-2 times the area of the jet holes thereon.

[0022] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle, the number of jet holes at each position on the two phase change cooling medium jet pipes is an odd number greater than three, and the included angle between the jet holes and the rear segment side wall or the side wall cover is not more than 90°, and the jet hole located in the middle is perpendicular to the rear segment side wall or the side wall cover.

[0023] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle further comprises:

[0024] Two partitions are arranged in the two cooling exhaust cavities, dividing the cooling exhaust cavities into front cooling exhaust cavities and rear cooling exhaust cavities corresponding to the front segment side walls and the rear segment side walls, wherein the front cooling exhaust cavities are communicated with the rear exhaust slots; the rear cooling exhaust cavities are communicated with each air film hole;

[0025] Two phase change cooling medium jet pipe penetrates the partition plate, and has a plurality of branch backwardly inclined branch pipe lines on the same, and a plurality of jet holes on each branch pipe line;

[0026] The upper branch pipe lines and the jet hole parts of the two phase change cooling medium jet pipes are located in the front cooling exhaust cavity and the rear cooling exhaust cavity, and the distribution density of the jet holes in the rear cooling exhaust cavity is greater than that of the jet holes in the front cooling exhaust cavity.

[0027] According to at least one embodiment of the present application, the above-mentioned aircraft engine nozzle further comprises:

[0028] Two gaskets are sleeved on the outer periphery of the two phase change cooling medium jet pipes and are welded on the outer sides of the connecting edges of the two opposite side walls;

[0029] Two connecting flanges are sleeved on the two phase change cooling medium jet pipes, are centered and positioned between the two gaskets through the stop collars, a sealing gasket is arranged therebetween, and the two gaskets are connected through bolts, and a spring washer is arranged between the bolt head and the connecting flange.

[0030] The present application has at least the following beneficial technical effects:

[0031] The present application provides an aircraft engine nozzle. In the case that the engine is in a large working condition or needs to be rapidly cooled to improve the infrared stealth capability, phase change cooling medium is introduced into the cooling exhaust cavity through the phase change cooling medium jet pipe, and the front section side wall, the rear section side wall and the side wall cover are cooled in the form of phase change. Then, the cooling medium is discharged through the backward exhaust slot and the gas film hole, and a gas film is formed on the inner side of the rear section side wall. The rapid cooling of the front section side wall, the rear section side wall and the side wall cover can reduce the temperature of the front section side wall, the rear section side wall and the side wall cover in a short time, avoid the ablation of the nozzle components, improve the infrared stealth capability of the engine, and make up for the insufficient cooling capacity of the outer flow. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 is the external view of the aircraft engine nozzle provided by the embodiment of the present application;

[0033] Figure 2 is the cross-sectional view of the aircraft engine nozzle provided by the embodiment of the present application;

[0034] Figure 3 is the side view of the aircraft engine nozzle provided by the embodiment of the present application, with the side wall cover removed;

[0035] Figure 4 is the schematic view of the partial structure of the aircraft engine nozzle provided by the embodiment of the present application;

[0036] Figure 5is a cross section schematic view of a phase change cooling medium jet pipe provided by the embodiment of the present application at a jet hole;

[0037] wherein:

[0038] 1 - round-to-square segment; 2 - converging segment; 3 - expanding segment; 4 - outer adjusting sheet; 5 - front segment side wall; 6 - rear segment side wall; 7 - side wall cover; 8 - phase change cooling medium jet pipe; 9 - partition plate; 10 - gasket ring; 11 - connecting flange; 12 - sealing gasket; 13 - bolt; 14 - spring washer;

[0039] A - rearward exhaust slot;

[0040] B - gas film hole;

[0041] C - jet hole.

[0042] In order to better illustrate the embodiment, some components in the drawings can be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0043] 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 conjunction with the drawings. It can 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, in order to facilitate the description, only the 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.

[0044] 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, which indicate the orientation in the description of the present application, are only used to indicate the relative direction 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 the relative positional relationship thereof can also be changed accordingly when the absolute position of the described object is changed, and therefore cannot be understood as a limitation on the present application. The "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 "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 quantity, but should be understood as the presence of at least one. The "includes" or "contains" and the like used in the description of the present application means that the elements or objects appearing before the word are covered by the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0045] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application 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 those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0046] The following will be described in detail in combination with the accompanying drawings Figures 1 to 5 The present application will be further described in detail.

[0047] An aero-engine nozzle comprises:

[0048] The circular-to-square segment 1 is connected at the front end to the rear end of the engine, and the outer wall of the rear end has a connecting edge;

[0049] The two converging segments 2 are hingedly connected at the front end to the connecting edges of the two opposite side walls at the rear end of the circular-to-square segment 1;

[0050] The two diverging segments 3 are hingedly connected at the front end to the rear ends of the two converging segments 2;

[0051] The two outer adjusting pieces 4 are located outside the two converging segments 2 and the diverging segments 3, and the front end is hingedly connected to the connecting edges of the two opposite side walls at the rear end of the circular-to-square segment 1;

[0052] Two front segment side walls 5 are connected at the front end to the connecting edges of the two opposite side walls at the rear end of the round-to-square segment 1, and the two opposite side walls at the rear end of the round-to-square segment 1 have position holes;

[0053] Two rear segment side walls 6 are connected at the front end to the rear end of the two front segment side walls 5, form rear exhaust slots A between the rear end of the two front segment side walls 5, and have a plurality of air film holes B on the wall surface;

[0054] Two side wall covers 7 are located outside the two front segment side walls 5 and the rear segment side walls 6, are connected at the front end to the connecting edges of the two opposite side walls at the rear end of the round-to-square segment 1, and are connected along the edges with the two front segment side walls 5 and the rear segment side walls 6 to form a cooling exhaust cavity between the two front segment side walls 5 and the rear segment side walls 6; the cooling exhaust cavity is communicated with each air film hole B;

[0055] Two phase change cooling medium jet pipes 8 extend into the cooling exhaust cavity through the two position holes, and the part of the side wall extending into the cooling exhaust cavity has a plurality of jet holes C distributed in the axial direction.

[0056] The above embodiment discloses an aircraft engine nozzle, wherein the connection relationship and specific structure design between the round-to-square segment 1, the converging segment 2, the diverging segment 3 and the outer adjusting sheet 4 can be referred to CN113107706, and will not be described in more detail here.

[0057] In the case of large engine conditions or the need for rapid cooling to improve infrared stealth capability, the above embodiment discloses an aircraft engine nozzle, which can introduce phase change cooling medium into the cooling exhaust cavity through the phase change cooling medium jet pipe 8, absorb heat in the form of phase change, cool the front segment side wall 5, the rear segment side wall 6 and the side wall cover 7, and then discharge through the rear exhaust slot A and the air film hole B to form an air film on the inner side of the rear segment side wall 6. This can achieve rapid cooling of the front segment side wall 5, the rear segment side wall 6 and the side wall cover 7, reduce the temperature of the front segment side wall 5, the rear segment side wall 6 and the side wall cover 7 in a short time, avoid ablation of the nozzle components, improve the infrared stealth capability of the engine, and make up for the insufficient cooling capacity of the outer flow.

[0058] In some optional embodiments, the above aircraft engine nozzle, the rear end of the two diverging segments 3 and the outer adjusting sheet 4 is in the form of a sharp cone, the front segment side wall 5, the rear segment side wall 6 and the side wall cover 7 are in the form of a V, and the rear exhaust slot A is in the form of a rearwardly expanding V, so as to ensure the aerodynamic performance of the engine nozzle, achieve better cooling effect, and have better radar stealth performance.

[0059] In some optional embodiments, the above aircraft engine nozzle, the two outer adjusting sheets 4 converge inward, which can reduce the noise of the nozzle discharging high-temperature gas and improve the stealth effect.

[0060] In some alternative embodiments, the above-mentioned aero-engine nozzle, the two phase change cooling medium jet pipes 8 extend into one end of the cooling exhaust cavity and block it, and the flow area is 1.75-2 times the area of the jet holes C thereon, so as to ensure the supply capacity of the phase change cooling medium and ensure the rapid cooling effect on the aero-engine components.

[0061] In some alternative embodiments, the above-mentioned aero-engine nozzle, the number of the jet holes C on the two phase change cooling medium jet pipes 8 is an odd number greater than three, and the jet holes C in the middle are perpendicular to the rear section side wall 6 or the side wall cover 7, so that the phase change cooling medium sprayed through the jet holes C can efficiently impact the rear section side wall 6 or the side wall cover 7, thereby ensuring the cooling effect on the rear section side wall 6 or the side wall cover 7.

[0062] In some alternative embodiments, the above-mentioned aero-engine nozzle further comprises:

[0063] Two partitions 9 are arranged in the two cooling exhaust cavities to divide the cooling exhaust cavities into front cooling exhaust cavities corresponding to the front section side wall 5 and rear cooling exhaust cavities corresponding to the rear section side wall 6, wherein the front cooling exhaust cavities are connected to the rear exhaust slots A, and the rear cooling exhaust cavities are connected to the film holes B.

[0064] The two phase change cooling medium jet pipes 8 are arranged through the partitions 9 and have a plurality of branch backwardly inclined branch pipelines thereon, and each branch pipeline has a plurality of jet holes thereon.

[0065] The branch pipelines and the jet holes C thereof on the two phase change cooling medium jet pipes 8 are partially located in the front cooling exhaust cavities, and the phase change cooling medium sprayed through the part of the jet holes C enters the front cooling exhaust cavities and is discharged through the rear exhaust slots A after phase change. The branch pipelines and the jet holes C thereof on the two phase change cooling medium jet pipes 8 are partially located in the rear cooling exhaust cavities, and the phase change cooling medium sprayed through the part of the jet holes C enters the rear cooling exhaust cavities and is discharged through the film holes B after phase change. The distribution density of the jet holes C in the rear cooling exhaust cavities is greater than that of the jet holes C in the front cooling exhaust cavities, so as to make the cooling effect on the front section side wall 5 and the rear section side wall 6 uniform.

[0066] In some alternative embodiments, the above-mentioned aero-engine nozzle further comprises:

[0067] Two gaskets 10 are sleeved on the outer periphery of the two phase change cooling medium jet pipes 8 and are welded on the outer sides of the two opposite side wall connecting edges.

[0068] Two connecting flanges 11 are sleeved on the two phase change cooling medium jet pipes 8, and are centered and positioned with the two gaskets 10 through the stopper therebetween, and the sealing gaskets 12 are arranged therebetween, and are connected with the two gaskets 10 through the bolts 13, and the spring washers 14 are arranged between the heads of the bolts 13 and the connecting flanges 11.

[0069] In some optional embodiments, the above-mentioned aero-engine nozzle, the phase change cooling medium jet pipe 8 and the corresponding components correspond to two groups for the two cooling exhaust cavities, and each group has two.

[0070] The above-mentioned aero-engine nozzle can realize active on-demand control of the phase change cooling medium flow rate, and can use the phase change cooling medium flow rate on demand according to actual scene requirements, such as active control of opening and use or flow increase in escape, and can be adjusted to a moderate flow rate state or not used in a conventional cruise state, wherein the phase change cooling medium can be supercritical carbon dioxide (-58.5 degrees Celsius) or liquid nitrogen (-196 degrees Celsius) and the like.

[0071] The above-mentioned aero-engine nozzle can realize active on-demand control of the phase change cooling medium flow rate, and can use the phase change cooling medium flow rate on demand according to actual scene requirements, such as active control of opening and use or flow increase in escape, and can be adjusted to a moderate flow rate state or not used in a conventional cruise state, wherein the phase change cooling medium can be supercritical carbon dioxide (-58.5 degrees Celsius) or liquid nitrogen (-196 degrees Celsius) and the like.

[0072] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0073] The technical solutions of the present application have 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, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An aircraft engine nozzle, characterized in that, include: The round-to-square section (1) is connected at the front end to the rear end of the 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 sidewalls at the rear end of the circular-to-square segment (1); 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), and their front ends are respectively hinged to the connecting edges of the two opposite sidewalls at the rear end of the round-to-square section (1); 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). The two opposite sidewalls at the rear end of the round-to-square section (1) have clearance holes. Two rear sidewalls (6) are connected at the front end to the rear end of two front sidewalls (5), forming a rearward exhaust slit (A) between them and the rear end of the two front sidewalls (5), and have multiple air film holes (B) on the wall surface. 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 air film hole (B); Two phase change cooling medium jet pipes (8) extend into the cooling exhaust chamber through two relief holes at one end. The side wall of the part extending into the cooling exhaust chamber has multiple jet holes (C) distributed along the axial direction.

2. The aero-engine nozzle according to claim 1, characterized in that, The two expansion sections (3) and the rear end of the outer adjustment plate (4) are conical; The two front sidewalls (5), the rear sidewall (6), and the sidewall cover (7) are V-shaped as a whole; The rear exhaust vent (A) is a V-shaped vent that expands rearward.

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

4. The aero-engine nozzle according to claim 1, characterized in that, Two phase change cooling medium jet pipes (8) are inserted into the cooling exhaust chamber at one end and sealed. The flow area is 1.75 to 2 times the area of ​​the jet hole (C) on it.

5. The aero-engine nozzle according to claim 1, characterized in that, The number of jet holes (C) on the two phase change cooling medium jet pipes (8) is an odd number greater than three, and they are oriented toward the two rear side walls (6) or side wall covers (7), with the included angle between them and the rear side walls (6) or side wall covers (7) not exceeding 90°, and the jet hole (C) located in the middle is perpendicular to the rear side walls (6) or side wall covers (7).

6. The aero-engine nozzle according to claim 1, characterized in that, Also includes: Two partitions (9) are provided in two cooling exhaust chambers, dividing the cooling exhaust chambers into a front cooling exhaust chamber and a rear cooling exhaust chamber corresponding to the front sidewall (5) and the rear sidewall (6), wherein the front cooling exhaust chamber is connected to the rear exhaust slit (A); and the rear cooling exhaust chamber is connected to each air film hole (B). Two phase change cooling medium jet pipes (8) are installed through the partition (9) and have multiple backward inclined branch pipes, each branch pipe having multiple jet holes; The branch pipes and their jet holes (C) on the two phase change cooling medium jet pipes (8) are partly located in the front cooling exhaust chamber and partly located in the rear cooling exhaust chamber. The distribution density of the jet holes (C) located in the rear cooling exhaust chamber is greater than that of the jet holes (C) located in the front cooling exhaust chamber.

7. The aero-engine nozzle according to claim 1, characterized in that, Also includes: Two gaskets (10) are fitted around the outer periphery of the two phase change cooling medium jet pipes (8) and welded to the outer side of the corresponding two opposite sidewall connection edges; Two connecting flanges (11) are fitted onto two phase change cooling medium jet pipes (8), and are centered and positioned between the two gaskets (10), with a sealing gasket (12) placed between them. They are connected to the two gaskets (10) by bolts (13), and a spring washer (14) is placed between the head of the bolt (13) and the connecting flange (11).

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